Design features and experimental researches of an arcjet thruster for small satellite

Abstract

The direction of solution of actual problems of further improvement of the small satellites with propulsion system (PS) by designing arcjet thruster with low power consumption (up to 70 W) and high specific impulse (up to 350 s) was considered on the basis of the research on the maneuvering smallsat with ammonia corrective propulsion system with Electroheat Microthrusters (EHMT). The purpose of the research is confirming technical possibility of designing an arcjet thruster for smallsat with power consumption 60…70 W and specific impulse 300…350 s. In the course of research tasks on determination of construction appearance of a demo sample of No. 2 of arcjet thruster, exploration of its temperature characteristics defining gauge of specific traction impulse of a study of erosion resistance of thruster cathode material at impact of an electric arc are resolved. A constructional scheme of arcjet thruster with visualization of an electric arc is developed, demo arcjet thruster samples are made and experimental arcjet thruster research is conducted in operation on nitrogen, argon. Working fluid temperature in arcjet thruster nozzle behind critical section is reached 1400 K at 68 W, which allows to predict specific impulse value of arcjet thruster in operation on ammonia in 300…350 s. On basis of experimental researches of erosion resistance of arcjet thruster cathode material (tungsten) at impact of an electric arc the necessity of the further research is shown for substantiation of a technical possibility of design arcjet thruster in composition of PS smallsat with required resource of operation. The experimental researches is the continuation of the works in the field of design of EHMT of various construction and represents practical interest during creation of PS for maneuvering smallsat.