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Backtracking calculation method for rocket launching point parameters

A technology of rocket launch and calculation method, which can be applied to rocket launch devices, use re-radiation, reflection/re-radiation of radio waves, etc., and can solve problems such as parameter errors of rocket launch points

Pending Publication Date: 2022-02-18
CHINA XIAN SATELLITE CONTROL CENT
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Problems solved by technology

[0003] The purpose of the present invention is to provide a method for backtracking calculation of rocket launch point parameters, which solves the problem that the error of the rocket launch point parameters obtained by the existing method is relatively large

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  • Backtracking calculation method for rocket launching point parameters
  • Backtracking calculation method for rocket launching point parameters
  • Backtracking calculation method for rocket launching point parameters

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Embodiment Construction

[0031] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0032] 1. Definition of basic coordinates

[0033]

[0034] The geodetic coordinate system is based on the reference ellipsoid of the earth, and is often represented by geodetic latitude, geodetic longitude, and geodetic elevation (B, L, H).

[0035] 2. Basic method

[0036] (1) Satellites can generally quickly find the target after the rocket is launched. The rocket is now in the vertical ascent stage just after launch, and there is no programmed turn or a small distance in the direction of the track. The first point detected by the satellite should be at the launch point. In the sky above, its latitude and longitude coordinates should be basically the same as those of the launching point.

[0037] (2) The launch process of the rocket generally keeps the launch orbit plane unchanged in the J2000.0 geocentric inertial coordinate system, ...

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Abstract

The invention discloses a backtracking calculation method for rocket launching point parameters, which comprises the following steps of: 1, calculating an observation vector from a satellite to a rocket target in a J2000 inertial coordinate system through rocket target data observed by the satellite; 2, calculating a linear equation of an observation vector in a J2000.0 inertial coordinate system; 3, calculating a position vector of the rocket target in the earth-fixed coordinate system by using radar external measurement data; 4, calculating a plane equation of a launching orbit plane in the J2000.0 inertial coordinate system; 5, calculating the coordinates of a rocket launching point by combining the plane equation of the launching orbit plane and the linear equation of the observation vector; and 6, calculating latitude and longitude parameters of a rocket launching point in the earth-fixed coordinate system. According to the backtracking calculation method for the rocket launching point parameters, accuracy and effectiveness are shown for measuring the active section of a rocket in a sky-ground non-cooperative mode and rapidly determining the launching point parameter calculation in a high-precision mode.

Description

technical field [0001] The invention belongs to the technical field of aerospace measurement and control methods, and in particular relates to a backtracking calculation method for rocket launch point parameters. Background technique [0002] Rockets usually launch vertically. After rising vertically for a few seconds, the rocket makes an attitude turn and maneuvers to enter the ballistic segment, and the launch orbital surface remains unchanged for a certain period of time. In order to provide important support for subsequent missions and decision-making, it is very necessary to quickly and accurately calculate the parameters of the rocket launch point. Ground-based radar measurement data can usually be tracked after a considerable period of time after launch, and there is a large delay with the launch time, and the parameter error of backtracking the launch point of the reverse propulsion rocket is relatively large; at the same time, the satellite can be found within a sho...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01S13/06G01C21/16F41F3/04
CPCG01S13/06G01C21/165F41F3/04
Inventor 马鹏斌杨杰汪彬
Owner CHINA XIAN SATELLITE CONTROL CENT
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