Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Method for determining the control parameters of spacecraft autonomous cooperative coarse-fine layering master-layer integration three-superior

A technology for controlling parameters and determining methods, which is applied to aerospace vehicles, aerospace vehicle guidance devices, aircraft, etc., and can solve the problem that it is difficult to achieve ultra-high-precision pointing and ultra-high stability control of the load optical axis, and the precision cannot achieve flexibility. Vibration and high-frequency micro-vibration active control, unable to further improve load pointing accuracy and stability, etc., to achieve the effect of improving design efficiency and control performance, realizing three-super performance control, and improving load stability indicators

Active Publication Date: 2022-03-04
BEIJING INST OF CONTROL ENG
View PDF7 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The flexible vibration and high-frequency micro-vibration existing in the spacecraft star are directly transmitted to the payload, so that the optical payload cannot further improve the imaging quality
However, the traditional spacecraft attitude system is limited by the bandwidth of the controller and the accuracy of the actuator, so it cannot realize the active control of the flexible vibration and high-frequency micro-vibration, and the further improvement of the control accuracy and stability of the star is limited.
[0006] 2. It is difficult to achieve ultra-high precision pointing and ultra-high stability control of the load optical axis
Limited by factors such as the measurement bandwidth of the sensor and the response bandwidth of the actuator, the pointing accuracy and stability of the load cannot be further improved
In the satellite control system model including the active pointing ultra-static platform and the fast mirror, it is necessary to design a multi-level composite pointing control scheme for the spacecraft. At the same time, in order to solve the problems of many multi-level composite control design components and complex transmission relationships of each channel, the given An index decomposition and parameter design method based on frequency domain analysis, which realizes the rapid and optimal design of multi-level compound control and realizes the three-superior control performance of spacecraft

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Method for determining the control parameters of spacecraft autonomous cooperative coarse-fine layering master-layer integration three-superior
  • Method for determining the control parameters of spacecraft autonomous cooperative coarse-fine layering master-layer integration three-superior
  • Method for determining the control parameters of spacecraft autonomous cooperative coarse-fine layering master-layer integration three-superior

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0064] The spacecraft multi-level system proposed by the present invention includes a star platform, an active pointing ultra-static platform, a load, a sensor system and a fast mirror;

[0065] The payload is an optical system for imaging celestial bodies;

[0066] The fast reflector is installed inside the load to adjust the direction of the load optical axis;

[0067] Sensor systems are used to measure data;

[0068] The star platform is used to support the active pointing ultra-static platform and load;

[0069] The active pointing ultra-static platform is installed between the load and the astral platform, the upper plane is connected with the load, and the lower plane is connected with the astral platform; the active pointing ultra-static platform is composed of six actuators, and each actuator includes a displacement sensitive devices, spring-damper structures, and linear motors;

[0070] The displacement sensor is used to measure the translational displacement of th...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

A method for determining the control parameters of spacecraft autonomous and cooperative coarse-fine layering, master-substrate, and three-super-control, which is suitable for fields such as astronomical observation and high-resolution earth observation that require ultra-high-precision determination of payloads. A control parameter design method is provided for spacecraft three-superior control with ultra-high precision, ultra-high stability, and ultra-agile control. Based on the index decomposition method, each controller parameter of the spacecraft three-superior control system is designed, which improves the design efficiency and control performance. The main design ideas are as follows: 1) First, according to the three-level control system architecture, establish the control model of the three-level control of the star, the load, and the fast mirror; ; 3) According to the noise characteristics of the selected sensors and actuators, the parameters of the controllers at all levels are designed through the method of frequency domain analysis, so that the power spectral densities of the control loops at all levels meet the design indicators, and the three-superior control performance of the spacecraft is realized. .

Description

technical field [0001] The invention relates to a star-load-fast mirror three-stage attitude control system and a parameter design method for realizing a spacecraft, belonging to the field of spacecraft attitude control. Background technique [0002] At present, spacecraft generally use components containing high-speed rotors such as flywheels and control moment gyroscopes as actuators for attitude control systems. These high-speed rotating parts will inevitably produce high-frequency jitter and micro-vibration, which directly affect the working performance of the load. This cannot meet the requirements of space missions such as astronomical observations and extremely high-resolution earth observations that require high-performance control of optical loads. The spacecraft multi-level composite control system came into being according to the demand for high-precision attitude control of such optical loads. The spacecraft multi-level composite control system refers to the sp...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
CPCB64G1/244B64G1/24B64G1/245
Inventor 姚宁汤亮袁利关新王有懿宗红郝仁剑张科备冯骁郭子熙刘昊龚立纲
Owner BEIJING INST OF CONTROL ENG
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products