Double-hinge control surface hinge moment derivative estimation method

Abstract

The invention discloses a double-hinge control surface hinge moment derivative estimation method, which relates to the aircraft aerodynamic characteristics estimation technology. The method is used for estimating double-hinge control surface hinge moment, separately calculating derivatives of hinge moments of front and back control surfaces with sideslip angle / angle of incidence and derivatives of the hinge moments with deflection angles of control surfaces through a single hinge estimation method, supposing a compensation ratio parameter according to a back control surface characteristic section parameter, calculating out a new hinge shaft position, moving the new hinge shaft position backward to obtain a new compensation ratio parameter, obtaining nose allowance of the back control surface, and calculating out the derivative of deflection angle of control surface of the front control surface and the derivative of deflection angle of control surface of the back control surface. The double-hinge control surface hinge moment derivative estimation method, provided by the invention, can perform derivative estimation on double-hinge control surface hinge moment, has the advantages of rational deduction process and clear principles, is suitable for double-hinge control surface hinge moment derivative estimation, and obtains rational and accurate calculation result quickly.

Description

technical field [0001] The invention relates to an aircraft aerodynamic characteristic estimation technology, in particular to a method for estimating a hinge moment derivative of a double-hinge rudder surface. Background technique [0002] The existing methods for estimating hinge moments of aircraft rudder surfaces include ESDU, DATACOM, AirplaneDesign, Aircraft Design Manual, Aeronautical Aerodynamic Engineering Calculation Manual, etc. However, the existing methods for estimating hinge moments of aircraft rudder surfaces The system can only estimate the hinge moment of single-hinge rudder surfaces. Existing aircraft control surfaces, especially rudders, use double-hinge rudder surfaces on a large scale, and the original aircraft rudder surface hinge moment estimation method system cannot meet the needs of existing aircraft designs. [0003] Therefore, based on the deficiencies in the above-mentioned existing method system for estimating the hinge moment of the aircraft ...

AI Technical Summary

Problems solved by technology

[0002] The existing methods for estimating hinge moments of aircraft rudder surfaces include ESDU, DATACOM, AirplaneDesign, Aircraft Design Manual, Aeronautical Aerodynamic Engineering Calculation Manual, etc. However, the existing methods for estimating hinge moments of aircraft rudder surfaces The system can only estimate the hinge moment of single-hinge rudder surface

Existing aircraft control surfaces, especially rudders, use double-hinge rudder surfaces on a large scale, and the original aircraft rudder surface hinge moment estimation method system cannot meet the needs of existing aircraft designs.

Images