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Method for controlling autonomous rendezvous between spacecrafts under action of impulse thrust

A control method, a technology of pulse action, applied in three-dimensional position/channel control and other directions, which can solve problems such as the influence of interference torque

Inactive Publication Date: 2013-04-24
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to solve the problem that the existing control method of spacecraft rendezvous under the action of pulse thrust adopts the open-loop control mode and is easily affected by the disturbance torque, and further provides an autonomous rendezvous control method of spacecraft under the action of pulse thrust

Method used

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  • Method for controlling autonomous rendezvous between spacecrafts under action of impulse thrust
  • Method for controlling autonomous rendezvous between spacecrafts under action of impulse thrust
  • Method for controlling autonomous rendezvous between spacecrafts under action of impulse thrust

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specific Embodiment approach 1

[0070] Specific implementation mode one: combine Figure 1 to Figure 3 Description of this embodiment: a pulse thrust action of this embodiment

[0071] The following spacecraft autonomous rendezvous control method, the specific process of the control method is:

[0072] Step 1. Establish a relative motion dynamics model of the spacecraft

[0073] For the tracking spacecraft (1) and the target spacecraft (2) that are rendezvous, the orbit of the target spacecraft (2) is a circular orbit, and the relative motion coordinate system is established with the center of mass of the target spacecraft (2) as the origin:

[0074] The center O of the circular orbit is the center of mass of the earth, the x-axis is in the orbital plane of the target spacecraft, and the positive direction is the direction where the center of the earth points to the spacecraft: the y-axis points to the running direction of the target spacecraft; the z-axis is perpendicular to the orbital plane and is aligne...

specific Embodiment approach 2

[0125]Specific embodiment 2: This embodiment is a further description of step 2 (7) in the autonomous rendezvous control method of a spacecraft under the action of a pulse thrust described in specific embodiment 1, using the MATLAB linear matrix inequality toolbox to formulate 11 to formula 14 are solved to obtain its feasible solution (X 1 , X 2 , Y 1 ).

Embodiment

[0126] Example: Combined Figure 4 to Figure 7 Describe this embodiment, set following technical parameters:

[0127] 1) Target spacecraft mass: 200kg;

[0128] 2) The orbital radius of the target spacecraft: 42241km;

[0129] 3) The average angular velocity of the target spacecraft orbit: 0.001117rad / s;

[0130] 4) The relative state of the two spacecraft at the initial moment: [300,200,0,0,0,0];

[0131] 5) Set the upper limit of pulse thrust to 100N;

[0132] 6) The sampling period of the discrete state equation is, and the pulse period is 100s;

[0133] Based on the MATLAB simulation software, the rendezvous process of the two spacecraft was simulated. The simulation process and results are as follows:

[0134] Control law solution: Utilize MATLAB software linear matrix inequality (LMl) toolbox to solve formula eleven to formula fourteen, obtain following feasible solution:

[0135] X 1 = 10 ...

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Abstract

The invention relates to a method for controlling an autonomous rendezvous between spacecrafts under action of impulse thrust, which belongs to the technical field of aerospace, and aims to solve the problem that a traditional method for controlling the rendezvous between the spacecrafts under the action of the impulse thrust is easy to be influenced by a disturbance moment because of adopting anopen-loop control mode. The method for controlling the autonomous rendezvous between the spacecrafts under the action of the impulse thrust comprises the following steps: establishing a kinetic modelof the relative motion between the spacecrafts, and converting a state space model of the relative motion into a discrete motion model; introducing state feedback control rate in the impulse action process; introducing virtual energy functions for a impulse action motion and a free motion; determining three inequalities meeting the requirement that the spacecrafts realize the autonomous rendezvous, satisfying a finite impulse thrust inequality, and converting the inequalities into linear matrix inequalities related with X1,X2 and Y1; and calculating a state feedback gain matrix K according tothe worked-out X1 and Y1 matrixes to obtain a state feedback sampling control law u(k)=Kx(k) of the relative motion between the spacecrafts, which meets the design requirement. The method for controlling the autonomous rendezvous between the spacecrafts under the action of the impulse thrust is suitable for the autonomous rendezvous process of the spacecrafts.

Description

technical field [0001] The invention relates to a method for controlling the relative position of a spacecraft, in particular to an autonomous rendezvous control method for a spacecraft under the action of a pulse thrust, and belongs to the field of aerospace technology. Background technique [0002] Autonomous spacecraft rendezvous is an important research content in the aerospace field, and it is of great significance to advanced space missions such as on-orbit maintenance, interception, formation flight, and space station establishment of spacecraft. According to the different action forms of the orbit control force, spacecraft orbital maneuvers can be divided into continuous thrust maneuvers and pulsed thrust maneuvers. [0003] For the continuous thrust maneuver mode, the orbit control force acts on the tracking spacecraft in a continuous manner, making it constantly change its motion state and achieve rendezvous with the target spacecraft. This method can keep the tra...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/10
Inventor 杨学博司玉林高会军
Owner HARBIN INST OF TECH
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