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High-speed aircraft transition position measurement sensor design method based on temperature balance

A high-speed aircraft, measurement sensor technology, applied in design optimization/simulation, instruments, calculations, etc., can solve problems such as poor accuracy, complex aircraft transition position measurement, etc., to achieve the effect of easy use and small measurement error

Active Publication Date: 2019-04-05
BEIJING AEROSPACE TECH INST
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Problems solved by technology

[0005] The invention provides a design method for a high-speed aircraft transition position measurement sensor based on temperature balance, which can solve the technical problems of complex measurement of aircraft transition position and poor accuracy in the prior art

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  • High-speed aircraft transition position measurement sensor design method based on temperature balance

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[0019] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. The following description of at least one exemplary embodiment is merely illustrative in nature and in no way taken as limiting the invention, its application or uses. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0020] It should be noted that the terminology used here is only for describing specific implementations, and is not intended to limit t...

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Abstract

The invention provides a high-speed aircraft transition position measurement sensor design method based on temperature balance, and the method comprises the steps: 1, determining the installation position of a temperature measurement element in an aircraft housing according to the surface heat flow distribution of an aircraft; 2, mounting a temperature measuring element at the mounting position ofthe temperature measuring element determined in the step 1, and connecting the temperature measuring element with a temperature measuring system outside the aircraft to form a temperature measuring loop; Step 3, measuring the temperature of the loop according to the temperature formed in the step 2; and in combination with the change of the trajectory parameters of the aircraft, when the temperature of the aircraft suddenly changes at the set moment measured by the temperature measurement loop, that the set moment is the transition position of the aircraft is judged and the design of the measurement sensor is finished according to the temperature measurement element and the temperature measurement system. By applying the technical scheme provided by the invention, the technical problems of complex measurement and poor accuracy of the transition position of the aircraft in the prior art are solved.

Description

technical field [0001] The invention relates to the technical field of aircraft transition measurement, in particular to a design method for a high-speed aircraft transition position measurement sensor based on temperature balance. Background technique [0002] During the flight test of high-speed aircraft (hereinafter referred to as aircraft), there are two flow states of laminar flow and turbulent flow on the surface of the aircraft. The difference in flow state will directly lead to the difference in aircraft lift, drag, surface heat flow and engine performance. The process of flow changing from laminar to turbulent is called transition. Accurately measuring the transition position of the outer surface of the aircraft plays a key role in the design of the aircraft and the establishment of calculation methods. [0003] At present, the transition measurement of high-speed aircraft mainly focuses on the ground wind tunnel test, using pulsation pressure sensors and heat flo...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 罗金玲吴宁宁符松康宏琳贾文利王亮
Owner BEIJING AEROSPACE TECH INST
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