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On-orbit dynamic load design method for flexible battery wing with pretensioning action mode

A flexible battery and design method technology, applied in the direction of software simulation/interpretation/simulation, program control device, etc., can solve the problems such as the fundamental frequency of the whole wing cannot be improved significantly, the static and dynamic buckling of the main extension mechanism, etc., to shorten the work Cycle time, improve design accuracy, and improve the effect of design reliability

Active Publication Date: 2014-07-16
SHANGHAI AEROSPACE SYST ENG INST
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Problems solved by technology

The dynamic load design method also needs to solve the problem of the structural layout of the tensioning ropes in the whole wing and the size control of the tension force generated. force will cause static and dynamic buckling problems in the main extension mechanism

Method used

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  • On-orbit dynamic load design method for flexible battery wing with pretensioning action mode
  • On-orbit dynamic load design method for flexible battery wing with pretensioning action mode
  • On-orbit dynamic load design method for flexible battery wing with pretensioning action mode

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Embodiment Construction

[0016] The following will combine Figure 1 ~ Figure 2 A further detailed description will be made on the design method for the on-orbit dynamic load of the membrane-type flexible battery wing with pretensioning effect of the present invention.

[0017] The method for designing the on-orbit dynamic load of a membrane-type flexible battery wing with pretensioning in this embodiment includes the following steps:

[0018] Step 1, establish a battery wing model with membrane flexibility and no additional tension;

[0019] In this embodiment, the NASTRAN software is used to establish the battery wing model, such as figure 1 As shown, the battery wing model includes the battery wing front 1, the main stretching mechanism 2, the displacement mechanism 3, the storage box 4 and the tensioning mechanism 5, each tensioning mechanism 5 is connected to the battery wing front 1 by a rope, The battery wing model established in step 1 has no rope effect added;

[0020] Step 2, establish a ...

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Abstract

The on-orbit dynamic load design method of membrane-type flexible battery wings with pre-tensioning effect of the present invention takes into account the tension force effect of large-area membrane-type flexible solar battery wings, and calculates according to the flexibility matrix algorithm that each tension mechanism rope exerts The tension force of the battery wing has realized the update of the stiffness matrix of the battery wing array under the action of the tension force. According to the rigid-flexible coupling dynamics, the simulation model of the spacecraft on-orbit dynamic system has been established, and the dynamic load design of each component of the flexible battery wing has been solved. problems, and the corresponding product design closed loop can be completed according to the dynamic load design. The on-orbit dynamic load design method of the membrane-type flexible battery wing with pretensioning effect of the present invention makes the on-orbit dynamic load design of the flexible battery wing more systematic and precise.

Description

technical field [0001] The invention relates to the design of battery wing loads in the field of manned spaceflight engineering, in particular to a design method for on-orbit dynamic loads of membrane-type flexible battery wings with pretensioning, covering the conventional rigid and semi-rigid battery wing dynamic load design methods. Background technique [0002] The spacecraft battery wing system is the source of electrical energy to maintain the normal operation of the system platform and various payloads. Ensuring the normal operation of the battery wing system under complex orbital conditions is one of the key factors for the stable operation of the spacecraft system. Therefore, the load design of the battery wing system Work is particularly important as the input condition of the whole wing structure design. [0003] Traditional rigid and semi-rigid battery wings are deployed in orbit to a stable locked state, and there is no pre-tensioning effect on the front of the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F9/455
Inventor 郭其威唐国安吕榕新
Owner SHANGHAI AEROSPACE SYST ENG INST
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