A closed-loop verification system and method for a lunar landing and take-off control system

A control system and verification system technology, applied in the field of spacecraft ground verification, can solve the problems of inability to realize closed-loop verification of the lunar soft landing process, inability to select, poor authenticity and reliability of ground verification, etc.

Active Publication Date: 2019-10-18
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] (1) The traditional closed-loop verification method can only simulate the jet duration of the thruster, but cannot simulate the thrust of the variable thrust engine, and cannot realize the closed-loop verification of the lunar soft landing process;
[0006] (2) When simulating the thruster through the serial port or parallel port pulse acquisition method, the thrust and response characteristics of the engine are mainly simulated by digital means, but this method is different from the communication sequence, action respon...

Method used

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  • A closed-loop verification system and method for a lunar landing and take-off control system
  • A closed-loop verification system and method for a lunar landing and take-off control system
  • A closed-loop verification system and method for a lunar landing and take-off control system

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Experimental program
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Effect test

Embodiment 1

[0086] Such as figure 1 As shown, the digital closed-loop verification system for the landing control system includes a control computer, a propulsion serial card and a dynamics computer;

[0087] When using the digital closed-loop verification method of the landing control system and in landing mode:

[0088] (11) The control computer receives the measurement output of the upper assembly star sensor, sun sensor, gyroscope, accelerometer, distance measuring sensor, speed sensor and other sensors, and calculates the position and speed of the upper assembly in the inertial space , attitude, angular velocity and other information, according to the on-board algorithm, calculate the required engine thrust and control torque, generate RS422 serial port commands according to the communication protocol with the propulsion circuit box, and send the RS422 serial port commands to the propulsion serial port card;

[0089] (12) After the serial port card receives the RS422 serial port com...

Embodiment 2

[0093] Such as figure 2 As shown, the digital closed-loop verification system for the takeoff control system includes a control computer, a propulsion serial card and a dynamics computer;

[0094] When using the digital closed-loop verification method of the takeoff control system and in takeoff mode:

[0095] (21) The control computer receives the measurement output of the ascender star sensor, sun sensor, gyroscope, accelerometer, and other sensors, and calculates the position, speed, attitude, angular velocity and other information of the upper assembly in the inertial space. Algorithm, calculate the required engine thrust and control torque, generate RS422 serial port commands according to the communication protocol with the propulsion circuit box, and send the RS422 serial port commands to the propulsion serial port card;

[0096] (22) advance the serial port card to receive the RS422 serial port instruction that the control computer sends, and the RS422 serial port ins...

Embodiment 3

[0100] Such as image 3 As shown, the physical closed-loop verification system of the landing control system includes a control computer, a propulsion circuit box, a propulsion load box, a stepper motor and a dynamic computer;

[0101] When using the physical closed-loop verification method of the landing control system and in landing mode:

[0102](31) The control computer receives the measurement output of the upper assembly star sensor, sun sensor, gyroscope, accelerometer, distance measuring sensor, speed sensor and other sensors, and calculates the position and speed of the upper assembly in the inertial space , attitude, angular velocity and other information, calculate the required engine thrust and control torque according to the on-board algorithm, generate RS422 serial port commands according to the communication protocol with the propulsion circuit box, and send the RS422 serial port commands to the propulsion circuit box;

[0103] (32) The propulsion line box rece...

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Abstract

The invention relates to a closed loop verification system and method for a lunar landing and taking off control system, particularly relates to the closed loop verification system and method for thelunar landing and taking off control system with a variable thrust engine, and belongs to the technical field of ground verification of space vehicles. According to the method, simulation of an orbitand attitude control engine is conducted through two working manners of digital simulation and entity simulation, engine signals are collected by a dynamic computer to achieve dynamic driving during the lunar landing and taking off process and provide position and attitude information for on-board equipment, and therefore a closed loop is achieved; the two working manners can be switched accordingto ground verification demands. The closed loop verification method is adopted by the ground verification of a GNC sub system of on-board combination of the third phase of lunar exploration, and a better effect is achieved in the process of systematic closed loop verification; the closed loop system plays an important role in the processes of system fault recognition, regression testing and problem rapid searching and positioning, and the authenticity, sufficiency and testing efficiency of ground verification are improved.

Description

technical field [0001] The invention relates to a closed-loop verification system and method of a lunar landing and take-off control system, in particular to a closed-loop verification system and method of a lunar landing and take-off control system including a variable thrust engine, and belongs to the technical field of spacecraft ground verification. Background technique [0002] According to the requirements of the third phase of the lunar exploration mission, the landing and ascending assembly will softly land on the lunar surface. After the automatic sampling of the moon, the ascending device will use the lander as a platform to take off and return to the orbit around the moon and rendezvous with the orbiting return assembly (orbiter and returner). , to complete the sample transfer. In order to complete the task, three types of engines are configured in the GNC subsystem of the upper assembly, namely, the constant thrust attitude control engine, the 3000N orbital contr...

Claims

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Application Information

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IPC IPC(8): G05B23/02
Inventor 于萍王华强杨洁赵宇杨巍于洁王志文
Owner BEIJING INST OF CONTROL ENG
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