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Decoupling algorithm suitable for real-time computing of aerodynamic parameter distribution on wings

A decoupling algorithm and real-time computing technology, applied in computing, computer-aided design, aircraft parts, etc., can solve problems such as high dimensionality, high interpolation dimensionality, and difficult implementation

Inactive Publication Date: 2017-09-15
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0006] 1. For a turboprop aircraft, under different flight conditions, the airflow state behind the propeller is different, and there are thousands of distributions of the incoming flow velocity in front of the wing. I want to calculate the aerodynamic characteristics offline that can cover all working conditions is mission impossible
[0007] 2. If you only perform simple interpolation calculations, the interpolation dimension will be very high. If the dimension is too low, the accuracy of the interpolation cannot be guaranteed. If the dimension is too high, it will be difficult to implement

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  • Decoupling algorithm suitable for real-time computing of aerodynamic parameter distribution on wings
  • Decoupling algorithm suitable for real-time computing of aerodynamic parameter distribution on wings
  • Decoupling algorithm suitable for real-time computing of aerodynamic parameter distribution on wings

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Embodiment Construction

[0034] Below in conjunction with accompanying drawing, technical scheme of the present invention is described in further detail:

[0035] The invention discloses a decoupling algorithm suitable for real-time calculation of wing aerodynamic parameter distribution, which introduces the decoupling parameter σ on the basis of the calculation result of Prandtl's wing lift line model, thereby obtaining empirical formula (1), based on experience Formula (1) is used to design the decoupling algorithm. The decoupling algorithm can realize the real-time calculation of the distribution of aerodynamic parameters on the wing, and is suitable for the establishment of the integrated real-time model of the propeller-engine-aircraft.

[0036] The decoupling parameter σ is defined as σ=α induced / λ, where α induced is the induced attack angle, λ is the compression factor, Ma is the Mach number;

[0037] Described empirical formula (1) is:

[0038]

[0039] In the formula, σ n is the d...

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Abstract

The invention discloses a decoupling algorithm suitable for real-time computing of aerodynamic parameter distribution on wings. According to the algorithm, a new decoupling parameter sigma is introduced on the basis of a wing lifting line model computing result, and the decoupling parameter sigma is defined as sigma=alpha<induced> / lambda, wherein alpha<induced> is an induced attack angle, lambda is a compressibility factor, and Ma is a Mach number. Therefore, an empirical formula is obtained, and the decoupling algorithm is designed based on the empirical formula. Through the decoupling algorithm, real-time computing of aerodynamic parameter distribution on the wings can be realized, and the decoupling algorithm is suitable for establishment of a propeller-engine-aircraft integrated real-time model.

Description

technical field [0001] The invention relates to a calculation method for the aerodynamic parameters of the wing of an aviation aircraft, in particular to a decoupling algorithm suitable for real-time calculation of the distribution of the aerodynamic parameters of the wing. Background technique [0002] For turboprop aircraft, the propeller, engine, aircraft fuselage, wings and other parts interact with each other, and the coupling effect is obvious. Traditional flight control systems are generally designed separately for each subsystem. For such a control system, when a certain subsystem reaches the optimal state, other subsystems may not be optimal. In order to optimize the performance of the whole aircraft, It is necessary to carry out comprehensive control of each subsystem, that is, integrated control. For a special structure such as a turboprop aircraft, integrated control is particularly important. However, to achieve integrated control, propeller-engine-aircraft int...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCB64F5/00G06F30/15G06F2119/06Y02T90/00
Inventor 黄向华黄佳沁王逸维张天宏孙庆彪曹云飞
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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