High Performance Hybrid Propulsion System for Small Satellites

Described in this paper is the design of and initial ground test results from a small spacecraft propulsion system. The system consists of a 25 N PMMA and nitrous oxide main hybrid thruster and multiple 1 N ethylene and nitrous oxide bipropellant reaction control thrusters (although only a single reaction control thruster has been tested). The primary objective of the propulsion system development project is to develop an inexpensive system that uses environmentally benign propellants and has performance comparable to the hydrazine and nitrogen tetraoxide bipropellants systems commonly used. Ground test results (using a non flight-weight configuration) show that reliable ignition and efficient and stable combustion have been achieved in the reaction control thruster. Ground testing of the main thruster is underway but is not complete at the point in time.