Use Of Cold Gas Propulsion System in a 3U Cubesat
- Paper number
IAC-13,V,2-B3.9,4,x20312
- Author
Mr. Surmit Bhui, University of Petroleum and Energy Studies, India
- Coauthor
Ms. Sumana Mukherjee, University of Petroleum and Energy Studies, India
- Coauthor
Ms. Sabina Mehra, University of Petroleum and Energy Studies, India
- Coauthor
Dr. Ugur Guven, United States
- Year
2013
- Abstract
CubeSats have become quite popular especially among university students as these miniaturized satellites help them in carrying out space exploration feasibly. Till date, CubeSats have never flown in space with any well defined propulsion system. But in order to increase mission capabilities like orbit raising and formation flying , or to perform proximity operations , fine attitude control , drag make up and de – orbit without much risks , it is important to use a propulsion system . Here in this paper we have focused on the use of cold gas thrusters in a 3U CubeSat. Cold gas thrusters consist of a pressurized tank containing gaseous propellant, such as nitrogen, and a solenoid actuated valve system leading to exit nozzles. Since the propellant is unheated and relies solely on the enthalpy of the stored gas, the velocity at the nozzle exit is relatively low resulting in a low specific impulse, typically around 60 sec, useful for small attitude adjustments and low ΔV maneuvers. However, the power level, pressure, and weight required in the vessel are though less, but still higher than the CubeSat Specifications provided by the CalPoly. A solution to this problem has been studied and discussed in this paper. Rather than relying on high pressure chambers, we propose the use of solid gas cartridges, which upon ignition by lasers can be released into a chamber containing the gas at a pressure slightly higher than the atmospheric pressure, from which nitrogen can be drawn for propulsive use. Moreover since only a fraction of the propellant is used for propulsion use, it helps in reducing the tank size and minimizes the risk of leakage and pressure limitations, with reduction in mass by around 20%. This way a suitable propulsion system for a CubeSat can be developed which renders increased performance with respect to mission capabilities without increasing the overall mass of the satellite. The idea would also prove to be of much benefit for industries which are planning future cubesat missions.
- Abstract document
- Manuscript document
IAC-13,V,2-B3.9,4,x20312.pdf (🔒 authorized access only).
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