Spacecraft low-thrust perturbation rendezvous trajectory optimization method and system

A trajectory optimization, small thrust technology, applied in the field of aerospace navigation control, can solve the problems of decreased efficiency of rendezvous trajectory optimization, increased calculation amount, and increased orbit integral calculation amount.

Active Publication Date: 2020-12-15
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

When optimizing the low-thrust rendezvous trajectory during the space debris removal mission, the influence of the perturbation term must be considered, but the corresponding orbital integral calculation amount is significantly inc

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  • Spacecraft low-thrust perturbation rendezvous trajectory optimization method and system
  • Spacecraft low-thrust perturbation rendezvous trajectory optimization method and system
  • Spacecraft low-thrust perturbation rendezvous trajectory optimization method and system

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Embodiment Construction

[0028] Such as figure 1 Shown is a specific embodiment of a method for fast optimization of a small-thrust perturbation rendezvous trajectory of a spacecraft in the present invention. In this embodiment, the orbital elements of the spacecraft and the target at the reference time are shown in Table 1:

[0029] Table 1 Reference time spacecraft and target orbit elements

[0030]

[0031] The initial mass of the spacecraft is 755.32kg, the thrust is 0.5N, and the specific impulse is 1000s. to be calculated at the relative reference time t 0 = 154.1 days to start orbit transfer, tth f =157.8 days rendezvous, Δt=3.7 days, the optimal control rate of the required small thrust.

[0032] Step 1: Given the spacecraft and the target at the initial time t 0 and the number of orbital elements at the rendezvous moment, at the rendezvous moment is t f , the orbit transfer time is Δt, and the calculated four-pulse velocity increment is Δv 1 ,Δv 2 ,Δv 3 ,Δv 4 , where the first two...

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Abstract

The invention discloses a low-thrust perturbation rendezvous trajectory optimization method and system. The method comprises the steps: giving the number of orbits of a spacecraft and a target at thestart and rendezvous moments, and calculating a four-pulse speed increment; supposing that the low-thrust switching strategy is an on-off-on mode, and estimating two startup durations of low thrust; recalculating a new four-pulse speed increment by taking a small-thrust midpoint moment as an equivalent pulse moment according to the two small-thrust startup durations; until the change of the pulseincrement calculated in the previous and later times is smaller than a preset value, outputting a small-thrust startup time length; inputting the estimated low-thrust startup time length as a constraint into an indirect method optimization model for solving to obtain an optimal control rate, an optimal transfer track and an optimal mass variation; and calculating the increment percentage delta ofthe speed increment and the pulse speed increment corresponding to the optimal control rate, if delta is greater than a threshold value, solving the step 5 again, and if delta is less than the threshold value, outputting the optimal control rate and the transfer track.

Description

technical field [0001] The invention belongs to the technical field of aerospace navigation control, and in particular relates to a method and system for optimizing a spacecraft small-thrust perturbation rendezvous trajectory. Background technique [0002] In low-Earth orbit, the earth's non-spherical gravitational perturbation and atmospheric drag are the most important perturbations. When optimizing the low-thrust rendezvous trajectory during the space debris removal mission, the influence of the perturbation term must be considered, but the corresponding orbital integral calculation amount is significantly increased compared with the two-body analytical dynamic model. Moreover, when the number of transfer circles is large, the amount of calculation will increase significantly, and the efficiency of rendezvous trajectory optimization will decrease. Therefore, it is necessary to find a new intersection trajectory planning method to improve planning efficiency. Contents o...

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Application Information

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IPC IPC(8): G06F30/15G06F30/20G06F111/04G06F119/14
CPCG06F30/15G06F30/20G06F2111/04G06F2119/14Y02T90/00
Inventor 罗亚中黄岸毅李恒年张进杨震严冰
Owner NAT UNIV OF DEFENSE TECH
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