Static pressure probe used for gyroplane low speed measurement
A static pressure probe, rotorcraft technology, applied in fluid velocity measurement, velocity/acceleration/impact measurement, measurement device and other directions, can solve the problems of inaccurate pressure, static pressure signal can not be used normally, etc., to achieve the improvement of data utilization. Effect
Active Publication Date: 2016-03-23
TAIYUAN AERO INSTR
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Problems solved by technology
[0006] The present invention solves the problem that the traditional pitot tube on a general rotorcraft cannot effectively sense the downwash airflow, and at the same time, due to the influence of the downwash airflow, the pressure felt by the static pressure hole when the rotorcraft is hovering and flying at a low speed is not an accurate static pressure , the problem that the static pressure signal cannot be used normally, provides a static pressure probe for small speed measurement of rotorcraft
Method used
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Embodiment
[0023] Embodiment: on certain type rotorcraft, we have carried out as follows to the pitot tube by analyzing the fuselage influence of certain type rotorcraft and the influence of rotor airflow image 3 The profile improvement shown uses the profile and hole positions and methods of the present invention.
[0024] According to the influence of the fuselage of the rotorcraft and the influence of the rotor airflow, the pitot tube body adopts a unique spindle streamlined surface. The unique aerodynamic effect of this surface can achieve a lower unit static pressure error on a shorter unit shape, effectively shortening the Tube length and weight reduction.
[0025] Pitot spindle streamlined surface such as image 3 As shown, the first section is a parabolic surface section, the second section is a straight slope section, and the third section is a normal straight line section.
[0026] The surface formula of the first parabolic surface L1 is as follows: φD=(a+bX+cX 2 +dX 3 +eX...
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The invention belongs to the technical field of static pressure probes, particularly relates to a static pressure probe used for gyroplane low speed measurement, and solves the problems that the conventional airspeed head on a common gyroplane cannot effective perceive downwash airflow, pressure perceived by static pressure holes is not accurate static pressure when the gyroplane hovers and performs low-speed flight due to the effect of downwash airflow and static pressure signals cannot be normally used. The static pressure probe comprises the airspeed head. A spindle streamline surface is adopted as the airspeed head body. The airspeed head body is provided with two static pressure holes which are arranged on the spindle streamline surface and upwardly installed. Compared with common static pressure probes, data utilization rate is greatly enhanced. In the speed section of 0-V1 of the gyroplane, the downwash airflow pressure signals can be effective perceived so that downwash airflow speed can be solved. When speed is greater than V2, the static pressure signals of the gyroplane body can be effectively perceived so that height and speed parameters can be solved.
Description
technical field [0001] The invention belongs to the technical field of static pressure probes, and in particular relates to a static pressure probe for low-speed measurement of rotorcraft, which is directly applied to the measurement of downwash air velocity when the rotorcraft hovers and flies at low speed. Background technique [0002] The total static pressure pitot is an important part of the rotorcraft air data system. The total static pressure pitot tube is generally installed above the front side of the rotorcraft, which can sense the total pressure and static pressure on the aircraft and transmit the pressure signal to the atmospheric machine, which can be calculated into barometric altitude, indicated airspeed, true speed, Mach Atmospheric parameters such as number, lifting speed, etc. [0003] When the rotorcraft is in flight, the airflow will be pressed obliquely downward, and a downward airflow will be generated under the rotor, which is called downwash airflow....
Claims
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IPC IPC(8): G01P5/00
CPCG01P5/00
Inventor 石岩杜振宇张慧鑫段瑞
Owner TAIYUAN AERO INSTR