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Method for filling moving trajectory of unmeasurable area of coasting-flight phase of vehicle

A technology of running trajectory and sliding section, which is applied in the field of aerospace measurement and control, and can solve problems such as measurement blind spots.

Inactive Publication Date: 2016-06-01
中国人民解放军63796部队
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the geographical location and tracking performance of the measurement and control equipment, there are often measurement blind spots in the tracking measurement of the carrier glide section

Method used

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  • Method for filling moving trajectory of unmeasurable area of coasting-flight phase of vehicle
  • Method for filling moving trajectory of unmeasurable area of coasting-flight phase of vehicle
  • Method for filling moving trajectory of unmeasurable area of coasting-flight phase of vehicle

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Embodiment Construction

[0068] Below in conjunction with accompanying drawing, the present invention will be further described:

[0069] The object of the present invention is to propose a method for filling up the running track of the blind area in the measurement of the glide section of the carrier. This method includes:

[0070] 1. Man-machine combination initial trajectory point selection strategy

[0071] Through the man-machine control interface, the operator can set the initial orbit calculation trajectory time point t multiple times in the sliding section of the carrier r , each time a trajectory time point is set, the trajectory will be reselected and the subsequent steps will be repeated.

[0072] If the initial trajectory calculation trajectory time point t is manually set r , select the ballistic value of GNSS and YCGZ at the manually set time point, that is, Orbit GNSS (t r ), Orbit YCGZ (t r ).

[0073] If there is no manual setting of the initial orbit calculation time point, t...

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Abstract

The invention claims for protecting a method for filling a moving trajectory of an unmeasurable area of a coasting-flight phase of a vehicle. The method mainly has the following advantages: in a satellite launching test task, a flight trajectory of the vehicle at the whole coasting-flight phase is computed by a real-time integrative processing system by real-time preliminary orbit extrapolation after an active flight phase of the vehicle is ended, a flight trajectory of the unmeasurable area of the coasting-flight phase of vehicle is filled in real time, a whole course flight trend of the vehicle is shown, various kinds of command decision support information are generated, and whole course guidance on measuring equipment is realized. The method comprises the following steps: 1, proposing a strategy for selecting a preliminary orbit trajectory point; 2, proposing a preliminary orbit optimum selection strategy; 3, determining an orbit extrapolation computing method for the coasting-flight phase of the vehicle; 4, making a method for filling the flight trajectory of the vehicle.

Description

technical field [0001] The invention relates to a data analysis and processing technology of a carrier in the field of aerospace measurement and control, in particular to the calculation of the flight trajectory of the carrier's glide section, and in particular to a method for filling up the running trajectory of the measurement blind area of ​​the glide section of the carrier. Background technique [0002] During the satellite launch process, the vehicle has a certain position and speed at the shutdown point after the powered flight of the active stage, and starts from the shutdown point to the unpowered free flight stage, that is, the taxiing stage. Due to the geographic location and tracking performance of the measurement and control equipment, there are often measurement blind spots in the tracking measurement of the carrier glide section. In order to provide command and decision-making support information in the measurement blind area of ​​the taxiing section, display t...

Claims

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Application Information

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IPC IPC(8): G06F19/00
CPCG16Z99/00
Inventor 何京江魏志东董继辉
Owner 中国人民解放军63796部队
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