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A Method for Estimating the Tension Direction of a Tethered Satellite

A technology for tethered satellites and direction estimation, applied in calculation, design optimization/simulation, special data processing applications, etc., can solve the problems of complex and large errors in three-axis tension sensors

Active Publication Date: 2018-01-16
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, due to the complexity of the three-axis tension sensor, it also has high requirements for supporting hardware and software, and there are often large errors

Method used

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  • A Method for Estimating the Tension Direction of a Tethered Satellite
  • A Method for Estimating the Tension Direction of a Tethered Satellite
  • A Method for Estimating the Tension Direction of a Tethered Satellite

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Embodiment Construction

[0061] The present invention provides a method for estimating the tension direction of a tethered satellite. In order to make the purpose, technical solution and effect of the present invention clearer and clearer, the present invention is further described in detail with reference to the accompanying drawings and examples. It should be pointed out that the specific implementations described here are only used to explain the present invention, not to limit the present invention.

[0062] like figure 1 As shown, the method of the present invention is specifically as follows: first determine the reference coordinate system and known physical quantities; estimate the moment acting on the satellite based on the disturbance observer Decompose the pulling force F acting on the satellite into the direction along r (tether radial direction) and the direction perpendicular to r; use the definition of moment to solve the component force in the direction perpendicular to r Use the Pyth...

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Abstract

The invention discloses a pull direction estimation method for a tethered satellite. The method specifically comprises the steps of 1, determining a reference coordinate system and a known physical quantity; 2, acquiring an estimated value, FORMULA, of torque by observing based on a disturbance observer; 3, decomposing a pull force F acting on the satellite to be along a r direction, namely radial direction of a tether, and a direction perpendicular to the radial direction r of the tether, and determining a component force Fr along the radial direction of the tether and a component force, FORMULA, along the direction perpendicular to the radial direction of the tether; and 4, determining the direction of the pull force F by using the components forces Fr and FORMULA. Compared with traditional methods, the method has far lower requirements on hardware and software, and is also greatly reduced in estimation error in the premise of high enough computation accuracy and accurate enough disturbance observer model.

Description

technical field [0001] The invention belongs to the technical field of spacecraft measurement and control, and specifically refers to a method for estimating the pulling force direction of a tethered satellite, which can be used for estimating and controlling tether swing angles in a tethered satellite system. Background technique [0002] A tethered satellite system refers to a combination of two or more artificial satellites flying together by means of flexible tethers. Since the concept of the tethered satellite system was proposed, it has been paid attention to and studied by many scientific and technological workers because of its unique structure and properties. Data show that tethered satellites are used for microgravity generation, satellite attitude stabilization, spacecraft reentry, tether rendezvous and capture, spacecraft launch and orbit transfer, space debris removal, earth observation and deep space exploration, etc. occasion. In order to ensure the normal o...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 文浩韦正涛金栋平
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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