Table of Contents

Background and History

Research Paper Topics

Awards

Rules and Guidelines

Deadline

Eligibility

Format

Scoring

Contact & Entry Information

Frequently Asked Questions

 

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Background

Exploration Systems Mission Directorate (ESMD) was developed by the National Aeronautics Space Administration (NASA) specifically to create a constellation of new capabilities, supporting technologies and foundational research that enables sustained and affordable human and robotic exploration.  This competition is one of many projects designed to contribute to our Nation’s efforts in achieving excellence in science, technology, engineering and math (STEM) education. 

            Join NASA’s mission to bring us to the moon, Mars and beyond by submitting a research paper on one of the four ESMD topics listed below.  Your research may be used as the solution to current NASA challenges. 

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Enter a research paper on one of the following topics:

Click on the links below for background information you will need to complete your paper.

1. Spacecraft Landing and Recovery Architecture: Historical Approaches and Ideas for the Future

2. Synergistic degradation effects of materials exposed to radiation, micrometeors, thermal sinks and lunar dust

3. Loading of Cryogenic Propellant in Space Launch Vehicle

4. Determination of the Optimum Internal Cockpit Layout

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Awards

Four 1^st place prizes of $3500 cash scholarships--one for each research topic

VIP seating to an upcoming launch

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Rules and Guidelines

Submission Deadline

The deadline for submitting the research paper is midnight EST January 25, 2010.

Eligibility

Open to students who are United States citizens in an undergraduate or graduate studies program

Students must be in good standing and enrolled full or part-time and attending a college or university in the United States

Papers may be submitted by an individual or team

Papers that have been previously submitted in other competitions are permitted

Format

• IEEE Citation Style (PDF)
• Microsoft Word document
• 8 ½ x 11 paper
• Top and bottom margins 1.00”
• Left and right margins 1.00
• Double-spacing in a single column
• Full text justification
• No indentation- use a double blank line to separate paragraphs

 

            The following information must be placed at the top of the first page

• Project Title: 14 pt. (Times Roman or Ariel typeface), bold, centered
• Authors(s): 12 pt. (Times Roman or Ariel typeface), bold, centered, include author’s name and e-mail address(es)

 

Scoring

Judging will be performed by a panel of NASA engineers using the following criteria:

• Innovative Idea (20%)
1. Demonstration of original ideas and concepts
2. Development of new solutions or procedures
• Value to NASA (20%)
  1. Explanation of useful benefits to NASA
  2. Has the capacity to be implemented
• Demonstration of Knowledge and Understanding of Subject (20%)
  1. Subject is clearly defined and organized
  2. Comprehension of engineering and scientific practices
• Quality and Accuracy of Research (30%)
1. Significant depth and breadth of research are demonstrated
2. Methods are appropriate and complete
3. Data collection is accurate and pertains to the subject
• Quality and Clarity of Paper Presentation (10%)
1. Use of appropriate tables, labeled correctly
2. Use of appropriate figures, labeled correctly
3. All references properly marked
4. Correct grammar and punctuation 
5. Accurate spelling

 

Entry Instructions

Please submit an email of your intentions to enter the competition to Diane Ingraham at zola.d.ingraham@nasa.gov. 

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Background information for each of the topics

Topic 1: Spacecraft Landing and Recovery Architecture:  Historical Approaches and Ideas for the Future

Goal and Objective

The main goal is to provide NASA with a study on landing and recovery procedures focusing on Orion missions to the International Space Station (ISS). The Orion Crew Module (CM), a spacecraft component of the new Constellation Program, will be recovered in a similar manner to predecessor capsule designs.  Include a historical perspective of landing and recovery operational procedures for the early capsule-based programs:  Mercury, Gemini, and Apollo/Skylab.  Show proposed methods to optimize both nominal recovery and contingency rescue, as defined below.  Consider support from foreign governments.  Show all references, to include web links.

Topic Background

Basic Concepts for Orion Landing and Recovery:

Nominal Recovery:

Orion is launched by an Ares I rocket to rendezvous with the ISS.  Since the ISS is at an inclination of 51.6 degrees, all nominal and off nominal landings will occur at latitudes equal to or lower than 51.6 degrees.  Each day, there is a primary landing site (PLS) available offshore between San Francisco and midway down the Baja Peninsula.  PLS landings are considered contingency landings.  The nominal end-of-mission (EOM) landing zone is defined as the coastal waters within 500 km (270 nmi) of NAS North Island.  This range is chosen primarily due to the limitations of the nominal EOM recovery ship.

The ISS ground tracks closest to NAS North Island from one day to the next vary from approximately 530-910 km (286-491 nmi) apart.  A recovery ship, traveling at 12 kts maximum cruise speed, would only be capable of traveling 467 km (252 nmi) between sequential EOM landing sites in a 24 hour period.  The ship must arrive at the next landing site at least three hours prior to wave-off time to check weather.  Occasionally the nearest ground track on a given day is outside the 500 km nominal EOM landing zone.  As a result, there may not be a nominal EOM site on certain days since the recovery ship may not be capable of reaching the next day’s closest landing opportunity in time to recover the CM and have side hatch open within 2 hours of splashdown. 

Besides the recovery ship’s available range on a given day, there are several other considerations when determining whether the next day’s landing opportunity will be suitable as a nominal EOM landing site.  These include weather constraints (sea state, surface winds and visibility, cloud ceilings, etc.), proximity to suitable trauma centers for medevac support, and distance from the recovery ship to helicopter ground refueling locations.

 

Contingency Rescue:

The overriding requirement driving contingency operations is to accomplish astronaut rescue within 24 hours of a contingency landing.  When addressing contingencies, the Program does not stack multiple independent failures.  There are few, if any, scenarios that will cause an unplanned, uncontrolled scenario … i.e. land anywhere scenario.  The overall contingency landing prioritization is based on utilization of orbital loitering prior to landing:

a.       If possible, splashdown at the next PLS opportunity near NAS North Island.

b.      If unable, splashdown at a pre-determined contingency landing target.

c.       If unable, splashdown in water near a known ship of opportunity or along a shipping lane.

d.      If unable, splashdown in water somewhere.

e.       If unable, as a last resort, make a contingency land landing in a large flat area.

Additional Resources

Selected Constellation Architecture (CA) Requirements:

Nominal Recovery: 

CA4122 - Ground Systems shall recover the flight crew within 2 hours after landing at a designated landing site.

Definition:  The recovery time starts with touchdown and ends with the CM on the recovery vessel with the hatch opened for crew egress. 

Contingency Rescue: 

CA5146 - Ground System shall rescue the crew within 24 hrs with a 95% probability of success following a landing at a site other than a designated landing site. 

Definition:  The crew is considered rescued once outside the CM and onboard a helicopter/ship.

CA0312 - The Constellation Architecture shall provide safe haven for the crew for at least 24 hours post touchdown on Earth while awaiting rescue and retrieval.

Definition:  The Orion safe haven provides a habitable environment, communications, maintains structural integrity, remains afloat in water, and provides emergency crew survival capabilities. 

Web links:

http://mod.jsc.nasa.gov/DA8/Space_Flight_Heritage/index.cfm

http://www.apollo2cev.org

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Topic 2: Synergistic degradation effects of materials exposed to radiation, micrometeors, thermal sinks and lunar dust.

Goals and Objectives

The main goal is to present NASA with new concepts on the lunar environment that will lead to increased mission success for future lunar missions. Provide innovative approaches to understanding the synergistic effects of radiation, micrometeors, thermal sinks and lunar dust on materials.  

 

Topic Background

Constellation Overview: http://www.nasa.gov/externalflash/CxEMM_SITE/index.html

Exploration 101: http://www.nasa.gov/exploration/library/exploration_101.html

Additional Resources

Required Reading:

Moon 101:  http://www.lpi.usra.edu/lunar/moon101/

Lunar Samples:  http://www.lpi.usra.edu/lunar/samples/

Overview of the Working Environment:  http://www.workingonthemoon.com/WOTM-EnviroIntro.html

Preliminary Science Reports: http://www.hq.nasa.gov/alsj/frame.html

Lunar Source Book: https://www.lpi.usra.edu/store/products.cfm?prod=57&cat=8

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Topic 3: Loading of Cryogenic Propellant in Space Launch Vehicle

Goals and Objectives

The main goal is to perform the analysis to determine the time for chill down of transfer line and propellant tanks.  One of the objectives is to optimize/improve the numerical algorithm of chill down analysis to reduce the time required for simulation.  The other objective is to improve the accuracy of simulation by performing research on the correlation of heat transfer coefficient applicable to chill down process.

Topic Background

One of the very first and long processes before rocket launch is the loading of cryogenic propellants from storage tanks to launch vehicle tanks. This process takes several hours because the cryogenic transfer line and propellant tanks must be chilled down to liquid propellant temperatures before tanks can be filled with propellants. Initially, the transfer lines and tank walls are at ambient temperature. The LH2 supply system must be cooled to liquid hydrogen temperature (-423 °F), and the LO2 supply system must be cooled to liquid oxygen temperature (-298 °F) prior to tank loading. Cryogenic propellants supplied from the storage tank immediately evaporate upon entering the transfer line, which is at ambient temperature. The energy required for evaporation is supplied by the walls of the transfer line. In this process, the walls of the pipe are chilled, while the liquid propellant turns into vapor, flows into the tank, and finally vents out of the tank. The vent line of hydrogen vapor goes to the flare stack, whereas oxygen vents to the atmosphere. Once the transfer lines are chilled to cryogenic temperature, the liquid propellant starts flowing into the tank. The tanks are also chilled down in a similar process. Cryogenic propellants immediately evaporate upon entering the tank by extracting energy from the tank wall. As a result the tank walls are cooled.

Additional Resources

Web links

http://www.nasa.gov/mission_pages/constellation/ares/aresl/index.html

http://gfssp.msfc.nasa.gov/

Published articles

Modeling of chill down in cryogenic transfer lines

Author(s)

CROSS Matthew F; MAJUMDAR Alok K; BENNETT John C; MALLA Ramesh B;

Abstract

A numerical model to predict chill down in cryogenic transfer lines has been developed. Three chill down cases using hydrogen as the working fluid are solved: 1) a simplified model amenable to analytical solution, 2) a realistic model of superheated vapor flow, and 3) a realistic model of initially sub cooled liquid flow. The first case compares a numerical

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Topic 4: Determination of the Optimum Internal Cockpit Layout

Goals and Objectives

The main goal is to design a cockpit cabin accommodating a wide range of astronauts to perform their daily tasks and duties and live in a safe and efficient environment for the duration of their space flight (from launch to landing). The capabilities include: displays and controls to fly the vehicle and monitor the vehicle health, seats, mobility aids, environmental control, waste management system (toilet), stowage for unused, spare, personal items, food galley, sleep, exercise (for Lunar missions).

Topic Background

For designing a human rated spacecraft, it is critical to consider the human as a system and include the human capabilities and limitations early in the spacecraft design. As NASA’s Crew Exploration Vehicle, Orion, is being designed to take four humans back to the moon, and lay the groundwork for future manned missions to Mars. It is being designed to accommodate up to six crewmembers for missions to the International Space Station (ISS), and up to four crewmembers for lunar missions.  Unlike its Apollo predecessor, Orion will allow for all crewmembers to descend to the lunar surface. To help meet the human aspect of this design challenge, we need to focus the vehicle design on the needs, safety, and performance of the human crew. It is critical to identify the key driving requirements and develop mission concept of operations so that the cockpit design is optimal for the crew. The Human System Integration Requirements (HSIR) is the document that lists the human capabilities the vehicle needs to accommodate. It covers requirements related to user interface design of displays and controls, crew accommodation, and anthropometry.

 

Additional Resources

Web links

 

Orion wiki site: https://ice.exploration.nasa.gov/ice/site/orion/

Habitability and human factors: http://sf.jsc.nasa.gov/

Constellation Overview: http://www.nasa.gov/externalflash/CxEMM_SITE/index.html

Exploration 101: http://www.nasa.gov/exploration/library/exploration_101.html

 

Reference Document/ Published Presentations

 

Document title

Constellation Human System Integration Requirements (HSIR)

See attached document titled: CxP 70007_revB_Change003_Final.pdf

Presentation title

Integrating Human Factors into Crew ExplD@skmage96866oration Vehicle (CEV) Design (M. Whitmore, K. Holden, S. Baggerman, P. Campbell)

See attached file titled: CEV IAA Symposium Pres.pdf

            Presented at the 16^th IAA Human in Space Symposium, Beijing, China (May 2007)

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Frequently Asked Questions

Can I submit more than one paper?

Yes, you can submit one paper for each research topic.

Are teams eligible to enter the competition?

Yes, teams as well as individuals are eligible to enter the competition.

Is the competition open to non-United States citizens?

No, only United States citizens are eligible to participate.

Will there be awards for 2^nd and 3^rd place?

No, there will be one 1^st place winner for each research topic. 

Check back here often for updates and answers to your questions