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A flexible satellite attitude-orbit coupling control method based on isolation margin method and pulse width fusion strategy

A technology for flexible satellites and isolation margins, which is applied in the direction of aerospace vehicle guidance devices, etc., and can solve problems such as failure to consider isolation margins, loss, and uncontrollable flywheels

Active Publication Date: 2016-06-08
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] The purpose of the present invention is to solve the problem that two sets of actuators for orbit control and attitude control need to be equipped during the attitude and orbit control process of the satellite, and the flywheel will not be able to control the layout of the corresponding thrusters without consideration of the plume. Due to the problems caused by the pulling deviation of the influence and moment of inertia, the failure to consider the isolation margin and the failure of the attitude to meet the requirements and cause serious losses, a flexible satellite attitude-orbit coupling control method based on the isolation margin method and the pulse width fusion strategy is proposed.

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  • A flexible satellite attitude-orbit coupling control method based on isolation margin method and pulse width fusion strategy
  • A flexible satellite attitude-orbit coupling control method based on isolation margin method and pulse width fusion strategy
  • A flexible satellite attitude-orbit coupling control method based on isolation margin method and pulse width fusion strategy

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specific Embodiment approach 1

[0068] Specific implementation manner 1: A flexible satellite attitude orbit coupling control method based on the isolation margin method and the pulse width fusion strategy of this embodiment is specifically prepared according to the following steps:

[0069] Step 1. According to the geocentric inertial coordinate system (Oi, Xi, Yi, Zi) (ECI) such as Figure 21 , The satellite body coordinate system (Ob, Xb, Yb, Zb) such as Figure 14 、Satellite layout coordinate system (O1, X1, Y1, Z1) (the origin is taken at the geometric center of the separating plane of the star and the arrow, the O1Z1 axis is in the separating plane of the star and the arrow, pointing vertically to the ground; the O1, Y1 axis is perpendicular to the separating plane of the star and arrow , Pointing to the payload bay; the O1X1 axis and the other two axes form the right-hand rule), and considering the various types of flexible satellite attitudes and various types of interference moments affecting the flexibl...

specific Embodiment approach 2

[0080] Specific embodiment two: This embodiment is different from the specific embodiment one in that the interference torque of the rotating part described in step one is as follows: Figure 16 with Figure 17 for:

[0081]

[0082] ω wby Indicates the speed of the rotating part, I wby Is the component of the inertia matrix of the rotating part relative to the origin; the disturbance moment T of the rotating part wb T wbx , T wby , T wbz Are the components on the corresponding x, y, and z axes;

[0083] The internal interference torque formula of the interference torque caused by the unlocking of the pyrotechnic device on the body is as follows Figure 18 ;

[0084]

[0085] ω wbz Indicates the rotating speed of the pyrotechnic device, I wbz Is the component of the inertia matrix of the pyrotechnic device relative to the origin;

[0086] The separation moment of the separating body includes the separation interference moment of the small satellite such as Figure 19 Separate t...

specific Embodiment approach 3

[0087] Specific embodiment three: This embodiment is different from specific embodiment one or two in that the specific process of establishing a dynamic model with windsurfing locked and uncontrolled by the satellite in step one is:

[0088] (1) Establish the satellite attitude dynamic equation with flexible solar panel attachment as:

[0089]

[0090] among them,

[0091] Modal coordinates of windsurfing board A;

[0092] Angular velocity of windsurfing board A;

[0093] R sa : Is the dyadic coupling inertia between the rotation of the windsurfing board and the rotation of the entire star;

[0094] F s : Is the rotation coupling coefficient matrix of windsurfing board A vibration to the whole satellite relative to the satellite system;

[0095] R as : Is the dyadic coupling inertia between the rotation of the entire star and the rotation of the windsurfing board;

[0096] F A : Is the coupling coefficient matrix of the vibration of windsurfing board A to the rotation of windsurfing ...

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Abstract

The invention relates to the field of flexible satellite attitude orbit coupling control, in particular to a flexible satellite attitude orbit coupling control method based on an isolation allowance method and a pulse width fusion strategy. The method solves the problems that in the satellite in-orbit attitude and orbit control process, a flywheel cannot control that the corresponding thruster layout is not given, the plume influence and rotational inertia level bias are not considered, isolation allowance is not considered and the attitude does not meet the requirement. The method comprises the steps of 1, obtaining sailboard locking and satellite uncontrollable dynamical model parameters; 2, determining installation position coordinates of a thrust; 3, determining an IM value; 4, obtaining an orbit-control LQG sequence; 5, determining the orbit-control pulse width and the air injection direction; 6, selecting air injection of the attitude-controlled thrust; 7, determining the range of the attitude-controlled thrust; 8, determining the attitude-controlled air injection time; 9, obtaining an equivalent force moment value. The flexible satellite attitude orbit coupling control method is applied to the field of flexible satellite attitude orbit coupling control.

Description

Technical field [0001] The invention relates to an orbit coupling control method, in particular to a flexible satellite attitude orbit coupling control method. Background technique [0002] For the attitude and orbit control of the satellite during its orbit, people began to adopt the method of separate control of attitude and orbit, "Integrated Control of Relative Orbit and Attitude of Formation Satellites", and separate control of the orbit and attitude requires both orbit control and attitude control. A set of actuators will increase the number of actuators such as thrusters and cause waste of resources. In terms of modeling, the attitude and orbit are handled separately, although the modeling problem is simplified, but the complexity of the model itself is increased, making the spacecraft control algorithm complicated and cumbersome, and at the same time occupying the limited computing resources of the on-board computer. With the development of aerospace technology, in the f...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
Inventor 孙延超刘萌萌马广富王晓东李传江朱津津
Owner HARBIN INST OF TECH