Carrier rocket task planning method for rapid spacecraft rendezvous

A technology for launch vehicles and mission planning, which is applied in the aerospace field and can solve problems such as long launch intervals

Active Publication Date: 2021-01-05
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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  • Abstract
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  • Application Information

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Problems solved by technology

[0004] The embodiment of the present invention provides a launch vehicle mission planning method for rapid rendezvous of spacecraft to solve the problem that in the related art, the time interval betw...

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  • Carrier rocket task planning method for rapid spacecraft rendezvous
  • Carrier rocket task planning method for rapid spacecraft rendezvous
  • Carrier rocket task planning method for rapid spacecraft rendezvous

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Embodiment Construction

[0040] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0041] The embodiment of the present invention provides a launch vehicle mission planning method for rapid rendezvous of spacecraft, which can solve the problem that in the prior art, the time interval between two adjacent launches of the launch vehicle is relatively long, and the target spacecraft needs to be adjusted in advance to achieve or...

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Abstract

The invention discloses a carrier rocket task planning method for rapid spacecraft rendezvous, and relates to the technical field of aerospace. The method comprises the following steps of S1, determining a longitude adjustment value of geographic longitudes of ascending nodes of a tracking spacecraft according to a propellant reserved by a carrier rocket; S2, calculating a geographic longitude interval in which the tracking spacecraft can rendezvous with a target spacecraft after the tracking spacecraft enters an orbit according to the longitude adjustment value and a plurality of selectable launching sites of the carrier rocket; S3, determining the geographic longitudes of the theoretical ascending nodes and a selected launching site of the carrier rocket according to the geographic longitude interval and the geographic longitudes of the ascending nodes of all circles of the target spacecraft orbiting the earth in one day; S4, calculating theoretical launching time according to the selected launching site and the geographic longitudes of the theoretical ascending nodes; and S5, launching the carrier rocket at the selected launching site and the theoretical launching time to enablethe tracking spacecraft to enter a rendezvous orbit. According to the carrier rocket task planning method, at least one launching moment can be ensured in one day, so that the tracking spacecraft canrendezvous with the target spacecraft rapidly.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a launch vehicle mission planning method for rapid rendezvous of spacecraft. Background technique [0002] With the development of aerospace technology, the rendezvous technology between tracking spacecraft and target spacecraft has become relatively mature. At present, the demand for space emergency rescue and cargo transportation tasks in emergency situations is becoming more and more urgent. Therefore, the construction of my country's space emergency system is of vital significance to my country's promotion of the construction of space stations, the protection of the safety of astronauts, and the steady advancement of my country's space exploration and the construction of an aerospace power. [0003] In related technologies, although the traditional rendezvous mode can realize the rendezvous and docking of the tracking spacecraft and the target spacecraft, it has relativel...

Claims

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Application Information

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IPC IPC(8): F41F3/04F41G9/00
CPCF41F3/04F41G9/00
Inventor 池贤彬韩通梁纪秋胡长伟王优胡万林
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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