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Method and apparatus for calculating gust load coefficient of low speed aircraft

A load factor and calculation method technology, applied in calculation, electrical digital data processing, design optimization/simulation, etc., can solve problems such as low flight speed of low-speed aircraft, large gust angle of attack, and aircraft lift line deviating from the linear area, etc., to achieve The effect of accurate and available data

Active Publication Date: 2019-01-01
四川腾盾科技有限公司
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Problems solved by technology

[0004] Low-speed aircraft fly at a low speed. After encountering natural gusts of wind and turbulence in the air, the angle of attack of gusts is large, which may touch the area where the lift line of the aircraft deviates from linearity. The empirical formula of the gust load coefficient in the military standard GJB67.2-85 and China Civil Aviation Airworthiness Regulations CCAR23 is no longer applicable

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  • Method and apparatus for calculating gust load coefficient of low speed aircraft
  • Method and apparatus for calculating gust load coefficient of low speed aircraft
  • Method and apparatus for calculating gust load coefficient of low speed aircraft

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Embodiment Construction

[0034] All features disclosed in this specification, or steps in all methods or processes disclosed, may be combined in any manner, except for mutually exclusive features and / or steps.

[0035] Any feature disclosed in this specification, unless specifically stated, can be replaced by other alternative features that are equivalent or have similar purposes. That is, unless expressly stated otherwise, each feature is one example only of a series of equivalent or similar features.

[0036] Taking China Civil Aviation Airworthiness Regulations CCAR23 as an example, the gust load factor is calculated according to the following formula:

[0037]

[0038] In the formula:

[0039] is the gust mitigation coefficient;

[0040] is the aircraft mass ratio;

[0041] u de The gust speed stipulated in CCAR23 of China Civil Aviation Airworthiness Regulations, m / s;

[0042] ρ 0 Atmospheric density at sea level, kg / m 3 ;

[0043] ρ H Atmospheric density at the height at which th...

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Abstract

The invention discloses a low-speed aircraft sudden wind load coefficient calculation method and equipment. The method comprises: obtaining aircraft lift coefficient varying with each angle of attack;the lift coefficient CL1 and the angle of attack alf1 of the plane being obtained. The change of angle of attack delta alf caused by the gust is obtained. The lift coefficient CL2 corresponding to alf 1 + delta alf is obtained by interpolating the angle of attack-lifte coefficient correspondence relation value; the lift coefficient increment delta CL=CL2-CL1 is calculated; the calculated lift coefficient increment delta CL is used to calculate the gust load coefficient using the gust load coefficient formula. The calculation method and the device of the invention can be used for any type of lift characteristic aircraft (including a lift line in a linear region and a non-linear region), according with the actual situation, and the data are accurate and usable.

Description

technical field [0001] The invention relates to the field of aircraft structural strength design, in particular to a method and equipment for calculating the gust load coefficient of a low-speed aircraft. Background technique [0002] The gust load is an additional load caused by the disturbed air flow when the aircraft flies in an unbalanced atmosphere, and it is one of the important basis for the structural strength design. [0003] National military standard GJB67.2-85 and China Civil Aviation Airworthiness Regulations CCAR23 have made specific regulations on the gust load coefficients of military aircraft and civil aircraft respectively, and provided estimation formulas. Considering the requirements of discrete gusts in military aircraft and civil aircraft specifications, the estimation formulas of the two are basically the same, only the regulations on the size of gusts are slightly different. [0004] The flying speed of low-speed aircraft is small. After encountering...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20
Inventor 李俊机郭东曾东
Owner 四川腾盾科技有限公司
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