Finite element analysis method for hinge moment balance with wing deformation
A hinge moment and analysis method technology, applied in the direction of instrumentation, geometric CAD, design optimization/simulation, etc., can solve the problems affecting the accurate measurement of control surface hinge moment, model force deformation, heavy workload, etc., to shorten the development cycle, Effect of reducing influence and improving measurement accuracy
Active Publication Date: 2021-07-09
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology
The rigidity of the balance and the model connected to the balance is weak, which leads to severe deformation of the model during the wind tunnel test, which affects the accurate measurement of the hinge moment of the control surface
[0004] At present, in order to improve the measurement accuracy of this type of hinge moment, according to engineering experience, before the wind tunnel test, after the balance is calibrated, when the loading error is large, an electric bridge (called an external electric bridge) is set on the wing model to correct Correction of each component signal of the hinge moment balance requires a large workload and low efficiency
Method used
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Embodiment 1
[0037] This embodiment is the rudder hinge moment balance of a certain type of aircraft.
[0038] Such as Figure 1-Figure 4 As shown, the present embodiment relates to a finite element analysis method of a hinge moment balance with wing deformation, and the steps are as follows:
[0039] Step 1. Use 3D modeling software to construct a 3D model of the wing 1, the hinge moment balance 3, the first cover 7 and the second cover 8; the constructed 3D model includes the wing 1, the hinge moment balance 3, the first Cover plate 7, the second cover plate 8, the hinge moment balance 3 is arranged on the wing 1 and the hinge moment balance 3 is located on the side of the wing 1 near the rudder 9, the first cover plate 7, the second cover plate 8 are respectively provided Both sides of the hinge moment balance 3 and the first cover plate 7 and the second cover plate 8 are respectively fixedly connected to the wing 1 .
[0040] Step 2, using the interface between the finite element ana...
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The invention provides a finite element analysis method for a hinge moment balance with wing deformation, and belongs to the technical field of wind tunnel pneumatic tests. Aiming at the measurement of the hinge moment of the control surface of the high-aspect-ratio aircraft, a finite element analysis method is adopted, and in the design stage of a hinge moment balance, three-dimensional models of wings and the hinge moment balance are constructed through three-dimensional modeling software; and then finite element analysis software is used for simulating stress conditions of a hinge moment balance and a wing in a wind tunnel test for simulation analysis, simulation results are compared and analyzed, structural design of the hinge moment balance and a cover plate is optimized, and the influence of wing deformation and a model cover plate on a measurement result of the hinge moment balance is reduced. Thus, a reasonable hinge moment balance calibration and test scheme is formulated. By adopting the method, the measurement uncertainty of the hinge moment balance can be improved, the development period of the hinge moment balance can be shortened, the working efficiency can be improved, and the method has good use value and social benefits.
Description
technical field [0001] The application relates to the technical field of wind tunnel aerodynamic testing, in particular to a finite element analysis method of a hinge moment balance with wing deformation. More specifically, the present invention provides a design method for a hinge moment balance with wing deformation, which is conducive to the structural optimization of the hinge moment balance and the cover plate, formulates a reasonable calibration and test plan, and improves the measurement accuracy of the hinge moment balance , shorten its development cycle, improve work efficiency, and have a good application prospect. Background technique [0002] The hinge moment balance is mainly used to measure the hinge moment acting on the aircraft control surface (aileron, rudder) or full motion airfoil (horizontal tail, canard) model. With the continuous development of aircraft technology, the application of aircraft with large aspect ratio is becoming more and more common, an...
Claims
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IPC IPC(8): G06F30/23G06F30/17G06F30/15G06F119/14
CPCG06F30/23G06F30/17G06F30/15G06F2119/14Y02T90/00
Inventor 彭超田沛洲向光伟史玉杰唐新武易国庆贾巍潘华烨张璜炜汪多炜庞超王玉花
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT