Air-breathing electric thruster for ultra-low orbit satellite
Air-breathing electric thruster for ultra-low orbit satellite
- New search for: LUO JUN
- New search for: HE JIANWU
- New search for: KANG QI
- New search for: DUAN LI
- New search for: HUANG HEJI
- New search for: MA LONGFEI
- New search for: FU JIAHAO
- New search for: LUO JUN
- New search for: HE JIANWU
- New search for: KANG QI
- New search for: DUAN LI
- New search for: HUANG HEJI
- New search for: MA LONGFEI
- New search for: FU JIAHAO
The invention discloses an air-breathing electric thruster for an ultra-low orbit satellite. The air-breathing electric thruster is characterized by comprising a flow control, storage and supply system, a low-air-resistance gas isolation-distribution system, a temperature self-regulation radio frequency ionization system, an ion optical system and an electricity neutralization system, according to the air suction type electric thruster for the ultra-low orbit satellite, large thrust is obtained through ionization and acceleration of captured ultra-low orbit atmospheric working media, it is guaranteed that the ultra-low orbit (100-300 km) of the satellite is maintained, the thrust range reaches 1-35 mN, the specific impulse is larger than or equal to 3500 s, and the plume divergence half angle is smaller than or equal to 20 degrees; the ignition power and the working power of the thruster are obviously reduced by providing a very small amount of Xe working medium (1-10%); a radio frequency coil of the temperature self-regulation radio frequency ionization system is composed of microgravity heat pipes, the porous phase change energy storage system and the radiation heat dissipation system are connected, and the influence of the thermal environment on the reduction of the service life of the thruster is reduced. Through the low-gas-resistance gas isolation-distributor, it is ensured that the electric thruster obtains enough working medium flow rate to maintain self-sustaining discharge of the thruster, and meanwhile plasma backflow is isolated.
本发明公开了一种用于超低轨卫星的吸气式电推力器，其特点是：包括流控与贮供系统、低气阻气体隔离‑分配系统、温度自调控射频电离系统、离子光学系统、电中和系统；本发明用于超低轨卫星的吸气式电推力器，通过电离并加速捕获的超低轨大气工质获得较大推力，保证卫星的超低轨道(100～300km)维持，推力范围达到1～35mN，比冲≥3500s，羽流发散半角≤20°；通过提供极少量Xe工质(1％～10％)，显著降低推力器的点火功率和工作功率；通过温度自调控射频电离系统，其射频线圈由微重力热管构成，连接多孔相变储能系统与辐射散热系统，降低热环境对推力器寿命减损的影响。通过低气阻气体隔离‑分配器，保证电推力器获得足够的工质流率维持推力器自持放电，同时隔绝等离子体反流。
Document information
Air-breathing electric thruster for ultra-low orbit satellite
一种用于超低轨卫星的吸气式电推力器
2024-03-29
Patent
Electronic Resource
Chinese
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