This paper describes the test results and capability of a high performance 5-lbf bipropellant thruster assembly utilizing hydrazine and nitrogen tetroxide (N_2H_4/N_2O_4) propellants. Moog-ISP manufactures the model DST-11H thruster utilizing a platinum/rhodium thrust chamber and nozzle to achieve high performance and high throughput capability. A series of successful qualification programs, leading to production flight units, has been accomplished. These qualification programs have further defined the functional and operational envelope of the DST-11H thruster. Steady state operation of the model DST-11H thruster delivers nominal 5.0 Ibf thrust with a specific impulse of 310 sec at nominal (230 psia) inlet conditions. Testing has been performed to determine the long burn capability of the thruster. The DST-11H thruster has demonstrated capability to perform a 3-hour continuous burn followed by twelve 2-hour burns. During one test campaign, a single DST-11H thruster accumulated 2019 Ibm of propellant throughput. This demonstrates the capability of the DST-11H thruster to perform as an apogee engine back-up. The DST-11H thruster has been successfully tested over a wide range of hot fire, shock, and vibration conditions which have expanded the environmental operation of the thruster. Currently, the DST-11H thruster is successfully employed on several satellites.
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