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Adaptative, multiple shooting optimization method for determining optimal spacecraft trajectories

A spacecraft, the optimal technology, applied in space navigation equipment, space navigation aircraft, aircraft and other directions, can solve problems such as low efficiency of known algorithms

Active Publication Date: 2013-01-30
TELEVISION BROADCASTS LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0090] The object of the present invention is to provide a method for determining the optimal transfer trajectory of a spacecraft that allows to solve the problems of the known art described before and to overcome the drawbacks that make the known algorithms inefficient

Method used

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  • Adaptative, multiple shooting optimization method for determining optimal spacecraft trajectories
  • Adaptative, multiple shooting optimization method for determining optimal spacecraft trajectories
  • Adaptative, multiple shooting optimization method for determining optimal spacecraft trajectories

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Embodiment Construction

[0134] The following description is presented to enable any person skilled in the art to make and use the invention. It will be apparent to a person skilled in the art that various modifications can be made to the embodiments without departing from the scope of the present invention as defined in the claims. Thus, the present invention is not intended to be limited to the embodiments shown, but is to be accorded the widest scope consistent with the principles and features disclosed herein and defined in the appended claims.

[0135] Furthermore, the present invention may be implemented by a software program carried in the memory of an electronic processor and comprising software code portions for performing the determination of an optimal transfer trajectory for a spacecraft as described below when the software program is run by the electronic processor Methods.

[0136] The present invention relates to an adaptive, multiple-shot approach, ie, an algorithm, for solving the so...

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Abstract

Disclosed herein is a method for determining a trajectory for a transfer of a spacecraft from a starting space body to a target space body with respect to a given central space body, wherein the determined trajectory is optimal with respect to a given space mission requirement to be met by the transfer of the spacecraft. The method -comprises providing, according to the Pontryagin maximum principle, a physical-mathematical model relating model quantities and physical quantities representing the transfer of the spacecraft with respect to the given central space body.

Description

technical field [0001] The present invention relates to the determination of an optimal spacecraft transfer trajectory (transfer trajectory), and the invention can be used to solve various problems regarding optimal transfer trajectories of spacecraft such as spacecraft, rockets, space shuttles, and the like. [0002] In more detail, the present invention can determine the optimal transfer trajectory within a given period (specific instant, epoch), which can generally meet the requirements of a given space mission, and in particular, the present invention can make the transfer Time, propellant consumption, or a combination thereof are minimized. Background technique [0003] As is well known, the determination of the optimal spacecraft trajectory for a given mission is technically defined as a "two-point boundary problem", which involves the determination of a trajectory, which, among all possible points, connects two distinct points in space ( represents the boundary condi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/00
CPCB64G1/007B64G1/2427
Inventor 安德里亚·博勒克里斯蒂安·奇尔奇吉斯皮·科劳
Owner TELEVISION BROADCASTS LTD
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