A review on solid propellant micro-thruster array based on MEMS technology
Jianbing Xu,
Jiangtao Zhang,
Fuwei Li,
Shiyi Liu,
Yinghua Ye,
Ruiqi Shen
Affiliations
Jianbing Xu
School of Chemistry and Chemical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China; Micro-Nano Energetic Devices Key Laboratory of MIIT, Nanjing 210094, China; Institute of Space Propulsion, Nanjing University of Science and Technology, Nanjing 210094, China
Jiangtao Zhang
School of Chemistry and Chemical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China; Micro-Nano Energetic Devices Key Laboratory of MIIT, Nanjing 210094, China; Institute of Space Propulsion, Nanjing University of Science and Technology, Nanjing 210094, China
Fuwei Li
School of Chemistry and Chemical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China; Micro-Nano Energetic Devices Key Laboratory of MIIT, Nanjing 210094, China; Institute of Space Propulsion, Nanjing University of Science and Technology, Nanjing 210094, China
Shiyi Liu
Laboratory of Aerospace Entry, Descent and Landing Technology, CASC, Beijing 100094, China
Yinghua Ye
School of Chemistry and Chemical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China; Micro-Nano Energetic Devices Key Laboratory of MIIT, Nanjing 210094, China; Institute of Space Propulsion, Nanjing University of Science and Technology, Nanjing 210094, China; Corresponding author.
Ruiqi Shen
School of Chemistry and Chemical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China; Micro-Nano Energetic Devices Key Laboratory of MIIT, Nanjing 210094, China; Institute of Space Propulsion, Nanjing University of Science and Technology, Nanjing 210094, China
With the development of micro-spacecraft technology, micro-nano satellites have the advantages of small size, low power consumption, short development cycle, formation networking, etc., and can complete many complex space tasks at a lower cost. Micro-nano satellites require a micropropulsion system with the capability of performing precise total impulse and thrust to execute maneuvers, such as attitude control, orbital transfer, and gravitation compensation. In contrast to other micropropulsion systems, solid propellant microthrusters (SPM) arrays based on micro-electromechanical system (MEMS) technology possess a simple structure and quick response, which is a potential micropropulsion system. In recent years, many research groups have done a lot of research on SPM arrays. In this paper, the latest progress of SPM arrays is summarized from the aspects of structure design, propellant selection, bonding technology, ignition unit type and micro-thrust test, and some suggestions for the future development direction are given.
