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Trajectory prediction and value filtration method for rocket launching unpowered flight segment

A technology for rocket launch and flight segment, applied in directions such as navigation calculation tools, can solve problems such as poor display effect and accuracy, and achieve the effects of reducing systematic errors and accidental errors, simple stress, and avoiding delayed processing.

Inactive Publication Date: 2016-05-18
中国人民解放军63791部队
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AI Technical Summary

Problems solved by technology

When the rocket is outside the measurement and control range, its flight trajectory data cannot be obtained. In order to ensure the data display requirements, the rocket trajectory must be supplemented. The traditional method is to use the speed within the measurement and control range as its speed outside the measurement and control range. Theoretical ballistics are outside the range of measurement and control, and the display effect and accuracy are poor

Method used

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  • Trajectory prediction and value filtration method for rocket launching unpowered flight segment
  • Trajectory prediction and value filtration method for rocket launching unpowered flight segment
  • Trajectory prediction and value filtration method for rocket launching unpowered flight segment

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Embodiment Construction

[0016] see figure 1 , the inventive method specifically comprises:

[0017] (1) Select a set of credible ballistic measurement data or two sets of position / velocity data to calculate the orbital element Kep of the unpowered segment into orbit: the credible ballistic measurement data refers to the smooth data in the ballistic curve, which does not belong to The data of abnormal points can be provided by other external data processing components.

[0018] Calculate the orbital element through a set of ballistic measurement data (r, v) r represents the position vector, v represents the velocity vector.

[0019] a. Calculate the area velocity vector h and its modulus h: h=r×v;

[0020] b. Calculate transition vector W=h / h;

[0021] c. Calculate the orbital inclination i; W x , W y , W z Respectively, the components of the X, Y, and Z directions of the transition vector W;

[0022] d. Calculate the right ascension of the ascending node Ω; Ω = ...

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Abstract

The invention discloses a trajectory prediction and value filtration method for a rocket launching unpowered flight segment. An instant orbit injection Kepler parameter of a trajectory is calculated according to a set of credible trajectory measurement data or two sets of position-speed vector data, and then trajectory data after the moment is predicted according to the orbit parameter. A trajectory data result is calculated according to multiple sets of the predicted data and credibility weighting, and the result can be used for displaying the trajectory and measuring anomalous point filtration of the trajectory data in real time. By adopting the trajectory prediction and value filtration method for the rocket unpowered flight segment on the basis of a spacecraft orbit determination method, the display effect and precision of the trajectory are significantly improved.

Description

technical field [0001] The invention relates to rocket trajectory processing and display technology, in particular to a trajectory extrapolation and filtering method for the unpowered flight of a rocket, which is suitable for rockets in the unpowered flight process based on existing measurement data (at least one set of position velocity vectors or two group time position or time velocity vector), calculate its instantaneous orbital parameters, and then extrapolate ballistic data and filter abnormal points of subsequent real-time measurement data, and use the ballistic extrapolation results and filter value results generated by the high-precision orbit determination method The accuracy is greatly improved compared with traditional methods. Background technique [0002] During the flight of the rocket, according to its flight characteristics, the engine is often shut down in the gliding section of the unpowered flight, so as to ensure that the key flight actions of the rocket...

Claims

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Application Information

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IPC IPC(8): G01C21/20
CPCG01C21/20
Inventor 胡杰刘剑锋白起光何孝港罗启富唐琦杰王英杰张鹏超陈锦平彭渔露
Owner 中国人民解放军63791部队
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