Distance and speed measurement sensor beam pointing determination method for Mars landing

Abstract

The invention relates to a distance and speed measurement sensor beam pointing determination method for Mars landing, which comprehensively considers the configuration layout of a detector, and considers the measurement precision requirements of long and short distance sections and heterogeneous backup of two types of distance and speed measurement sensors. The pointing directions of four fixed pointing beams of the microwave distance and speed measuring sensor and nine fixed beam pointing directions of the phased array sensor are determined. In actual use, the phased array sensor calculates and appoints four wave beams through a spaceborne computer in each measurement period to provide distance measurement and speed measurement information. Multi-beam information fusion processing is carried out on relative distance and speed information obtained in eight beam directions of the microwave distance and speed measuring sensor and the phased array sensor, so that the relative distance, speed and other information of the detector relative to the surface of the Mars can be solved.

Description

technical field [0001] The invention relates to a method for determining the beam direction of a range-measuring and speed-measuring sensor used for Mars landing, which is suitable for determining the direction of the distance-measuring and speed-measuring beam of a spacecraft during the Mars landing process. Background technique [0002] The Mars landing process begins when the probe touches the entry point of the Martian atmosphere and ends with a safe landing on the surface of Mars. It mainly includes several key stages such as aerodynamic deceleration, parachute deceleration and power deceleration, among which the power deceleration stage can be further divided into stages such as power avoidance, hovering imaging, obstacle avoidance maneuver and slow descent. In the stage before the atmosphere enters, it mainly relies on the initial position, velocity and attitude information determined by the orientation sensor of the ground-based orbit determination sensor as the init...

AI Technical Summary

Problems solved by technology

However, due to the performance limitations of the inertial measurement unit itself, the cumulative effect of navigation errors, and the uncertainty of the landing area, it is difficult to guarantee the safe landing of the probe solely by inertial navigation extrapolation.

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