Glide trajectory error propagation analysis method based on perturbation theory

A technology of gliding ballistics and error propagation, applied in the fields of electrical digital data processing, special data processing applications, instruments, etc., can solve the problems of difficult direct application of theories and methods, and achieve broad engineering application prospects, small method errors, and fast calculation speed. Effect

Active Publication Date: 2015-12-09
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

Judging from the existing literature, there is no established analysis method for the influence of perturbation factors on hypersonic gliding vehicles, which makes it difficult to directly apply theories and methods in similar fields

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  • Glide trajectory error propagation analysis method based on perturbation theory
  • Glide trajectory error propagation analysis method based on perturbation theory
  • Glide trajectory error propagation analysis method based on perturbation theory

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Embodiment Construction

[0088] Below in conjunction with specific example, the present invention will be further described:

[0089] Based on the CAV-H aerodynamic model, the gliding flight trajectory is taken as the research object, and the disturbance gravity during the flight is used as the single perturbation factor for simulation. The disturbance gravitational force of each point on the ballistic trajectory during the flight is calculated by the 1080th order spherical harmonic function method.

[0090] The initial conditions of the simulation are set as:

[0091] (1) Analyze the error propagation mechanism 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 =100°, geocentric latitude φ 0 =20°; ② State parameter of end point: speed V k =2000m / s, velocity inclination θ k = 0°, height H k =25km, longitude λ k =165°, geocentric latitude φ k =50°; ③The waiting distance from the target point ...

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Abstract

The invention relates to a glide trajectory error propagation analysis method based on the perturbation theory. The method comprises the following steps: establishing a pole-changing coordinate system by adopting a glide trajectory reentry longitudinal plane as a pole-changing equatorial plane; establishing an aircraft kinetic model in the pole-changing coordinate system and a motion perturbation equation; solving a state-transition matrix to obtain the analytic solution of the perturbation equation; and establishing an error propagation module in a common coordinate system based on the coordinate change. The glide trajectory error propagation analysis method provided by the method strives for filling up the blank of a glide trajectory perturbation factor influence mechanism analysis method of a hypersonic velocity glide aircraft, and lays a foundation and a method support for deepening the error propagation mechanism acquaintance and establishing a trajectory rapid correction method.

Description

technical field [0001] The invention belongs to the field of aircraft dynamics modeling, in particular to a method for analyzing the error propagation mechanism of hypersonic gliding aircraft gliding ballistic perturbation factors. Background technique [0002] Aircraft trajectory planning and guidance control design are usually carried out based on approximate models due to imperfect physical cognition or to improve computational efficiency. The error introduced by the approximation mainly involves the modeling error of the aircraft body and the error of the geophysical environment factors, which are collectively referred to as the perturbation factors affecting the flight state. 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 and guidance control design. Perturbation factors mainly include aircraft body modeling error and geophysical environment facto...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 汤国建周欢郑伟刘鲁华
Owner NAT UNIV OF DEFENSE TECH
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