Satellite attitude control Ground full physical simulation intelligent control system

A satellite attitude control and intelligent control system technology, applied in the field of measurement, can solve the stability adjustment of the aircraft attitude control ground simulation system, does not involve the debugging and analysis of the air bearing platform, etc., achieves low transformation cost, easy maintenance, and simple principle Effect

Active Publication Date: 2019-07-05
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this method does not involve issues such as bearing capacity and air supply pressure, and cannot be directly used to adjust the stability of the aircraft attitude control ground simulation system
[0004] Chinese invention patent application number: CN201410390718, the patent name is a test system and method for simulating the three-axis attitude coupling motion of a flexible satellite using a single-axis air-floor table. By expanding the function of the single-axis air bearing table, the combination of physical characteristics and mathematical models is adopted, and the calculation of the mathematical model is used to integrate the three-axis coupling torque, the disturbance torque of the flexible attachment and the The space environment disturbance torque is realized by the torque output device, which can improve the effectiveness of using a single-axis air bearing table to verify the single-axis attitude movement of the flexible satellite, and more truly reflect the single-axis attitude movement of the satellite in orbit. Debugging and analysis of floating platform stability, etc.

Method used

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  • Satellite attitude control Ground full physical simulation intelligent control system
  • Satellite attitude control Ground full physical simulation intelligent control system
  • Satellite attitude control Ground full physical simulation intelligent control system

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0042] combine figure 1 , a satellite attitude control ground full physical simulation intelligent control system, comprising a pressure regulating valve 1, a pressure sensor 2, a level instrument 3, a load cell 4 and a controller 5; it is characterized in that the supply of the pressure regulating valve 1 and the air bearing The air pipeline is connected, the pressure sensor 2 is connected to the buffer chamber of the air-floating ball bearing, the control end of the pressure regulating valve 1 and the output end of the pressure sensor 2 are both connected to the controller 5, the level meter 3 and the load cell 4 are installed on the ball bearing The lower end of the seat, the output ends of the level meter 3 and the load cell 4 are all connected to the controller 5; the level meter 3 measures the levelness of the base and outputs the data to the controller 5, and the load cell 4 measures the weight of the test bench body in real time and The data is output to the controller...

Embodiment 2

[0074] The principle of controller design is analyzed as follows:

[0075] According to the closed-loop system described in embodiment 1, in order to analyze the stability of the system, the Lyapunov function is selected as follows:

[0076]

[0077] Deriving the above formula,

[0078]

[0079] use and the following lemma:

[0080] Lemma 1 (Schuler's complement lemma): For symmetric matrices The following descriptions are equivalent:

[0081] 1) L<0,

[0082]

[0083]

[0084] Lemma 2: For matrices and vector equations such that the following integral is defined, then the following inequalities hold:

[0085]

[0086] in

[0087]

[0088] η(t)=[x T (t) x T (t-d(t))x T (t-h)] T (18)

[0089] The following formula can be obtained:

[0090]

[0091] in

[0092]

[0093]

[0094]

[0095]

[0096] Continue processing, you can have:

[0097]

[0098] where is h ij A piecewise linear description, h ij ≡w i m j , Y ij ≥Ω i...

Embodiment 3

[0116] From the above analysis, it can be seen that the obtained controller design method contains a membership function, which means that the method is dependent on the membership degree, which can effectively reduce the conservatism of the system. In addition, the time-delay The idea of ​​cutting is to divide the delay interval [0, h] into [0, d(t) / 2], [d(t) / 2, d(t)], [d(t), [d(t) )+h] / 2] and [[d(t)+h] / 2, h] four sub-intervals, which can increase the degree of time-delay dependence on the one hand, and avoid increasing the heavy computational burden on the other hand.

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Abstract

The invention provides a satellite attitude controlled ground full-physical simulation intelligent control system, comprising a pressure regulating valve, a pressure sensor, a spirit level, a weighing sensor and a controller, wherein the control end of the pressure regulating valve and the output end of the pressure sensor are connected with the controller, and the spirit level and the output end of the weighing sensor are connected with the controller; the spirit level measures the levelness of a base and outputs data to the controller, and the weighing sensor measures the weight of a test bed in real time and outputs data to the controller; based on the thought of fussy intelligent control, a dependent variable is selected for establishing a system model, the controller enabling the system to be asymptotically stable is designed according to the Lyapunov stability analysis theory, the conservatism of the system design is lower by adopting the thought of piecewise linearization, and the description rules of the controlled object and the controller are not limited so as to improve the flexibility of the system design. The system is simple in principle and convenient to maintain.

Description

technical field [0001] The invention relates to measurement technology, in particular to a satellite attitude control ground full physical simulation intelligent control system. Background technique [0002] The special operating environment of the space vehicle makes the ground simulation test particularly important. The core equipment of the full physical ground simulation system developed for the space vehicle is an air flotation simulation platform based on the air flotation ball bearing. The air film formed between the bearing seats makes the simulated platform body float, so as to realize the relative motion condition of approximately frictionless, so as to simulate the mechanical environment in which the satellite is subjected to a small disturbance moment in outer space. Among them, the eddy current moment and bearing capacity are the two most critical indicators. Different air supply pressure and bearing capacity will show different eddy current moments. The eddy cu...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B17/02
Inventor 王常虹夏红伟李莉马广程任顺清
Owner HARBIN INST OF TECH
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