Mars atmosphere entry section accompanying flight beacon auxiliary navigation method

Abstract

The invention discloses a Mars atmosphere entry section accompanying flight beacon auxiliary navigation method, relates to a beacon auxiliary navigation method, and belongs to the technical field of deep space exploration. According to the method, on the basis of the Mars atmosphere entry section inertial navigation, an accompanying flight beacon is introduced; by adding the radio distance measurement and speed measurement among a landing device, a rail device and the accompanying flight beacon as a measuring quantity, an initial state deviation is corrected; a geometrical configuration during the radio navigation of the landing device and the rail device is improved; the entry section navigation precision is further improved. The Mars atmosphere entry section accompanying flight beacon auxiliary navigation method disclosed by the invention can solve the problems of the inertial navigation that the initial state deviation cannot be corrected during inertial navigation, and the measurement errors are accumulated along with time. The geometrical configuration of the radio navigation can be improved; the high-precision estimation of a full state of the landing device is obtained; the entry section navigation precision is further improved.

Description

technical field [0001] The invention relates to a beacon-assisted navigation method, in particular to a beacon-assisted navigation method during the Mars atmosphere entry stage, and belongs to the technical field of deep space exploration. Background technique [0002] Future Mars exploration requires landers to achieve precise soft landings. The descent into the atmosphere of Mars is the longest stage of the landing process. A certain guidance algorithm can control the lander to fly to the predetermined parachute opening point. The accuracy of the parachute opening point is an important factor affecting the final landing accuracy. In order to ensure the high accuracy of the parachute opening point, the navigation system of the entry phase must provide accurate position and velocity information of the lander. Therefore, constructing a navigation scheme that can accurately determine the position and velocity of the lander is the basis for the success of the fixed-point landi...

AI Technical Summary

Problems solved by technology

[0005] In view of the problems existing in the prior art that the inertial navigation cannot correct the initial state deviation, the measurement error accumulates over time, and the poor geometric configuration when the lander and a single orbiter perform radio navigation

The invention discloses a method for assisting navigation with flying beacons in the Martian atmosphere entry stage. The technical problem to be solved is to overcome the inertia by adding the flying beacons and introducing the radio ranging and speed measurement information between the lander, the orbiter and the flying beacons. The navigation cannot correct the initial state deviation and the problem of measurement error accumulating over time, and improve the geometric configuration of the radio navigation, obtain a high-precision estimation of the full state of the lander, and improve the navigation accuracy of the entry segment

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