Study on Characteristics of a High-Precision Cold Gas Micro Thruster
- 1 Advanced Space Propulsion Lab, Beijing Institute of Control Engineering, Beijing, China
- 2 Advanced Space Propulsion Lab, Beijing Institute of Control Engineering, Beijing, China
- 3 Advanced Space Propulsion Lab, Beijing Institute of Control Engineering, Beijing, China
- 4 Advanced Space Propulsion Lab, Beijing Institute of Control Engineering, Beijing, China
- 5 Advanced Space Propulsion Lab, Beijing Institute of Control Engineering, Beijing, China
Abstract
In order to improve the reliability of the spacecraft micro cold gas propulsion system and realize the precise control of the spacecraft attitude and orbit, a micro-thrust, high-precision cold gas thruster is carried out, at the same time due to the design requirements of the spacecraft, this micro-thrust should be continuous working more than 60 minutes, the traditional solenoid valve used for the thrusts can ’ t complete the mission, so a long-life micro latching valve i s developed as the control valve for this micro thruster, because the micro latching valve can keep its position when it cut s off the outage. Firstly, the authors introduced the design scheme and idea of the thruster. Secondly, the performance of the latching valve and the flow characteristics of the nozzle were simulated. Finally, from the experimental results and compared with the numerical study, it shows that the long-life micro cold gas thruster developed in this paper meets the mission requirements.
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