Dynamics modeling method for obtaining antenna on-track vibration influence

A technology of dynamic modeling and vibration influence, applied in simulators, instruments, control/regulation systems, etc., can solve the problems of lack of modeling and simulation, and achieve the effect of effective separation

Active Publication Date: 2016-08-10
BEIJING INST OF SPACECRAFT SYST ENG
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the current model development process, there is still a lack of modeling, simulation, and analysis methods at the entire satellite level. For the transmission mechanism of the entire satellite’s on-orbit vibration and the impact of on-orbit vibration o

Method used

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  • Dynamics modeling method for obtaining antenna on-track vibration influence
  • Dynamics modeling method for obtaining antenna on-track vibration influence
  • Dynamics modeling method for obtaining antenna on-track vibration influence

Examples

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Example Embodiment

[0083] Embodiment 1. A dynamic modeling method for obtaining the influence of antenna on-orbit vibration, such as figure 1 As shown, including the following steps:

[0084] Step (1) Take the loop antenna in the shaping system and the deployment arm used to support the loop antenna as substructures, and establish the rigid-flexible coupling dynamics equations of the entire star system, including the translational motion equation of the center of mass of the entire star system and the system around the center of mass Rotational motion equation of, the vibration equation of the unfolded arm with rigid loop antenna, the vibration equation of the loop antenna itself, the vibration equation of the +Y axis and -Y axis solar wing, where the Y axis is the center of mass of the system established with the center of mass of the entire star as the origin The Y axis of the coordinate system.

[0085] The rigid-flexible coupled dynamic equations of the entire star system specifically include:

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Abstract

The invention discloses a dynamics modeling method for obtaining antenna on-track vibration influence. The dynamics modeling method includes the steps of taking annular antennas and all expanded arms for supporting the annular antennas in a whole-spacecraft system as substructures, establishing rigid-flexible coupling dynamic equation set for the whole-spacecraft system, calculating the modality coordinate array of the expanded arms with the annular antennas and the modality coordinate array of the annular antennas, establishing an attitude control model to simulate attitude control for the whole-spacecraft system, and calculating the annular antenna vibration response according to the attitude control simulation result. The annular antenna vibration response includes integral involved position change, of the expanded arms with the annular antennas, supposing with the self position change of the annular antennas, wherein the integral involved position change of the expanded arms with the annular antennas is solved by the modality coordinate array of the expanded arms with the annular antennas, and the self position change of the annular antennas is solved by the modality coordinate array of the annular antennas. The invention belongs to the technical field of antenna on-track vibration.

Description

technical field [0001] The invention belongs to the technical field of antenna on-orbit vibration, and in particular relates to a dynamic modeling method for obtaining the influence of antenna on-orbit vibration. Background technique [0002] With the development of my country's aerospace industry and the urgent need of national defense construction, my country is developing a series of new spacecraft such as new electronic reconnaissance satellites, communication satellites and earth observation systems with large antennas. The large flexible and deployable antennas of these spacecraft present typical complex dynamic characteristics such as large flexibility, light weight, weak damping, and nonlinearity, which bring a series of dynamic and control problems to this type of spacecraft. In the future, more and more large-scale deployable antennas will be used on spacecraft, with larger apertures and stricter indicators. Mechanical movements caused by satellite attitude and orb...

Claims

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Application Information

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IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor 葛东明邹元杰刘绍奎史纪鑫邓润然
Owner BEIJING INST OF SPACECRAFT SYST ENG
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