Ames Research Center (ARC)

Small Spacecraft

ARC1-04-SD, 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.
 

Photonic or Electronic Hit Indicator: MMOD impact detector for Orion

ARC4-09-SD, Spacecraft

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.
 

Fluidized Bed Synthesis of Carbon Nanotubes

ARC4-08-SD, Spacecraft

The project involves producing carbon nanotubes in large enough quantities to fabricate composites for civil and space aviation.
 

NASA Technology Database

ARC2-05-SD, Ground Operations

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.
 

Prognostics for Complex Systems - Damage Propatation Modeling

ARC2-06-SD, Ground Operations

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)
 

Prognostics for Complex Systems

ARC2-07-SD, Ground Operations

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.
 

FDIR Tool and Simulation Evaluation-1

ARC2-10-SD, Ground Operations

Build a simulation of the FDIR generic LH2 subsystem, the Constellation (CxP) Ground Ops LCS Blue Wagon Test Bed (fluid loading operations) or the Ames Research Center ADAPT (power management) Test bed. Nominal and off-Nominal data will be provided by NASA to validate student simulations.
 

FDIR Tool and Simulation Evaluation-2

ARC2-11-SD, Ground Operations

Build a model of the FDIR generic Liquid Hydrogen subsystem, the CxP Ground Ops LCS Blue Wagon Test Bed (fluid loading operations) or the Ames Research Center ADAPT (power management) Test Bed using a tool or algorithm which performs anomaly detection, fault detection, fault isolation, fault recovery (automated recovery or recovery recommendation) or prognostics. tool evaluation criteria include figures of merit such as speed of diagnosis, accuracy, usability, ease of model integration and ease of model maintainability. the tool or algorithm tested must be acquired by the evaluator.
 

Prognostics Analysis

ARC2-12-SD, Ground Operations

Analyze design specifications of generic hardware components (valves, sensors, transducers, relays, data acquisition modules, etc.) to identify the component dynamics/characteristics necessary to model in order to perform prognostics on a component or class of components
 

Automation Tools 1

ARC2-13-SD, Ground Operations

Develop tool(s) to automate the generation of all or a portion of a TEAMS Designer subsystem model (requires purchase of TEAMS Designer license)
 

Automation Tools 2

ARC2-14-SD, Ground Operations

Develop tool(s) or method(s) to automate the accreditation (verification) of a TEAMS Designer model (requires purchase of TEAMS Designer license) or a TEAMS-RT dependency matrix (requires purchase of TEAMS-RT Development license)
 

Automation Tools 3

ARC2-15-SD, Ground Operations

Develop tool(s) to automate the generation of an Inductive Monitoring System knowledge base
 

Automation Tools 4

ARC2-16-SD, Ground Operations

Develop tool(s) or method(s) to automate the accreditation (verification) of an Inductive Monitoring System knowledge base

Dryden Flight Research Center (DFRC)

Lunar Landing Training Vehicle

DFRC1-15-SD, Lunar and Planetary Surface Systems

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.
 

Aero-Assist Options for Mars Surface Sensor Deployment

DFRC1-17-SD, Lunar and Planetary Surface Systems

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.
 

Propulsions Systems for Planetary Gravitational Simulator

DFRC3-16-SD, Propulsion

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.

Glenn Research Center (GRC)

Extreme Environment Lander Design

GRC1-07-SD, Lunar and Planetary Surface Systems

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.
 

Lunar Surface Mobility

GRC1-08-SD, Lunar and Planetary Surface Systems

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.
 

Mechanical Components for Cryogenic Tank

GRC3-06-SD, Propulsion

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)

Design of a Spacecraft to Support a Lunar Mission

GSFC1-01-SD, Lunar and Planetary Surface Systems

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.
 

Inverse Synthetic Aperture Radar (ISAR) for Interior Mapping of Asteroid

GSFC1-11-SD, Lunar and Planetary Surface Systems

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.
 

Lunar Transverse Map Contest

GSFC1-12-SD, Lunar and Planetary Surface Systems

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.
 

Communications, Standards, & Technology Laboratory

GSFC1-13-SD, Lunar and Planetary Surface Systems

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.
 

Use of a Fabry-Perot interferometer for precise column carbon dioxide measurements and monitoring.

GSFC2-05-SD, Ground Operations

Use existing Fabry-Perot Interferometer to make daily-long term measurements of CO2 column; check calibration/stability of instrument and evaluate data.
 

Use of a Fabry-Perot Interferometer for precise column carbon dioxide measurements and monitoring

GSFC2-13-SD, Ground Operations

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)

Spacecraft Flight Project and Design Practices Software for Mission Operations Assurance

JPL2-01-SD, Ground Operations

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)

Remote Image System Acquisition (RISA) - Space Environment Monitoring

JSC1-01-SD, Lunar and Planetary Surface 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.

Remote Image System Acquisition (RISA) - Space Camera 4 (SC4) Development

JSC1-02-SD, Lunar and Planetary Surface Systems

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.
 

Remote Image System Acquisition (RISA) - Multispectral Imaging, Optical System Development

JSC1-04-SD, Lunar and Planetary Surface Systems

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]
 

Advanced Lunar Pressurized Rover (EC Priority #2)

JSC1-06-SD, Lunar and Planetary Surface Systems

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.
 

Lunar Lander EVA Crew and Small Cargo Lifting System (EC Pr #4)

JSC1-08-SD, Lunar and Planetary Surface Systems

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.
 

Hand-held magnetic lunar dust removal brush.

JSC1-09-SD, Lunar and Planetary Surface Systems

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.
 

Peel-off space suit visor protective film

JSC1-10-SD, Lunar and Planetary Surface Systems

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.
 

Dust tolerant hand tools

JSC1-11-SD, Lunar and Planetary Surface Systems

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.
 

Lunar lander dust mat

JSC1-12-SD, Lunar and Planetary Surface Systems

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.
 

Design of a Wireless Sensor Scavenging Network

JSC1-15-SD, Lunar and Planetary Surface Systems

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.
 

Dust Tolerant EVA Compatible Connectors

JSC1-17-SD, Lunar and Planetary Surface Systems

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.
 

Advanced EVA Airlock with Pressure Assisted Airlock Hatches and Dust Mitigation

JSC1-18-SD, Lunar and Planetary Surface Systems

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.
 

Producing Oxygen from Lunar Soil

JSC1-19-SD, Lunar and Planetary Surface Systems

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.
 

Proton Exchange Membrane Fuel Cells

JSC1-20-SD, Lunar and Planetary Surface Systems

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.
 

Electric Propulsion Systems

JSC1-21-SD, Lunar and Planetary Surface 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.
 

Velcro Inprovement or Replacement for Use on Space Suits and other Equipment in Dusty Lunar Environment

JSC1-22-SD, Lunar and Planetary Surface Systems

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.
 

Wall Surfaces that Allow Condensation and Low-Energy Evaporation

JSC1-23-SD, Lunar and Planetary Surface Systems

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.
 

Freeze Back Radiator

JSC1-24-SD, Lunar and Planetary Surface Systems

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.
 

Low Energy/Low Water Laundry Equipment for Space

JSC1-29-SD, Lunar and Planetary Surface Systems

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.
 

Advanced Clothing for Long Duration Human Exploration Missions

JSC1-30-SD, Lunar and Planetary Surface Systems

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.
 

Active Response Gravity Offload System Control Algorithm Development

JSC1-31-SD, Lunar and Planetary Surface Systems

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.
 

Active Response Gravity Offload System Gimbal Development

JSC1-32-SD, Lunar and Planetary Surface Systems

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.
 

Active Response Gravity Offload System Advanced Control Algorithm Development

JSC1-33-SD, Lunar and Planetary Surface Systems

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.
 

Biotechnology System Development for Lunar Outpost in Situ Resource Utilization

JSC1-38-SD, Lunar and Planetary Surface Systems

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.
 

Lunar and Martian Gravity Simulator Development for Long Duration Bed Rest Studies

JSC1-39-SD, Lunar and Planetary Surface Systems

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
 

Lightweight Electric Vehicle Transmission

JSC1-44-SD, Lunar and Planetary Surface Systems

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.
 

High Voltage, High Current 3-Phase Motor Control with PID Control

JSC1-45-SD, Lunar and Planetary Surface Systems

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.
 

Cryogenic Component Checkout and Problem Resolution

JSC1-46-SD, Lunar and Planetary Surface Systems

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.
 

DESIGN OF A HIGHLY EFFICIENT HORIZONTAL-AXIS WASHING MACHINE FOR LUNAR HABITAT

JSC1-47-SD, Lunar and Planetary Surface Systems

Clothing and laundry are key technology areas in the Constellation Program. The Constellation Program that will return astronauts to the Moon by 2020 has identified laundering as a likely necessity for life in a lunar habitat.

In a lunar habitat both water and energy are precious consumable. Hence, the best laundering system is that which requires minimum amount of water through all the washing cycles, and requires minimum drying heat and time. The wash load, after the final rinse of the washing cycles, must have the lowest possible Remaining Moisture Content (RMC) to reduce drying time and energy expenditure.

Energy in the conventional h-axis laundering process is consumed during washing by two main mechanisms: heating up the water and running motor and controls, and during the drying operation in three ways: running a fan to blow air, heating the air with an electrical element, and running the motor to the drum. Most of the energy is consumed in heating the air during the drying process. Therefore designing a washing machine that allows for a maximum water extraction from the wash load before drying is highly desirable.
 

Microphone beamforming array estimation model

JSC4-13-SD, Spacecraft

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.
 

A Field Programmable Analog Array (FPAA) Voice Activated Switch (VOX)

JSC4-14-SD, Spacecraft

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.
 

Splash-down Space Capsule Cooling

JSC4-25-SD, Spacecraft

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.
 

Space Vehicle Transfer Tunnel Automated Mating Design

JSC4-26-SD, Spacecraft

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.
 

Hydrogen Detection in a 100% Humidity Environment for Oxygen Generation Technologies

JSC4-27-SD, Spacecraft

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.
 

Robust Miniature Lightweight Multifunction General Purpose Measurement Tool

JSC4-34-SD, Spacecraft

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.
 

Telemetry in Audio Compression CODEC

JSC4-35-SD, Spacecraft

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.
 

Implement Codecs on FPGAs

JSC4-36-SD, Spacecraft

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.
 

Development of a Multi-Functional Internal Configuration for a Lunar Lander

JSC4-37-SD, Spacecraft

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).
 

Materials Science of Manned Spacecraft Radiation Shielding

JSC4-41-SD, Spacecraft

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 2010.
 

Geomagnetic Storms, Traveling Ionospheric Disturbances (TIDs), and Solar Cycle Effects on Neutral Atmosphere

JSC4-42-SD, Spacecraft

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 2010.
 

International Space Station as a Nano/Micro Satellite Base

JSC4-43-SD, Spacecraft

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 2010.

Kennedy Space Center (KSC)

Senior Biological Engineer

KSC1-02-SD, Lunar and Planetary Surface Systems

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.
 

Lunar Regolith Excavation O2 Prod/Outpost Emplace

KSC1-05-SD, Lunar and Planetary Surface Systems

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.
 

Lunar Operations Cryogenics Consumables Transfer

KSC1-06-SD, Lunar and Planetary Surface Systems

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.
 

Umbilicals and Quick Disconnect Couplings for Lunar Cryogenics Consumables Transfer

KSC1-07-SD, Lunar and Planetary Surface Systems

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.

Packetized Telemetry Converter

KSC2-01-SD, Ground Operations

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.
 

Habitat Design

KSC2-04-SD, Ground Operations

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.
 

Innovative uses of ESMD's Distributed Observer Network (DON) for education & other NASA purposes

KSC2-08-SD, Ground Operations

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.
 

Simulation that Supports Synthesis

KSC2-09-SD, Ground Operations

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.
 

Universal Wireless Sensor

KSC2-11-SD, Ground Operations

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.
 

Cryogenic Fluid Management

KSC2-12-SD, Ground Operations

Thermodynamics and refrigeration analysis for planning the Integrated Ground Operations Demonstration. This project will include zero loss LH2 launch site storage and transfer using high efficiency transfer lines and cryogenic refrigeration systems.
 

Corrosion Resistant Flame Trench Refractory Materials

KSC2-13-SD, Ground Operations

Design/materials expertise in developing component level system/testbed for testing refractory materials that must provide acceptable performance and maintain integrity during/after exposure to launch environment conditions, without spalling and with minimal cracking.

Langley Research Center (LaRC)

Design, Modeling, and Performance Simulation of Lidar Systems for Sensing Trace Gases

LARC1-17-SD, Lunar and Planetary Surface Systems

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.
 

Development of Mid-IR Laser-Based Differential Absorption Lidar (DIAL) for Water Vapor Detection

LARC1-18-SD, Lunar and Planetary Surface Systems

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.)
 

Lidar performance modeling and simulation for ACTIVE SENSING OF CO2 EMISSIONS OVER NIGHTS, DAYS, AND SEASONS (ASCENDS) program.

LARC1-25-SD, Lunar and Planetary Surface Systems

Tasks include direct detection lidar performance simulation, instrumentation modeling, investigation of modulation techniques to support CO2 and O2 lidars.
 

Development of Mars Lander Educational Display

LARC4-13-SD, Spacecraft

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.
 

Design of Scaled Spacecraft and Test Apparatus to Enable Assessment of Water Landing for Orion-Type Vehicles

LARC4-19-SD, Spacecraft

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.
 

Determination of the Chemical Composition of Nanomaterials for Aerospace Applications

LARC4-20-SD, Spacecraft

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.
 

Determination of the Surface Conductivity of Nanomaterials for Aerospace Applications

LARC4-21-SD, Spacecraft

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.
 

Determination of the Surface Energy of Nanomaterials for Aerospace Applications

LARC4-22-SD, Spacecraft

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.
 

Electromagnetic Materials Characterization of Nanomaterials for Aerospace Applications

LARC4-23-SD, Spacecraft

This project involves the electromagnetic materials characterization of nanomaterials for aerospace applications. 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.
 

Determination of the Surface Roughness of Nanomaterials for Aerospace Applications

LARC4-24-SD, Spacecraft

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)

Radiation Effects on Electronics Modeling

MSFC1-07-SD, Lunar and Planetary Surface Systems

Develop advanced models of the natural radiation environment to diagnose and predict the effects of Single Event Effects (SEEs) on modern electronic architectures.
 

Reconfigurable Computers

MSFC1-08-SD, Lunar and Planetary Surface Systems

Provide reconfigurable computing capability, resulting in reduction of flight spares and risk reduction for limited circuit lifetimes.
 

Integration of Surface Mobility Systems through Systems Engineering

MSFC1-09-SD, Lunar and Planetary Surface Systems

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.