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  • 1
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    The Iodine Satellite (iSat) Project Development Towards Critical Design Review (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: Despite the prevalence of small satellites in recent years, the systems flown to date have very limited propulsion capability. SmallSats are typically secondary payloads and have significant constraints for volume, mass, and power in addition to limitations on the use of hazardous propellants or stored energy. These constraints limit the options for SmallSat maneuverability. NASA's Space Technology Mission Directorate approved the iodine Satellite flight project for a rapid demonstration of iodine Hall thruster technology in a 12U (cubesat units) configuration under the Small Spacecraft Technology Program. The mission is a partnership between NASA MSFC, NASA GRC, and Busek Co, Inc., with the Air Force supporting the propulsion technology maturation. The team is working towards the critical design review in the final design and fabrication phase of the project. The current design shows positive technical performance margins in all areas. The iSat project is planned for launch readiness in the spring of 2017.
    Keywords: Lunar and Planetary Science and Exploration; Spacecraft Propulsion and Power; Spacecraft Design, Testing and Performance
    Type: M15-4663 , International Electric Propulsion Conference; 6ý10 Jul. 2015; Kobe; Japan
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Systems Engineering Lessons Learned for Class D Missions (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: One of NASA's goals within human exploration is to determine how to get humans to Mars safely and to live and work on the Martian surface. To accomplish this goal, several smaller missions act as stepping-stones to the larger end goal. NASA uses these smaller missions to develop new technologies and learn about how to survive outside of Low Earth Orbit for long periods. Additionally, keeping a cadence of these missions allows the team to maintain proficiency in the complex art of bringing spacecraft to fruition. Many of these smaller missions are robotic in nature and have smaller timescales, whereas there are others that involve crew and have longer mission timelines. Given the timelines associated with these various missions, different levels of risk and rigor need to be implemented to be more in line with what is appropriate for the mission. Thus, NASA has four different classifications that range from Class A to Class D based on the mission details. One of these projects is the Resource Prospector (RP) Mission, which is a multi-center and multi-institution collaborative project to search for volatiles in the polar regions of the Moon. The RP mission is classified as a Class D mission and as such, has the opportunity to more tightly manage, and therefore accept, greater levels of risk. The requirements for Class D missions were at the forefront of the design and thus presented unique challenges in vehicle development and systems engineering processes. This paper will discuss the systems engineering process at NASA and how that process is tailored for Class D missions, specifically the RP mission.
    Keywords: Lunar and Planetary Science and Exploration
    Type: JSC-CN-34095 , AIAA Space 2015; Aug 31, 2015 - Sep 02, 2015; Pasadena, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Propulsion System Development for the Iodine Satellite (iSAT) Demonstration Mission (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The development and testing of a 200-W iodine-fed Hall thruster propulsion system that will be flown on a 12-U CubeSat is described. The switch in propellant from more traditional xenon gas to solid iodine yields the advantage of high density, low pressure propellant storage but introduces new requirements that must be addressed in the design and operation of the propulsion system. The thruster materials have been modified from a previously-flown xenon Hall thruster to make it compatible with iodine vapor. The cathode incorporated into this design additionally requires little or no heating to initiate the discharge, reducing the power needed to start the thruster. The feed system produces iodine vapor in the propellant reservoir through sublimation and then controls the flow to the anode and cathode of the thruster using a pair of proportional flow control valves. The propellant feeding process is controlled by the power processing unit, with feedback control on the anode flow rate provided through a measure of the thruster discharge current. Thermal modeling indicates that it may be difficult to sufficiently heat the iodine if it loses contact with the propellant reservoir walls, serving to motivate future testing of that scenario to verify the modeling result and develop potential mitigation strategies. Preliminary, short-duration materials testing has thus-far indicated that several materials may be acceptable for prolonged contact with iodine vapor, motivating longer-duration testing. A propellant loading procedure is presented that aims to minimize the contaminants in the feed system and propellant reservoir. Finally, an 80-hour duration test being performed to gain experience operating the thruster over long durations and multiple restarts is discussed.
    Keywords: Ground Support Systems and Facilities (Space); Spacecraft Propulsion and Power; Propellants and Fuels; Cybernetics, Artificial Intelligence and Robotics
    Type: M15-4731 , IEPC-2015-09 , ISTS-2015-b-09 , International Electric Propulsion Conference (IEPC); Jul 06, 2015 - Jul 10, 2015; Kobe-Hyogo; Japan|Nano-Satellite Symposium (NSAT); Jul 06, 2015 - Jul 10, 2015; Kobe-Hyogo; Japan|International Symposium on Space Technology and Sciences (ISTS); Jul 06, 2015 - Jul 10, 2015; Kobe-Hyogo; Japan
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    The Iodine Satellite (iSAT) Hall Thruster Demonstration Mission Concept and Development (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The use of iodine propellant for Hall thrusters has been studied and proposed by multiple organizations due to the potential mission benefits over xenon. In 2013, NASA Marshall Space Flight Center competitively selected a project for the maturation of an iodine flight operational feed system through the Technology Investment Program. Multiple partnerships and collaborations have allowed the team to expand the scope to include additional mission concept development and risk reduction to support a flight system demonstration, the iodine Satellite (iSAT). The iSAT project was initiated and is progressing towards a technology demonstration mission preliminary design review. The current status of the mission concept development and risk reduction efforts in support of this project is presented.
    Keywords: Spacecraft Propulsion and Power
    Type: M14-3865 , AIAA/ASME/SAE/ASEE Joint Propulsion Conference; Jul 28, 2014 - Jul 30, 2014; Cleveland, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    The Iodine Satellite (iSat) Project Development Towards Critical Design Review (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Spacecraft Design, Testing and Performance; Lunar and Planetary Science and Exploration; Spacecraft Propulsion and Power
    Type: IEPC-2015-303 , M15-4730 , Conference Nano-Satellite Symposium; Jul 04, 2015 - Jul 10, 2015; Kobe; Japan|Joint Conference of International Symposium on Space Technology and Science; Jul 04, 2015 - Jul 10, 2015; Kobe; Japan|Conference of Electric Propulsion Conference; Jul 04, 2015 - Jul 10, 2015; Kobe; Japan
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Resource Prospector Lander: Architecture and Trade Studies (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: NASA's Resource Prospector (RP) is a multi-center and multi-institution collaborative project to investigate the polar regions of the Moon in search of volatiles. The mission is rated Class D and is approximately 10 days. The RP vehicle comprises three elements: the Lander, the Rover, and the Payload. The Payload is housed on the Rover and the Rover is on top of the Lander. The focus of this paper is on the Lander element for the RP vehicle. The design of the Lander was requirements driven and focused on a low-cost approach. To arrive at the final configuration, several trade studies were conducted. Of those trade studies, there were six primary trade studies that were instrumental in determining the final design. This paper will discuss each of these trades in further detail and show how these trades led to the final architecture of the RP Lander.
    Keywords: Spacecraft Design, Testing and Performance
    Type: JSC-CN-32043
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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