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Spacecraft optimal Lambert orbit rendezvous method based on multi-objective optimization algorithm

A multi-objective optimization and track rendezvous technology, applied in design optimization/simulation, instrumentation, adaptive control, etc., can solve the problem that fuel consumption and time consumption cannot be optimal at the same time, and achieve good convergence and good uniform distribution Effect

Inactive Publication Date: 2020-05-01
HARBIN INST OF TECH
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  • Abstract
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  • Application Information

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Problems solved by technology

[0008] The present invention aims to solve the problem that the fuel consumption and time consumption cannot be optimal at the same time in the existing optimal Lambert orbit rendezvous method for spacecraft

Method used

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  • Spacecraft optimal Lambert orbit rendezvous method based on multi-objective optimization algorithm
  • Spacecraft optimal Lambert orbit rendezvous method based on multi-objective optimization algorithm
  • Spacecraft optimal Lambert orbit rendezvous method based on multi-objective optimization algorithm

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specific Embodiment approach 1

[0033] This embodiment is a method for spacecraft optimal Lambert orbit rendezvous based on a multi-objective optimization algorithm. Before describing this embodiment, first, the spacecraft optimal Lambert orbit rendezvous will be described:

[0034] The pulse thrust Lambert rendezvous is as follows:

[0035] (1), Time-open double pulse rendezvous

[0036] Such as figure 1 As shown, at the initial moment, the tracking spacecraft is in the initial orbit P cI At , the target spacecraft is in the target orbit P tI place. The tracking spacecraft first resides in the initial orbit for a period of time Δt 1 , reaching P cT at (corresponding position vector r 1 ) to apply the first pulse ΔV to the tracking spacecraft 1 Enter the transfer orbit, and run Δt on the transfer orbit f After reaching P R point (corresponding to position vector r 2 ). At the same time, the target spacecraft moves Δt on the target orbit 2 =Δt 1 +Δt f After time, from P tI Movement to P R poin...

Embodiment

[0159] The feasibility verification of the multi-objective optimization algorithm is carried out through the following examples.

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Abstract

The invention discloses a spacecraft optimal Lambert orbit rendezvous method based on a multi-objective optimization algorithm, and belongs to the technical field of spacecraft orbit rendezvous. The invention aims to solve the problem that the fuel consumption and the time consumption of the existing spacecraft optimal Lambert orbital rendezvous method cannot be optimal at the same time. The method comprises the following steps: determining a Lagrange representation form of a Lambert problem corresponding to pulse thrust Lambert intersection according to a spacecraft, and calculating transferorbit parameters of different-plane Lambert intersection to obtain performance indexes of fuel consumption and intersection time of the Lambert intersection; and optimizing through an optimization algorithm to obtain a comprehensively optimal motion trail of the fuel consumption and the rendezvous time. The method is mainly used for spacecraft optimal Lambert orbital intersection design and control.

Description

technical field [0001] The invention relates to a method for spacecraft optimal Lambert orbit rendezvous. The invention belongs to the technical field of spacecraft orbital rendezvous. Background technique [0002] With the rapid development of space technology, space on-orbit tasks such as non-cooperative target capture, space station docking, on-orbit maintenance, and space object tracking and observation have attracted the attention of many space powers. As a key link in the completion of on-orbit missions, the fuel consumption and time consumption of long-range long-distance orbit transfers have a great impact on the life of the spacecraft and the efficiency of on-orbit missions. Therefore, designing the optimal transfer orbit for spacecraft long-distance rendezvous has become one of the research focuses of space on-orbit missions. [0003] Impulse thrust can quickly change the speed, and has been widely used in orbital rendezvous tasks. At the same time, many scholars...

Claims

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Application Information

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IPC IPC(8): G06F30/20G05B13/04
CPCG05B13/041
Inventor 宋申民武冠群张禹琛
Owner HARBIN INST OF TECH
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