Aircraft flight attitude simulation supporting device

A technology of flight attitude and support device, which is applied in the field of flight attitude simulation in wind tunnel tests, can solve the problems of inability to simulate the flight attitude of an aircraft, and achieve the effects of avoiding device kinematic errors, providing accuracy, and improving altitude

Pending Publication Date: 2022-05-10
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0004] However, after the icing wind tunnel test, it is necessary to simulate the flight attitude of the aircraft outside the icing wind tunnel. Because the weather cannot be simulated outside the icing wind tunnel, the use of three-degree-of-freedom spherical joints cannot make the aircraft model form a certain attitude. To achieve the effect of simulating the flight attitude of the aircraft, so the present invention proposes a support device for simulating the flight attitude of the aircraft

Method used

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Embodiment Construction

[0037] The following description provides many different embodiments, or examples, for implementing various features of the invention. The elements and arrangements described in the following specific examples are only used to express the present invention in a concise manner, and are only used as examples rather than limiting the present invention.

[0038] In describing the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", " The orientation or positional relationship indicated by "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying the referred device or Elements must have certain orientations, be constructed and operate in certain orientations, and therefore should not be construed as limitati...

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Abstract

The invention belongs to the field of wind tunnel test flight attitude simulation, and particularly relates to an aircraft flight attitude simulation supporting device which comprises a yaw mechanism, a pitching mechanism and a rolling mechanism, the yaw mechanism is connected with the pitching mechanism, the pitching mechanism is connected with the rolling mechanism, and the rolling mechanism is used for being connected with an aircraft model; the yawing mechanism enables the pitching mechanism, the rolling mechanism and the airplane model to synchronously rotate together, and enables the airplane model to realize yawing rotation; the pitching mechanism enables the rolling mechanism and the airplane model to synchronously rotate together, and enables the airplane model to realize pitching rotation; and the rolling mechanism enables the airplane model to realize rolling rotation. According to the supporting device disclosed by the invention, the flight model can simulate the flight attitude of the airplane in the absence of meteorological conditions.

Description

technical field [0001] The invention belongs to the field of wind tunnel test flight attitude simulation, and in particular relates to an aircraft flight attitude simulation support device. 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 o...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/04G01M9/08B64F5/60G09B25/00
CPCG01M9/04G01M9/08B64F5/60G09B25/00
Inventor 任忠才聂博文岑飞刘志涛张磊郭天豪蒋永
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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