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A Fast Correction Method for Gliding Trajectory Aiming at the Compensation of Perturbation Factors

A gliding ballistic and ballistic technology, applied in the field of fast correction of gliding ballistics of hypersonic gliding aircraft

Active Publication Date: 2018-12-28
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Aiming at the problem of rapid correction of the gliding trajectory of a hypersonic gliding vehicle, the present invention proposes for the first time a method for rapid correction of the gliding trajectory oriented to the compensation of perturbation factors

Method used

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  • A Fast Correction Method for Gliding Trajectory Aiming at the Compensation of Perturbation Factors
  • A Fast Correction Method for Gliding Trajectory Aiming at the Compensation of Perturbation Factors
  • A Fast Correction Method for Gliding Trajectory Aiming at the Compensation of Perturbation Factors

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Embodiment Construction

[0149] Below in conjunction with specific example, the present invention will be further described:

[0150] Based on the CAV-H aircraft model, the simulation is carried out with the disturbance gravity during flight as the single perturbation factor. The 1080-order spherical harmonic method is used to calculate the disturbance gravity along the gliding trajectory.

[0151] The initial conditions of the simulation are set as:

[0152] (1) Analyze the accuracy of the method for a typical gliding trajectory: ①Initial point state parameter: velocity V 0 =6500m / s, velocity inclination θ 0 = 0°, height H 0 = 80km, longitude λ 0 =0°, geocentric latitude φ 0 =0°; ②End point state parameter: speed V k =2500m / s, velocity inclination θ k = 0°, height H k = 30km, longitude λ k =55°, geocentric latitude φ k =30°; ③Flight constraints: maximum heat flux Maximum dynamic pressure q max =100kPa, maximum overload n max =3g; ④ The waiting distance from the target point at the end o...

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Abstract

The present invention provides a perturbation factor effect-compensated method for rapidly correcting a glide trajectory. The method comprises: establishing a pole-changed coordinate system; establishing a dynamics model of an aircraft in the pole-changed coordinate system; calculating longitudinal and transverse deviations; establishing a relationship between longitudinal and transverse ranges and the latitude and longitude of a glide trajectory terminal; calculating a partial derivative of the longitudinal and transverse ranges versus the latitude and longitude of a falling point; calculating latitude and longitude variations of the glide trajectory terminal; calculating a partial derivative of the latitude and longitude variations of the glide trajectory terminal versus a resistance acceleration; calculating a partial derivative of the latitude and longitude variations of the glide trajectory terminal versus trajectory data; calculating corrected trajectory data; and calculating a corrected trajectory. Implementing the method provided by the present invention to rapidly correct a glide trajectory enables that longitudinal and transverse range deviations of a corrected trajectory can be about 1 km and trajectory precision can be improved about 20 times, thereby meeting a precision requirement of rapid correction of a glide trajectory. Moreover, according to the method provided by the present invention, a glide trajectory can be rapidly corrected for multiple perturbation factors and under various conditions; there is no singular point in calculation; and an application scope is wide.

Description

technical field [0001] The invention belongs to the field of aircraft trajectory planning, in particular to a fast correction method for hypersonic gliding aircraft glide trajectory for perturbation factor compensation. Background technique [0002] The gliding trajectory is the main part of the full course trajectory of the hypersonic gliding vehicle, and it has complex trajectory characteristics that are significantly different from other vehicle trajectories. Due to the complexity of the modeling of aircraft body and geophysical environmental factors and the imperfect physical cognition of geophysical perturbation factors, ballistic planning methods are usually established based on simplified models, and the errors introduced by model approximation are collectively referred to as perturbation factors. Perturbation factors will cause the actual motion state of the aircraft to deviate from the design state, which is the main source of method errors in trajectory planning an...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 周欢郑伟汤国建
Owner NAT UNIV OF DEFENSE TECH
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