Research on Radar Aided SINS Autonomous Navigation Scheme for Lunar Soft Landing

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.

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Observability-based Mars Autonomous Navigation Using Formation Flying Spacecraft

Journal of Navigation ◽

10.1017/s0373463317000510 ◽

2017 ◽

Vol 71 (1) ◽

pp. 21-43 ◽

Cited By ~ 6

Author(s):

Yangwei Ou ◽

Hongbo Zhang

Keyword(s):

Autonomous Navigation ◽

Formation Flying ◽

Line Of Sight ◽

Gravity Gradient ◽

Optimal Parameters ◽

Gravity Gradient Tensor ◽

Navigation Simulation ◽

Formation Flying Spacecraft ◽

Cross Track ◽

Navigation Scheme

This paper concentrates on designing an autonomous navigation scheme for Mars exploration. In this scheme, formation flying spacecraft are used to realise absolute orbit determination when orbiting around Mars. Inertial Line-Of-Sight (LOS) vectors from “deputy” spacecraft to the “chief” are measured using radio cross-link, optical devices and attitude sensors. Since the system's observability is closely related to the navigation performance, an analytical approach is proposed to optimise the observability. In this method, the gravity gradient tensor difference is chosen as the performance index to optimise two navigation scenarios. When there is one deputy flying around the chief, optimal parameters are obtained by solving the constrained optimisation problem. When a second deputy is added into the formation, the optimal configuration is also obtained. These results reveal that the observability is mainly determined by the magnitude of the in-track and cross-track distances in the configuration. An Extended Kalman Filter (EKF) is used to estimate the position and velocity of the chief. The results of a navigation simulation confirms that adding more deputies can significantly improve the navigational performance.

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An autonomous navigation scheme using global positioning system/geomagnetism integration for small satellites

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1243/0954410001532015 ◽

2000 ◽

Vol 214 (4) ◽

pp. 207-215 ◽

Cited By ~ 2

Author(s):

W Zuo ◽

F Song

Keyword(s):

Global Positioning System ◽

Autonomous Navigation ◽

Positioning System ◽

Small Satellites ◽

Global Positioning ◽

Navigation Scheme

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Trajectory Options for MAV Navigation

International Journal of Micro Air Vehicles ◽

10.1260/1756-8293.4.4.305 ◽

2012 ◽

Vol 4 (4) ◽

pp. 305-313 ◽

Cited By ~ 6

Author(s):

Chimpalthradi R. Ashokkumar

Keyword(s):

Flight Control ◽

Autonomous Navigation ◽

Vehicle Control ◽

Micro Air Vehicle ◽

Input System ◽

Air Vehicle ◽

Multiple Input ◽

Aircraft Trajectories ◽

Navigation Scheme

Unmanned micro air vehicle control in pitch plane is quite challenging. In order to develop an autonomous navigation scheme in pitch plane, longitudinal autopilot design for flight control modes such as take-off, landing, climb, altitude hold, etc., have been actively pursued in the literature. The aircraft trajectories that a controller generates are important to understand these modes. In this paper, it is shown that a multiple input system can offer infinitely a large number of trajectory options that can be used to develop various flight control modes and plan an MAV navigation scheme. Accordingly, the controllers are determined. An MAV example is considered and trajectory options for climb and descend modes are illustrated.

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