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针对深空探测接近目标天体段轨道,提出了以B平面参数为制导目标参数的自主轨道控制方法.由自主导航系统确定探测器的当前位置和速度,通过精确轨道动力学积分外推到目标天体的近心点得到B平面误差,利用线性制导公式计算出修正轨道需要的速度增量,并用误差椭圆来统计修正后B平面误差.以火星探测为例进行蒙特卡罗仿真,验证了该方法的正确性.
For deep space exploration approaching orbit of the target celestial segment, an autonomous orbit control method using B-plane parameters as the guidance target parameters is proposed. The autonomous navigation system determines the current position and velocity of the projectile and extrapolates the accurate orbit kinetic integral to the target celestial body The B-plane error is obtained, and the linear guidance formula is used to calculate the incremental velocity needed to correct the orbit, and the error ellipse is used to calculate the corrected B-plane error.The Monte Carlo simulation of Mars exploration proves that this method Correctness