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

A beam pointing and determining method technology, which is applied in the directions of the landing device of the spacecraft and the system of the spacecraft returning to the earth's atmosphere, which can solve the problems of uncertainty in the navigation and landing area, and difficulty in ensuring the safe landing of the detector.

Active Publication Date: 2021-12-10
BEIJING INST OF CONTROL ENG
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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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  • Distance and speed measurement sensor beam pointing determination method for Mars landing
  • Distance and speed measurement sensor beam pointing determination method for Mars landing
  • Distance and speed measurement sensor beam pointing determination method for Mars landing

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Embodiment Construction

[0059] In order to make the object, technical solution and advantages of the present invention clearer, the implementation manner of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0060] During the Mars landing process, the measurement of the ranging and speed measuring sensor starts after the separation of the heat-resistant outsole. Considering that the multi-beams all hit the outsole and give wrong ranging and speed measurement information, it generally needs to be measured after the outsole is separated. After a period of time, the measurement starts and provides distance and speed information. In addition, comprehensively considering the speed constraints at the moment of landing, the performance of ranging and speed measuring products, and the dust blown by the engine, etc., after the detector reaches a certain height, the measurement information of the ranging and speed measuring sensor is no longer used, ...

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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...

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Application Information

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IPC IPC(8): B64G1/62
CPCB64G1/62
Inventor 刘旺旺赵宇王晓磊郝策徐李佳王云鹏李茂登郭敏文周益张琳徐超
Owner BEIJING INST OF CONTROL ENG
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