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A modeling analysis method for gust response of a fixed-wing aircraft

An analysis method and fixed-wing technology, applied in special data processing applications, complex mathematical operations, instruments, etc., can solve the problems of reduced accuracy, long calculation time, small calculation amount, etc., and achieve the reduction of structural model order and model order. The effect of low, high computational precision

Active Publication Date: 2019-06-04
XIAN AISHENG TECH GRP +1
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AI Technical Summary

Problems solved by technology

Traditionally, the vortex grid method is used to calculate the aerodynamic force on the wing. This method has a relatively small amount of calculation, but the accuracy is not high.
Computational fluid dynamics (CFD) methods can provide high accuracy, but the calculation time is very long, and the degrees of freedom are too large to be used in gust mitigation control design
In addition, due to the introduction of passive gust mitigation devices at the wingtips, the flow at the wingtips is more complicated, which further reduces the accuracy of traditional methods such as the vortex grid method.

Method used

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  • A modeling analysis method for gust response of a fixed-wing aircraft
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Embodiment Construction

[0036] In order to make the purpose, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the examples. It should be understood that the specific examples described here are only used to explain the present invention and are not intended to limit the present invention. .

[0037] A fixed-wing aircraft gust response modeling analysis method, comprising the following steps:

[0038] 1) The first four modes of a wing with a passive gust mitigation device are calculated using the finite element method, and the deformation of the wing is described by generalized coordinates.

[0039] 2) Analyze the structural mode of the wingtip device, use the orthogonal decomposition method to decouple the structural mode of the wingtip device and the structural mode of the wing, and obtain the rotational mode of the wingtip device.

[0040] 3) Define the unit step input as:

[0041]

[0042] ...

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Abstract

The invention discloses a modeling analysis method for gust response of a fixed-wing aircraft, which reduces the order of a model by reducing the order of an aerodynamic model, has higher precision and small calculated amount compared with the traditional method, and is suitable for engineering analysis. After the model is coupled with an aircraft structure model, an atmosphere model, a steering engine model and the like, a gust response model with low order is obtained, and gust response analysis and gust slowing control design are facilitated.

Description

technical field [0001] The invention belongs to the technical field of aircraft gust mitigation control, and in particular relates to a gust response modeling analysis method of a fixed-wing aircraft. Background technique [0002] There are complex airflow movements in the atmosphere, and fixed-wing aircraft are susceptible to these disturbances when flying in it. Among them, the vertical gust will not only cause a large overload of the aircraft, generate a large dynamic structural load, accelerate structural fatigue damage, but also reduce the flight quality of the aircraft, which is not conducive to the normal operation of airborne equipment. Therefore, when designing an aircraft, it is necessary to establish a gust response model of the aircraft and analyze its gust response characteristics in order to design gust mitigation control. [0003] Guo Shijun of Clayfield University and Li Daochun of Beihang University have studied a passive gust mitigation device. The device...

Claims

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Application Information

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IPC IPC(8): G06F17/50G06F17/16
CPCY02T90/00
Inventor 龚喜盈王丹李道春田茂江向锦武张琳王安文李凡凡
Owner XIAN AISHENG TECH GRP
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