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A Tether Swing Suppression Method Utilizing the Maneuvering of a Towed Aircraft in a Towed Orbit Change

A technology of aircraft and tethers, which is applied in the direction of attitude control, etc., can solve the problems of target star attitude stability conflicts, tethers cannot be quickly released, etc., to avoid the problem of quick release, avoid tether tension conflicts, and avoid quick release effects

Inactive Publication Date: 2019-10-18
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

The patent with the publication number 201610323425.5 "Using Tether Thrusters to Jointly Take Over Control Method of Space Non-cooperative Target Attitude" and "Space Tether Mechanism with Rigid Arm" published in the 4th issue of "Science in China: Physics, Mechanics and Astronomy" in 2013 Bias Control" respectively gives a new method of using tether tension to assist in controlling the attitude of the target star; in terms of tether attitude maintenance, the article "Stability and control of tethered satellite with chemical propulsion in Nonlinear Dynamics" published in August 2013 Orbital plane" and the article "A space tethered towing method using tension and platform thrusts" published in "Advances in Space Research" in October 2016 respectively give two methods to use the tether control force to simultaneously control the tether length and stabilize the tether swing. method, but the above two methods assume that the tether can be retracted as required, however, due to the semi-elastic nature of the tether, the tether cannot provide outward thrust like a rod, which may cause the tether to fail in many cases quick release
In addition, the above two methods of using the tether control force to retract and release the tether to stabilize the swing of the tether may conflict with the attitude stabilization requirements of the target star

Method used

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  • A Tether Swing Suppression Method Utilizing the Maneuvering of a Towed Aircraft in a Towed Orbit Change
  • A Tether Swing Suppression Method Utilizing the Maneuvering of a Towed Aircraft in a Towed Orbit Change
  • A Tether Swing Suppression Method Utilizing the Maneuvering of a Towed Aircraft in a Towed Orbit Change

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Embodiment Construction

[0033] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0034] In order to achieve the above object, the technical solution adopted in the present invention comprises the following steps:

[0035] Step 1: Establish a dynamic model of orbit change by tether dragging

[0036] Assumptions: 1. Since the tether is always in a tight state during the thrust orbit change section, the elasticity and flexibility of the tether are ignored;

[0037] 2. Since the out-of-plane swing and in-plane swing of the tether can be decoupled, the out-of-plane swing of the tether is ignored

[0038] 3. Ignore the volume of the towing vehicle and the target star, and assume that the dragging orbit change is an in-plane orbit change

[0039] The schematic diagram of dragging the track and the definition of the coordinate system are attached figure 1 shown. 1 is the towed aircraft, 2 is the space tether, 3 is the target star, 4 is the earth,...

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Abstract

The invention relates to a tethered swing suppression method using towing aircraft maneuvering in towing orbital transfer. Orbit control force of a towing aircraft is used and the orbit of the towing aircraft is also controlled and tethered swing is suppressed so that the problem of quick releasing of the tether can be avoided without using tethered control force, the conflict with the requirement of target satellite attitude stable control can be avoided, and the practicality is great. Compared with the similar technologies at home and abroad, the method has the following positive effects that additional arrangement of a thruster at the end of the target satellite can be avoided, tethered swing is suppressed by using the thruster and the complexity of the system can be reduced; the requirement of quick retreating and releasing of the tether can be avoided, the requirement for a tether retreating and releasing device can be reduced and the problem of quick releasing of the space tether can be avoided; and the tether tension conflict with the situation of using tether tension to stabilize the target satellite attitude can be avoided, and the design difficulty of the controller can be reduced.

Description

technical field [0001] The invention belongs to the field of maneuvering orbit change of a tethered spacecraft, and relates to a tether swing suppression method using a towed aircraft maneuvering in a towed orbit change, and in particular to a tether that utilizes a towed aircraft maneuvering during a tether-based orbit change process swing suppression method. Background technique [0002] With the rapid development of the aerospace industry, a large number of space debris and abandoned satellites are flooding the orbit, and orbital resources are becoming increasingly tight, and have begun to affect the safety of space facilities such as space satellites and space stations. The task of removing orbital garbage such as abandoned satellites is imminent. The non-cooperative and unstable characteristics of abandoned satellites make it very difficult for manipulator-type space robots to capture and assist removal. The use of space tethered robots to drag and change the target is...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
Inventor 孟中杰邓远旺王秉亨黄攀峰张夷斋刘正雄张帆
Owner NORTHWESTERN POLYTECHNICAL UNIV
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