Airspeed head structure capable of automatically removing ice

Abstract

The invention relates to the technical field of atmospheric sensor equipment, and discloses an airspeed head structure capable of automatically removing ice. The structure comprises a front main pipe,the front main pipe is movably connected with a rear main pipe through a separable movable joint, the movable joint is movably connected with a fixed pipe, and both the front main pipe and the rear main pipe are fixedly connected with the fixed pipe. According to the airspeed head structure capable of automatically removing ice, after the inner wall of the airspeed head is frozen, ice falls off through proper heating and is discharged from the discharging opening, accumulated water in the speed control pipe is reduced through discharging in the form of ice blocks, the drainage design requirement of the airspeed head is lowered; and the main heating part and the driving part are arranged at the bottom of the airspeed head, so that the arm of force is shortened and the overall pressure of the airspeed head is reduced obviously; in addition, the overall pressure on the airspeed head is remarkably reduced, the overall equipment weight is reduced due to the reduction of the power requirement, the design requirement for the structural strength is further reduced, and the development requirement for light weight and miniaturization of the airspeed head is met.

Description

technical field [0001] The invention relates to the technical field of atmospheric sensors, in particular to a pitot tube structure capable of automatic deicing. Background technique [0002] The pitot is an atmospheric sensor for the aircraft to detect its own speed, please refer to Figure 7 , the external atmosphere enters the total pressure chamber and the static pressure chamber respectively through the front total pressure inlet and the side static pressure inlet, the total pressure chamber and the static pressure chamber are airtightly isolated, the total pressure chamber and the static pressure chamber The pressure is sent to both sides of the barometer through the trachea respectively, and the flight parameters such as the flight speed, flight Mach number and altitude of the aircraft are measured. [0003] Due to the low temperature in the high altitude, and the pitot tube is exposed outside the body, the possibility of freezing is relatively high, especially at the...

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Problems solved by technology

[0003] Due to the low temperature in the high altitude, and the pitot tube is exposed outside the body, the possibility of freezing is relatively high, especially at the position where the airflow changes most violently at the air inlet of the main pipe, there is a high possibility of freezing, so in order to To prevent freezing, a heating device is usually installed at the air inlet of the main pipe for deicing. The airflow velocity in the high altitude is faster, and the temperature is dissipated faster. However, the heating device usually does not work continuously and usually works intermittently. On the one hand, due to air The speed tube is slender and heats up quickly. In order to ensure the deicing effect, the heating device usually requires a large electric power and a large volume. Moreover, the high-power function is also a large burden for small aircraft. Another On the one hand, because the pitot tube has high requirements on the structural strength, the thermal insulation performance is usually relatively high, the heat at the inlet moves to the inside with the airflow, and the temperature is rapidly lowered, and more water will condense when the high-temperature water vapor dissipates heat, which increases the airspeed Pipe Drainage Requirements

[0004] Secondly, high power means large volume and large mass, and considering insulation, icing feedback, heat dissipation and other issues, it will further increase the volume and quality of the heating structure, and since the heating device is usually located at the total pressure inlet of the principle body, Larger moment arm will additionally increase the structural strength design requirements for high attack speed, making the overall structure of the pitot tube more complicated, which is not conducive to the light weight and miniaturization requirements of the pitot tube

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