Pusher-type aero-propeller anti-icing function verification flight test method

A technology of aviation propellers and testing methods, which is applied in the testing of machine/structural components, measuring devices, measuring heat, etc., can solve the problems of unpredictable actual temperature, etc., and achieve the effect of high application value

Active Publication Date: 2018-03-06
CHINESE FLIGHT TEST ESTAB
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, the design institute has only made a rough estimate of the temperature of the blades by sticking temperature change test paper on the blades during the bench test, but the actual temperature during the flight is still unpredictable

Method used

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  • Pusher-type aero-propeller anti-icing function verification flight test method

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Embodiment

[0036] In the test flight of a certain type of propulsive aviation propeller aircraft, the method of this paper is used to test and verify the anti-icing function of the exhaust propeller of the aviation propeller. The specific implementation method is as follows:

[0037] (1) Propeller temperature measuring point selection and temperature sheet installation

[0038] The tested propeller is a three-bladed propeller, such as figure 2 As shown, three sections of the propeller prone to icing are selected, and two temperature measuring points are selected on the convex front edge of each blade, and each two measuring points are mutually backup.

[0039] (2) Data transmission and monitoring

[0040] Using radio telemetry technology, a wireless telemetry transmitting device is installed on the propeller disk, and a wireless telemetry receiving device is installed at the rear end of the engine to form a test system, which realizes short-distance wireless transmission and collection...

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Abstract

The invention belongs to the technical field of propeller flight test and specifically relates to a pusher-type aero-propeller anti-icing function verification flight test method. The method, on the basis of static component temperature measurement, realizes temperature signal transmission of a rotating member based on radio short-range telemetry technology, designs flight test task points according to propeller flight envelope to test actual temperature of a blade under each flight state, establishes propeller blade temperature distribution laws and provides basis for engine exhaust anti-icing function verification. The method realizes propeller blade temperature measurement and flight test, obtains the actual temperature of the propeller blade under each flight condition, provides data support for exhaust anti-icing function verification of a pusher-type aero-propeller and provides technical support for application and popularization of exhaust anti-icing in the pusher-type aero-propeller, can carry out real-time data monitoring on the anti-icing working state of the aero-propeller under the flight conditions to ensure safe flight of the propeller and solves the difficulty that it is hard to measure the temperature of the rotating member.

Description

Technical field: [0001] The patent of the invention belongs to the technical field of propeller flight test, and is specifically applied to the flight test of the exhaust anti-icing function verification test of propulsion aviation propeller. Background technique: [0002] Due to the low fuel consumption and high efficiency brought by propeller technology, aviation propellers have been well applied in transport aircraft, regional airliners and other fields, especially the promotion of pusher propellers in the field of military aircraft. At present, there are many models at home and abroad that use pusher propellers, which are installed at the rear end of the engine, and the engine exhaust is used to directly de-ice the propellers. This propeller anti-icing method has certain advantages compared with the traditional anti-icing guide ring anti-icing method. It cancels the influence of the resistance wires and appendages on the front edge of the propeller blades on the aerodyna...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M99/00G01K7/18
CPCG01K7/18G01M99/008
Inventor 郭海东张永峰牛宏伟陶冶文敏
Owner CHINESE FLIGHT TEST ESTAB
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