2018.B.2.4. The Experiment Investigation and On-orbit Flying application of Solid Cool Gas Micro-propulsion Module

Author(s)

Xuhui Liu (1)
Xudong Wang (1)
Jinyue Geng (1)

Beijing Institute of Control Engineering, China

Session

B.2

Keywords

Solid Cool Gas Micro-propulsion Module ; on orbit flying application;experiment Investigation

Abstract

Micro-nano satellites formation flight, station keeping and other tasks require the propulsion system with a higher total impulse, lower power consumption, modular design, pluging in and playing. We have designed solid cool gas micro-propulsion module with the high performance, completed the relevant performance tests. The solid cool gas micro-propulsion module includes solid solid cool gas generators, the control circuit, 2 thruster components, 1 sensor and module chamber structure. The module just need the micro-nano satellites power and communication interface, through threaded connections and mechanical connections with the satellite to meet the plug-and-play. The solid cool gas micro-propulsion module using the cylinder charge and micro igniter has high total impulse and low power consumption. 1U(100mm×100mm×100mm) module’s weight is 1100g, and the total impulse is more than 80Ns. The module instantaneous power is less than 1.5W, usual power is less than 50mW. The communication interface is RS422. The single generator’s producing gas efficiency is more than 45%, and gas temperature below 60 ℃. The 1U module can be extended according to total impulse need. The module integrated 18 generators, producing 7g gas.

The interior ballistic model of the module is established based on the mass flow model. The simulation is carried out based on the model. For meeting with the nano satellite application requirement, the mechanical and thermal tests are carried out, and the firing test is made. 18 generators worked perfectly and single one released the 7±0.1g gas. The module thrust is tested based on the balance method. The thrusters can produce 108mN with 1.33MPa,and the working time is about 210s based on the single generator. Through the comparison and analysis, the thrust test curve agrees well with the theoretical calculation curve.

For meeting with the on orbit application requirement, the on orbit calibration method and thruster working time prediction method are built, which can calculate the accurate thruster working time for the orbit control based on the high pressure drop ratio working mode.