Structure Design And Performance Testing Of Micro Solid Thrusters

With the progress of aerospace technologies, human's activities have extended into the deep space. One of the most important trends of modern spacecrafts is miniaturization. Thus,lighter and more precise propulsion system is needed for missions such as orbit control and attitude maneuver. In some spacecrafts, the quick response ability of its propulsion system is also required.The structure of traditional liquid propulsion system is so complex that they are not suitable to be applied in micro-spacecraft with a mass less than 20kg. Micro solid thrusters can not only avoid the above-mentioned problems, but also give an advantage of propellant longtime storing.The objective of this thesis is to solve the problems related to the design and manufacturing of micro solid thrusters with a chamber size of several millimeters level for orbit control or a chamber size of several hundreds of micrometers level for attitude maneuver.The key technologies of micro solid thruster are studied in this thesis, which include propulsion system structure design, key component MAO processingignition design, propellant choice and thrust performance testing. The design of micro-spacecraft propulsion system for orbit control and attitude maneuver is given. The heat-resistant performance of MAO (Microarc Oxidation) processed ceramic layer is evaluated by experimental and numerical methods. The results showed that MAO technologies can be successfully used in micro solid thrusters. Based on the research of the work principle and structure of semiconductor bridge(SCB), a method to determine SCB structure parameters is described. A new SCB structure is proposed, which is promised to have better ignition performance. The common use propellants performance and thrust measurement means are analyzed. Based on the analysis, thrust measurement experiment is conducted.