Space-ground integrated lunar surface landing navigation method

Abstract

The invention discloses a heaven and earth integrated lunar surface landing navigation method. The method comprises the following steps: S1, constructing a lunar surface landing navigation state quantity solved by a lander and an orbiter in a combined manner; s2, establishing a lander navigation state equation and an orbiter navigation state equation; s3, the relative distance and the relative speed between the lander and the orbiter are measured, and a measurement matrix is solved; and S4, performing time updating and measurement updating on the measurement matrix by using an extended Kalman filtering algorithm, and realizing estimation of lunar surface landing navigation state quantity based on the lander state equation and the orbiter navigation state equation. According to the method, radio measurement between space and ground users is only utilized, the navigation state quantity of a lander is estimated, meanwhile, the orbital state quantity of an orbital device can be corrected, space and ground integrated multi-device combined navigation is formed, measurement and calculation are simple, dependence on foundation and space-based observation is avoided, remote sensing images obtained in orbit are used as initial orbit determination observation data, and the method is suitable for large-scale popularization and application. The method is more independent, and the on-orbit survival capability is improved.

Description

technical field [0001] The invention relates to the technical field of extraterrestrial celestial body landing and navigation, in particular to a method for landing and navigation on the lunar surface integrated with space and ground based on relative measurement. Background technique [0002] With the continuous exploration of deep space by countries all over the world, landing on the surface of extraterrestrial celestial bodies for resource exploration and the construction of human habitable places in the future has become an important focus of space development in various countries, among which safe landing on the surface of extraterrestrial celestial bodies is the mission. necessary condition. [0003] In the landing navigation of extraterrestrial celestial bodies, due to the limitations of communication delay and long-distance measurement power and accuracy, the traditional navigation method relying on ground measurement and control is not suitable for deep space long-d...

AI Technical Summary

Problems solved by technology

[0004] Among these measurement methods, the method based on radio relative measurement has the characteristics of simple calculation and high measurement accuracy. By establishing radio communication with the orbiter and performing relative measurement to realize integrated navigation with inertia, it is a kind of ground inertial / GPS-like system. Combined navigation method, but the position of the orbiter itself in deep space cannot be obtained as accurately as GPS navigation satellites. It is a spatial reference with an imprecise and known position, so it also has the need for autonomous navigation and positioning

Images