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A control method for stable retraction and release of space vehicle ropes

A technology for a space vehicle and a control method, which is applied in the field of aircraft control and can solve problems such as increasing the difficulty of operation technology and system uncertainty.

Active Publication Date: 2015-07-29
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0011] But this will greatly increase the technical difficulty of the operation and the uncertainty of the system, and at the same time put forward more stringent requirements for space energy

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  • A control method for stable retraction and release of space vehicle ropes
  • A control method for stable retraction and release of space vehicle ropes
  • A control method for stable retraction and release of space vehicle ropes

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Embodiment

[0059] Based on the speed control of the rope retraction proposed in this patent, a set of parameters is taken to carry out numerical simulation on the release of the spacecraft rope. Assume that the system operates on a Kepler elliptical orbit with eccentricity e=0.05, and the initial true anomaly angle ν 0 = 0; at the initial moment, the system has a perturbed pitch angle θ 0 =0.04, dimensionless rope length ξ 0 =0.01; at the same time, according to the condition of rope asymptotically stable release, the desired pitch angle θ can be taken e =-0.04.

[0060] The numerical simulation results of the embodiment are shown in Fig. 2(a) and Fig. 2(b). Figure 2(a) shows the release trajectory of the rope under the orbital coordinate system o-χη (that is, the origin o is fixed at the center of mass of the aircraft, the x-axis points to the opposite direction of the movement of the center of mass of the system, and the axis η points from the center of mass of the earth to the cent...

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Abstract

The invention discloses a method of controlling stable collecting and releasing of a spacecraft rope. The method comprises the steps of first setting an expected pitch angle meeting value requirements; and then realizing stable releasing / collecting processes through rope collecting and releasing speed control. The method overcomes the defect that in a traditional control method the rope produces a big swing range and a large swing angle speed so as to cause damage to precise instruments inside a detector easily.

Description

technical field [0001] The invention belongs to the field of aircraft control, and more specifically relates to a method for stably retracting and releasing a space vehicle rope. Background technique [0002] In space exploration, small satellite sampling, space formation flight and other new space missions, one or more space vehicles need to be released with ropes, and recovered after the mission is completed. Stable and safe release and recovery of spacecraft via tethers is key to the success of this type of space mission. Various control methods have been proposed. For example, optimal control: to ensure that the detector is retracted to the designated position with the optimal trajectory or time, the references are as follows: [0003] [1] Jin DP, Hu HY. Optimal control of a tethered subsatellite of three degrees of freedom. Nonlinear Dynamics, 2006, 46(1~2): 161~178. [0004] [2] Williams P. Deployment / retrieval optimization for flexible tethered satellite systems. N...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/10G05B13/04
Inventor 余本嵩金栋平
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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