Sampling control method for relative motion of spacecrafts

A technology of relative motion and control method, applied in three-dimensional position/track control and other directions, which can solve problems affecting the accuracy and safety of spacecraft orbits

Inactive Publication Date: 2012-02-15
HARBIN INST OF TECH
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Problems solved by technology

[0005] In order to solve the problem that the existing sampling control method of the relative motion of the spacecraft ignores the processing cycle and deviation of ...

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  • Sampling control method for relative motion of spacecrafts
  • Sampling control method for relative motion of spacecrafts
  • Sampling control method for relative motion of spacecrafts

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specific Embodiment approach 1

[0085] Specific embodiment one: the sampling control method of the relative movement of the spacecraft in this embodiment is realized by the following steps:

[0086] Step A, establish the relative motion dynamics model of the spacecraft:

[0087] Assuming that two spacecraft are the tracking spacecraft and the target spacecraft, the target orbit is an approximate circular orbit, and the relative motion coordinate system is established with the target spacecraft as the origin (such as figure 2 shown)

[0088] Take the center of mass of the target spacecraft as the origin o of the coordinate system, the ox axis is located in the orbital plane of the target spacecraft, and the forward direction is the direction of the center of the earth pointing to the spacecraft; the y axis is the running direction of the target spacecraft; the oz axis is perpendicular to the orbital plane and aligned with other The two axes form a right-handed Cartesian coordinate system;

[0089] Let the ...

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Abstract

The invention relates to a sampling control method for a spacecraft, more particularly to a sampling control method for relative motion of spacecrafts. According to the current sampling control method for a spacecraft relative motion, a processing period and a deviation of a digital controller are neglected, so that an accuracy and security of a spacecraft track are influenced; however, the above-mentioned problems can be solved with utilization of the sampling control method provided in the invention. The method comprises the following steps that: step A, a dynamical model on a spacecraft relative motion is established; step B, sampling is carried out on relative states of two spacecrafts; step C, an M matrix and an N matrix are constructed by utilizing an upper boundary line and a lowerboundary line of a sector area described in the step B; step D, a corresponded state feedback control law is obtained; step E, two positive definite symmetric matrixes P and Q are introduced and a following lyapunov function is defined; step F, an intersection process is obtained and is completed, wherein a trust satisfies a formula upper boundary constraint condition (3); and step G, a feasible solution is obtained by utilizing an LMT of MATLAB software. According to the invention, the sampling control method can be applied in design of a spacecraft controller.

Description

technical field [0001] The invention relates to a sampling control method of a spacecraft. Background technique [0002] Continuous thrust control is an important form of orbital maneuver control of spacecraft, and it has been widely used in various spacecraft relative motion tasks such as spacecraft autonomous rendezvous, formation flight, and space station docking. [0003] At present, many orbital maneuver control methods using continuous thrust form are completely based on continuous system model and continuous controller form. However, with the rapid development of computer technology, most of the controllers used in actual engineering are computer systems in the form of digital signals. In this system, the control process needs to use the sampler to sample the relative motion state of the spacecraft at fixed time intervals, the controller digitally processes the sampled signal and generates a corresponding discrete control signal, and the control signal is input throu...

Claims

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Application Information

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IPC IPC(8): G05D1/10
Inventor 杨学博孙光辉高会军
Owner HARBIN INST OF TECH
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