A Celestial Assisted INS Initialization Method for Lunar Explorers
Open Access
- 3 July 2011
- Vol. 11 (7), 6991-7003
- https://doi.org/10.3390/s110706991
Abstract
The second and third phases of the Chinese Lunar Exploration Program (CLEP) are planning to achieve Moon landing, surface exploration and automated sample return. In these missions, the inertial navigation system (INS) and celestial navigation system (CNS) are two indispensable autonomous navigation systems which can compensate for limitations in the ground based navigation system. The accurate initialization of the INS and the precise calibration of the CNS are needed in order to achieve high navigation accuracy. Neither the INS nor the CNS can solve the above problems using the ground controllers or by themselves on the lunar surface. However, since they are complementary to each other, these problems can be solved by combining them together. A new celestial assisted INS initialization method is presented, in which the initial position and attitude of the explorer as well as the inertial sensors’ biases are estimated by aiding the INS with celestial measurements. Furthermore, the systematic error of the CNS is also corrected by the help of INS measurements. Simulations show that the maximum error in position is 300 m and in attitude 40″, which demonstrates this method is a promising and attractive scheme for explorers on the lunar surface.Keywords
This publication has 16 references indexed in Scilit:
- On the observability of linear motion quantities in navigation systemsSystems & Control Letters, 2011
- An Integration of GPS with INS Sensors for Precise Long-Baseline Kinematic PositioningSensors, 2010
- A new autonomous celestial navigation method for the lunar roverRobotics and Autonomous Systems, 2009
- A novel method improving the alignment accuracy of a strapdown inertial navigation system on a stationary baseMeasurement Science and Technology, 2004
- Nonlinear filtering methods application in INS alignmentIEEE Transactions on Aerospace and Electronic Systems, 1997
- A fast initial alignment method for strapdown inertial navigation system on stationary baseIEEE Transactions on Aerospace and Electronic Systems, 1996
- Strapdown INS error model for multiposition alignmentIEEE Transactions on Aerospace and Electronic Systems, 1996
- Observability analysis of piece-wise constant systems. II. Application to inertial navigation in-flight alignment (military applications)IEEE Transactions on Aerospace and Electronic Systems, 1992
- Identity between INS position and velocity error equations in the true frameJournal of Guidance, Control, and Dynamics, 1988
- Inertial navigationProceedings of the IEEE, 1983