Optimum Design of Low-Pressure Micro-Resistojet Applied to Nano- and Pico-Satellites

Conference Paper (2018)
Author(s)

Dadui C. Cordeiro Guerrieri (TU Delft - Space Systems Egineering)

Marsil A.C. de Athayde Costa e Silva (TU Delft - Space Systems Egineering)

A Cervone (TU Delft - Space Systems Egineering)

E.K.A. Gill (TU Delft - Space Engineering)

Research Group
Space Systems Egineering
Copyright
© 2018 D. Cordeiro Guerrieri, M. de Athayde Costa e Silva , A. Cervone, E.K.A. Gill
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Publication Year
2018
Language
English
Copyright
© 2018 D. Cordeiro Guerrieri, M. de Athayde Costa e Silva , A. Cervone, E.K.A. Gill
Research Group
Space Systems Egineering
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Abstract

A Low-Pressure Micro-Resistojet (LPM) is under development at TU Delft with the intention to provide future nano- and pico-satellites with the necessary capability to execute formation flying maneuvers, orbit change maneuvers, and station keeping. In this particular type of electro-thermal thruster, water is a green propellant of excellent performance, which can be stored as a liquid or solid operating at very low pressure, under evaporation or sublimation conditions. The formed vapor flows to a series of hot microchannels in a heater chip. Then, the flow is heated and expanded at high Knudsen numbers to a high exhaust velocity. This concept is very promising when associated to the typical CubeSat or PocketQube requirements that demand low tank pressure, low system mass, intrinsic safety, “green” propellants – non-corrosive, non-flammable, non-toxic, with limited energetic content – and a sufficiently long operational life. This paper discusses the optimization of the LPM design applied to two different missions, one for a CubeSat mission which requires a formation flight and other for a PocketQube mission which will be used as a flight demonstration platform.

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