The invention provided an inter-
satellite measurement and gyro attitude
orbit integrated
smoothing estimation method. According to the inter-
satellite measurement and gyro attitude
orbit integrated
smoothing estimation method, relative navigation and
attitude determination of non-cooperative targets are realized via following steps: formation
satellite attitude integration dynamical equation is used, and
observability problems of the
system are solved via using a large amount of inter-satellite measurement and gyro measurement data combined with Kalman
smoothing algorithm, wherein the formation satellite attitude integration dynamical equation is composed of attitude dynamics constructed from
quaternion error under inertial frame, and
relative motion dynamics constructed under track
satellite orbit frame, only based on gyro and inter-satellite measurement information. Compared with existing technology, advantages of the inter-satellite measurement and gyro attitude
orbit integrated smoothing
estimation method are that:
system configuration requirements are simple, only inter-satellite measurement and gyro information is needed, dependence of the
system on orientation systems such as
star sensor is reduced, and system reliability is increased; the inter-satellite measurement and gyro attitude orbit integrated smoothing estimation method can be used for satellites of non-cooperated formation; an indirect measurement equation is adopted,
coupling properties of an
observation matrix are poor,
algorithm calculation is simple, and
engineering application is convenient.