Project ID
|
NASA Center
|
ESMD Related Area
|
Title
|
Description
|
|
Ames
Research Center (ARC) |
|
ARC1-01-SD
|
Ames Research
Center (ARC) |
Lunar and Planetary Surface
Systems |
REAL-TIME VISION
FOR VEHICLE NAVIGATION |
REAL-TIME VISION FOR VEHICLE
NAVIGATION .The goal of this project is to develop a
real-time computer vision library to support vehicle
navigation (mobile robots, lunar transport rovers, etc).
The library will allow vehicle control system developers
to quickly assess the nearby environment, e.g., to
determine if a particular arc is collision-free over a
specified distance. This library will take advantage of
real-time performance provided by a hardware-based
stereo vision system (Tyzx G2 camera) and include
methods for processing 3D point clouds, generating
grid-based occupancy/obstacle maps, and evaluating drive
arcs. This project will involve computer vision theory,
cross-platform software development, and testing on a
mobile robot. |
|
ARC1-02-SD
|
Ames Research
Center (ARC) |
Lunar and Planetary Surface
Systems |
NON-PREHENSILE
MOBILE MANIPULATION |
NON-PREHENSILE MOBILE
MANIPULATION The goal of this project is to design
non-prehensile robot manipulation devices for lunar site
operations, such as cable running, leveling/grading, and
rock clearing. A variety of approaches are possible
including pushing, tapping, or rolling. These modes of
manipulation require the robot to have some
understanding of the physics of interacting with a part,
particularly friction and contact. In addition, robotic
systems should take advantage of different strategies
for manipulation, such as picking up a part by pushing
it against a fixed obstacle. This project involves
electrical and mechanical engineering and some embedded
system (e.g., microcontroller) programming. |
|
ARC1-03-SD
|
Ames Research
Center (ARC) |
Lunar and Planetary Surface
Systems |
GEOCAM: A LOW-COST
CAMERA FOR RAPID GEO-REFERENCED AERIAL MAPPING |
GEOCAM: A LOW-COST CAMERA FOR
RAPID GEO-REFERENCED AERIAL MAPPING The goal of this
project is to develop the ?GeoCam?, a camera system that
can be used to rapidly map local areas from low-flying
vehicles (small planes, lunar hoppers, etc).
High-resolution digital imagery acquired from
low-altitude flight can supplement wide-area coverage
provided by orbiting cameras, particularly when surface
features are best viewed up close or satellite task time
is limited. The GeoCam will be designed to: attach
easily/rapidly (while respecting operational
regulations), provide high-precision pose estimates
(position and pointing) for each captured image, and be
as low-cost as possible. This project will involve trade
studies (capture device, storage medium, etc.),
mechatronic system engineering, and development of
position estimation software. |
|
ARC1-04-SD
|
Ames Research
Center (ARC) |
Spacecraft |
Small Spacecraft |
Small spacecraft show great
promise for future NASA missions. Because of their
nature, these spacecraft typically have very low margins
in mass, power, and propulsion. In order to make these
systems viable, NASA needs evaluate what is possible
with innovative concepts for microspacecraft landers,
rovers, and communications relays that could be used for
very low cost robotic lunar precursor missions. |
|
ARC4-09-SD
|
Ames Research
Center (ARC) |
Spacecraft |
Photonic or
Electronic Hit Indicator: MMOD impact detector for Orion |
Further advance a detector to
determine the extent of MMOD damage to the Orion vehicle
for its ISS and Lunar missions. The detector has a low
false positive rate, uses minimial spacecraft resources
and is based on a DoE system used to determine strikes
on ballistic missile targets. |
|
ARC4-08-SD
|
Ames Research
Center (ARC) |
Spacecraft |
Fluidized Bed
Synthesis of Carbon Nanotubes |
The project involves producing
carbon nanotubes in large enough quantities to fabricate
composites for civil and space aviation. |
|
ARC2-05-SD
|
Ames Research
Center (ARC) |
Ground Operations |
NASA Technology
Database |
Assist researchers in the
determination of technology that affect ESMD mission
using next generation of NASA Technology Database and
explore approaches for improving NASA Technology
Transfer meeting OMB Requirements. Senior design team
will help model aspects of the technology descriptions
and maturity control and collect and analyze data as
needed. |
|
ARC2-06-SD
|
Ames Research
Center (ARC) |
Ground Operations |
Prognostics for
Complex Systems - Damage Propatation Modeling |
The Prognostics Center of
Excellence at NASA Ames Research Center is conducting
research in systems health management. This involves the
early assessment of abnormal conditions and damage as
well as the estimation of "remaining life" of a
component or subsystem. The goal is to research damage
propagation mechanisms and to model damage using a
physics-based approach for select application domains
(e.g., power semiconductors, electro-mechanical
actuators, composite structures, batteries, ?) |
|
ARC2-07-SD
|
Ames Research
Center (ARC) |
Ground Operations |
Prognostics for
Complex Systems |
The Prognostics Center of
Excellence at NASA Ames Research Center is conducting
research in systems health management. This involves the
early assessment of abnormal conditions and damage as
well as the estimation of "remaining life" of a
component or subsystem. The goal is to contribute
towards the state of the art in uncertainty management
which is a critical component of prognostics. |
|
Dryden Flight Research Center (DFRC) |
|
DFRC1-15-SD
|
Dryden Flight
Research Center (DFRC) |
Lunar and Planetary Surface
Systems |
Lunar Landing
Training Vehicle |
This projects seeks senior
design concepts for Lunar Landing Training Vehicles. The
concepts must account for reduced lunar gravity, and
allow the terminal stage of lunar descent to be flown
either by remote pilot or autonomously. Platform should
allow for both sensor evaluation and pilot training. |
|
DFRC1-17-SD
|
Dryden Flight
Research Center (DFRC) |
Lunar and Planetary Surface
Systems |
Aero-Assist Options
for Mars Surface Sensor Deployment |
This projects seeks senior
design concepts for using aero-assist to deliver a
constellation of small sensors to the surface of Mars.
In this study the surface delivery of pico-sat sized
sensors using ONLY aerodynamic deceleration will be
addressed. Study should identify aero-shell geometry,
required L/D ratios, mass fractions, launch options, and
number and size of sensors deliverable to the Mars
surface. Class of allowable ballistic coefficients for
sensor packages, and required parachute/decelerator
systems should be described. |
|
DFRC3-16-SD
|
Dryden Flight
Research Center (DFRC) |
Propulsion |
Propulsions Systems
for Planetary Gravitational Simulator |
This projects seeks senior
design concepts for propulsion or lift-system concepts
for gravity offset for a Lunar Landing Training Vehicle
(LLTV). Project should perform trades to evaluate the
most effective and reliable methods for gravity offset.
Potential methods include roto-craft, jet engines, small
rocket systems, and cold-jet lift concepts. Issues to be
addressed include scalable lift mass, reliability,
onboard propellant mass fractions, and vehicle
stability/handling qualities. |
|
DFRC4-07-SD
|
Dryden Flight
Research Center (DFRC) |
Spacecraft |
Dynamic
soaring/Autonomous autopilot |
Develop aerial platforms that
exhibit autonomy and dynamic soaring capabilities |
|
Glenn
Research Center (GRC) |
|
GRC1-07-SD
|
Glenn Research
Center (GRC) |
Lunar and Planetary Surface
Systems |
Extreme Environment
Lander Design |
The goal of this project is to
develop a conceptual lander design capable of long-term
operation under extreme environmental conditions. The
design must provide sufficient power and environmental
protection for a pre-selected set of scientific
instruments. A 3D CAD model of the lander is required to
provide thermal and stress analysis, as well as to
determine packaging and overall system mass. |
|
GRC1-08-SD
|
Glenn Research
Center (GRC) |
Lunar and Planetary Surface
Systems |
Lunar Surface
Mobility |
NASA is currently developing
the technology for long-range exploration of the lunar
surface. This includes the development of a mobile
landing platform and a lunar truck. In both cases, it’s
critical that their tires envelop the rocky surface of
the Moon. The enveloping action isolates motion, which
improves astronaut ride quality and power efficiency.
The objective of this senior design project is to create
a scale-model manned lunar vehicle tire (of unspecified
radius and weight) for long range use.
The functional characteristics must include:
• Operation for 1million cycles. (E, N)
• Envelopment of a 90 degree wedge, with at least 15% of
the tire’s radius, under the nominal load. (P)
The limitations imposed on the design are:
• Unloaded radius/width ratio of 1.3 or more. (P)
• Average footprint pressure of 40 kPa or less, under
the nominal load. (P)
Besides meeting the objective, the goodness of the
design will be judged by:
• Robustness to lunar conditions. E.g. Hard vacuum,
temperature variations between 40 and 400K, direct solar
radiation, un-weathered regolith and dust. (E)
• Severity of the primary failure mode. The less risk to
the mission the better. (E)
• Level of redundancy: The number and efficacy of the
backup operation modes. (E)
• Manufacturability / scalability: Ability to be
manufactured at the full scale radius of 40.64 cm and
support the nominal ground load of 2.7kN. (E)
• Development risk / cost: Likelihood of success and
cost of creating the full scale prototype. (E)
• Design versatility: Ability to tune the stiffness
properties in all directions. (E)
• Tire handing: Responsiveness to footprint forces
(longitudinal, lateral, aligning torque). (E)
• Low power number: Input energy required, per unit
ground load, per unit distance traveled when the tire is
pulling 40% of the nominal ground load over sandy
terrain. (E,N)
• High load number: Nominal ground load per unit tire
weight. (P)
Key: E: Student must estimate this, P: Student must
prove this, N: NASA will evaluate this.
|
|
GRC3-06-SD
|
Glenn Research
Center (GRC) |
Propulsion |
Mechanical
Components for Cryogenic Tank |
Cryogenic propellant tanks,
such as those used for the Lunar Lander, are rather
complex systems with many electro-mechanical components
for fuel supply, thermal control, pressure control, and
low gravity propellant gauging. The objective of this
senior design project opportunity is to consider the
operability and reliability of those mechanisms inside
or connected to the tank where the operating temperature
range is extremely large. Thermal expansion of
mechanical components, materials to withstand thermal
cycles, sizes and weights of the mechanisms are some of
important considerations. |
|
Goddard Space Flight Center (GSFC) |
|
GSFC1-01-SD
|
Goddard Space
Flight Center (GSFC) |
Lunar and Planetary Surface
Systems |
Design of a
Spacecraft to Support a Lunar Mission |
Engineers would give the
students a set of instruments and a lunar orbit and let
them design the spacecraft to support the mission. This
project would be suitable for a class where the student
already knows something of designing spacecraft. |
|
GSFC1-07-SD
|
Goddard Space
Flight Center (GSFC) |
Lunar and Planetary Surface
Systems |
Lunar Terrain
Categorization |
Lunar Terrain Categorization:
Surface mission operational planning has been identified
as one area of special interest within the Scientific
Context of the Moon Exploration. Specifically,
technologies that will enable scientists to perform
terrain categorization, and in particular to detect,
identify and characterize rocks, will be studied. Once
lunar data is geo-registered & mosaiced to a common
Lunar Geodetic Grid, these tools will assist scientists
in determining general regions of interest, in
performing precise targeting of specific types of
samples, & in avoiding hazardous landing sites. Regions
of interest will mainly be determined by understanding
and characterizing potential lunar resources (minerals,
ice, etc.) and their spatial distribution, their
abundance, density, and distribution, relative to future
missions and in-situ instruments that will be needed to
perform additional detailed analyses. Rock
identification will play an essential role in targeting
specific samples, and rock location and distribution
will be essential for selecting landing sites while
avoiding hazards. Another importance tool in selecting
landing sites will be accurately compute slopes and
surface roughness parameters, from laser altimeter or
stereo data, taking into account appropriate solar
illumination models. Specifically, the work will focus
on terrain classification and SAR data hazard analysis.
Classification with methods such as shape analysis,
textural analysis, mathematical morphology, & shading
analysis, as well as both unsupervised clustering &
supervised classification will be investigated and
evaluated, and SAR Data Hazard Analysis will be used to
generate hazard maps using methods such as texture and
mathematical morphology. |
|
GSFC1-10-SD
|
Goddard Space
Flight Center (GSFC) |
Lunar and Planetary Surface
Systems |
Thermal Ctrl Sys
(TCS) for Lunar (or Mars) Rovers |
For future rovers a robust,
simple, lightweight thermal control system will be
required. The conventional thermal architecture uses a
pumped fluid loop and was used on Mars Pathfinder and
Mars Exploration Rover (MER). An alternative system
using a miniature loop heat pipe (LHP) system has been
proposed, which is an order of magnitude lighter, less
costly and has no moving parts. The students will be
asked to perform trade studies on this and other
possible solutions, taking into account weight,
reliability, cost, ease of integration etc, as part of
their approach. They will be asked to determine the
environment and perform thermal analysis to show that
temperature limits have not been exceeded during 1)
interplanetary cruise 2) descent and landing 3) surface
operations. Mechanical or CAD drawings will be developed
to show how the system will be integrated into a typical
rover concept, such as Pathfinder or MER as well as how
the TCS interfaces with other supporting sub-systems
such as Power and C&DH. |
|
GSFC1-11-SD
|
Goddard Space
Flight Center (GSFC) |
Lunar and Planetary Surface
Systems |
Inverse Synthetic
Aperture Radar (ISAR) for Interior Mapping of Asteroid |
This project has a goal to
develop hardware & software for low frequency wideband
step frequency ISAR radar. Low frequency ISAR is used to
image interior structure of an unknown target such as
asteroid/comet and other planetary bodies. ISAR consists
of 3 basic subsystems: (1) Base band signal generation
and base band I & Q data processing, (2) Analog RF front
end, and (3) Antenna. Using either Xlinx/Altera FPGA
board and Analog Devices' DDS chips entire base band
operation will be programmed and implemented. The analog
RF front end will be assembled from commercially
available RF components. The data acquisition and
processing will be implemented through the FPGA.
Development of data processing algorithm to form a 2-D
image of interior portion of a target will also be part
of this project. |
|
GSFC1-12-SD
|
Goddard Space
Flight Center (GSFC) |
Lunar and Planetary Surface
Systems |
Lunar Transverse
Map Contest |
Next year more than 3 billion
dollars of new lunar data will start to flow in a
torrent. We would like to design an educational outreach
effort setting up a competitive mission design by
students for the most basic types of lunar robots. |
|
GSFC1-13-SD
|
Goddard Space
Flight Center (GSFC) |
Lunar and Planetary Surface
Systems |
Communications,
Standards, & Technology Laboratory |
The student intern will
participate in the development & integration of
technologies and systems into the GSFC Communications,
Standards, & Technology Laboratory (CSTL). The CSTL is a
facility capable of testing and demonstrating complete
end-to-end mission communications scenarios from onboard
spacecraft computer systems, ground station RF systems,
terrestrial networking systems, to the mission control
center. The work available ranges from software
development to digital and RF hardware design. Current
activities include demonstrations and development of
Lunar Surface communications scenarios. |
|
GSFC2-05-SD
|
Goddard Space
Flight Center (GSFC) |
Ground Operations |
Use of a Fabry-Perot
interferometer for precise column carbon dioxide
measurements and monitoring. |
Use existing Fabry-Perot
Interferometer to make daily-long term measurements of
CO2 column; check calibration/stability of instrument
and evaluate data. |
|
GSFC2-06-SD
|
Goddard Space
Flight Center (GSFC) |
Ground Operations |
Embedded science
data processing applications using high-performance
hybrid platforms |
Work on a robotic path planning
demonstration; R&D involving SAR and Hyper-spectral data
processing; and robust software architecture that will
help fly commercial processors reliably in a
space-radiation environment. Students need to have C
and/or VHDL experience, and combined hardware/software
experience. |
|
GSFC2-13-SD
|
Goddard Space
Flight Center (GSFC) |
Ground Operations |
Use of a Fabry-Perot
Interferometer for precise column carbon dioxide
measurements and monitoring |
Use existing Fabry-Perot
Interferometer to make daily-long term measurements of
CO2 column; check calibration/stability of instrument
and evaluate data. |
|
Jet
Propulsion Lab (JPL) |
|
JPL2-01-SD
|
Jet Propulsion Lab |
Ground Operations |
Spacecraft Flight
Project and Design Practices Software for Mission
Operations Assurance |
The proposed project includes a
high level software design that will implement the JPL
FPPs (Flight Project Practices) and DPs (Design
Practices) as a function of the various parameters of
the mission in flight (phase E) |
|
Johnson Space
Center (JSC) |
|
JSC1-01-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Remote Image System
Acquisition (RISA) - Space Environment Monitoring |
The RISA multispectral imager
has been shown to be able to detect and monitor space
radiation. Further study is required to determine the
usefulness and potential of employing the RISA imager in
this way. The ability to have a single instrument
provide multiple functions is of interest to NASA given
limit stowage and power available in the spacecraft
environment. In addition, temperature monitoring, and
other environmental characteristics shall be included in
the RISA design to serve to both indicate the ambient
environment and for sensor calibration. |
|
JSC1-02-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Remote Image System
Acquisition (RISA) - Space Camera 4 (SC4) Development |
The purpose of the RISA SC4
project is to produce a high quality / high reliability
wireless multispectral imager designed specifically for
the space environment. The imager will be used to
monitor the health and status of the crew and vehicle
while in space as well as on Lunar and Martian surfaces.
The SC4 design will be based on the existing SC3 and SC2
imagers. The project includes the: *development of
required functions in VHDL, * electronic circuit
development, * testing of alternate sensors, *
characterizing the performance of the system, and *
design and build of proof-of-concept prototypes using
flight equivalent parts. |
|
JSC1-04-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Remote Image System
Acquisition (RISA) - Multispectral Imaging, Optical
System Development |
The purpose of the RISA
Multispectral Imaging project is to develop methods to
use multispectral imaging for materials identification,
locating vegetation, locating evidence of life, locating
environments that will sustain life, atmospheric
penetration, biomedical applications, astronomical
imaging, and improving methods to identify properties of
interest to the NASA mission to meet exploration
objectives. Both optical and electrically tunable
filters shall be employed for the multispectral imaging
objectives. The optical design objectives will explore
the use of liquid lenses and other methods to mitigate
the effects of the space environment. Proof of concept
prototypes will be designed and built. [Disciplines:
Optical Engineering, Physics, Astronomy, Biomedical
Engineering, Remote Sensing, Electrical Engineering,
Software Engineering, Mechanical Engineering] |
|
JSC1-06-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Advanced Lunar
Pressurized Rover (EC Priority #2) |
Design of a 2-4 person rover
for lunar exploration with both robotic manipulator
capability and EVA capability. Rover would include
minimum gas loss and low power EVA airlock and dust
mitigation capabilities. CHALLENGE GOALS AND OBJECTIVES:
The task would be to design a future lunar pressurized
rover that can accommodate 2-4 crew members. This rover
would be an element of a future planetary lander.The
goal would be to perform surface exploration by
creatively designing the layout and the operation of the
pressurized rover. The Advanced EVA Technology Group
will provide information on concepts from previous
studies. Small models of advanced airlocks for rovers
that have been proposed could also be provided. High
level design requirements for rovers and airlocks from
NASA design standards would also be provided. |
|
JSC1-08-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Lunar Lander EVA
Crew and Small Cargo Lifting System (EC Pr #4) |
Design of a system for
routinely and safely transporting the EVA crew and small
cargo up and down from the airlock to the surface and
back, including innovative ladder designs and lifts.
CHALLENGE GOALS AND OBJECTIVES: The task would be to
design a future lunar lander EVA crew and small cargo
lifting system. This EVA crew and small cargo lifting
system would be an element of a future planetary lander.
The goal would be to minimize the overall, mass and
weight of a lunar lander crew and small cargo lifting
system. The Advanced EVA Technology Group will provide
information on the previous designs of crew ladders and
some concepts from previous studies. |
|
JSC1-09-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Hand-held magnetic
lunar dust removal brush. |
Since most of the lunar dust is
magnetic, a brush with magnetic bristles could be
designed to brush the space suit or any other items and
the dust would be attracted to it. If the brush was
electromagnetic or mechanical where the polarity could
be changed, then the poles could be reversed and the
dust would be repelled and dropped to the surface after
use. |
|
JSC1-10-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Peel-off space suit
visor protective film |
Since the space suit visor will
be scratched and get dust after each EVA, design a
peel-off film or coating that can periodically be
removed so the astronaut can clearly see and not have
scratches, especially during long duration missions. |
|
JSC1-11-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Dust tolerant hand
tools |
Standard tools, such as
ratchets, folding handles on tools, and extendable
devices, such as tripods will be used during lunar
assembly, maintenance, and science tasks. Design some
typical tools, such as a folding handle or ratchet, that
has mechanisms that are extremely robust and dust
tolerant. |
|
JSC1-12-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Lunar lander dust
mat |
Since there will much walking
and preparation at the base of the lander/habitat ladder
or stairs after an EVA, and prior to entering the
airlock, design a lunar mat or surface so the astronauts
are not walking constantly in the lunar dust. This may
sound simple, but the requirements are: * light weight,
* low volume when stowed, * easily deployed, * dust can
be removed or falls between mesh. The crewmembers would
prepare sample boxes, repair equipment, dust off on this
mat or surface prior to entering the airlock. |
|
JSC1-15-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Design of a
Wireless Sensor Scavenging Network |
Design a wireless sensor energy
scavenging network that provides communications to a
base station (mobile or stationary) from an array of
intelligent sensors nodes comprised of various
transducers , sensors ,RF transmitters/receivers and
controllers with their own power source that does not
require batteries to operate. The wireless network
sensors obtain power from the environment (power
harvesting) and would respond to an interrogation
command from the base station to send their data
acquisition data to the base station. The wireless
sensor scavenging network is programmable for sending
data on demand or periodically. In addition, the sensor
network can be reconfigured to acquire different types
of data from each sensor by the base station. This has
applicability for the lunar and beyond outposts. Design
includes what trades were made to arrive at the design
and concept of operations. |
|
JSC1-17-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Dust Tolerant EVA
Compatible Connectors |
In the dusty lunar environment,
astronauts will be making and breaking various
electrical and fluid connectors with their gloved hands.
A goal is keep out dust when the electrical or fluid
connector is exposed. Design an electrical or fluid
connector for lunar exploration with EVA capability. The
connector should include dust mitigation capabilities.
CHALLENGE GOALS AND OBJECTIVES: The task would be to
design an electrical or fluid connector for lunar
exploration with EVA capability and keeps dust out.
These connectors could be on the space suit for
recharging the portable life support system or on lunar
surface systems for assembly or maintenance. The goal
would be to creatively design a connector that is easy
to operate with a gloved hand while keeping dust out
with minimum crew operations and complexity. The
Advanced EVA Technology Group will provide information
on concepts from previous studies. |
|
JSC1-18-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Advanced EVA
Airlock with Pressure Assisted Airlock Hatches and Dust
Mitigation |
Due to the expected large
number of space walks that will be performed on the
lunar surface, innovative designs for an airlock will be
needed. Both the internal and external hatches shall be
pressure assisted. The EVA airlock should also include
minimum gas loss, low power, and dust mitigation
capabilities. CHALLENGE GOALS AND OBJECTIVES: The task
would be to design a minimum gas loss airlock with
pressure assisted hatches that accommodate 2 astronauts.
This airlock would be an element of a future planetary
lander, habitat, or pressurized rover. The Advanced EVA
Technology Group will provide information on concepts
from previous studies. Small models of advanced airlocks
that have been proposed could also be provided. High
level design requirements for airlocks from NASA design
standards would also be provided. |
|
JSC1-19-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Producing Oxygen
from Lunar Soil |
America will send a new
generation of explorers to the moon. Once on the moon,
astronauts will stay in pressurized habitats. This
project involves the design of in-situ resource
utilization oxygen production pilot plants. These plants
will produce pure oxygen from lunar regolith (soil) to
enable a sustainable lunar outpost. |
|
JSC1-20-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Proton Exchange
Membrane Fuel Cells |
Fuel cells are likely to be key
to lunar lander and lunar outpost operations. Key to
developing lightweight and reliable fuel cell plants is
the ability to manage reactants and water with no active
pumps or other components. This project would examine
the technologies needed for passive reactant control,
passive cooling, and water removal by wicking.
Prototyping of one or many of these technologies is
desirable. |
|
JSC1-21-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Electric Propulsion
Systems |
In this project you will: *
Investigate new forms of electric propulsion that can be
used for future exploration objectives. Build prototypes
of existing methods of electric propulsion and compare
them to alternate methods developed under this effort. *
Research recent breakthroughs in propulsion and develop
quantitative results documenting their characteristics.
* Develop new theories of advanced propulsions systems
and build prototypes to test concepts. |
|
JSC1-22-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Velcro Inprovement
or Replacement for Use on Space Suits and other
Equipment in Dusty Lunar Environment |
Velcro is currently used
routinely to attach and removal thermal blankets, close
flaps on soft goods containers, and attach and close
various components on the space suit, such as the
Thermal Micrometeorite Garment (TMG). In this dusty
lunar environment, Velcro will allow fine lunar dust to
migrate through the Velcro connection and adversely
affect equipment. The design challenge would be to
improve the current Velcro such as to not degrade its
performance and to not allow dust to migrate through it
or to design a totally new technology to replace Velcro,
but its performance is just like Velcro. This Velcro
-like attachment system would have the same requirements
as Velcro, such as easily attaches and removes, is
flexible and can be sewed to textiles, meets lunar
temperature limits, attaches while misaligned, and does
not allow dust to migrate through it. |
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|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Wall Surfaces that
Allow Condensation and Low-Energy Evaporation |
One problem with enclosed
living spaces is that sometimes surfaces will collect
condensation due to a cold surface behind the wall. This
water could promote the growth of plant or animal life
(mold and bugs!). For this project, you are to
investigate how you can design a ?wall system? that will
trap any condensation that forms, then evaporate it
periodically (e.g.. every six hours) actively using very
little energy or passively when the adjacent air warms
above dewpoint. The solution could be a new material, a
sensor/heater system, or any other viable design that
can be demonstrated on a small scale. |
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|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Freeze Back
Radiator |
How would you cool a lunar
outpost on the rim of Shackleton Crater? There will be
high heat loads when the outpost is occupied plus
unoccupied periods of low activity and heat load. One
heat rejection system option is a freeze-back radiator
of reflux boilers. For this project you will investigate
reflux boilers, assess scaling laws for the reduced
lunar gravity, build a scaled reflux boiler using
commonly available materials, and test its performance. |
|
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|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Vacuum Cleaner for
Spacecraft Cabin Housekeeping for Lunar Surface Missions |
Dust and particulate matter
contamination of spacecraft cabin atmosphere and
surfaces are challenges that must be overcome for lunar
surface exploration. Particulate contamination
originating from the external surface environment or
from internal sources are both of concern. Development
of process technologies and equipment to minimize the
impacts of surface dust on crew health and equipment
inside the habitable volume are sought. This project
focuses on development of an advanced vacuum cleaner for
removal of particulates from internal cabin surfaces and
equipment, including space suit components, and for
additional use as a portable atmospheric dust filter.
This tool will have particular challenges based on the
affects of gravity and the physical properties of lunar
dust. Particulates may range from several millimeters
into the sub-micron range, and operation of the vacuum
must not contribute to atmospheric particulates.
Atmospheric requirements include maintaining
particulates in the range 0.5 microns to 100 microns
below 0.2 mg/m3 and lunar dust contaminants of less than
10 micron size below 0.05 mg/m3. Candidate technology
solutions should provide high efficiency, long-lived
removal capacity, low noise, and minimized use of power
and consumables. Novel methods for particulate removal
and filter regeneration are encouraged, including
electrostatic, magnetic, inertial and/or cyclonic
separation and/or backwashing processes. Technologies
must be tolerant to the abrasive effects of dust
particles. Performance should be demonstrated with
appropriate lunar dust analogs or simulants. |
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|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Low Energy/Low
Water Laundry Equipment for Space |
For long-duration human
exploration missions including a Lunar Outpost, the
clothing system will be a large factor in mission cost.
Currently clothing used in space is discarded and is a
major source of trash. Clothes washing and drying is
expected to be cost effective for mission durations of
the order of three months or longer. Aqueous-based
systems with extremely efficient water-use are
desirable. Initial use will be for lunar surface
missions, thus operation in a fractional gravity
environment and ability to remove lunar dust will be
required. Systems engineering approaches, including
synergy with clothing made from advanced fabrics, use of
novel detergents or alternative cleaning agents, and
compatibility with physicochemical and/or biological
regenerative water recovery systems must be considered.
This project will involve the design and prototyping of
a washing and drying system for re-use of clothing that
minimizes requirements for mass, volume, energy, heat
rejection, consumable supplies and crew involvement,
while meeting toxicity, flammability, out gassing, and
human factors requirements. |
|
JSC1-30-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Advanced Clothing
for Long Duration Human Exploration Missions |
Currently clothing is not
re-used in space. It is a bulky consumable of
considerable mass that must be re-supplied, and once
soiled, becomes a solid waste problem. Significant
benefit may be realized from improvements to space
clothing systems. Advancements in textiles, including
high performance fibers, fabrics and materials
treatments may benefit clothing systems for future human
space exploration missions. Benefits may include reduced
mass and volume for stowage of clean and used clothing,
increased use life, safety for use in enriched oxygen
atmospheres, and compatibility with low water and low
energy laundering and drying systems, while meeting
requirements for crew comfort. Properties of interest
include mass, thickness, durability, strength, thermal
conductivity, wicking, flammability, linting,
off-gassing and antimicrobial characteristics. This
project includes the investigation or new materials of
changes to existing materials. |
|
JSC1-31-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Active Response
Gravity Offload System Control Algorithm Development |
In preparation for returning to
the moon, a means must be developed to allow astronauts
to practice performing tasks in a reduced gravity
environment, and engineers to evaluate systems, such as
space suits, used in the performance of these tasks. To
these ends, the Active Response Gravity Offload System
(ARGOS) is being developed. ARGOS will use
electro-mechanical devices and sensors to compensate for
the difference between earth and lunar gravity, while
keeping the actuation point above the center of gravity
during translations. Of interest to NASA is a control
algorithm that will command the motors in response to
the astronaut?s movements with negligible lag time. |
|
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|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Active Response
Gravity Offload System Gimbal Development |
In preparation for returning to
the moon, a means must be developed to allow astronauts
to practice performing tasks in a reduced gravity
environment, and engineers to evaluate systems, such as
space suits, used in the performance of these tasks. To
these ends, the Active Response Gravity Offload System
(ARGOS) is being developed. ARGOS will use
electro-mechanical devices and sensors to compensate for
the difference between earth and lunar gravity, while
keeping the actuation point above the center of gravity
during translations. A key component of the system is
the gimbal, which allows the astronaut to bend and turn
while suspended from above. Of interest to NASA is a
system that will remain aligned with the astronaut's
center of gravity when bending forward or leaning both
backwards and to the side. |
|
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|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Active Response
Gravity Offload System Advanced Control Algorithm
Development |
In preparation for returning to
the moon, a means must be developed to allow astronauts
to practice performing tasks in a reduced gravity
environment, and engineers to evaluate systems, such as
space suits, used in the performance of these tasks. To
these ends, the Active Response Gravity Offload System
(ARGOS) is being developed. ARGOS will use
electro-mechanical devices and sensors to compensate for
the difference between earth and lunar gravity, while
keeping the actuation point above the center of gravity
during translations. Since mass constraints could result
in lunar transport vehicle suspension systems that do
not function in earth's gravity, it would be beneficial
if ARGOS, or a similar system, could be used to perform
"test drives" of development hardware. Of interest to
NASA is a control algorithm that would allow multiple
gravity compensation devices to work in tandem to
support a large mobile system. |
|
JSC1-38-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Biotechnology
System Development for Lunar Outpost in Situ Resource
Utilization |
This project seeks to develop
and test an innovative biotechnology-based resource
production system for future space exploration. This
research will provide new opportunities for the in situ
resource utilization (ISRU) enterprise for cleaner,
safer, and more efficient production of oxygen, metals,
fuels, and organics for lunar outpost needs. The
objective is to develop a sustainable integrated system
covering the whole life cycle of products to enhance
human activity at the lunar outpost. We propose to
develop and test a hybrid, geobiochemical, light-driven
reactor to provide outpost resources. The process is
based on our discovery that the extracellular products
synthesized by litholitic cyanobacteria are able to
dissolve (synonyms: leach, deteriorate, break down,
weather) rocks; e.g., ilmenite, an analog of lunar
glasses. In the initial phase, we will extend our
current studies on biomining by litholitic cyanobacteria
to characterize the biogeochemical dissolution
(leaching, etc.) of lunar soils and minerals within the
system ?microbes ? rocks.? The major objective is to
develop an effective biotechnological process to extract
elements and compounds, including Fe, Ti, Al, Si, Mn,
and O. We propose that this process will require less
mass and energy for the extraction of elements and will
work as a beneficial component of both ISRU and a life
support system with lower environmental risk. The most
critical feature of our project is to make
extraterrestrial mining more compatible with oxygen,
propellant and food production, and waste recycling to
form an integrated bioindustrial system that would be
the core of successful lunar outpost sustainability and
growth. Such a synthesis of technological capability
could decrease the demand for energy, transfer mass, and
cost of future lunar settlements. Anticipated results on
the ability of lunar rocks to host cyanobacteria may
contribute to the NASA Planetary Protection Program and
the NASA Astrobiology Program. |
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JSC1-39-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Lunar and Martian
Gravity Simulator Development for Long Duration Bed Rest
Studies |
The Flight Analogs / Bed Rest
Research Project at the Johnson Space Center provides
NASA with a ground based research platform to complement
space research. By mimicking the conditions of
weightlessness in the human body here on Earth, NASA can
test and refine scientific theories and procedures on
the ground before using these in space. Future space
exploration will challenge NASA to answer many critical
questions about how humans can live and work for
extended missions away from Earth. The Flight Analogs
Bed Rest Research Project is one way NASA will answer
these questions and devise ways to ensure astronaut
safety and productivity on extended missions. Looking
forward to support the Vision of Space Exploration, the
FAP has developed a Lunar Gravity Simulator which will
add to the complement of ground analogs a device to
simulate the forces encountered by astronauts on the
lunar surface at the FAP facility. The LGS, which
reclines a subject at 9.5 degrees of head up tilt, will
be the primary method for studying the effects of Lunar
Gravity on the human body here on Earth. The LGS will be
used by subjects for 16 hours a day for up to 90 days in
duration during the long term bed rest studies. The
objective of this project will be to develop new and
novel approaches for simulating Lunar and Martian
gravity for the Flight Analogs Project. The simulators
must be designed so that human test subjects are exposed
to the forces encountered in Lunar and Martian gravity
in the long axis of the body for 16 hours a day and up
to a total duration of 90 days. It is desirable that the
design will be able to simulate either gravity situation
through adjustment on the simulator tilt. The simulators
must be able to reside in a standard hospital room, and
must meet human factors and safety considerations. It is
preferred that the device can accommodate a seated and
standing position for the subject with minimal effort
for reconfiguration. See also:
http://sk.jsc.nasa.gov/sk211/analogs.aspx |
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|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Lightweight
Electric Vehicle Transmission |
Vehicles used on the lunar
surface will need electric motors. Since the lunar
surface will have variable grades and variable masses
(due to different payloads in the vehicle), a drive
system with a transmission will be needed. A
transmission made from steel will be too heavy, so a
lightweight, yet reliable transmission is planned. This
project includes the design and prototyping of such a
transmission. It must be able to operate in the extreme
lunar temperature conditions as well. |
|
JSC1-45-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
High Voltage, High
Current 3-Phase Motor Control with PID Control |
Vehicles used on the lunar
surface will need electric motors. Since the lunar
surface will have variable grades and variable masses
(due to different payloads in the vehicle), a drive
system with a transmission will be needed. The center of
this drive system is a 3-phase brushless DC motor. The
motor is expected to use 350 volts and be driven with 30
Amps. The control of this motor (PID or similar
closed-loop system) will need to ensure constant torque
is delivered and constant velocity is maintained. The
design challenges include using such a high voltage,
circuit board design that support high currents, and
maintaining control stability when the vehicle is
decelerating. This project includes the design and
prototyping of such a motor control system, including
the motor and motor control board. It must be able to
operate in the extreme lunar temperature conditions as
well. |
|
JSC1-46-SD
|
Johnson Space
Center (JSC) |
Lunar and Planetary Surface
Systems |
Cryogenic Component
Checkout and Problem Resolution |
In order for NASA to return to
the moon there will be a reliance on cryogenic
technologies for use with descent propulsion systems,
crew breathing air, and fuel cell reactant storage. As
part of it?s initial development efforts of these
systems NASA is interested in determining whether
current off the shelf fluid components, not currently
rated for use with cryogens, can be used in these
extreme conditions and if not, what design changes need
to be made in order to make them function in a cryogenic
environment. The intent of this project will be to
receive selected components from NASA?s Johnson Space
Center for testing with liquid nitrogen and or helium
fluids and perform a number of checkout tests. If the
component fails checkout testing NASA is interested in
understanding what design changes should be made to
improve its performance at cryogenic conditions. A
comparison with current cryogenic-rated components would
be useful. |
|
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|
Johnson Space
Center (JSC) |
Propulsion |
Electric Propulsion
Systems |
The RISA multispectral imager
has been shown to be able to detect and monitor space
radiation. Further study is required to determine the
usefulness and potential of employing the RISA imager in
this way. The ability to have a single instrument
provide multiple functions is of interest to NASA given
limit stowage and power available in the spacecraft
environment. In addition, temperature monitoring, and
other environmental characteristics shall be included in
the RISA design to serve to both indicate the ambient
environment and for sensor calibration. |
|
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|
Johnson Space
Center (JSC) |
Spacecraft |
Microphone
beamforming array estimation model |
Develop a beamforming
microphone array model and compare against an actual
microphone array measured data. This model would help
predict microphone array configuration performance. The
model would be developed in MatLab that would help
determine the theoretical lower bound of performance
using the Cramer-Rao lower bound method. An actual
microphone array is built and data gathered and compared
against the theoretical model. This project has
potential applicability in the Constellation program
CEV, lunar lander, and EVA spacesuit where a crew-worn
headset is not necessary. |
|
JSC4-14-SD
|
Johnson Space
Center (JSC) |
Spacecraft |
A Field
Programmable Analog Array (FPAA) Voice Activated Switch
(VOX) |
Develop a VOX device through
the use of FPAA devices. Investigate the feasibility of
using FPAA for simplifying the attack and decay time
adjustments of the VOX through the use of digital
techniques. This has applicability in the constellation
program for not only for the audio systems but also
understanding FPAA technology in use for other
constellation systems. A circuit will be developed and
data gathered to understand the performance of the VOX
circuit. A process for implementing FPAA circuits will
also be written. |
|
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|
Johnson Space
Center (JSC) |
Spacecraft |
Splash-down Space
Capsule Cooling |
How do you effectively cool the
confined inside enclosure of a just-returned space
capsule that is bobbing in the Pacific Ocean? One
problem is that there is insufficient energy available
in the capsule to run a vapor compression cycle to chill
the environment. Can you use the ocean water to cool the
air in the capsule? Remember, the temperature of the
ocean water at the surface varies, since the capsule can
land anywhere between 56 degrees North and 56 degrees
South latitude. For this project you will need to
investigate the typical ocean temperature, and then
design an energy efficient system to use this ocean
water to effectively cool the capsule air. |
|
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|
Johnson Space
Center (JSC) |
Spacecraft |
Space Vehicle
Transfer Tunnel Automated Mating Design |
In the design of the next
generation vehicles to be used during NASA?s return to
the Moon, there is a need to allow crew transfer between
vehicles / modules in a pressurized, shirt sleeve
environment. This type of transfer is called ?IVA
(Inter-Vehicle Activity) Transfer?. Generically, this
type of transfer is performed between any two connected
or docked vehicles. The specific case under
consideration in this project is the IVA transfer
between a Lander Ascent Module (AM) and Airlock (AL).
The current lander concept has the IVA transfer tunnel
between the AM and the AL pre-mated at Earth launch. The
AL remains behind on the Moon and the AM ascends to
rendezvous with a vehicle in lunar orbit. The tunnel is
pyrotechnically separated and retracted to allow for AM
ascent without contact. During a nominal mission, this
separation between the AM and AL can be easily managed,
as timing is not highly critical. However, in the event
of an abort, the tunnel must separate and provide
clearance (via retraction) so that the AM does not
contact any portion of the tunnel or AL. This retraction
must happen very quickly to improve abort reliability.
One way to avoid this complication is to fly the mission
with the tunnel disconnected. This may provide for
increased safety, but adds a serious complication that
the tunnel must be mated and sealed in an automated
manner once the vehicle lands on the moon. The tradeoff
becomes added complexity for automated connection /
sealing versus improved safety. This project focuses on
the design and potentially fabrication of a mock-up IVA
tunnel / connection mechanism and demonstration of the
ability to create a pressure seal. |
|
JSC4-27-SD
|
Johnson Space
Center (JSC) |
Spacecraft |
Hydrogen Detection
in a 100% Humidity Environment for Oxygen Generation
Technologies |
Key to any exploration effort
will be generating oxygen for the crew. For example, the
Oxygen Generator Assembly (OGA) on the International
Space Station (ISS) generates oxygen by electrolysis of
water. A current problem of this process is that the
oxygen exits the OGA at ambient temperature and
pressure, but at 100% relative humidity (RH) due to
un-reacted water vapor. The by-product of the
electrolysis process is hydrogen, which is very
flammable. Normally, hydrogen is vented from the cabin
environment, but there are several hydrogen sensors
located in and around the OGA to check for hydrogen
leaks. If the hydrogen sensor indicates anything other
than nominal, the entire OGA is shut down. ?Other than
nominal? has, in the past, meant moisture has condensed
on the sensor, rather than hydrogen being detected. The
design project would be to make this system halt from
occurring. The recommended approach is three-fold: 1)
attempt to heat the sensor slightly and/or thermally
insulate it; 2) create a cold spot upstream of the
sensor so that water vapor will deliberately condense
away from the sensor and then the condensed water would
need to be continuously wick away the water vapor (no
gravity available!); and 3) then heat the air back to
ambient temperature, resulting in a less-than-100%
relative humidity exit stream. This will require
applying fluid mechanics of two phase flow in zero
gravity, steam thermodynamics, and heat transfer
techniques and design. This project and resulting
prototype would not need to involve 100% O2 or H2 to
test the approach. |
|
JSC4-34-SD
|
Johnson Space
Center (JSC) |
Spacecraft |
Robust Miniature
Lightweight Multifunction General Purpose Measurement
Tool |
In current and future space
travel, electronics will play an important part. These
electronics are increasingly complex. Occasionally, an
electrical or electronics system will fail. In order to
troubleshoot the problem, a single handheld instrument
is needed. It should have the combined capabilities of a
multi-meter, oscilloscope, protocol analyzer, network
analyzer, spectrum analyzer, hand held computer, and
technical reference database in a rugged, radiation
tolerant, easy to use unit. This tool would be the Swiss
Army Knife of the International Space Station, Crew
Exploration Vehicle and Lunar Habitat Electrical and
Electronics Installation and Test. Some capabilities
include: ? Unit should be easily used by an astronaut,
with a user interface that can be used in bright
sunlight, or dimly lit environment. ? Use of high
reliability universal front end electronics and virtual
instrument interface coupled with field programmable
analog arrays, and FPGA to maximize universality. |
|
JSC4-35-SD
|
Johnson Space
Center (JSC) |
Spacecraft |
Telemetry in Audio
Compression CODEC |
The Constellation Vehicle Orion
will utilize the Internet Protocol (IP) for voice and
data communications via the radio frequency links to the
Mission Control Center (MCC) routing through Tracking
and Data Relay Satellite (TDRSS). For redundancy and
safety a ?dissimilar? audio link will communicate
simultaneously with the ground via line-of-sight, during
critical mission phases, i.e. launch and landing. This
communications link will not be IP but will be digital
with compressed audio. The audio speech compressor (Vocoder)
will be Conjugate Structured Algebraic Code Excited
Linear Predictor (CS-ACELP) as defined by ITU-T G.729.
The IP data will be delayed due to the difference in
path from the ground to the vehicle, i.e. one is
line-of-sight the other via the TDRSS. This project will
be to create the algorithms and prototype the system for
this redundant audio link. It is the intent to deliver
both audio communications simultaneously to the headsets
of the onboard astronauts, without degradation in
intelligibility cause by time delay echo. It is desired
to encode a short duration, 10-20ms, sync. signal at the
beginning of a ground based voice transmission allowing
the line-of-sight speech data to be synchronized with
the IP voice data, thus presenting the audio to the
astronauts headsets simultaneously. A method of reliably
encoding sync. data in the G.729 encoder needs to be
developed. |
|
JSC4-36-SD
|
Johnson Space
Center (JSC) |
Spacecraft |
Implement Codecs on
FPGAs |
This project will be to
implement ITU standard G.729 (CS-ACELP) and G.722.2
(AMR-WB) speech compression codecs on FPGA target. These
codecs are typically implemented on Digital Signal
Processors (DSP). Constellation wants to implement the
codecs on an FPGA so that redundant data-bus audio
packet management, speech signal extraction and
compression can happen on a single chip, minimizing
mass, power and size requirements. |
|
JSC4-37-SD
|
Johnson Space
Center (JSC) |
Spacecraft |
Development of a
Multi-Functional Internal Configuration for a Lunar
Lander |
Given the pressurized
volumetrics of a lunar lander module, develop the
internal configuration for a human crew of four
astronauts for 7 days. This module must provide for the
habitability of the crew as well as the support
functions necessary to accomplish the mission
objectives. This project will have applicability to the
Constellation Program. The project objective is to
design this lunar lander module's functional areas
(types required will be provided) in such a way that
allows for singular or multi-task activities to occur.
Constraints will also be provided (e.g., mass
allotments). |
|
JSC4-40-SD
|
Johnson Space
Center (JSC) |
Spacecraft |
Verification
Analyses in Support of the Second ISS Treadmill |
NOTE: This is a one semester
project that must be done in the Fall semester 2008. The
International Space Station Program is planning to begin
six man operations in mid 2009. The Treadmill is a
critical countermeasure device required to maintain crew
health while on-orbit and prepare them for return to
Earth. To augment the needs of a six member crew, a
second treadmill is required. The overall approach for
the T2 project is to utilize as much existing NASA
Program Hardware as possible and couple it with an
existing, commercially available high reliability
treadmill. The Treadmill and supporting subsystems
(power, cooling, etc.) will be housed in an
International Standard Payloads Rack (ISPR) and the
vibration isolation system will be a modified Passive
Rack Isolation System (PaRIS). The entire assembly is
planned to be housed in the Node 2, and will then be
moved to Node 3 upon its arrival to ISS. The targeted
launch of the T2 system is currently ULF-2. Senior
Design Project Description: Verification Analyses in
Support of the Second ISS Treadmill The senior design
project will consist of a grouping of 3 to 6 analyses
(depending on complexity) required to verify the Second
ISS Treadmill (T2) design meets the Engineering
Specifications and/ or Environmental Compliance
Requirements for the International Space Station.
Treadmill Project will provide: 1. Description of the
problems/analyses to be performed 2. All relevant data
needed for analysis including: Relevant Treadmill Design
Data and applicable test data results. Senior Design
Team will provide: 1. Written analysis that clearly
determines whether the design and/or test data provided
meets the ISS requirement. 2. If design does not meet
requirement, recommendation on test or design change to
bring design into compliance with requirement. |
|
JSC4-41-SD
|
Johnson Space
Center (JSC) |
Spacecraft |
Materials Science
of Manned Spacecraft Radiation Shielding |
This project will involve
examining crew dose, materials dose, and avionics single
event effects (SEE) environments and how it is affected
by manned spacecraft radiation shielding. The project
team will use the FLUKA (http://www.fluka.org/ )
ionizing radiation transport code to explore the
effectiveness of various materials and materials
combinations in attenuation of galactic cosmic ray and
solar cosmic ray dose to the interior of relatively
massive (compared to robotic vehicles) manned
spacecraft. The objective here is to compare different
materials in simple geometries so that materials effects
on secondary particle production and stopping power can
be determined and visualized directly with no
complications from specific spacecraft configuration
effects. Validation of the FLUKA tool against available
space flight data and ground based accelerator data is
an essential part of the project. Participants in this
project should strongly consider a similar internship
available at JSC during the Summer of 2009. |
|
JSC4-42-SD
|
Johnson Space
Center (JSC) |
Spacecraft |
Geomagnetic Storms,
Traveling Ionospheric Disturbances (TIDs), and Solar
Cycle Effects on Neutral Atmosphere |
The objective of this project
is to evaluate existing (albeit cutting edge) tools used
to predict the scale of the ISS attitude control or
satellite drag anomalies expected as a result of
geomagnetic storm events or as the upper atmosphere
become immediately denser during geomagnetic storms and
gradually denser as we approach the upcoming solar
maximum, the magnitude and character of which is proving
more difficult to predict than was the case for the last
several solar maxima. Participants in this project
should strongly consider a similar internship available
at JSC during the Summer of 2009. |
|
JSC4-43-SD
|
Johnson Space
Center (JSC) |
Spacecraft |
International Space
Station as a Nano/Micro Satellite Base |
This project is an evolution of
the sounding rocket base (Wallops, White Sands, Poker
Flats etc.) idea as suggested by the free launch
services provided for micro satellite and nano
satellites by ESA on the Arianne launcher and used
extensively by Surrey Satellite customers. Specifically,
the project team will need to provide a report with the
following information: a) Feasibility - assessment of
earth-to-orbit transportation opportunities to ISS in
the post Shuttle era. b) Concept - multi-satellite
carrier to attach to ISS externally and provide
controlled mechanical deployment/launch over some range
of vectors compatible with ISS safety (collision
avoidance). c) Launch opportunities for satellite
carrier assembly - Progress, Soyuz, ESA/ATV, JAXA/HTV,
Commercial Carriers (COTS Program), Orion. d) Matching
the concept to the agency road maps and science
objectives/needs of, for example, the National Science
Foundation, NASA Science Mission Directorate, and the
National Oceanics and Atmospherics Administration.
Participants in this project should strongly consider a
similar internship available at JSC during the Summer of
2009. |
|
Kennedy Space
Center (KSC) |
|
KSC1-02-SD
|
Kennedy Space
Center (KSC) |
Lunar and Planetary Surface
Systems |
Senior Biological
Engineer |
The goal of this senior design
project is the design, integration, and evaluation of
components, subsystems, and systems of a prototype
habitat module. NASA could then validate and test
concepts for the ultimate design of a ?Surface Habitat
Module? to be used on the Moon or Mars. The focus will
be on the design of components, subsystems, and systems
to reduce resupply of life support elements (i.e., air,
water, and food), and incrementally evolve and integrate
current resupply methods and physical-chemical
technologies with bioregenerative technologies. This
project should emphasize the critical system selection
criteria of minimum launch mass, efficient utilization
of volume and power, and minimization of crew labor time
and lifecycle costs. Depending on the desired scope of
the senior design project, a sub-set of the design
elements and requirements may be selected to reduce the
scope of the project so that it would be suitable for a
senior design project related to this topic. The POC for
this project has agreed to be contacted prior to the
start of the project for more specifics concerning
current priority focus areas and recommendations
concerning elements to include for a reduction of the
project to a desired scope. This project is recommended
for majors including mechanical engineering, biology,
microbiology/bacteriology, agricultural engineering, and
chemical engineering. The design elements to be
considered include: structures, automation and
mechanization (robotic manipulators), sensors,
command/control and data handling, and power. The
habitat subsystems will consist of plant-based food
production and processing, integrated biological
processors for liquid and solid waste streams, systems
monitoring with steady state and predictive control, and
mass transfer interfaces for each subsystem utilizing
NASA standard human life support (food, air, water and
waste) input/output streams. Reliability of the
mechanical and biological elements should be considered
in the component design, and elements selected should be
adaptable for remote, automated/semi-automated
operation. Each dynamic subsystem should be mechanized
where possible and incorporate configurations that
accommodate expansion and integration of the habitat
life support system. Incremental infrastructure
developments should be integrated into all system
element designs. The system must be able to identify
abnormal operations and reconfigure to normal operations
without human intervention. The six requirements for the
system elements are: 1. Automation/Mechanization -
Should require less than 1 crew member hour per day to
maintain (crew of 4 requires 4 hours/day) 2. Food,
Water, and Oxygen Production - System should produce
quantities of each element based on ISS crew
requirements (crew of 4) for an extended mission
(greater than 9 months) 3. In-Situ Resource Utilization
- System shall reduce mission mass by making maximal use
of available resources 4. Reliability - Elements should
be designed to minimize single point failures 5. Fault
Tolerance - Elements/System should maintain
functionality through reconfiguration or by switching to
a redundant backup 6. Modularity - Elements/System
should be designed to interface with current life
support technologies and allow for ease in upgrading,
expansion, or repair The bioregenerative technologies
for the plant production subsystem should support
multiple crops with an emphasis on incremental expansion
from fresh vegetable production to 50% caloric dietary
production. Consideration should be given to the
capability to photosynthetically revitalize the
atmosphere (CO2/O2 cycling), take advantage of
transpired water production, and improve the efficiency
of processing water and food production in a controlled
environment. The terminal design should develop the
subsystems for an integrated biological system that will
provide at least a 1 person-equivalent of air
revitalization, a 5 person-equivalent of water, and a
0.1 to 0.5 person-equivalent of food. System elements
for the plant production subsystem should include water
and nutrient delivery technologies, control, monitoring,
and sensors for remote, semi-automated operation. Other
major elements should include LED lighting to support
plant growth, thermal control systems, atmospheric
monitoring and control (CO2, O2, H2O, ethylene, etc.),
and crop health monitoring. Biological waste processing
elements/systems should be designed to treat inedible
plant material and other solid wastes, provide a soluble
nutrient source for recycling back to hydroponic plant
production, and the recovery and polishing of water
processed through the plant systems. Design
considerations should include the capability for
integration of biological systems with resupply and
physical/chemical systems to achieve a reduction of
resupply mass and improved life cycle costs coupled with
increased reliability and robustness. The design
problems should be reduced to an appropriate focus and
scope for the student?s experience, academic
backgrounds, and expected outcome within the allotted
time of the design course. Design elements should be
compartmented from the habitat subsystems; plant-based
food production and processing, solid waste processing,
and water recovery; and address one or more specific
aspects of the six requirements for the system elements
to serve as stand-alone design projects. |
|
KSC1-05-SD
|
Kennedy Space
Center (KSC) |
Lunar and Planetary Surface
Systems |
Lunar Regolith
Excavation O2 Prod/Outpost Emplace |
The feedstock required for O2
production on the moon is Lunar Regolith (soil). 100
metric tonnes (MT) of Lunar Regolith will be required
each year for Oxygen Production of 1 MT. In addition up
to 2,000 MT of regolith excavation will be required per
year in the initial stages of Outpost construction. This
project will investigate concepts for Lunar Regolith
excavation equipment and propose solutions in the form
of completed designs and prototypes. |
|
KSC1-06-SD
|
Kennedy Space
Center (KSC) |
Lunar and Planetary Surface
Systems |
Lunar Operations
Cryogenics Consumables Transfer |
Oxygen that is produced on the
moon must be transferred to the end user. In addition
there will be residual propellants on the descent stage
that can be scavenged and re-used as valuable
commodities. This project will identify methods for
cryogenics consumables transfer and appropriate dust
tolerant interfaces. |
|
KSC1-07-SD
|
Kennedy Space
Center (KSC) |
Lunar and Planetary Surface
Systems |
Umbilicals and
Quick Disconnect Couplings for Lunar Cryogenics
Consumables Transfer |
A Quick Disconnect (QD) Fluid
Coupling that is dust tolerant and does not leak is
required for transferring cryogenic and other liquid
consumables on the moon. |
|
KSC2-01-SD
|
Kennedy Space
Center (KSC) |
Ground Operations |
Packetized
Telemetry Converter |
Utilizing reconfigurable logic
devices, develop a system that accepts packetized
telemetry (reference CCSDS 702.1-R-1, 714.0-B-1,
727.0-B-3 and 732.0.B-2) and outputs a PCM stream
compatible with IRIG-106-05 Ch.4 for input to existing
ground based telemetry processors. The intent of this
project is to determine whether existing KSC telemetry
processing devices can be utilized in the Constellation
packet telemetry environment or if all the PCM based
devices need to be replaced. The use of FPGA type
devices provides the flexibility to update the
translation routines without requiring hardware
change-out. |
|
KSC2-04-SD
|
Kennedy Space
Center (KSC) |
Ground Operations |
Habitat Design |
The goal of this senior design
project is the design, integration, and evaluation of
components, subsystems, and systems of a prototype
habitat module. NASA could then validate and test
concepts for the ultimate design of a "Surface Habitat
Module" to be used on the Moon or Mars. The focus will
be on the design of components, subsystems, and systems
to reduce resupply of life support elements (i.e., air,
water, and food), and incrementally evolve and integrate
current resupply methods and physical-chemical
technologies with bioregenerative technologies. This
project should emphasize the critical system selection
criteria of minimum launch mass, efficient utilization
of volume and power, human factors, habitation, cultural
interaction, minimization of crew labor time, and
lifecycle costs. This project is appropriate for human
factors, any engineering major, anthropology, or
psychology majors. |
|
KSC2-08-SD
|
Kennedy Space
Center (KSC) |
Ground Operations |
Innovative uses of
ESMD's Distributed Observer Network (DON) for education
& other NASA purposes |
Form a multidisplinary team to
interface with KSC intern to test and evaluate other
uses of DON and provide results in oral and written
form. Various aspects of simulation usage including
communication and teaming, human factors, use of
simulation for educational purposes (k-12 through
professional), and distributed teaming will be
addressed. This project is appropriate for human
factors, computer science, any engineering major,
anthropology, psychology, graphical arts, or education
majors. |
|
KSC2-09-SD
|
Kennedy Space
Center (KSC) |
Ground Operations |
Simulation that
Supports Synthesis |
Analyze existing simulation
tools and recommend tools and techniques to improve the
usability of simulation tools. Various aspects of
simulation usage including communication and teaming,
human factors, and distributed teaming will be
evaluated. This project is appropriate for human
factors, computer science, any engineering major,
anthropology, psychology, or graphical arts majors. |
|
KSC2-11-SD
|
Kennedy Space
Center (KSC) |
Ground Operations |
Universal Wireless
Sensor |
Recent developments in the
availability of low cost, low power microcontrollers
have underscored the amazing things one can do in
integrated silicon in today’s market. In particular,
there is an ever increasing trend to integrate more
peripheral’s into modern microcontrollers including
additional A/D channels, digital I/O, serial
communication interfaces, analog comparators, and Pulse
width modulation channels for analog outputs with prices
starting at under $0.48 and averaging less than $5.00.
As an example consider the device from ATMEL semi, the
8-bit RISC processor, ATMEGA168, with a single unit
price of ~$4.00
Device: Flash (Kbytes) EEPROM (Kbytes) SRAM (Bytes)
F.max (MHz) Vcc (V) 16-bit Timers 8-bit Timer PWM
(channels) RTC SPI UART TWI ISP 10-bit A/D (Channels)
Analog Comparator
ATmega168 16 0.5 1024 20 1.8-5.5 1 2 6 Yes 1+USART 1 Yes
Yes 8 Yes
This unit has (8) 10bit A-D channels, 6 analog output
channels (PWM), has serial communication interface built
in, and can operate from off the self alkaline batteries
for weeks. This is in contrast to a typical
programmable logic controller deployment with KSC’s
ground power system which involves over $10K in
controller hardware for a very similar IO count. More
recently, microcontroller vendors have begun to offer
wireless communication chipsets that are designed for
integration with their controller lines. While many of
the products that will emerge have not made it to market
yet, the simplicity of the hardware all but guarantees
they will. However, the time constants in the R&D cycle
as well as UL listing often delay products to market.
This makes for an excellent opportunity to develop ahead
of the private sector a wireless device suitable for KSC
use that costs under $20.00 in materials and is fully
functional in KSC ground applications. Proposed
Requirements:
I/O Capability: (1) Support Analog input with 10 bit or
better resolution AND (1) digital sensor using I2C, TWI
or other standard serial interfaces
Sample Rate: Variable based in battery life requirements
but be configurable from 1 sample/minute to
100kSamples/sec
Power Requirements: Make use of controller sleep and
standby modes to extend battery life to fullest extent
Size: Limited to one 2”x4” single layer PCB
Connectivity: Transmit wirelessly over Zigbee IEEE
802.15.4 and via USB to a laptop
Data Storage: Support onboard data storage or remote
poll via Zigbee.
Cost: Under $20.00 BOM for 10k units
Project Program: Microcontroller specific C Code
Deliverables:
(1.) (3) Demo units configured to demonstrate Zigbee’s
mesh networking capabilities with both digital and
analog sensor inputs
(2.) C code for entire project
(3.) Development tools if not freeware (ATMEL
development environment is totally free)
(4.) PCB layout files so that the government can produce
at its leisure from PCB express or other online
builders.
|
|
Langley Research Center (LaRC) |
|
LARC1-12-SD
|
Langley Research
Center (LaRC) |
Lunar and Planetary Surface
Systems |
Development of
Lunar Technology Educational Display |
The primary objective for this
project is to develop an educational display and/or
software to understand the challenges engineers face as
they create technologies that will enable humans to live
and work on the Moon. The display or software could
include a simulation of the Small Pressurized Vehicle,
which will help astronauts work on the Moon. |
|
LARC1-14-SD
|
Langley Research
Center (LaRC) |
Lunar and Planetary Surface
Systems |
Design of a Robot
Operator/Controller |
This project involves the
design of an operator/controller for a robot arm. The
user would define a visual image using a video camera
and guide the end-effecter to the location of an object.
A student team would undertake a feasibility study and
design the controller interface and algorithms. |
|
LARC1-15-SD
|
Langley Research
Center (LaRC) |
Lunar and Planetary Surface
Systems |
Design of an
End-Effecter for a Robot Arm |
This project involves the
design of an end-effecter for a robot arm. Tasks to be
performed by the robot arm include: deployment of a
science instrument/sensor, scooping, and gripping/moving
material/items. Constraints include power, mass, and
space considerations. The project also involves the
determination of additional potential lunar functions
for the end-effecter. |
|
LARC1-16-SD
|
Langley Research
Center (LaRC) |
Lunar and Planetary Surface
Systems |
Algorithm
Development for Robot Guidance and Control |
This project involves the
development of algorithms which use various types of
input data to accomplish autonomous robot guidance and
control. The students will develop algorithms which
process and merge data from various sources - video,
laser range finders, gyro, GPS, etc. - in order to
control a robotic device. An appropriate user interface
will also be developed. |
|
LARC1-17-SD
|
Langley Research
Center (LaRC) |
Lunar and Planetary Surface
Systems |
Design, Modeling,
and Performance Simulation of Lidar Systems for Sensing
Trace Gases |
Lidars for sensing water vapor,
ice, and several atmospheric trace gases are being
investigated. Students will develop computer models for
evaluating the merits of several lidar techniques for
optimum system development. There could be some test
experiments, provided students have requisite training
in using lasers that includes laser safety training and
eye exams. |
|
LARC1-18-SD
|
Langley Research
Center (LaRC) |
Lunar and Planetary Surface
Systems |
Development of
Mid-IR Laser-Based Differential Absorption Lidar (DIAL)
for Water Vapor Detection |
Students will be involved in
developing the capability (modeling and simulation) of
sensing water vapor on Mars and in other planetary
atmospheres using lidars. (There could be some test
experiments provided students have requisite training in
using lasers that include laser safety training and eye
exams.) |
|
LARC4-11-SD
|
Langley Research
Center (LaRC) |
Spacecraft |
Development of
Gravitational Acceleration Educational Display |
The primary objective for this
project is to develop an educational display and/or
software comparing the gravitational acceleration of the
ARES 1 rocket, including the Launch Abort System, to
roller coasters, games of the winter Olympics, skate
boards, and other games and sports that youth can relate
to. The display could be a kiosk that would be used at
museums, science centers, educational activities, and
outreach events. |
|
LARC4-13-SD
|
Langley Research
Center (LaRC) |
Spacecraft |
Development of Mars
Lander Educational Display |
The primary objective for this
project is to develop an educational display and/or
software emphasizing the challenges of entry, descent,
and landing on Mars. The user would become the
"engineer" and solve problems related to landing on a
planet that has an atmosphere. |
|
LARC4-19-SD
|
Langley Research
Center (LaRC) |
Spacecraft |
Design of Scaled
Spacecraft and Test Apparatus to Enable Assessment of
Water Landing for Orion-Type Vehicles |
This work is important in the
context of the development of the Orion Landing System
and has potential for future spacecraft design. The
focus of the undergraduate engineering design team will
be the design and fabrication of a scaled capsule and
testing apparatus for landing in water. The model of the
Orion spacecraft should land in water with various
combinations of horizontal and vertical velocities and
impact attitudes in a parametric study. Measurements of
interest will be tri-axial accelerations at the center
of gravity and pressure variation on the heatshield. |
|
LARC4-20-SD
|
Langley Research
Center (LaRC) |
Spacecraft |
Determination of
the Chemical Composition of Nanomaterials for Aerospace
Applications |
This project involves the
characterization of the chemical composition of
nanomaterials for aerospace applications using energy
(or wavelength) dispersive spectroscopy, x-ray
diffraction, atomic absorption (or emission)
spectroscopy, mass spectrometry, and/or nuclear magnetic
resonance spectroscopy. The materials will be provided
to the project team by the NASA POC. The overarching
purpose of this and related projects is to understand
the morphology and mechanical, electrical, magnetic, and
chemical properties of the fabricated materials and then
attempt to correlate those results to the modeled and
observed nanoscale structures. |
|
LARC4-21-SD
|
Langley Research
Center (LaRC) |
Spacecraft |
Determination of
the Surface Conductivity of Nanomaterials for Aerospace
Applications |
This project involves the
characterization of the surface conductivity of
nanomaterials for aerospace applications using a
four-point probe for mapping. The materials will be
provided to the project team by the NASA POC. The
overarching purpose of this and related projects is to
understand the morphology and mechanical, electrical,
magnetic, and chemical properties of the fabricated
materials and then attempt to correlate those results to
the modeled and observed nanoscale structures. |
|
LARC4-22-SD
|
Langley Research
Center (LaRC) |
Spacecraft |
Determination of
the Surface Energy of Nanomaterials for Aerospace
Applications |
This project involves the
characterization of the surface energy of nanomaterials
for aerospace applications using contact-angle
goniometery. The materials will be provided to the
project team by the NASA POC. The overarching purpose of
this and related projects is to understand the
morphology and mechanical, electrical, magnetic, and
chemical properties of the fabricated materials and then
attempt to correlate those results to the modeled and
observed nanoscale structures. |
|
LARC4-23-SD
|
Langley Research
Center (LaRC) |
Spacecraft |
Determination of
the Surface Chemistry of Nanomaterials for Aerospace
Applications |
This project involves the
characterization of the surface chemistry of
nanomaterials for aerospace applications using x-ray
photoelectron spectroscopy. The materials will be
provided to the project team by the NASA POC. The
overarching purpose of this and related projects is to
understand the morphology and mechanical, electrical,
magnetic, and chemical properties of the fabricated
materials and then attempt to correlate those results to
the modeled and observed nanoscale structures. |
|
LARC4-24-SD
|
Langley Research
Center (LaRC) |
Spacecraft |
Determination of
the Surface Roughness of Nanomaterials for Aerospace
Applications |
This project involves the
characterization of the surface roughness of
nanomaterials for aerospace applications using an atomic
force microscope. The materials will be provided to the
project team by the NASA POC. The overarching purpose of
this and related projects is to understand the
morphology and mechanical, electrical, magnetic, and
chemical properties of the fabricated materials and then
attempt to correlate those results to the modeled and
observed nanoscale structures. |
|
Marshall Space Flight Center
(MSFC) |
|
MSFC1-07-SD
|
Marshall Space
Flight Center (MSFC) |
Lunar and Planetary Surface
Systems |
Radiation Effects
on Electronics Modeling |
Develop advanced models of the
natural radiation environment to diagnose and predict
the effects of Single Event Effects (SEEs) on modern
electronic architectures. |
|
MSFC1-08-SD
|
Marshall Space
Flight Center (MSFC) |
Lunar and Planetary Surface
Systems |
Reconfigurable
Computers |
Provide reconfigurable
computing capability, resulting in reduction of flight
spares and risk reduction for limited circuit lifetimes. |
|
MSFC1-09-SD
|
Marshall Space
Flight Center (MSFC) |
Lunar and Planetary Surface
Systems |
Integration of
Surface Mobility Systems through Systems Engineering |
Designing and building surface
mobility mechatronics systems by multi-disciplinary
teams. Not only the design of such systems but also the
process of developing the entire system will be
emphasized. |
|
MSFC1-13-SD
|
Marshall Space
Flight Center (MSFC) |
Lunar and Planetary Surface
Systems |
Using Lunar
materials and solar energy for Lunar Base self-reliance |
Design a self-supporting system
for the Lunar outpost using lunar materials and solar
energy. The system can supply any necessity for the
astronauts (water, oxygen, spair parts, food etc.) |
|
MSFC1-14-SD
|
Marshall Space
Flight Center (MSFC) |
Lunar and Planetary Surface
Systems |
Planetary
Instrument Sample Collection Device |
Marshall Space Flight Center
has been developing a miniaturized Scanning Electron
Microscope for in situ imaging and chemical mapping of
samples for use on the Moon (as well as other planetary
bodies.) This project would require the mechanical
design and prototyping of a sample collection scheme
that would take samples from the lunar surface and
introduce them into a sample chamber for analysis. A
fully automated sample collection device would allow for
the instrument to be operated remotely from a rover.
Some key considerations instrumental to this design are
dust mitigation, selectable sample size, temperature
fluctuations on the lunar surface, and compactness of
design. |
|
MSFC1-20-SD
|
Marshall Space
Flight Center (MSFC) |
Lunar and Planetary Surface
Systems |
NASA X-TOOLSS (eXploration
Toolset for Optimization Of Launch and Space Systems) |
Description: Use of the NASA
X-TOOLSS software for design optimization of conceptual
space systems. NASA X-TOOLSS is based on genetic and
evolutionary algorithms, which have proven successful
for global optimization of complex systems, and for
applications where unique and innovative designs are
sought. An advantage of NASA X-TOOLSS and
genetic/evolutionary optimization is that the design
space is not limited to existing designs and approaches.
Example applications of interest for NASA X-TOOLSS
include habitats for the Moon and Mars, lunar surface
mobility and power systems, lunar descent module and
lander concepts, and thermal/structural design of small
satellites and other spaceflight hardware. |
|
MSFC1-22-SD
|
Marshall Space
Flight Center (MSFC) |
Lunar and Planetary Surface
Systems |
Development,
characterization and Evaluation of Lunar Regolith and
Simulants |
MSFC is developing a method to
create lunar regolith simulants that will match the
properties of the lunar surface. This process requires
preparation of silicate mineral separates from inneous
rocks. Design, testing and cost analysis of a system
able to produce batches of separates between 1 and 100
tons is needed. A successful method will be an
important step in an overall effort involving a dynamic
national and international team. |
|
MSFC1-23-SD
|
Marshall Space
Flight Center (MSFC) |
Lunar and Planetary Surface
Systems |
Development of
lunar composting capability |
Composting of human food and
other waste on the moon will be desirable, both from the
standpoint of reuse of biochemicals (in support of
longterm habitation) and in order to protect human
health. While composting in lunar soil may desirable, it
not be feasible. Lunar soil is, in contrast with most
earth soils, completely mineral. More importantly, it is
believed to be mechanically, and possibly chemically,
hazardous to biological systems. Semester 1: Assess
existing literature; identify sources of unpublished
data and evaluate publication of recovered information.
Characterize the risks and benefits of use of lunar
soils for composting foodwastes, paper and cardboard,
and sewage. Address each type of waste separately and in
combination, as well as microbiological culture
required. Develop design concepts for a composting
system. Plan testing that addresses regolith simulators
and effects of gravity; document in a test plan.
Semester 2: Execute complete design based on concepts.
Fabricate and assemble. Conduct testing defined in test
plan and execute report. |
|
MSFC1-24-SD
|
Marshall Space
Flight Center (MSFC) |
Lunar and Planetary Surface
Systems |
Lunar habitat
situational awareness |
In order to provide radiation
shielding, thermal insulation, and impact protection,
the covering of the lunar habitat will be very thick,
likely including regolith. Physical windows in the
habitat hull will be limited at best. Suggest schema and
technologies to allow the crew to be kept informed
(without constant human monitoring of the hemisphere
around the habitat. System requirements would include,
but not be limited to, planning and coordination of
multiple ExtraVehicular Activities (EVA); habitat
integrity monitoring; and recording of environmental
events, such as meteoroid strikes or passages, and solar
energetic events. The system should consist of internal
controls and displays in the habitat and the external
means to gather information. Multispectral data
collected simultaneously (visible, IR, UV, and high
energy) may be useful. Consider methods such as
?difference modeling? to extract crew-useful information
from the collected data. Semester 1: Develop the
concepts for the situational awareness system. Address
cost, mass, and volume, as well as where the system
components would be located both inside and outside the
module. Describe the technologies to be used and note
which are commercially available and which need further
development. Semester 2: Prototype the system and
demonstrate its capabilities. Propose further work. |
|
MSFC1-25-SD
|
Marshall Space
Flight Center (MSFC) |
Lunar and Planetary Surface
Systems |
Design of Lunar
Garage |
NASA will need a garage
facility to repair & maintain Lunar Roving Vehicles
(LRVs) once we return to the moon. The garage could be
pressurized for a shirt sleeve environment or
unpressurized for a space suit environment or perhaps
both (unpressurized for minimal maintenance, pressurized
for more extensive repairs). Semester 1: Using the size
of the Apollo LRV as a guide to the vehicle size to be
accommodated, propose concepts for the garage using
minimal launched mass as a major constraint. This might
lead to an inflatable design, or one built from regolith
in sand bags for example. Consider what tasks might need
to be done on the LRV, based on the Apollo experience,
and provide clearance in the garage for the work to be
done by two crew. Plan evaluation activities and
document in test plan. Semester 2: Construct & test the
garage based on the overall design constraints
formulated during the first semester. |
|
MSFC1-26-SD
|
Marshall Space
Flight Center (MSFC) |
Lunar and Planetary Surface
Systems |
Partial Gravity
Crew Interface Design |
The microgravity experience has
illustrated the need to accommodate the differences in
human performance due to different gravity fields.
NASA?s short term interest is in 1/6 g for Lunar
habitats, but is also in 1/3 g for Mars. Appropriate
architectural design for habitats requires establishing
partial Gravity Crew interface design principles such as
the transition angles between ramps, stairs, stair
ladders, and stairs. These are well established for 1 g,
but are still unknown for 1/6 & 1/3 g. Semester 1:
Propose methods to determine the transition angles for
Lunar habitats. Document in test plan. Semester 2: Carry
out the experiments and determine the transition angles
for 1/6 g, and (time permitting) 1/3 g. |
|
MSFC2-28-SD
|
Marshall Space
Flight Center (MSFC) |
Ground Operations |
Simulation of
Propellant loading in Launch Vehicle |
MSFC has developed a
Generalized Fluid System Simulation Program (GFSSP) for
modeling and simulation of propulsion systems. GFSSP is
a finite volume based network flow analysis code that
can model cryogenic propulsion systems. MSFC is
currently working on a project to develop numerical
modeling techniques for simulating propellant loading of
Ares I Launch Vehicle. The objective of this
computational project is to develop a methodology to
estimate the time required to chilldown the ground
system, amount of propellant used to chilldown and to
ensure that during loading operation, the propulsion
system does not violate any design criterion. |
|
MSFC3-06-SD
|
Marshall Space
Flight Center (MSFC) |
Propulsion |
Nuclear Fission
Surface Power Design |
This project will focus on the
design and potential utilization of a 20?40 kWe Fission
Surface Power System for use anywhere on the surface of
the moon or Mars. The project will include performing a
top level design of the Fission Surface Power System,
including the reactor, shield, power conversion, power
management and distribution, and radiator. Potential
uses of the electrical or thermal energy from the
reactor should be identified. Methods for emplacing and
deploying the system should also be discussed. Emphasis
should be on systems that minimize programmatic risk and
utilize well proven technologies. |
|
MSFC3-12-SD
|
Marshall Space
Flight Center (MSFC) |
Propulsion |
Liquid engine
system performance modeling and Predictions |
To further develop PSTAR, the
first order modeling tool, by providing the capability
to perform off-design analysis of liquid rocket engines
,while improving performance, weight and cost
predictions. There are up to 4 senior design projects
available -- off design capability, performance
improvements, weight model improvements and cost model
improvements. |
|
MSFC3-16-SD
|
Marshall Space
Flight Center (MSFC) |
Propulsion |
Diagnostics for
plasma propulsion systems |
Plasma-based systems are
typically applied to situations where very high gas
velocities are required. As a space thruster,
plasma-based devices expel their propellant at a much
greater velocity than chemical rockets. Consequently,
they require less propellant to complete a given
mission, leaving more room on a spacecraft for
hardware/consumables/instruments. Plasma based devices
also find use in studies where the fast plasma can be
used to accelerate small particles up to the speeds
typical of in-space micrometeorites impacting a
spacecraft or habitat. There is a need to have
diagnostics that can measure the time-varying plasma
properties in such devices to validate the present
theoretical understanding and to serve as experimental
benchmarks that can support the development of models.
Senior project opportunities are available in designing
and constructing robust, stand-alone diagnostic packages
with plug-n-play capability for use with many pulsed
plasma sources and in designing and fabricating
experiments for evaluation of new diagnostic techniques. |
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MSFC3-17-SD
|
Marshall Space
Flight Center (MSFC) |
Propulsion |
Liquid metal system
components for nuclear surface power |
There is presently an effort
underway at MSFC to evaluate components that might be
included in the design and eventual deployment of space
and lunar-based nuclear reactor systems. The evaluation
effort involves the use of a simulated nuclear reactor
core (comprised of resistive heating elements) where
pumped NaK (sodium-potassium eutectic) is used as the
heat-transfer medium. In these systems there is
significant need for improvement over present
state-of-the-art component technology. This includes the
need for lighter-weight, more efficient liquid metal
pumps, more accurate flow rate measurement techniques,
and capabilities to monitor the state of the liquid
metal (liquid level, temperature, etc), especially in
locations that are not easily accessible. Senior
projects would aim at evaluating different strategies to
improve technology over the present state-of-the-art
through a combination of literature research,
theoretical and numerical modeling, performance
analysis, fabrication and testing. |
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MSFC3-18-SD
|
Marshall Space
Flight Center (MSFC) |
Propulsion |
ROCETS (Rocket
Engine Transient Simulation) Improvements |
RTo improve the Rocket Engine
Transient Simulation (ROCETS) tool by making the
optimization scheme more robust, adding new design
modules and improving existing modules |
|
MSFC3-19-SD
|
Marshall Space
Flight Center (MSFC) |
Propulsion |
Main Propulsion
System and Turbomachinery Analysis by GFSSP (Generalized
Fluid System Simulation Program) |
GFSSP (Generalized Fluid System
Simulation Program) is a finite volume based network
analysis code developed at MSFC for analyzing chilldown,
loading, stratification, pressurization, feed system,
recirculation and fluid transients. It has also been
extensively used for secondary flow analysis in
turbo-pumps and many other applications that require
coupled thermo-fluid analysis involving conjugate heat
transfer. GFSSP has an user-friendly visual pre and post
processor and a modular code structure with extensive
documentation with example problems that make it ideally
suitable for Senior Design Project. |
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MSFC3-27-SD
|
Marshall Space
Flight Center (MSFC) |
Spacecraft |
Analyze, Build, and
Flight-test Rockets |
Analyze, build, and flight-test
rockets to develop systems engineering skills. Each
team will build a rocket and predict and then measure
acceleration, altitude and two other variables: such as
tank pressure and chamber pressure, Pitot pressure and
temperature, vibration, magnetic orientation in two
axes, sun sensor, gyro position, etc. |
|
MSFC4-01-SD
|
Marshall Space
Flight Center (MSFC) |
Spacecraft |
Design for
Reliability and Safety |
Safety and Reliability is a top
priority for NASA in the development of new launch
systems. There is a need to define and develop a process
that describes how to "design for reliability and
safety". This is a system engineering design project
that addresses all what needs to be done throughout all
the phase of a program (quantitative and qualitative) to
design highly reliable and safe launch systems. This
includes identification of products, tools, approaches,
etc.. by program phase. |
|
MSFC4-23-SD
|
Marshall Space
Flight Center (MSFC) |
Spacecraft |
Optimized De-Orbit
Propulsion Systems for Various Mass-Class Payloads |
NASA classifies satellites as
standard (>500 kg range), small (100-500 kg range), mini
(10-100 kg range), and nano (less than 10 kg). Each size
satellite has associated volume constraints which
together define the launch mass and volume of the
payload. All spacecraft programs are required to have a
de-orbit plan for all satellites in Low Earth Orbit.
This study will focus on determining the optimum
de-orbit system for each of the satellite sizes. The
de-orbit systems to be considered are: 1. solar sail, 2.
chemical /liquid fuel thruster, 3. natural decay, 4.
electro-dynamic tethers, 5. other. To normalize the
study, start by considering all satellites at an
altitude of 1000 km, in a circular orbit, and 28.5˚
inclination. To start the study, assume the following
masses: Standard = 500 kg Small = 250 kg Mini = 50 kg
Nano = 5 kg The study should evolve into optimization
over available trade space. |
|
MSFC4-24-SD
|
Marshall Space
Flight Center (MSFC) |
Spacecraft |
Remediation of
environmental pollutants and contaminants through
non-mechanical technologies |
Current technologies for
removal of toxic and hazardous materials from
life-contact fluids (air, wastewater) include filters
and chemical exchangers that must be discarded after
use. The limitations on mass that can be carried on
long-term missions to the moon and Mars will demand that
regenerative capabilities be developed to remove
biological materials, outgassed abiological compounds,
and lunar dust from water and air. Semester 1: Develop
concepts for remediation technologies that could be
achieved within 15 years. Address regenerative
abiological chemistries, nanotechnology, and biological
or biochemical systems. Develop proposal for
construction of one or more systems, including test
plan. Semester 2: Develop system and conduct appropriate
tests, based on test plan. Report results. |
|
Stennis
Space Center (SSC) |
|
SSC3-01-SD
|
Stennis Space
Center (SSC) |
Propulsion |
Stratification
Rates of Nitrogen Contamination in Hydrogen |
Determination of the diffusion
rate constant and buoyancy force balance at small
concentrations for nitrogen contamination in hydrogen.
The project would be the experimental determination of
the rate of stratification of gaseous nitrogen in a
container of hydrogen by introducing a small fixed
amount of nitrogen in into a volume of hydrogen (or
possibly helium for safety) and monitoring the
stratification process. |
|
SSC3-02-SD
|
Stennis Space
Center (SSC) |
Propulsion |
Determination of
Circumferential Temperature Distribution |
Determination of the
circumferential heat leak through a vacuum jacketed pipe
carrying cryogenic fluid. The project would be the
experimental determination of the circumferential
temperature distribution and heat leak under cryogenic
conditions for a vacuum-jacketed pipe in a horizontal
orientation. One of the primary goals of the
investigation would be the separation of the external
radiation component from the convective component of
heat transfer producing the circumferential temperature
variation with a partially filled inner tube. |
|
SSC3-03-SD
|
Stennis Space
Center (SSC) |
Propulsion |
Design of A Shell
Tube Heat Exchanger |
When discussing space travel
(including satellite launches), there is and always has
been a desire to lift as much payload as possible at the
lowest cost possible. In fact, SSC has been asked to
deliver 162 degree Rankine Liquid Oxygen (LOX) to
support testing of X-33, J-2X Powerpack and recently
SSME. This was accomplished by "bubbling" gaseous helium
through the LOX storage vessel until the desired
temperature was achieved. This "denser" propellant
enabled the rockets to achieve better engine performance
. Recently, a customer approached SSC with a desire to
test with 150 degree Rankine LOX, which is outside of
the capability of "bubbling". The customer described a
shell tube heat exchanger type apparatus used in
conjunction with Liquid Nitrogen to achieve temperatures
as low as 145 degree Rankine in a previous project. This
heat exchanger would not be available for our testing
series. We need to design a shell tube heat exchanger
(and associated piping) which uses Liquid Nitrogen to
achieve 145 degree Rankine LOX. The actual storage
vessel to be used is an 11,000 gallon Liquid Oxygen tank
and the required time to decrease LOX temperature is 12
hours maximum. Proof of concept can be done on a much
smaller scale to demonstrate proper operation. |
|
SSC3-04-SD
|
Stennis Space
Center (SSC) |
Propulsion |
Thermocouple
Analysis For Cryogenics Temperature Measurement in
Testing of Rocket Engines |
In the testing of rocket
engines for space exploration, it is important to
understand temperature measurement in cryogenic fluids.
Temperature measurement helps characterize the rocket
engine's operating conditions and performance.
Accurately determing the temperature requires a good
fundamental background in sensor characteristics of
numerous temperature devices and the reason for using
each in specific situations. All devices have one common
performance indicator called a "time constant".
Determing the time constant of termperature sensors that
are suddenly submerged in a cryogenic fluid can be a
challenge. Rapid boiling ensues once a room temperature
probe is dipped into the cryogenic fluid. Therefore,
NASA has a need to determine the time constant of
different types of thermocouples ( T/Cs ) and Resistance
Thermal Devices (RTDs) in cryogenics (normally LN2 will
be used). There are many different types of
thermocouples and RTDs available for rocket engine
testing . Analysis is needed for determining the best
overall thermocouple and RTD. This project seeks to
analyze and record the characteristics of various types
of thermocouples and RTDs in order to accomplish that
task . The thermocouples and RTDs will undergo a
cryogenic dip test and a specialized oil dip test.
Variables of the thermocouple include type, probe
diameter, length, depth of dip, grounded or ungrounded,
open tip or closed tip, orientation, output mv, and body
materials compatibilty with certain cryogenics. In
addition, T/Cs should be compared to RTDs that are
specifically used in the rocket engine testing world for
more accurate measurement in steady state conditions.
Normally, RTDs are slower in response. Similar variable
information will be needed for RTDs. In Industry, RTD
manufacturers measure time constants in a specific Dow
Corning Oil at a certain temperature and flow to
accurately determine the time constant without boiling.
The Dow Corning oil will be used as a control for the
experiment and is required for T/Cs and RTDs alike. It
is anticipated that the results of this project will
provide a wealth of information and experience to the
students as well as practical and valuable information
available to NASA for rocket engine testing. |
|
SSC3-05-SD
|
Stennis Space
Center (SSC) |
Propulsion |
Cryogenic Pipe
Stress |
At NASA Stennis Space Center
the use of cryogenics is very important to the testing
of rocket engines used for space exploration. It is
important to know the characteristics of piping that
carry cryogenic fluid to the testing stands. For this
project we need to be able to evaluate piping surface
temperature and stress as a function of flow condition
(full LN flow, trickle LN flow and no flow) and
environment for a pipe containing Liquid Nitrogen (LN).
For example, if the pipe is chilled with LN we should be
able to measure the surface temperature and pipe stress
for the different flow conditions. Next we should be
able to expose the top of the pipe to sunlight and rain
to see how that affects the pipe outer temperatures and
stresses along with the varied flow conditions. The
collected data should be compared with a model of the
system in ANSYS or equivalent software. |
