Probe used for total pressure measurement of rotorcraft

A rotorcraft and total pressure technology, applied in the direction of measuring devices, measuring fluid pressure, instruments, etc., can solve the problems of poor accuracy of total pressure perception and inability to detect total atmospheric pressure

Active Publication Date: 2016-03-23
TAIYUAN AERO INSTR
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Problems solved by technology

[0005] In order to solve the problem that the total pressure probe of the rotorcraft is affected by the downwash airflow component, the total pressure sensing accuracy is poor, especially

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  • Probe used for total pressure measurement of rotorcraft
  • Probe used for total pressure measurement of rotorcraft
  • Probe used for total pressure measurement of rotorcraft

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Embodiment Construction

[0019] The specific embodiment of the present invention will be further described in conjunction with the accompanying drawings.

[0020] The installation position of the probe for the total pressure measurement of the rotorcraft is usually difficult to avoid the rotor influence area. The present invention adopts two total pressure probes to be symmetrically installed on the aircraft, such as figure 2 location shown. The streamline of the helicopter downwash at the installation location is shown image 3 shown.

[0021] In the present invention, double total pressure probes are installed symmetrically on the left and right. Each probe adopts a non-rotating shape design. The front surface of the front pressure sensing hole is designed to form a certain oblique angle with the incoming flow direction, and the front pressure sensing hole is facing downwards. The direction of the wash airflow, while reducing the design of the inner cone angle of the pressure sensing hole at the ...

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Abstract

The invention belongs to the technical field of aerospace total pressure probes and specifically relates to a probe used for total pressure measurement of a rotorcraft. The probe solves the problem that total pressure sensing accuracy of a total pressure probe of the rotorcraft is poor due to influences of a downwash airflow component and also solves the problem that a total atmosphere pressure cannot be detected under a low forward speed. The two probes are installed symmetrically on the left and the right of the rotorcraft, installation positions are located on a flow line of a downwash airflow of a helicopter, the probe has a non-convolution body shape, a front end face of a pressure sensing hole in the front end is designed to form an inclined angle relative to an incoming flow direction, the pressure sensing hole in the front end turns the back to the downwash airflow direction, and an inner conical angle of the pressure sensing hole in the front end is smaller than or equal to 30 DEG. In comparison with the prior art, the probe used for the total pressure measurement of the rotorcraft provided by the invention effectively increases total pressure sensing accuracy during utilization of the total pressure probe in the rotorcraft and increases a low-speed applicable scope of the total pressure probe.

Description

technical field [0001] The invention belongs to the technical field of aerospace total pressure probes, and in particular relates to a probe for measuring the total pressure of a rotorcraft, which is suitable for detecting the total pressure signal of the oncoming airflow during the flight of the rotorcraft, and the total pressure signal is used for calculation Flight parameters related to flight speed. Background technique [0002] The total pressure is an important atmospheric parameter during the flight of the aircraft. It is sensed by the total pressure probe installed outside the skin of the aircraft, and the total pressure signal sensed by the total pressure probe is transmitted to the air data computer to calculate the flight parameters related to the speed. [0003] The total pressure probe of the aircraft is usually designed in the shape of a gyratory body. The front end is vertically opened with a pressure sensing hole with a taper. The cone angle is generally 60°....

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Application Information

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IPC IPC(8): G01L19/00
CPCG01L19/00
Inventor 曹文白杜振宇张丽
Owner TAIYUAN AERO INSTR
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