Ignition key technologies of large-scale solid propellant micro-thruster array

To apply solid propellant micro-thruster array to attitude and orbit control, it is necessary to study the relevant ignition techniques. The application of ignition circuit in the attitude and orbital control was analyzed, and the driver circuit was designed to meet the requirement of ignition. The ignition delay time and the interval time of multi-group ignition were studied. When the ignition power was 2 W, the maximum of ignition delay time was 7.6 ms. The test results show that the minimum interval time is 50 μs. The experiment and simulation have proved that the ignition system is reliable and compatible; the success rate of ignition can be 100%, and the system meets the need of the attitude and orbit control for the satellite.