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Overview of NASA GRCs Green Propellant Infusion Mission Thruster Testing and Plume Diagnostics [PDF]

The Green Propellant Infusion Mission (GPIM) is sponsored by NASA's Space Technology Mission Directorate (STMD) Technology Demonstration Mission (TDM) office.
Arrington, Lynn A., Deans, Matthew C., Kojima, Jun J., McLean, Christopher H., Reed, Brian D., Williams, George J., Yim, John T.   +6 more
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Development and design of a 10 N monopropellant thruster.

Transactions of the Institute of Aviation, 2015
Samantha Booth, Jordan Kenton, Patrick Nienhaus, Erich Zahn   +3 more
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Cryogenic propellant management in space: open challenges and perspectives. [PDF]

NPJ Microgravity
Simonini A, Dreyer M, Urbano A, Sanfedino F, Himeno T, Behruzi P, Avila M, Pinho J, Peveroni L, Gouriet JB.   +9 more
europepmc   +1 more source

Interstellar Mapping And Acceleration Probe: The NASA IMAP Mission. [PDF]

Space Sci Rev
McComas DJ, Christian ER, Schwadron NA, Gkioulidou M, Allegrini F, Baker DN, Bzowski M, Clark G, Cohen CMS, Cohen I, Collura C, Cully MJ, Dalla S, Desai MI, Driesman A, Eng D, Fox NJ, Funsten HO, Fuselier SA, Galli A, Giacalone J, Hahn J, Hegarty KP, Horbury T, Horanyi M, Kistler LM, Kubiak MA, Kubota S, Livi S, Lugaz N, Lee CO, Luhmann J, Matthaeus W, Mitchell DG, Mitchell JG, Moebius E, Pope S, Provornikova E, Rankin JS, Reisenfeld DB, Reno C, Richardson JD, Russell CT, Shaw-Lecerf MM, Scherrer J, Skoug RM, Shen MM, Spence HE, Sternovsky Z, Strumik M, Szalay JR, Tapley M, Tokumaru M, Turner DL, Weidner S, Westlake J, Wurz P, Zank GP.   +57 more
europepmc   +1 more source

Development of Radiation Heat Shield of Monopropellant Thruster for Spacecraft

Journal of the Korean Society for Aeronautical & Space Sciences, 2006
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Numerical analysis of hydrogen peroxide monopropellant thruster

International Journal of Sustainable Aviation, 2021
Numerical analysis can be used to optimise design of the green propulsion thruster with competitive costs compared to optimisation process through experiments. Furthermore, it could be used to predict engine performance and provide information of the combustion process that can be used to identify the cause of the experimental phenomenon.
Shahrin, Muhammad Shahrul Nizam, Othman, Norazila, Nik Mohd., Nik Ahmad Ridhwan, Abd. Wahid, Mastura   +3 more
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Simulation Model for Catalytic Monopropellant Hydrazine Thrusters

IFAC Proceedings Volumes, 1992
Abstract Hydrazine thrusters are often used as actuators for spacecraft attitude and orbit control systems, for example for the missions of METEOSAT, OTS, INTELSAT and GIOTTO. The reason is that hydrazine requires less hardware than other propellants, and thrusters with thrust levels down to 0.5 N with reproducible minimum impulse bit down to 0.005 N
CAVALLO, Alberto, DE MARIA, Giuseppe, MARINO, Pompeo   +2 more
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Evaluating the Miniaturisation of a Monopropellant Thruster

42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2006
In this paper the miniaturisation of a hydrogen peroxide monopropellant thruster is considered. The performance of the thruster is characterised with reference to the characteristic exhaust velocity, c* and the decomposition temperature achieved. The use of two different catalyst beds is investigated: a monolithic catalyst bed and a compressed powder ...
Sarah Barley, Phil Palmer, Ian Coxhill
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Effects of Aniline Impurities on Monopropellant Hydrazine Thruster Performance

Journal of Spacecraft and Rockets, 1976
Both a 0.45-N and a 0.9-N thruster representative of the designs being flown on 3-axis stabilized spacecraft were used in testing various grades of hydrazine for the phenomenon of monopropellant hydrazine thruster catalyst bed poisoning. Both designs employed Shell 405 ABSG spontaneous catalyst. It is found that pulse shape distortion can be minimized,
L. HOLCOMB, L. MATTSON, R. OSHIRO
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Pulse Response Times of Hydrogen Peroxide Monopropellant Thrusters

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2009
The transient behavior of a monopropellant thruster was investigated. Throughout the study, MnO2/Al2O3 was used as the catalyst bed in order to eliminate the influence of the catalyst bed on the transient behavior. Three 50 Newton level test thrusters with different injectors, ullage volumes, and bed sizes were built.
Sungyong An, Rachid Brahmi, Charles Kappenstein, Jeongsub Lee, Sejin Kwon   +4 more
openaire   +1 more source