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Method for predicting skipping trajectory of hypersonic glide warhead in near space

A hypersonic, near-space technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problem of low trajectory prediction accuracy of maneuvering targets

Active Publication Date: 2015-07-15
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention aims to solve the problem of low prediction accuracy of the trajectory of maneuvering targets in existing methods, and provides a method for predicting the trajectory of hypersonic glide warheads in near space

Method used

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  • Method for predicting skipping trajectory of hypersonic glide warhead in near space
  • Method for predicting skipping trajectory of hypersonic glide warhead in near space
  • Method for predicting skipping trajectory of hypersonic glide warhead in near space

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specific Embodiment approach 1

[0046] Specific Embodiment 1: A method for predicting the jumping trajectory of a near-space hypersonic glide warhead according to the present embodiment, which is implemented in the following steps:

[0047] 1. The establishment of the ballistic equation of the hypersonic glide warhead;

[0048]Establish the ballistic equations of hypersonic glide warheads in near space, including aerodynamic calculation equations, acceleration calculation equations, velocity and position calculation equations, velocity and ballistic angle calculation equations, and attitude angle calculation equations;

[0049] Based on the comprehensive calculation equations, the velocity and position equations of the center of mass of the hypersonic glide warhead are obtained as equations (1)-(3).

[0050] 2. Design of tracking filter for hypersonic glide warhead;

[0051] Design the trajectory tracking Kalman filter of the hypersonic glide warhead to track and estimate the position, velocity and accelera...

specific Embodiment approach 2

[0059] Specific implementation mode two: the difference between this implementation mode and specific implementation mode one is:

[0060] Definition of the first step coordinate system

[0061] In order to obtain the prediction method of the hypersonic glide warhead jumping trajectory in the near space, a set of equations need to be established to describe the motion of the hypersonic glide warhead in the near space. To this end, several related coordinate systems need to be defined first.

[0062] (1) Geocentric inertial coordinate system (o I x I the y I z I )

[0063] Such as figure 1 As shown, the origin o I at the center of the earth, o I the y I Pointing to ground radar detection point, o I x I axis lies in the target incoming plane, with o I the y I The axis is vertical, pointing to the target is positive, o I z I Determined by the right-hand rule.

[0064] (2) The inertial coordinate system of the detection point (o F xyz)

[0065] The origin is the ...

specific Embodiment approach 3

[0116] Specific implementation mode three: the difference between this implementation mode and specific implementation mode one or two is that step two is specifically:

[0117] (1) On the three axes of the inertial coordinate system of the detection point, the Singer model is used to describe the variation of the acceleration component of the hypersonic glide warhead, namely

[0118] a · x = - λ x a x + w x a · y = ...

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Abstract

The invention relates to an aircraft trajectory predicting method, in particular to a method for predicting a skipping trajectory of a hypersonic glide warhead in near space and belongs to the technical field of target tracking. The method aims to solve the problem that by the adoption of an existing method, the prediction precision of the trajectory of a maneuvering target is low. The method comprises the steps that firstly, a trajectory equation of the hypersonic glide warhead is established; secondly, a kalman filter tracking the movement curve of the hypersonic glide warhead is designed; thirdly, according to the position, the speed and the acceleration of the hypersonic glide warhead at the tracking end moment and the trajectory equation, the attack angle and the roll angle of the hypersonic glide warhead in fight are estimated, the hypersonic glide warhead in the near space flies by a constant attack angle and a constant roll angle in a subsequent flight time period, recursive calculation for the trajectory at a next moment is conducted through the trajectory equation, and then a trajectory prediction value of the hypersonic glide warhead after a time period is obtained.

Description

technical field [0001] The invention relates to a trajectory prediction method, in particular to a prediction method for the jump trajectory of a hypersonic glide warhead in adjacent space. Background technique [0002] Near-space hypersonic glide warhead is a kind of non-powered gliding in near space for thousands to more than 10,000 kilometers, and has strong lateral maneuverability and penetration performance, and can carry nuclear warheads or conventional warheads to carry out long-distance rapid strikes. Due to the high lift-to-drag ratio of this type of aircraft and the long-term flight in the atmosphere, its trajectory often presents a "jump" feature. [0003] Judging from the current research situation of ballistic prediction at home and abroad, foreign research on ballistic prediction methods is limited to ballistic missiles, and there is no public report on the research on maneuvering target prediction methods. Domestic research on ballistic prediction methods is ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F19/00
CPCY02T90/00
Inventor 周荻秦雷李君龙邹昕光
Owner HARBIN INST OF TECH
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