Distributed calculating method for spacecraft dynamics

A distributed computing and spacecraft technology, applied in the direction of instruments, simulators, control/regulation systems, etc., can solve the problems of limited computing power of a single simulation computer, unable to complete multi-spacecraft simulation computing tasks, etc., to improve computing efficiency Effect

Active Publication Date: 2017-10-27
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0004] 1) Due to the different number and types of spacecraft involved in different missions and different formation configurations, the same spacecraft may be repeatedly modeled in different simulation missions, and the dynamic model or simulation calculation structure needs to be redesigned
[0005] 2) Due to the limited computing power of a single simulation computer, when there are many spacecraft that need to be simulated at the same time, it will inevitably lead to the inability to complete the simulation calculation tasks of multiple spacecraft in the same control cycle

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  • Distributed calculating method for spacecraft dynamics

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Embodiment Construction

[0059] A spacecraft dynamics distributed computing method proposed by the invention can be used to complete multi-spacecraft joint simulation.

[0060] In this method, each spacecraft model that needs to be simulated at the same time is first laid out on its own simulation computer.

[0061] Each simulation computer only performs dynamic calculation for one spacecraft, and different simulation computers obtain dynamic data of other spacecraft through data exchange, and then complete the distributed joint calculation of multi-spacecraft dynamics. Such as figure 1 As shown, the dynamic calculation of each simulation computer includes the following steps:

[0062] (1) Power initialization

[0063] Initialize the physical parameters of the spacecraft (referred to as the spacecraft) in its own layout. The physical parameters include mass, moment of inertia, center of mass position, sailboard flexible model, docking port position (only for rendezvous and docking functions), sensor...

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Abstract

The invention discloses a distributed calculating method for spacecraft dynamics, and belongs to the technical field of control and simulation. The method comprises the steps: employing a distributed calculating strategy, enabling the dynamics simulation operation of a plurality of spacecraft to be distributed to different simulation computers, enabling each simulation computer to just carry out the dynamics resolving for one spacecraft, obtaining the dynamics data of other spacecraft through the data exchange among different simulation computers, and completing the combined simulation testing task of the plurality of spacecraft. The method irons out the defects that a conventional centralized-type simulation technology is not sufficient in calculation capability of simulation computers during the centralized simulation of the dynamics of a plurality of objects and needs to carry out the repeated modeling, and improves the simulation calculation efficiency.

Description

technical field [0001] The invention relates to a distributed computing method for spacecraft dynamics, in particular to a distributed computing method for joint simulation of multi-objective dynamics, which belongs to the technical field of control and simulation. Background technique [0002] For the design and verification of the spacecraft GNC system, the spacecraft dynamics simulation is an indispensable link and runs through the whole project. It simulates the space environment of the spacecraft and the orbit and attitude movement of the spacecraft, and provides a mathematical simulation environment for the design of the spacecraft control system. Based on the attitude information and sensor information generated by the dynamics simulation system, the control system calculates the control information and feeds it back to the dynamics simulation system, thereby verifying the effectiveness of the control system. [0003] When the spacecraft is performing ground physics ...

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Application Information

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IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor 李明明蔺玥郎燕乔德治张迎发于丹范松涛蒋金哲
Owner BEIJING INST OF CONTROL ENG
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