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Rapid approximation method of disturbing gravity along flight trajectory

A technique for perturbing gravity and ballistics, used in special data processing applications, instruments, electrical digital data processing, etc.

Inactive Publication Date: 2015-07-01
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The difficulty of this problem is to meet the storage capacity and computing power requirements of the missile-borne computer under the premise of ensuring the necessary assignment accuracy

Method used

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  • Rapid approximation method of disturbing gravity along flight trajectory
  • Rapid approximation method of disturbing gravity along flight trajectory
  • Rapid approximation method of disturbing gravity along flight trajectory

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Embodiment Construction

[0089] Below in conjunction with specific embodiment, the present invention will be further described:

[0090] Take a certain type of ballistic missile as the simulation object; the initial unit size of the active segment is δx 0 =δy 0 = δz 0 =0.5km, the increase of unit side length is δx i+1 -δx i =δy i+1 -δy i = δz i+1 -δz i =2km; the size of the initial unit of the passive section is δr 0 = δξ 0 =200km, δf 0 =2°, the increase of unit side length is δr j+1 -δr j = δξ j+1 -δξ j =20km, δf j+1 -δf j = 0.5°.

[0091] The initial conditions of the simulation are set as follows: (1) The firing range is 12000km, the launch azimuth is α=90°, and the launch points are respectively selected as ① plain area (longitude λ=115°E, latitude Height H=0km); ② hilly area (longitude λ=110°E, latitude Height H=1km); ③ very large mountainous area (longitude λ=80°E, latitude Height H=3km); (2) the range is 12000km, and the launch point is located in a super mountainous area (...

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Abstract

The invention provides a rapid evaluation method of the disturbing gravity along a flight trajectory for the first time. The rapid approximation method with ballistic missiles as research objects aims at solving the problem of rapid evaluation on the disturbing gravity in the missile flight process. The rapid evaluation method comprises generating a standard trajectory according to a launch task; generating a flight pipeline with the standard trajectory as a benchmark and performing airspace subdivision; performing evaluation on the node disturbing gravity by a point quality method or a high-order spherical harmonic function method; calculating a disturbing gravity value of any point on an actual trajectory based on a network function approximation theory inside a calculation unit and achieving the whole rapid evaluation calculation on the disturbing gravity along the flight trajectory. Compared with the existing method, the rapid evaluation on the disturbing gravity along any flight trajectory can be implemented, the trajectory calculation requirements for the evaluation precision of the rapid evaluation method are met, the evaluation speed, the data storage and other indexes are excellent, and the real-time evaluation on the disturbing gravity missiles is implemented.

Description

technical field [0001] The invention belongs to the field of aircraft dynamics modeling, in particular to a method for quickly approaching disturbance gravity along flight trajectory. Background technique [0002] It is an inevitable trend in the development of my country's new generation of ballistic missiles to continue to improve the performance of pre-launch maneuvering and rapid launch and the accuracy of landing. The construction of the earth disturbance gravitational model is a necessary link in the pre-launch preparation, and its construction speed directly affects the launch speed. Among the factors that affect the accuracy of the ballistic missile's landing point, the disturbance of gravity during the flight is the main source of errors in the guidance method other than the flatness of the earth and the deviation of the vertical line. Therefore, it is of great military significance and engineering value to establish a fast reconstruction method for the disturbance...

Claims

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Application Information

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IPC IPC(8): G06F19/00G06F17/50
Inventor 郑伟周欢汤国建谢愈安雪滢
Owner NAT UNIV OF DEFENSE TECH
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