采用GPS或INS／运动方程确定气动力变轨段导航信息

DETERMINATION OF NAVIGATION INFORMATION BY GPS(or INS)/EQUATIONS OF MOTION DURING AEROASSISTED ORBITAL TRANSFER

基于航天器气动力辅助变轨的基准飞行轨道，提出采用ＧＰＳ（或ＩＮＳ）／运动方程来确定航天器的六自由度导航信息。采用航天器高超音速空气动力的近似计算公式，导出了ＧＰＳ（或ＩＮＳ）／运动方程导航方案的滤波方程、观测方程等。数字仿真表明，ＧＰＳ（或ＩＮＳ）／运动方程导航方案的精度高于ＧＰＳ或ＩＮＳ，而且较单纯的ＧＰＳ或ＩＮＳ增加了导航信息冗余度。

Based on the norminal trajectory of aeroassisted orbital transfer,the paper gives a new navigation scheme for the space vehicle:Nayigation hardware/Equations of Motion(EM),GPS/EM,INS/EM are studied for the vehicle to determine the navigation information during aeroassisted orbital transfer.High supersonic aerodynamic calculation formulasare introduced to deduce the equations of filter and observation for the hybrid navigation system.The numerical results show that the navigation precision of GPS(or INS)/EM are much higher than that of single EM.GPS,or INS.The GPS(or INS)/EM has more redundance thlan the GPS(or INS).