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  • 1
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    Fabrication of Composite Combustion Chamber/Nozzle for Fastrac Engine (2001)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Fastrac Engine developed by the Marshall Space Flight Center for the X-34 vehicle began as a low cost engine development program for a small booster system. One of the key components to reducing the engine cost was the development of an inexpensive combustion chamber/nozzle. Fabrication of a regeneratively cooled thrust chamber and nozzle was considered too expensive and time consuming. In looking for an alternate design concept, the Space Shuttle's Reusable Solid Rocket Motor Project provided an extensive background with ablative composite materials in a combustion environment. An integral combustion chamber/nozzle was designed and fabricated with a silica/phenolic ablative liner and a carbon/epoxy structural overwrap. This paper describes the fabrication process and developmental hurdles overcome for the Fastrac engine one-piece composite combustion chamber/nozzle.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Proceedings of the 4th Conference on Aerospace Materials, Processes, and Environmental Technology; NASA/CP-2001-210427
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Low Temperature Hybrid Mars Ascent Vehicle Concept Development at MSFC (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Spacecraft Design, Testing and Performance
    Type: M18-6841 , AIAA Propulsion and Energy Conference; Jul 09, 2018 - Jul 11, 2018; Cincinnatti, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    A Design for a Two-Stage Solid Mars Ascent Vehicle (2019)
    In:  CASI
    Details
    Publication Date: 2019-09-07
    Description: A solid propulsion system design is being considered for a conceptual Mars Ascent Vehicle (MAV) as part of a potential robotic Mars Sample Return campaign. A Preliminary Architecture Assessment for a MAV is being conducted at Marshall Space Flight Center. Experts from all relevant areas are involved in a rapid design and analysis cycle to define a MAV vehicle utilizing solid propulsion. The design presented here is the solid motor propulsion concept result of the study. Whereas solid motors have been used on Mars missions in the past during descent, none have been required to reside on the surface for a period of time prior to functioning. This difference will expose the MAV to relatively extreme temperatures. Other challenges exist in designing a solid propulsion system for MAV including performance interactions with other vehicle inert masses and minimizing orbit dispersions. These considerations were examined and a preliminary CAD model of the motors was created. Along with additional pertinent inputs from other disciplines, a solid propulsion vehicle concept for the MAV is described.
    Keywords: Spacecraft Design, Testing and Performance
    Type: M19-7535 , AIAA Propulsion and Energy Forum; Aug 19, 2019 - Aug 22, 2019; Indianapolis, IN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A Quantitative Reliability, Maintainability and Supportability Approach for NASA's Second Generation Reusable Launch Vehicle (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The United States National Aeronautics and Space Administration (NASA) is in the midst of a 10-year Second Generation Reusable Launch Vehicle (RLV) program to improve its space transportation capabilities for both cargo and crewed missions. The objectives of the program are to: significantly increase safety and reliability, reduce the cost of accessing low-earth orbit, attempt to leverage commercial launch capabilities, and provide a growth path for manned space exploration. The safety, reliability and life cycle cost of the next generation vehicles are major concerns, and NASA aims to achieve orders of magnitude improvement in these areas. To get these significant improvements, requires a rigorous process that addresses Reliability, Maintainability and Supportability (RMS) and safety through all the phases of the life cycle of the program. This paper discusses the RMS process being implemented for the Second Generation RLV program.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Workshop on Life Cycle System Engineering; Nov 06, 2002 - Nov 07, 2002; Redstone Arsenal, AL; United States
    Format: application/pdf
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  • 5
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    Entry, Descent, and Landing Operations Analysis for the Mars Phoenix Lander (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Mars Phoenix lander was launched August 4, 2007 and remained in cruise for ten months before landing in the northern plains of Mars in May 2008. The one-month Entry, Descent, and Landing (EDL) operations phase prior to entry consisted of daily analyses, meetings, and decisions necessary to determine if trajectory correction maneuvers and environmental parameter updates to the spacecraft were required. An overview of the Phoenix EDL trajectory simulation and analysis that was performed during the EDL approach and operations phase is described in detail. The evolution of the Monte Carlo statistics and footprint ellipse during the final approach phase is also provided. The EDL operations effort accurately delivered the Phoenix lander to the desired landing region on May 25, 2008.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA/AAS Astrodynamics Specialist Conference; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
    Format: application/pdf
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  • 6
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    Mars Reconnaissance Orbiter Operational Aerobraking Phase Assessment (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Mars Reconnaissance Orbiter (MRO) was inserted into orbit around Mars on March 10, 2005. After a brief delay, it began the process of aerobraking - using the atmospheric drag on the vehicle to reduce orbital period. The aerobraking phase lasted approximately 5 months (April 4 to August 30, 2006), during which teams from the Jet Propulsion Laboratory, Lockheed Martin Space Systems Corporation, and NASA Langley Research Center worked together to monitor and maneuver the spacecraft such that thermal margin on the solar arrays was maintained while schedule margin was upheld to provide a final local mean solar time (LMST) at ascending node of 3:00pm on the final aerobraking orbit. This paper will focus on the contribution of the flight mechanics team at NASA Langley Research Center (LaRC) during the aerobraking phase of the MRO mission.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AAS 07-244 , 17th AAS/AIAA Space Flight Mechanics Meeting; Jan 28, 2007 - Feb 01, 2007; Sedona, AZ; United States
    Format: application/pdf
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  • 7
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    Autonomous Aerobraking Using Thermal Response Surface Analysis (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Aerobraking is a proven method of significantly increasing the science payload that can be placed into low Mars orbits when compared to an all propulsive capture. However, the aerobraking phase is long and has mission cost and risk implications. The main cost benefit is that aerobraking permits the use of a smaller and cheaper launch vehicle, but additional operational costs are incurred during the long aerobraking phase. Risk is increased due to the repeated thermal loading of spacecraft components and the multiple attitude and propulsive maneuvers required for successful aerobraking. Both the cost and risk burdens can be significantly reduced by automating the aerobraking operations phase. All of the previous Mars orbiter missions that have utilized aerobraking have increasingly relied on onboard calculations during aerobraking. Even though the temperature of spacecraft components has been the limiting factor, operational methods have relied on using a surrogate variable for mission control. This paper describes several methods, based directly on spacecraft component maximum temperature, for autonomously predicting the subsequent aerobraking orbits and prescribing apoapsis propulsive maneuvers to maintain the spacecraft within specified temperature limits. Specifically, this paper describes the use of thermal response surface analysis in predicting the temperature of the spacecraft components and the corresponding uncertainty in this temperature prediction.
    Keywords: Spacecraft Design, Testing and Performance
    Type: 45th AIAA Aerospace Sciences Meeting and Exhibit; Jan 08, 2007 - Jan 11, 2007; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Autonomous Aerobraking Development Software: Phase 2 Summary (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA has used aerobraking at Mars and Venus to reduce the fuel required to deliver a spacecraft into a desired orbit compared to an all-propulsive solution. Although aerobraking reduces the propellant, it does so at the expense of mission duration, large staff, and DSN coverage. These factors make aerobraking a significant cost element in the mission design. By moving on-board the current ground-based tasks of ephemeris determination, atmospheric density estimation, and maneuver sizing and execution, a flight project would realize significant cost savings. The NASA Engineering and Safety Center (NESC) sponsored Phase 1 and 2 of the Autonomous Aerobraking Development Software (AADS) study, which demonstrated the initial feasibility of moving these current ground-based functions to the spacecraft. This paper highlights key state-of-the-art advancements made in the Phase 2 effort to verify that the AADS algorithms are accurate, robust and ready to be considered for application on future missions that utilize aerobraking. The advancements discussed herein include both model updates and simulation and benchmark testing. Rigorous testing using observed flight atmospheres, operational environments and statistical analysis characterized the AADS operability in a perturbed environment.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NF1676L-17308 , AAS 13-736 , AAS/AIAA Astrodynamics Specialist Conference; Aug 11, 2013 - Aug 15, 2013; Hilton Head, SC; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Low Temperature Hybrid Mars Ascent Vehicle Concept Development and Planning at MSFC (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Return of samples from Mars has been a goal of NASA's for decades. The current Mars Sample Return mission concepts have a multiple launch rocket from the earth, where one mission delivers a caching rover to collect and package the Martian soil samples. Another rocket sends the Mars Ascent Vehicle that takes those samples to orbit. Another rocket sends an orbiter, that also meets up with the samples in orbit, and brings them back to earth. Our tasks have been focused on the Mars Ascent Vehicle. To leave the Martian surface, it requires a two burn trajectory, one to get off the planet and another to circularize the orbit. Recent studies have led to the investigation of a hybrid rocket solution. That technology has been under development for several years. This paper will discuss some of the work going on at MSFC to understand how to process the fuel, some test firings done to characterize some design features and some planning done to scope out what it would take to qualify a hybrid rocket motor for this application.
    Keywords: Spacecraft Design, Testing and Performance
    Type: M18-6462 , AIAA/SAE/ASEE Joint Propulsion Conference; Jul 09, 2018 - Jul 11, 2018; Cincinnati, OH; United States
    Format: application/pdf
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  • 10
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    A Design for a Two-Stage Solid Mars Ascent Vehicle (2019)
    In:  CASI
    Details
    Publication Date: 2019-09-07
    Description: No abstract available
    Keywords: Spacecraft Design, Testing and Performance
    Type: M19-7606 , AIAA Propulsion and Energy Forum; Aug 19, 2019 - Aug 22, 2019; Indianapolis, IN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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