As a new information provider of autonomous navigation, the on-orbit landmark observation offers a new means to improve the accuracy of autonomous positioning and attitude determination. A novel autonomous navigation method based on the landmark observation and the inertial system is designed to achieve the high-accuracy estimation of the missile platform state. In the proposed method, the navigation scheme is constructed first. The implicit observation equation about the deviation of the inertial system output is derived and the Kalman filter is applied to estimate the missile platform state. Moreover, the physical observability of the landmark and the mathematical observability of the navigation system are analyzed. Finally, advantages of the proposed autonomous navigation method are demonstrated through simulations compared with the traditional celestial-inertial navigation system and the deeply integrated celestial-inertial navigation system.
Rendezvous and docking with noncooperative targets is one of the key technologies for on-orbit service such as satellite maintenance, space supply and space debris cleaning, etc. For the rendezvous and docking with maneuvering noncooperative targets, a relative measurement scheme based on one monocular camera and one distance sensor is designed. A dynamic compensation filter (DCF) is also proposed to estimate the relative state and the unknow maneuver of the noncooperative target. Meanwhile, the control scheme to fulfill the rendezvous and docking mission is given. Compared with the extended Kalman filter (EKF) and variable state dimension estimator (VSDE), the numerical simulation results demonstrate that the proposed estimator has better performance in estimating the relative state and target maneuver. The control scheme based on DCF can accomplish the rendezvous and docking task when the noncooperative target performs time-varying maneuvers. INDEX TERMS Noncooperative target, unknown maneuver, space rendezvous and docking, navigation, control.
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