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Method for rapidly designing and optimizing low-thrust transfer orbit

A technology for transferring orbits and optimizing methods, applied in the field of deep space exploration, can solve problems such as large amount of calculation, cumbersome solution, low precision, etc., and achieves the effect of reducing calculation time and convenient and simple operation.

Inactive Publication Date: 2013-07-31
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
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  • Application Information

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Problems solved by technology

[0003] The technical problem to be solved by the present invention is to overcome the deficiencies of the existing technology, aiming at the problems of cumbersome design and optimization technology for small thrust orbits, large amount of calculation and low precision, and proposes a rapid design and optimization method for small thrust transfer orbits

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  • Method for rapidly designing and optimizing low-thrust transfer orbit
  • Method for rapidly designing and optimizing low-thrust transfer orbit
  • Method for rapidly designing and optimizing low-thrust transfer orbit

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Embodiment

[0086] Example background: Taking the design of the fuel consumption-optimal low-thrust rendezvous orbit of the near-Earth asteroid Apophis as an example, set the launch window of the probe between January 1, 2016 and January 1, 2018, and the flight time should not exceed 800 Today, the thrust model adopts the solar electric propulsion model. The performance parameters of the solar electric propulsion engine are as follows:

[0087] Input power: P 0 =6.5kw

[0088] Working specific impulse: I sP =3000s

[0089] Work efficiency: η=0.65

[0090] Initial mass of aircraft: m 0 =1200kg

[0091] Computing platform: MATLAB (2009a)

[0092] Implementation steps:

[0093] Step A, describe the design and optimization problem of the small-thrust transfer orbit as an optimal control problem

[0094] Based on the space motion equation of the low-thrust spacecraft, the optimization design problem of the low-thrust rendezvous orbit of the near-Earth asteroid Apophis is expressed as ...

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Abstract

The invention discloses a method for rapidly designing and optimizing a low-thrust transfer orbit. The method comprises the steps as follows: an inverse sextic polynomial method is introduced as an initial design, a high-performance optimal parameter initial value is provided for follow-up accurate optimization, and the calculating time of an entire optimizing process is reduced; a Radau legendre pseudospectral method is adopted to parameterize a low-thrust transfer orbit optimization problem into a nonlinear programming problem, not only is the number of the optimization parameters reduced, but also the accuracy of an optimization result is improved; and tedious first-order optimal necessary conditions are not needed to be deduced, even though the low-thrust transfer orbit containing various complicated constrains are processed, the operation is also convenient and simple. The method for rapidly designing and optimizing the low-thrust transfer orbit has an extremely important application value in the field of the design and optimization of transfer orbits of low-thrust propulsion spacecraft such as solar sail propulsion, solar energy electric propulsion, and the like.

Description

technical field [0001] The invention belongs to the technical field of deep space exploration, and in particular relates to a method for quickly designing and optimizing a small-thrust transfer orbit. Background technique [0002] Orbit design and optimization is one of the key issues that must be solved for human beings to carry out deep space exploration activities. Low-thrust orbit design and optimization methods are mainly divided into indirect method, direct method and hybrid method. The traditional indirect method needs to derive cumbersome first-order optimal necessary conditions and guess the initial value of the costate variable without actual physical meaning, and the convergence region of this method is very narrow, and the sensitivity to the initial value is high. Therefore, the operation of the indirect method is more difficult. The traditional hybrid method also needs to derive cumbersome first-order optimal necessary conditions. In particular, when constrai...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 李爽朱永生王宇凯江秀强
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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