Injector design and test of a prototype low-thrust hydrazine thruster

T. Yuan, C. H. Yao, W. C. Chen, L. K. Liu

Research output: Contribution to journalArticlepeer-review


This research has completed the design, fabrication and hot firing tests of a 1-lbf hydrazine thruster. The design of this thruster was based on the experimental data from previous researches. The thruster was tested either with single-tube radial type injector or axially porous disk type injector, and packed with 7.4g or 8.1g Shell 405 catalyst. At the propellant flow rate at ∼0.005 lbm/sec, the thruster with radial type injector and packing with 8.1g of catalyst produced a chamber pressure of 220.2psia, which corresponding to sea-level thrust of 0.63 lbf and specific impulse of 126 sec. Through a theoretical calculation, the ideal vacuum thrust was 1.01 lbf and the ideal specific impulse was ∼200 sec. The response time of the thrusters were 42∼82ms. Which is longer than that from commercial products. In order to improve the firing characteristics of the thruster, researches on multi-tube or spiral-tube radial type injectors is recommended to better utilize the catalyst surface for hydrazine dissociation.

Original languageEnglish
Pages (from-to)335-340
Number of pages6
JournalTransactions of the Aeronautical and Astronautical Society of the Republic of China
Issue number4
Publication statusPublished - 2000 Dec 1

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


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