Method for correcting sideslip elastic angle of aircraft model in wind tunnel test
A technology for wind tunnel testing and aircraft, applied in aerodynamic testing, testing of instruments, machinery/structural components, etc., can solve the problems of large model aerodynamic load, inability to interpolate, and test data errors, etc., to achieve accurate Control and improve the effect of universal applicability
Active Publication Date: 2015-12-09
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology
For the angle of attack, interpolation and rounding are usually used to obtain the data of the expected angle of attack, but for the sideslip angle, due to the small number of data points, interpolation and rounding cannot be used, resulting in large experimental data errors
Especially in the large-scale wind tunnel test, the aerodynamic load of the model is large, the strut is long, and the elastic angle in the direction of the sideslip angle of the aircraft model is larger, so that the expected attitude angle of the aircraft and the actual attitude angle of the aircraft model are greatly different. The deficiencies of the existing side-slip elastic angle correction method will lead to greater experimental data errors
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[0045]The present invention will be further described in detail below in conjunction with the accompanying drawings, so that those skilled in the art can implement it with reference to the description.
[0046] It should be understood that terms such as "having", "comprising" and "including" as used herein do not entail the presence or addition of one or more other elements or combinations thereof.
[0047] like figure 1 As shown, the method for correcting the actual attitude angle of an aircraft model in a wind tunnel test provided by the present invention is used to continuously correct the sideslip elastic angle of the aircraft model in the wind tunnel test process of simulating the flight attitude of the aircraft until the desired Said sideslip elastic angle reaches within the allowable error range of predetermined attitude angle, it is characterized in that, comprises the following steps:
[0048] Step 1. Set the predetermined attitude angle, and convert the control atti...
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The invention discloses a method for correcting a sideslip elastic angle of an aircraft model in a wind tunnel test. The method comprises the following steps of: setting a predetermined attitude angle, and calculating a control attitude angle according to the predetermined attitude angle; controlling a mechanism to act according to the control attitude angle so as to enable the aircraft model to reach the e predetermined attitude angle; blowing the aircraft model and collecting the stress value of the aircraft model; calculating a practical attitude angle of the aircraft model according to the stress value, and calculating a corrected attitude angle according to the difference between the practical attitude angle and the predetermined attitude angle; controlling the mechanism to make correction action according to the corrected attitude angle, and correcting the practical attitude angle ; and continuously repeating the above steps, and continuously correcting the sideslip elastic angle of the aircraft model until the error is within an allowable error range. The method is used in the wind tunnel test for simulating the flight attitude of an aircraft, and the sideslip elastic angle of the aircraft model is continuously corrected, so that the high precision test requirement of the aircraft is met.
Description
technical field [0001] The invention relates to the technical field of experimental aerodynamic measurement and control. More specifically, the present invention relates to a method for correcting the side-slip elastic angle of an aircraft model in a wind tunnel test, which is applicable to the correction and precise control of the aircraft model's side-slip elastic angle when blowing air in a low-speed, sub-span supersonic and hypersonic wind tunnel . Background technique [0002] The direct purpose of the wind tunnel test is to obtain reliable aerodynamic data with high precision. The test object is the aerodynamic load of the aircraft model in the flow field, so the high-precision attitude control of the aircraft model directly determines the accuracy of the wind tunnel test data. . [0003] The high-precision attitude control of the aircraft model is completed by the model support system. According to different structures and uses, the model support system can be divid...
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Inventor 张江谢锋尼文斌秦永明
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS