On-satellite autonomous emergency reentry return orbit design method

A design method and technology for returning to orbit, applied to space navigation equipment, space navigation equipment, space vehicle guidance devices, etc., to achieve the effects of simple and reliable calculation, fuel consumption saving, and intuitive physical meaning

Active Publication Date: 2020-07-10
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

[0004] The purpose of the present invention is to overcome the deficiencies of the prior art, provide an emergency re-entry return orbit design method, solve the orbit design and airport selection problems of the emergency return of the space shuttle aircraft, and provide conditions for rapid derailment braking control within a specified time

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  • On-satellite autonomous emergency reentry return orbit design method
  • On-satellite autonomous emergency reentry return orbit design method
  • On-satellite autonomous emergency reentry return orbit design method

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Embodiment Construction

[0034] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0035] Such as figure 1 , 2 The schematic diagram of the emergency re-entry return orbit design and the emergency de-orbit window are shown in the figure. It can be seen from the figure that each emergency window is obtained from the geographical parameters of the landing airport. By adjusting the current orbit, the re-entry vehicle can quickly enter the de-orbit window. Control and reentry return control to achieve return to the emergency airport. Specific steps are as follows:

[0036] 1. Calculate the corresponding emergency de-orbit window according to the latitude and longitude of the main and standby airports for landing

[0037] Design the emergency de-orbit window according to the orbital characteristics of the re-entry vehicle, the airport and the vertical and horizontal range requirements. According to the characteristics of the ai...

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Abstract

The invention discloses an on-satellite autonomous emergency reentry return orbit design method, and relates to a reentry spacecraft deorbit brake control technology. According to the method, a full-autonomous emergency track design scheme is adopted; and emergency return circles are autonomously calculated according to the geographic positions of the current track and main and standby landing airports, optimization of multiple airports is achieved, and the transition track design of an emergency deorbit window is achieved quickly.

Description

technical field [0001] The invention relates to the technical field of off-orbit braking control for re-entry spacecraft, in particular to an emergency re-entry return orbit design method. Background technique [0002] In recent years, due to the needs of space long-range rapid transportation systems and global rapid and precise strikes, various aerospace vehicles that can travel between the earth's surface and space orbit have become research hotspots in various countries. The representative one is the X-37B orbital test vehicle developed by the United States. It can not only be used for space transportation and space experiments, but also has great potential in military applications such as reconnaissance, surveillance and early warning, and global rapid and precise strikes. [0003] The return process of an aerospace re-entry vehicle can be divided into an orbital segment, a transitional segment, and an atmospheric re-entry segment. The transition section is the connecti...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 段佳佳王献忠刘赟艾奇武静施常勇
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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