The invention discloses an autonomous guidance method for a recoverable aircraft carried on an ultra-low orbit satellite platform. The return type aircraft is arranged to be carried on the ultra-low orbit satellite platform, and long-term stable operation is achieved through the ultra-low orbit satellite platform. And in the process of entering the braking orbit of the recoverable aircraft from the operating orbit, the ultra-low orbit satellite measures the atmospheric density in real time, and the atmospheric resistance estimated value of the recoverable aircraft is obtained through calculation. And when the return type aircraft returns for two circles at the preset return moment, the ultra-low orbit satellite releases the return type aircraft and transmits the atmospheric resistance estimated value to the return type aircraft at the same time. After separation, the return aircraft is navigated by adopting a combined method of inertial navigation orbit extrapolation and GNSS measurement correction, and autonomous correction of ascending node and inclination angle errors is carried out in a return circle. And solving speed increments on a first braking point and a second pulse point of a given return circle by using a Lanbert problem typical algorithm, and outputting speed vectors of the return aircraft before and after a braking moment by taking the speed increments as initial values.
本发明公开了一种搭载于超低轨卫星平台的返回式飞行器自主制导方法。设置返回式飞行器搭载在超低轨卫星平台上,利用超低轨卫星平台长期稳定运行。在从运行轨道进入返回式飞行器的制动轨道过程中,超低轨卫星实时测量大气密度,计算得到返回式飞行器的大气阻力估计值。在返回式飞行器预定的返回时刻两圈次时,超低轨卫星释放返回式飞行器,同时将大气阻力估计值传输给返回式飞行器。分离后,返回式飞行器采用惯导轨道外推加GNSS测量修正的组合方法进行导航,在返回圈进行升交点与倾角误差的自主修正。并使用兰伯特问题典型算法求解给定的返回圈次首次制动点和第二脉冲点上的速度增量,以此为初值,输出制动时刻前后的返回式飞行器速度矢量。
Autonomous guidance method for recoverable aircraft carried on ultra-low orbit satellite platform
一种搭载于超低轨卫星平台的返回式飞行器自主制导方法
2024-04-02
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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