Simulation method applicable to space tethered system of stratospheric satellite system

A satellite system and space tether technology, applied in the field of simulation, can solve the problems that cannot reflect the real situation of the system movement, complexity, interference, etc.

Inactive Publication Date: 2014-08-13
NORTHWESTERN POLYTECHNICAL UNIV
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  • Application Information

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Problems solved by technology

[0003] The motion process of the space tether of the stratospheric satellite system is a complex dynamic problem, and inappropriate tether modeling and simulation methods will cause large errors in the tether motion process
At present, for the stratospheric satellite system, the tether is generally considered simply as a light rigid body in a straight line state. remains unchanged, but this modeling method ignores the influence of gravity and flexibility of the system, which will cause the simulation results to seriously devia...

Method used

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  • Simulation method applicable to space tethered system of stratospheric satellite system
  • Simulation method applicable to space tethered system of stratospheric satellite system
  • Simulation method applicable to space tethered system of stratospheric satellite system

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Embodiment

[0061] 1. Tether discrete segments

[0062] For such as figure 1 The stratospheric satellite system shown is composed of a superpressure balloon, a tether and a pneumatic sail. The superpressure balloon and the pneumatic sail are connected by the tether, and the control force generated by the pneumatic sail is transmitted to the superpressure balloon through the tether. The control system Run along the predetermined track. Such as figure 2 As shown, the tether is divided into 30 segments of the same length on average, that is, n=30, and the segment near the end of the aerodynamic sail is numbered 1, and the segment near the top balloon is numbered n; correspondingly, n+1 nodes are obtained , the connection between rope segment 1 and the pneumatic sail is node 0, and the connection between rope segment n and the balloon is node n. The tether of each segment is regarded as a rigid rod, the center of mass is located at its geometric center, and the upper and lower tether tens...

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Abstract

The invention provides a simulation method applicable to a space tethered system of a stratospheric satellite system. The method comprises the steps of averagely dividing a tether to be a plurality of sections with the same length, building a mathematic model for the stratospheric satellite system, deriving a node constraint equation and solving a second derivative according to the position relationship between a node and each section of the tether, and performing integral solution on the equation by using a fourth-order Runge-Kutta method, so as to finish a simulation task for the tethered system of the stratospheric satellite system. According to the simulation method provided by the invention, with a view to the gravity and softness of the space tethered system, the accuracy and effectiveness for transferring the magnitude and direction of the control force by the space tethered system can guaranteed.

Description

technical field [0001] The invention relates to a simulation method, in particular to a simulation of stratospheric satellites. Background technique [0002] Stratospheric satellites operate in the 20-35km stratosphere, and carry different payloads to complete tasks such as data communication, ground observation, and battlefield monitoring. Stratospheric satellites are based on traditional high-altitude balloons, using space tethers to connect the superpressure balloons at the top and the aerodynamic sails at the end to form a stratospheric satellite system consisting of "superpressure balloons + space tethers + aerodynamic sails". The pneumatic sail realizes the trajectory control of the system, so that the system moves around the earth along a specific orbit in the stratosphere. [0003] The motion process of the space tether of the stratospheric satellite system is a complex dynamic problem, and inappropriate tether modeling and simulation methods will cause large errors...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCY02A90/10
Inventor 刘涛李旺乾闫斌斌于云峰符文星常晓飞
Owner NORTHWESTERN POLYTECHNICAL UNIV
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