The invention relates to a spacecraft resistance reduction and heat reduction device and method. The device comprises a shock wave needle, a first tungsten electrode, a second tungsten electrode, a third tungsten electrode, a fourth tungsten electrode and a high-voltage pulse power module. The shock wave needle is arranged in the center of the bluff body head of the spacecraft; the first tungstenelectrode and the second tungsten electrode are embedded in one side of the shock wave needle at intervals, and the third tungsten electrode and the fourth tungsten electrode are embedded in the otherside of the shock wave needle at intervals. The high-voltage pulse power module is arranged in the bluff body of the spacecraft, the anode is connected with the first tungsten electrode through a first switch and connected with the third tungsten electrode through a third switch, the cathode is connected with the second tungsten electrode through a second switch and connected with the fourth tungsten electrode through a fourth switch, and the high-voltage pulse power module is used for providing pulse high voltage for breakdown flow field gas. And a voltage regulator is arranged on the high-voltage pulse power module and is used for regulating power supply parameters of the high-voltage pulse power module. According to the invention, local pressure load and thermal load caused by shock wave interference can be reduced by arc energy deposition.
本发明涉及一种航天器减阻降热装置及方法,该装置包括:激波针、第一钨电极、第二钨电极、第三钨电极、第四钨电极和高压脉冲电源模块;激波针设于航天器的钝体头部中心;第一钨电极、第二钨电极间隔嵌设于激波针的一侧,第三钨电极、第四钨电极间隔嵌设于激波针的另一侧;高压脉冲电源模块设于航天器的钝体内部,正极通过第一开关连接第一钨电极,还通过第三开关连接第三钨电极,负极通过第二开关连接第二钨电极,还通过第四开关连接第四钨电极,用于提供击穿流场气体的脉冲高压;高压脉冲电源模块上设有电压调节器,用于调节高压脉冲电源模块的供电参数。本发明可依靠电弧能量沉积减小由于激波干扰造成的局部压力载荷和热载荷。
Spacecraft resistance reduction and heat reduction device and method
一种航天器减阻降热装置及方法
2021-01-01
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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