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Method for simulating space tether system based on integral interpolation method

A technology of space tethering and simulation methods, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as high algorithm complexity, dependence on system calculation accuracy, and high calculation efficiency

Active Publication Date: 2012-06-27
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

The accuracy of this method is very high, and it can perform fine analysis on the motion of the tether, but the complexity of the algorithm itself is very high, and the calculation efficiency is low; by selecting the global basis function that meets the geometric boundary conditions of the system, the continuous Discrete solution of the system of equations of the form
This method has high calculation efficiency and fast calculation speed, but the calculation accuracy of the system depends on the subjective selection of the basis function

Method used

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  • Method for simulating space tether system based on integral interpolation method
  • Method for simulating space tether system based on integral interpolation method
  • Method for simulating space tether system based on integral interpolation method

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Embodiment Construction

[0085] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0086] (1) Establish a mathematical model of the system:

[0087] For such as figure 1 For the space tether system shown, the motion of the tether can be described as:

[0088]

[0089] In the formula, the total natural length of the tether is L=500m, and the linear density of the tether is ρ=4.524×10 -3 kg / m, the perturbing force on the tether f=0, and

[0090]

[0091] In the formula, the earth's gravitational constant μ e =398600.5km 3 / s 2 , the orbit of the parent spacecraft B is a perfect circle, and the orbit radius R B =6871km, R B =(6.871×10 6 ,0,0) T , ω B = 0.0011085 rad / s.

[0092] For the release point, its motion can be described as:

[0093] r(ξ,t)=0

[0094] For sub-spacecraft A, its motion can be described as:

[0095]

[0096] In the formula, the mass of the sub-spacecraft m A =10kg, the perturbation force F=0 acting on t...

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Abstract

The invention relates to a method for simulating a space tether system based on an integral interpolation method. The longitudinal movement of a tether is described by using a strain epsilon of a tether upper point, the transverse movement of the tether is described by using a tangent vector tau of the tether upper point, and separation solving of epsilon and tau is realized in the model discretization process, so that the defect of morbidity of the system is overcome, and the solving efficiency of the system is improved. The method has the advantages that: description of the tether release and pull-back process is implemented by increasing and decreasing the length of a first section of tether, and the first section of tether is processed according to the characteristic of a flexible rope, so that errors caused by regarding the tether as a rigid rod are avoided; meanwhile, during insertion of a new node, the state of the new node is computed by using an interpolation method, so that simulation noise caused by subjectively setting the state of the new node is avoided.

Description

technical field [0001] The invention relates to a simulation method of a space tether system based on an integral interpolation method. Background technique [0002] The space tether system has a broad application prospect due to its wide range of action and flexible characteristics. At present, it has become one of the key areas of space technology development in various aerospace powers. In the research and application of the space tether system, the research on the numerical simulation algorithm of the system is a basic and very important work, but due to the existence of the flexible tether, the system has obvious pathological characteristics, and the system is in motion. The length, position and shape of the tether will change greatly during the process, which is very different from the rigid body and flexible body studied in solid mechanics, and the method of solving them is also very different. [0003] For the simulation of the space tether system, there are mainly ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 黄攀峰胡仄虹孟中杰刘正雄
Owner NORTHWESTERN POLYTECHNICAL UNIV
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