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Interplanetary continuous thrust transfer orbit evaluating method

A technology for transferring orbit and thrust, which is applied in the aerospace field, can solve the problems of poor applicability and low calculation efficiency, and achieve the effects of wide application range, improved evaluation efficiency, and avoiding the numerical optimization process

Inactive Publication Date: 2018-03-27
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0005] In order to solve the problems of low calculation efficiency and poor applicability of the existing interplanetary continuous thrust transfer orbit performance evaluation method, the present invention proposes an interplanetary continuous thrust transfer orbit evaluation method

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Embodiment Construction

[0019] The following will take the evaluation of the interplanetary continuous thrust transfer orbit of the probe starting from the earth as an example, and the embodiments of the present invention will be described in detail with reference to the accompanying drawings.

[0020] An interplanetary continuous thrust transfer orbit evaluation method of the present invention, and the specific steps of the embodiment are as follows:

[0021] Step 1. Establish a continuous thrust transfer orbit optimization model

[0022] For the problem that the probe is transferred from the earth to the target star A and realizes the rendezvous with the star A under the action of continuous thrust, an optimization model of the continuous thrust transfer orbit is established. Let U(t) be the continuous thrust control law in the transfer process, in this embodiment, the optimization parameters of the transfer orbit optimization model are

[0023] Z=[E 0 ,E A ,U(t)]

[0024] of which: E 0 is the...

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Abstract

The invention provides an interplanetary continuous thrust transfer orbit evaluating method. The problem that an existing interplanetary continuous thrust transfer orbit performance evaluating methodis low in calculation efficiency and poor in applicability is solved. The interplanetary continuous thrust transfer orbit evaluating method includes the following steps that a continuous thrust transfer orbit optimization model is set up; the optimal transfer orbit sample data is generated; a statistic mapping model of the optimal transfer orbit performance parameters is constructed; the transferorbit performance parameters are evaluated.

Description

technical field [0001] The invention relates to an interplanetary continuous thrust transfer orbit evaluation method, which is suitable for rapid evaluation of the interplanetary continuous thrust transfer orbit, and belongs to the technical field of aerospace. Background technique [0002] Continuous propulsion systems such as plasma electric propulsion can effectively improve the efficiency of propellant use and reduce the fuel consumption required in the process of detector transfer, and have been widely used in deep space exploration missions. However, the solution is difficult due to the complex dynamics of the continuous thrust transfer orbit. At present, the performance evaluation of continuous thrust transfer orbits mainly relies on tedious numerical optimization, which requires a large amount of calculation and a long evaluation time. In the initial design stage of deep space exploration missions, it is usually necessary to evaluate and analyze the performance of a...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/18G06K9/62
CPCG06F17/18G06F18/213G06F18/214
Inventor 尚海滨许铃健乔栋喻志桐秦啸
Owner BEIJING INSTITUTE OF TECHNOLOGYGY