Replacement and extrapolation combined navigation method

Abstract

The invention discloses a replacement and extrapolation combined landing navigation method which is suitable for height and speed navigation in the landing process of an extraterrestrial celestial body of a space detector. The method comprises the following steps of: determining the landing altitude and speed of the detector in a landing preliminary stage by adopting a method in which the inertial navigation and a measuring sensor are in a weighting eclectic manner; and directly determining the landing altitude and speed of the detector by adopting measuring information of the measuring sensor below the specific height of a landing terminal stage, and determining the height and speed in an updating interval of the measuring information by adopting the inertial navigation extrapolation. The method is used, the navigation accuracy of the landing altitude and speed is obviously improved, and the replacement rate and the data smoothing property of navigation data of the detector are guaranteed.

Description

technical field The invention relates to a landing navigation method with replacement and extrapolation, which is suitable for navigation calculation with uncertain initial attitude in the landing process of space probe extraterrestrial celestial bodies. Background technique During the landing process of the extraterrestrial celestial body, the probe needs to obtain the distance and speed information of itself relative to the target celestial body (the target celestial body is assumed to be the moon in the following). There are two main methods for the detector to independently obtain translational motion information. The first is to use inertial attitude measurement sensors (star sensors, gyroscopes, and accelerometers) to obtain the inertial attitude of the probe and the acceleration information received, and combine the orbit initial value information provided by the ground measurement and control system to perform calculation and extrapolation to obtain its relative posi...

AI Technical Summary

Problems solved by technology

The first method is less accurate at the end of the landing, while the second method is not suitable for the initial landing

Generally speaking, the weighted compromise between the navigation values ​​determined by the two navigation methods during the landing process is the usual navigation method for landing detectors. The determinism and inertial navigation cumulative error have a greater impact, so it is not suitable for detectors with higher requirements for landing altitude and speed control

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