Method for computing control surface hinge moment coefficient when airplane incidence angle, sideslip angle and rudder deflection angle are all zero degree

A technology of hinge moment and control surface, which is applied in the field of aircraft aerodynamic calculation, can solve problems such as calculation error, influence of aircraft control performance, discount of practical value, etc., and achieve the effect of ensuring flight safety and aircraft control performance

Active Publication Date: 2014-02-12
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

However, the existing estimation methods are incomplete in the calculation of the hinge moment, and do not include the hinge moment coefficient at zero angle of attack, zero sideslip angle, and zero rudder angle, only the derivative of the hinge moment with the angle of attack and the This undoubtedly reduces the practical value of the calculation method, because for the rudder and elevator, the zero angle of attack,

Method used

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  • Method for computing control surface hinge moment coefficient when airplane incidence angle, sideslip angle and rudder deflection angle are all zero degree
  • Method for computing control surface hinge moment coefficient when airplane incidence angle, sideslip angle and rudder deflection angle are all zero degree
  • Method for computing control surface hinge moment coefficient when airplane incidence angle, sideslip angle and rudder deflection angle are all zero degree

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Embodiment 1

[0040] Taking the aileron of a regional airliner as an example, the test result of the zero-degree hinge moment coefficient of the aileron is m j0 =-0.118, given by drawing The result of calculating its relative camber value is: N 1Y =0.14968,N 2Y =-0.05276, N 3Y =-0.05418,N 4Y =-0.05094,N 5Y =-0.03726,N 6Y =-0.02481,N 7Y =-0.01387,N 8Y =-0.00507,N 9Y =0.001519,N 10Y =0.005813,N 11Y =0.006988,N 12Y =0.005266,N 13Y =0.003038,N 14Y =0; calculate the zero-lift angle of attack α 0 = -0.16 and zero lift pitching moment m z0 =-0.04545; The angle α between the control surface and the stabilizer surface is obtained from the drawings 1 =6.63°, hinge axis position λ=6.1% and formula m j 0 = ( α 1 - α 0 ) × m j δ ...

Embodiment 2

[0044] Taking the aileron of a certain type of transport aircraft as an example, the test result of the zero-degree hinge moment coefficient of the aileron is m j0 =-0.142, given by drawing The result of calculating its relative camber value is: N 1Y =0.075025, N 2Y =0.06378,N 3Y =0.057848,N 4Y =0.05802,N 5Y =0.05852,N 6Y =0.05756,N 7Y =0.05454,N 8Y =0.049807,N 9Y =0.045766,N 10Y =0.03731,N 11Y =0.02746,N 12Y =0.0148,N 13Y =0.007162, N 14Y =0; calculate the zero-lift angle of attack α 0 =-5.406 and zero lift pitching moment m z0 =-0.06983; The angle α between the control surface and the stabilizer surface is obtained from the drawings 1 =0.78, hinge axis position λ=4.784% and the formula get:

[0045] m j0 =(0.78-(-5.406))×(-0.009276)+(-0.06983) / (1-0.04784)=-0.131;

[0046] The calculation accuracy is 0.137 / 0.142=97%.

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Abstract

The invention belongs to the airplane aerodynamic computation technology, and relates to a method for computing a control surface hinge moment coefficient when an airplane incidence angle, a sideslip angle and a rudder deflection angle are all zero degree. The method for computing the control surface hinge moment coefficient is characterized by comprising the steps of determining computation conditions, computing the relative curvature degree of a mean camber line (3), computing the zero-lift incidence angle, computing a zero-lift hinge pitching moment, and computing the control surface hinge moment coefficient when the airplane incidence angle, the sideslip angle and the rudder deflection angle are all the zero degree. According to the method, the computation accuracy of the hinge moment coefficient obtained when the airplane incidence angle, the sideslip angle and the rudder deflection angle are all the zero degree is improved, and the airplane control performance and the air safety are ensured.

Description

technical field [0001] The invention belongs to aircraft aerodynamic calculation technology, and relates to a calculation method for control surface hinge moment coefficient when the angle of attack, sideslip angle and rudder deflection angle of the aircraft are all zero degrees. Background technique [0002] The existing methods for estimating the hinge moments of aircraft rudder surfaces include "ESDU", "DATACOM", "Airplane Design", "Aircraft Design Manual", "Aerodynamic Engineering Calculation Manual" and so on. However, the existing estimation methods are incomplete in the calculation of the hinge moment, and do not include the hinge moment coefficient at zero angle of attack, zero sideslip angle, and zero rudder angle, only the derivative of the hinge moment with the angle of attack and the This undoubtedly reduces the practical value of the calculation method, because for the rudder and elevator, the zero angle of attack, sideslip angle and rudder deflection angle hing...

Claims

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Application Information

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IPC IPC(8): G06F19/00
Inventor 李继伟
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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