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Integrated test simulation system for spacecraft attitude control algorithm

A simulation system and spacecraft technology, applied in the field of spacecraft attitude simulation system, can solve the problems of high cost, limited modular intervention support of control algorithms, limited authenticity and integrity, etc.

Inactive Publication Date: 2015-09-09
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0011] The purpose of the present invention is to propose an integrated test for spacecraft attitude control algorithm in order to solve the problems of limited authenticity and integrity, high cost and limited support for modular intervention of control algorithm in the existing test simulation platform. Simulation System

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Embodiment Construction

[0042] The technical solution of the present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0043] The integrated test emulation system that the present invention proposes for spacecraft attitude control algorithm adopts two kinds of development tools of Matlab-Simulink and C++ to realize, provides the software model of two kinds of versions, wherein Matlab version model uses Simulink tool to build sub-model object, system structure It has a certain degree of visibility; the C++ version model uses the code conversion function provided by Matlab software to convert the Matlab model into a standard C++ program on the x86 / x64 platform, and encapsulates the model as an object, providing a standardized controller programming interface and external The data interface is for users to use.

[0044] The structure of the integrated test simulation system for the spacecraft attitude control algorithm is as follows: f...

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Abstract

The invention relates to an integrated test simulation system for a spacecraft attitude control algorithm and belongs to the computer simulation technology and application technical field. The integrated test simulation system includes a controller, a measurement model, an actuator model, a spacecraft attitude dynamic model, an antenna model, a sailboard model and a load model, wherein the controller includes a mode management module, a path optimization module, a closed loop control module and an accessory monitoring module. According to the system of the invention, the components of the system are configured based on a universal satellite platform; modeling is performed on system equipment related to typical attitude control and dynamic characteristics; and a simulation on-orbit simulation environment supporting modularized applications can be provided for the control algorithm; near-earth orbit satellite mission modes are preset in the mode management module, and a user can select one kind of near-earth orbit satellite mission mode to fast establish a simulation scene, and test data is of practical significance; the path optimization module provides a function for planning paths of spacecraft attitude maneuver, and therefore, the performance of a closed-loop control mechanism can be improved.

Description

technical field [0001] The invention relates to a spacecraft attitude simulation system applied to control algorithm integration testing, which belongs to the field of computer simulation technology and application. Background technique [0002] Modern spacecraft have diverse functions and complex structures. Aerospace engineering projects are characterized by high investment and high risk. Cost is the key factor limiting the application of innovative ideas and new technologies. Sufficient technical pre-research, risk assessment, and a large number of ground simulations and tests are necessary preparatory steps before satellites enter orbit. [0003] Establishing the correct state is a necessary prerequisite for the spacecraft to perform on-orbit tasks. The performance of the attitude control system directly determines the mission quality and completion efficiency of the satellite. The attitude control system is one of the most complex subsystems of modern spacecraft. [00...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
CPCG05B23/0202
Inventor 李震辛星刘向东刘胜利路平立
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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