Spaceflight friction resistance sensor based on K-shaped pipe differential pressure measurement
A sensor and differential measurement technology, applied in pressure difference measurement between multiple valves, measurement device, measurement of fluid pressure, etc., can solve the problems of large volume, difficult data correction, and large disturbance of the straight hole of aerospace friction sensor, etc. Achieve high measurement accuracy, meet surface friction resistance measurement requirements, and reduce flow interference.
Active Publication Date: 2021-04-30
中国空气动力研究与发展中心超高速空气动力研究所
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Problems solved by technology
However, the oblique hole in this form of aerospace friction sensor has a large disturbance to the straight hole, data correction is difficult, and the volume is large, so it is not suitable for installation on the position where the surface slope of the aircraft is large and the installation space is small.
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Embodiment 1
[0036] The diameter of the aerospace friction sensor head structure 1 of the present embodiment is 30 mm, and the height is 17 mm. The diameter of the small boss of the head structure 1 is 20 mm, and the height is 3 mm. The ratio is 5:1, the distance between the centers of the two holes is 5mm, and the inclination angle of the inclined hole is 30°. The absolute pressure measurement range of the pressure sensor 3 is 0-5000Pa, and the measurement accuracy is 0.5%.
[0037] Before the wind tunnel test, determine the sensitivity coefficient curve of the aerospace friction sensor through the following steps:
[0038] a. Select the typical friction test state parameters and the shape and size of the test model;
[0039] b. Carry out numerical simulation and establish a mathematical model of the correlation between the pressure difference and friction of the aerospace friction sensor;
[0040] c. Select a high-precision MEMS friction sensor to carry out a comparative wind tunnel te...
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Abstract
The invention discloses a spaceflight friction resistance sensor based on K-shaped pipe differential pressure measurement. A vertical straight hole is formed in the front portion of the upper surface of a gauge outfit base body of the gauge outfit structure of the spaceflight friction resistance sensor in the airflow direction, an inclined hole inclining downwards is formed in the rear portion of the upper surface of the gauge outfit base body in the airflow direction, the included angle between the inclined hole and the horizontal direction is an inclination angle alpha, and the inclination angle alpha ranges from 20 degrees to 30 degrees. The straight hole is connected to the inlet end of a three-way joint through a connecting pipe I and a pressure measuring hose I in sequence, one outlet end of the three-way joint is connected to a measuring port I of a transmitter body of the high-precision differential pressure micro-pressure transmitter through a pressure measuring hose II, and the other outlet end of the three-way joint is connected with a micro pressure sensor; and the inclined hole is connected to a measuring port II of a transmitter body of the high-precision differential pressure micro-pressure transmitter through a connecting pipe II and a pressure measuring hose III in sequence. The spaceflight friction resistance sensor is high in measuring precision, compact in structure, convenient to carry and capable of meeting the requirement for measuring the surface friction resistance of the hypersonic flight vehicle under the flight condition.
Description
technical field [0001] The invention belongs to the technical field of hypersonic aircraft wind tunnel tests, and in particular relates to an aerospace friction sensor based on K-shaped tube pressure difference measurement. Background technique [0002] Surface frictional resistance, referred to as frictional resistance, refers to the tangential force generated by viscous fluid flowing over the surface of an object. In aerodynamics, friction is an important physical quantity. In actual engineering design, friction is an important part of the aerodynamic force of modern hypersonic vehicles (vehicles for short). performance. [0003] Under hypersonic flight conditions, when the boundary layer on the surface of the aircraft transitions, its friction and heat flow will increase by 3-5 times, seriously affecting the aerodynamic performance, safety and thermal protection system of the aircraft. Accurate prediction of friction can provide important support for aircraft aerodynam...
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IPC IPC(8): G01M9/02G01M9/06G01M9/08G01L13/00
CPCG01M9/02G01M9/06G01M9/08G01L13/00
Inventor 王雄朱涛谢峰杨庆涛
Owner 中国空气动力研究与发展中心超高速空气动力研究所
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