Aircraft icing risk monitoring method

A risk monitoring, aircraft technology, applied in aircraft parts, de-icing devices, transportation and packaging, etc., can solve problems such as limiting flight risks

Active Publication Date: 2021-05-25
象辑科技股份有限公司
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Problems solved by technology

And the method may include performing remedial or warning measures when the TWE value reaches the TWE threshold; however, when the aircraft of this technical solution is performing an icing risk experiment, it has corresponding requirements for meteorological conditions, which limits the ability to measure the aircraft in the icing risk experiment. The problem of flight risk during icing under different meteorological conditions

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Embodiment approach

[0048] As an embodiment of the present invention, the engine part of the aircraft model is also provided with a return air slot 8, and the return air slot 8 protrudes on the circumferential direction of the inner wall of the engine; the inner wall of the engine is also provided with a surrounding electric heating wire 9. The heating wire 9 maintains a constant heating state; the return air slot 8 guides the airflow entering the engine through the pipeline to the wing and discharges along the nozzle of the engine; Simulate the high-temperature engine parts during the operation of the aircraft, and at the same time use the return air slot 8 to guide the airflow entering the engine to the wings for circulation, which is equivalent to the engine bleed air structure in the aircraft deicing device, and is consistent with the aircraft model Combined with the electric heater 7, the icing risk of the aircraft is detected under different operating conditions, thereby improving the accura...

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Abstract

The invention relates to the technical field of aircraft risk monitoring, in particular to an aircraft icing risk monitoring method which comprises the steps of flight condition simulation, attitude adjustment, ice shape recording, deicing testing and risk analysis. The used flight condition simulation assembly further comprises an annular frame, an air blowing cylinder and a spraying opening; Due to the fact that the disturbed phase change condition of aerodynamic performance of an aircraft in the icing process is difficult to obtain, and an aircraft model in an icing wind tunnel weakens the simulation effect in a fixed posture, the accuracy of aircraft icing risk monitoring is reduced; therefore, the spherical top arranged on the supporting rod and the spherical opening of the aircraft model are installed in a sliding mode, the attitude change that the aerodynamic performance of an aircraft is affected after the aircraft is frozen is reflected, the elastic backing ring at the end of the spherical opening is matched with the pressure sensor below the spherical top, and the stress change condition of the aircraft model in the annular frame during flight simulation is monitored. The specific parameters of the aerodynamic performance of the aircraft influenced in the icing state are obtained, so that the accuracy of the aircraft icing risk monitoring method is improved.

Description

technical field [0001] The invention relates to the technical field of aircraft risk monitoring, in particular to an aircraft icing risk monitoring method. Background technique [0002] Aircraft icing refers to the accumulation of ice on certain parts of the aircraft body surface. It is mainly formed by the freezing of supercooled water droplets in clouds or supercooled rain in precipitation after hitting the aircraft body. It can also be formed by water vapor directly condensing on the body surface. As the altitude increases, the atmospheric temperature gradually decreases, and the atmosphere contains water vapor formed by the evaporation of water on the ground. During the flight of the aircraft, it changes with the dew point and water vapor content of the atmospheric environment, and then in Icing forms on the aircraft. During the flight of the aircraft, if the surface of the aircraft accumulates ice, it will affect the aerodynamic shape of the aircraft, resulting in a dec...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D15/20
CPCB64D15/20
Inventor 张超李强陈俊锋邱珩
Owner 象辑科技股份有限公司
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