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Configured control optimization method for high-speed aircrafts based on pneumatic nonlinearity and coupling

A technology of high-speed aircraft and optimization method, which is applied in the fields of instruments, special data processing applications, electrical digital data processing, etc., and can solve problems such as poor optimization effect.

Inactive Publication Date: 2013-05-22
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0005] In order to overcome the shortcomings of the existing high-speed aircraft follow-up optimization method with poor optimization effect, the present invention provides a high-speed aircraft follow-up optimization method based on aerodynamic nonlinearity and coupling

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  • Configured control optimization method for high-speed aircrafts based on pneumatic nonlinearity and coupling
  • Configured control optimization method for high-speed aircrafts based on pneumatic nonlinearity and coupling
  • Configured control optimization method for high-speed aircrafts based on pneumatic nonlinearity and coupling

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Embodiment Construction

[0103] The specific steps of the high-speed aircraft follow-up optimization method based on aerodynamic nonlinearity and coupling in the present invention are as follows:

[0104] refer to Figure 1~3 . The invention aims at performing follow-up control optimization of the aerodynamic characteristics of the wing-body assembly aircraft. The body of the aircraft is composed of a pointed cone section, a truncated cone section, a cylindrical section and a shrinking tail; the wings of the aircraft are divided into single-swept wing and double-swept wing layout; the vertical tail of the aircraft is divided into single vertical tail and double vertical tail layout. In addition, elevators (differential rudders) and rudders are installed on the wings and vertical tail of the aircraft.

[0105] 1. The definition of aerodynamic nonlinear evaluation index.

[0106] The aerodynamic nonlinearity evaluation index is the aerodynamic nonlinearity of the pitch channel , which is defined as...

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Abstract

The invention discloses a configured control optimization method for high-speed aircrafts based on pneumatic nonlinearity and coupling and aims to solve the technical problem that the existing configured control optimization method for high-speed aircrafts is poor. According to the technical scheme, the method includes: firstly, defining pneumatic nonlinearity evaluation indicators and pneumatic coupling evaluation indicators; secondly determining configured control optimization target functions; and thirdly establishing a configured control optimization model. Optimization is targeted at the pneumatic nonlinearity evaluation indicators and pneumatic coupling evaluation indicators of aircrafts, and a multi-target configured control optimization algorithm in coordination of ideal point method and simulated annealing algorithm is adopted. Pneumatic nonlinearity and coupling features of the aircrafts are decreased by continuously changing the appearances of the aircrafts, so that a linear model is more similar to a nonlinear model, a decoupling model and a coupling model and the pneumatic nonlinearity and coupling features of the aircrafts are optimal under certain limitations.

Description

technical field [0001] The invention relates to a high-speed aircraft follow-up optimization method, in particular to a high-speed aircraft follow-up optimization method based on aerodynamic nonlinearity and coupling. Background technique [0002] The aerodynamic shape optimization of high-speed aircraft combines the aerodynamic performance analysis of the design object with the optimal method. By continuously changing the shape of the design object, the aerodynamic performance of the aircraft can be optimized under certain constraints. [0003] The shape optimization of hypersonic vehicles follows the multidisciplinary optimization design method of traditional aircraft, such as document 1 "Advancements in Multidisciplinary Design Optimization Applied to Hypersonic Vehicles to Achieve Closure (AIAA-2008-2591)" based on parametric CAD models and aerodynamic disciplines using engineering method, the multidisciplinary and multi-objective optimization of the lifting body and wav...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F19/00
Inventor 周军林鹏葛振振周敏王立祺
Owner NORTHWESTERN POLYTECHNICAL UNIV
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