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Control association modeling method of elastic mode of aircraft

A technology of elastic mode and modeling method, which is applied in the direction of instruments, special data processing applications, electrical digital data processing, etc., and can solve the problems of no control system, limited control system bandwidth, and the failure of aircraft to achieve performance, etc.

Active Publication Date: 2017-09-29
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0004] Modern aircraft represented by air-breathing hypersonic vehicles usually use lightweight materials, and its slender body configuration makes the aircraft fuselage prone to obvious elastic deformation, and the frequency of vibration is reduced to the same frequency band as the bandwidth of the control system. It will limit the bandwidth of the control system, resulting in the control system not having sufficient authority to compensate for the structural mode effects, resulting in the failure of the aircraft to achieve the expected performance

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  • Control association modeling method of elastic mode of aircraft
  • Control association modeling method of elastic mode of aircraft
  • Control association modeling method of elastic mode of aircraft

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Embodiment Construction

[0092] Firstly, the vehicle is regarded as a cantilever beam structure with two sections connected to the mass point. In order to reflect the coupling between the rigid body and the elastic mode in the equation of motion, the dynamic equation of the elastic body vehicle is constructed according to the Lagrangian equation and the principle of virtual work (in the form of Longitudinal dynamic equations are taken as an example, and only the first-order elastic mode is considered).

[0093]

[0094] Among them, the rigid body state {V, γ, h, a, q} represents the velocity, track angle, height, angle of attack and pitch angle velocity respectively; q is the pitch angle; represent the generalized coordinates of the front and rear bodies and their derivatives respectively; ζ is the damping ratio; ω a , ω f is the natural frequency of the front and rear body, N a , N f For the generalized force.

[0095] During the flight of the aircraft, fuel consumption and aerodynamic heatin...

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Abstract

The invention discloses a control association modeling method of an elastic mode of an aircraft. The method comprises the following steps that a mechanism model of the elastic structure mode of the aircraft is built, and dynamic response data of the elastic mode is obtained; based on a beam element, the form of an agent model of the elastic mode is determined; coefficient setting is conducted by using a system identification method, a control association model of the elastic mode is obtained, the effectiveness of the built agent model is further verified based on the goodness of fit, the influence of the elastic mode on the open-loop performance and close-loop performance of an aircraft body is analyzed, and the association relationship between the body characteristic and the elastic mode is analyzed. Therefore, the influence rule of the elastic mode on the overall system and the design of the control system is found, and a good technical support is provided for the actual engineering design.

Description

technical field [0001] The invention relates to a control correlation modeling method of an aircraft elastic mode. Background technique [0002] Traditional aircraft design methods generally adopt distributed design ideas, decomposing aircraft design tasks into multiple design disciplines, and the design of each discipline is relatively independent. This design idea is efficient and feasible when the coupling relationship between various disciplines is weak, or when the mutual influence between disciplines is linear. [0003] However, for modern aircraft, its design idea breaks through this idea, and there are big differences in aerodynamic shape, propulsion system and control system design. Usually, there is a strong nonlinear coupling relationship between aircraft subsystems, and for design variables with high sensitivity. Therefore, the results obtained by using this distributed design method are not satisfactory, and often cannot meet the requirements of performance an...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/23G06F2119/06
Inventor 刘燕斌沈海东陈柏屹祝宇陆宇平
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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