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

Xu Hui Liu*, Shu Zhou Fang, Yu Lin Wang, Hong Mei Li, Teng Li

*Corresponding author for this work

Research output: Contribution to journalArticlepeer-review

1 Citation (Scopus)

Abstract

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.

Original languageEnglish
Pages (from-to)183-187+192
JournalGuti Huojian Jishu/Journal of Solid Rocket Technology
Volume35
Issue number2
Publication statusPublished - Apr 2012

Keywords

  • Attitude and orbit control
  • Ignition delay time
  • Ignition system
  • Logic control
  • Solid propellant micro-thruster array

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Liu, X. H., Fang, S. Z., Wang, Y. L., Li, H. M., & Li, T. (2012). Ignition key technologies of large-scale solid propellant micro-thruster array. Guti Huojian Jishu/Journal of Solid Rocket Technology, 35(2), 183-187+192.