Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

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
View PDF2 Cites 13 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

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, sideslip angle and rudder deflection angle hinge moment coefficient are basically zero, which does not affect the use, but for the auxiliary For the wing, the value is relatively large, and using zero instead of the hinge moment coefficient at zero angle of attack, zero side slip angle and zero rudder angle will lead to a large calculation error, which will affect the aircraft's maneuverability and cause safety hazards

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • 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

Examples

Experimental program
Comparison scheme
Effect test

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%.

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

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

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
IPC IPC(8): G06F19/00
Inventor 李继伟
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com