Modeling method of space three-body flexible tethered satellite formation system under non-inertial reference coordinate system

A satellite formation and system modeling technology, applied in the field of spacecraft flight, can solve the problems of reducing the accuracy of the model and ignoring the flexibility of the tether

Active Publication Date: 2018-12-14
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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In addition, when discussing the flexible tether, it is often considered as an ideal rigid rod model, ignoring t

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  • Modeling method of space three-body flexible tethered satellite formation system under non-inertial reference coordinate system
  • Modeling method of space three-body flexible tethered satellite formation system under non-inertial reference coordinate system
  • Modeling method of space three-body flexible tethered satellite formation system under non-inertial reference coordinate system

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[0071] The specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0072] Such as figure 1 An in-orbit three-body tethered satellite formation system shown, the system consists of three flexible tethers connecting three satellites S 1 , S 2 and S 3 Composition, the center of mass of the formation system is o.

[0073] Satellite S 1 The mass of is denoted as m 1 ;Satellite S 2 The mass of is denoted as m 2 ;Satellite S 3 The mass of is denoted as m 3 ;Connect to satellite S 1 and S 2 The length of the flexible tether is L 12 , the stiffness is E 12 A 12 , the line density is Connect to Satellite S 2 and S 3 The length of the flexible tether is L 23 , the stiffness is E 23 A 23 , the line density is Connect to Satellite S 1 and S 3 The length of the flexible tether is L 31 , the stiffness is E 31 A 31 , the line density is Three spatially flexible tethers are ...

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Abstract

The invention belongs to the technical field of spacecraft flight, and particularly relates to a modeling method of a space three-body flexible tethered satellite formation system under a non-inertialreference coordinate system. The modeling method comprises the following steps that firstly, a satellite formation system model and a non-inertial reference system fixed to the system centroid are established; secondly, a flexible tether connecting a satellite is discrete into a plurality of tether units, and the satellite and tether unit particles are numbered; and finally, dynamic equations ofdiscrete element particles under the non-inertial reference system are established, and then the dynamic equations of the satellite formation system are derived. According to the modeling method of the space three-body flexible tethered satellite formation system under the non-inertial reference coordinate system, modeling is carried out under the non-inertial reference system, redundant steps such as selecting generalized coordinates and coordinate transformation are not required, and simultaneously flexibility of the space tether is considered, so that the method is faster and more accuratein describing various space dynamic behaviors of a formation system and revealing spin stability and instability states of the system. In addition, the modeling method of the space three-body flexibletethered satellite formation system under the non-inertial reference coordinate system can further be extended to modeling of a four-body or multi-body space tethered formation system and has great practical value.

Description

technical field [0001] The invention relates to the technical field of spacecraft flight, in particular to a modeling method for a space three-body flexible tethered satellite formation system under a non-inertial reference coordinate system. Background technique [0002] As a new type of on-orbit spacecraft, the space tether satellite formation system has the advantages of wide observation range, high mobility, and reusability. Task [1-4] , and the modeling method of the formation system, as the key technical basis for realizing and completing these tasks, is receiving more and more attention from the majority of scientific researchers. [0003] In the developed space tethered satellite formation system modeling method, based on the second type of Lagrangian equation, Qi Rui et al. constructed the dynamic equation of the double pyramidal tethered satellite formation system, and deduced the formula to point out that There is an analytical static equilibrium solution for th...

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Application Information

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IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 余本嵩金栋平文浩耿凌璐
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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