Multi-control-surface aircraft modal calculation and verification method

A verification method and aircraft technology, applied in the direction of calculation, instrumentation, special data processing applications, etc., can solve problems such as distortion of modal characteristics in finite element modeling of large complex products, achieve accurate prediction of rudder surface modal characteristics, and ensure effectiveness , to overcome the effect of the gap

Active Publication Date: 2014-12-10
CHINA ACAD OF LAUNCH VEHICLE TECH
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AI Technical Summary

Problems solved by technology

[0003] The technical solution of the present invention is to overcome the deficiencies of the prior art, provide a multi-rudder aircraft modal calculation and verification method, and solve the problems caused by large-scale and complex product finite element modeling and rudder surface modal tests due to gaps. The problem of distorted state characteristics

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  • Multi-control-surface aircraft modal calculation and verification method
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  • Multi-control-surface aircraft modal calculation and verification method

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Embodiment Construction

[0032] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0033] Such as figure 1 As shown, a multi-rudder aircraft modal calculation and verification method includes two parts: the calculation of the aircraft modal characteristics and the verification of the aircraft modal characteristics calculation results;

[0034] (a) The specific steps for calculating the modal characteristics of the aircraft are as follows:

[0035] (a1) Utilize equal stiffness method to set up the finite element model of aircraft rudder surface transmission mechanism; Described rudder surface transmission mechanism comprises rear steering gear support, steering gear, rocking arm, rudder shaft and rudder surface; (rudder surface transmission mechanism is divided into Ailerons, flaps, rudders, parachute; non-rudder transmission mechanism fuselage, wings, empennage several categories)

[0036] The establishment method ...

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Abstract

The invention discloses a multi-control-surface aircraft modal calculation and verification method. An aircraft control surface transmission mechanism finite element model is established with an equivalent-rigidity method, a full-aircraft finite element model is established with a finite element model assembly method, and main modal characteristics of an aircraft are predicted; a stepping sine scanning method is adopted for carrying out modal tests for verification, and the problem that in a multi-control-surface aircraft modal test, because connecting gaps exist between control surface mechanisms, modal stability is influenced is solved. A control surface loading method is adopted in the method, control surface mechanical gaps are eliminated, and modal frequency instability and modal resonance instability are eliminated. The method effectively verifies scientificity of a modal prediction method, and meanwhile, the modal instability is effectively eliminated through the control surface gradual loading method.

Description

technical field [0001] The invention relates to a multi-rudder surface aircraft modal calculation and verification method, which belongs to the field of load and mechanical environment prediction and verification. Background technique [0002] At present, the modal parameters of aircraft are the main input conditions for analyzing structural dynamics problems, especially for multi-rudder aircraft, structural dynamics problems are prone to occur. Therefore, it is of great significance to analyze and study the modal characteristics of this kind of aircraft. With the rapid development of computer technology, on the one hand, modal analysis can guide the optimization design of product structure in the design stage, and provide reference for modal test; Models can solidify experience, and subsequent similar models of aircraft can use modal predictions to replace modal tests, saving time and money. In the existing modal analysis process, the product finite element model is estab...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 张家雄何咏梅张华山楚龙飞张世军陈尚陈洪波曹晓瑞曹霄辉杨勇朱永贵彭小波
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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