Rotor type aircraft water landing model test method

An aircraft model and model test technology, which is applied in the directions of fluid dynamics test, machine/structural component test, measurement device, etc., and can solve the problem of no rotor-type aircraft ditching model test method, etc.

Active Publication Date: 2017-03-22
CHINA SPECIAL TYPE FLIER RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, there is no practical method for ditching model test of rotorcraft

Method used

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  • Rotor type aircraft water landing model test method
  • Rotor type aircraft water landing model test method
  • Rotor type aircraft water landing model test method

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Embodiment Construction

[0033] Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0034] In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", " Orientation indicated by rear, left, right, vertical, horizontal, top, bottom, inside, outside, clockwise, counterclockwise, etc. The positional relationship is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, rather than ...

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Abstract

The invention provides a rotor type aircraft water landing model test method. Firstly, a test device is installed, and electrical signal connection and test are completed. Then, a hydrodynamic high speed test trailer moves in an orbit and drives a model to move, when the speed of the model reaches the running speed required by the test and is stable, data acquisition equipment is started, after the normal working of the data acquisition equipment is determined, a model connection component is controlled to loosen the model, and the model freely separates and goes into water to slide. After the model goes into the water, the hydrodynamic high speed test trailer brakes and slows down until parking. After the test process is ended, the effectiveness of collected test data is analyzed, valid test parameters are recorded, and the valid test parameters comprises model weight, center of gravity, forward speed and sinking speed at the instant of going into water, a pitch angle, a roll angle and a yaw angle in a model initial state, and a pitch angle, a roll angle and a yaw angle, overload of center of gravity, cockpit overload, bottom pressure of the model after the model goes into the water. According to the method, a reliable basis is provided for effectively evaluating the water landing performance of a rotor type aircraft.

Description

technical field [0001] The invention relates to the technical field of rotorcraft testing, in particular to a ditching model test method for rotorcraft. Background technique [0002] Rotor-type aircraft generally complete take-off and landing on land. However, along with the promotion of the scope of use of rotor-type aircraft, there are more and more cases of using rotor-type aircraft to patrol and rescue at sea. When the rotorcraft breaks down, it needs to ditch on the sea surface. , [0003] Ditching performance is one of the important hydrodynamic performances of rotorcraft, which directly affects the safety of rotorcraft after ditching. When the helicopter makes an emergency landing on water, the impact load will cause the dynamic response of the aircraft structure, mainly in three aspects: on the one hand, the impact area will bear huge pressure, which may lead to local structural damage; on the other hand, it will cause the entire aircraft The severe flutter of the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M10/00
CPCG01M10/00
Inventor 焦俊廉滋鼎王明振魏飞刘晓峰
Owner CHINA SPECIAL TYPE FLIER RES INST
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