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A Dynamics Modeling Method for Liquid-Filled Flexible Spacecraft Based on Kane Equation

A flexible spacecraft and dynamic modeling technology, which can be used in instruments, complex mathematical operations, geometric CAD, etc., to solve problems such as the inability to handle large-scale shaking dynamics, and achieve the effect of solving the dynamic rigidity of flexible accessories.

Active Publication Date: 2020-10-20
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0003] The purpose of the present invention is to solve the problem that the above-mentioned prior art cannot deal with the large-scale shaking dynamics, and proposes a dynamic modeling method for liquid-filled flexible spacecraft based on the Kane equation

Method used

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  • A Dynamics Modeling Method for Liquid-Filled Flexible Spacecraft Based on Kane Equation
  • A Dynamics Modeling Method for Liquid-Filled Flexible Spacecraft Based on Kane Equation
  • A Dynamics Modeling Method for Liquid-Filled Flexible Spacecraft Based on Kane Equation

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Embodiment 1

[0025] A typical liquid-filled flexible spacecraft with four liquid tanks, two symmetrically installed flexible solar panels and three-axis reaction wheels for attitude control based on the Kane method (see figure 2 ) as an example of the rigid-liquid-flexible-controlled coupled dynamics modeling, figure 2 Among them, the spacecraft includes a main rigid body, three-axis reaction wheels for attitude control, four spherical liquid-filled tanks arranged in parallel, and two symmetrically installed flexible solar panels.

[0026] For the specific implementation process of the method of the present invention, see figure 1 , the specific steps are:

[0027] Step 1. For the motion of each part of the spacecraft system, including the large-scale translation and rotation of the main rigid body platform of the spacecraft, the rotation of the attitude control reaction wheel around its own axis of rotation, the equivalent center of mass of the No. 1 to No. 4 liquid-filled tanks is con...

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Abstract

The invention relates to a liquid-filled flexible spacecraft dynamics modeling method based on a Kane equation, and relates to the field of aerospace science and technology. The method comprises the following steps of 1, selecting a proper generalized rate to describe and express aiming at the motion of each part of a spacecraft system; 2, representing the speed and the angular speed of each partof the system by adopting the generalized speed selected in the step 1; 3, determining the deviation speed and the deflection speed of the system; 4, linearizing the partial velocity and the partial acceleration obtained in the step 3, and further deriving the linearized acceleration and angular acceleration of each part of the system so as to obtain the generalized inertia force of the system; 5,deducing the generalized acting force borne by the system according to the linearized eccentric speed and deflection angle speed obtained in the step 4; and 6, substituting the generalized inertia force and the generalized acting force obtained in the step 4 and the step 5 into the Kane equation, and forming a state vector of the system by all generalized rates to obtain an integrated spacecraftdynamic model.

Description

technical field [0001] The invention relates to a dynamic modeling method for a liquid-filled flexible spacecraft based on the Kane equation, and belongs to the technical field of spacecraft dynamics. Background technique [0002] The existing dynamic modeling research on spacecraft systems with relatively simple structures, such as the flexible spacecraft model, only considers the rigid-flexible coupling dynamics between the vibration of the flexible accessories and the rigid body motion of the spacecraft body, charging The liquid spacecraft model only considers the rigid-liquid coupling dynamics between the small sloshing of the liquid in a single tank and the rigid body motion of the spacecraft main body, which can no longer adapt to the gradual increase of modern spacecraft to large-scale, combined structures and maneuvering tasks. The trend of complex development. On the one hand, the traditional sloshing equivalent mechanical models (such as the spring-mass model and ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20G06F30/15G06F17/11G06F119/14
CPCG06F17/11
Inventor 岳宝增刘峰
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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