A double-body super large aspect ratio aircraft wind tunnel force test support device

A technology of force measurement test and support device, applied in the field of aerodynamics, can solve the problem that the aircraft model cannot be fixed for the test balance test, and achieve the effect of improving the test accuracy and the overall structure is simple

Active Publication Date: 2017-07-07
AERODYNAMICS NAT KEY LAB
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] The purpose of the present invention is to provide a support device for the wind tunnel dynamometer test of a double-body super-large aspect ratio aircraft, which solves the problem that the aircraft model cannot be tested with a fixed test balance in the wind tunnel test, and ensures the test accuracy

Method used

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  • A double-body super large aspect ratio aircraft wind tunnel force test support device
  • A double-body super large aspect ratio aircraft wind tunnel force test support device
  • A double-body super large aspect ratio aircraft wind tunnel force test support device

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Embodiment Construction

[0031] Such as figure 1 As shown, this type of aircraft is a new type of aircraft, which is characterized by long and narrow wings. This type of aircraft is different from current various types of aircraft. However, the aircraft with this type of structure has its own unique characteristics, so it is a development trend in some fields at present. To complete the finalization of the aircraft, it is necessary to test its aerodynamic indicators, and wind tunnel tests are essential. link.

[0032] figure 1 The model in is installed with a scale-down loading test device, in order to complete the fixation of the wing itself and ensure that it is not affected by external forces during the blowing process. Therefore adopt to put a wing cover on the wing, the inside of this cover is hollow structure, can make the wing cover wear on the wing. However, in the blowing process, in order to ensure the uniformity of the force on the wing, the wing cover cannot be in contact with the wing...

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Abstract

The invention discloses a support device for a wind tunnel force measurement test of a twin-body super-large aspect ratio aircraft, which comprises a wing cover, a balance cover and a rod-type balance; the balance cover is a cylindrical structure with two ends, and the balance cover is One end is connected to the wing cover, and the balance cover and the wing cover are integrated; both the balance cover and the wing cover are hollow structures, and the balance cover and the hollow structure in the wing cover are vertically connected ; The other end of the balance cover is provided with a joint for connecting with the pole. The invention firstly solves the problem of fixing the large aspect ratio aircraft model in the wind tunnel test, and at the same time, because of the uniqueness of the device structure, it can ensure that the model test can be effectively completed in the wind tunnel blowing test; Some test methods destroy the test environment, and ultimately the test results cannot be obtained.

Description

technical field [0001] The invention relates to the field of aerodynamics, in particular to a support device for a wind tunnel dynamometer test of a twin-body super large aspect ratio aircraft. Background technique [0002] Near-space solar-powered aircraft is a new concept of near-space aircraft. At present, its power source is generally solar energy, so it is called near-space solar-powered aircraft. The flight altitude of this kind of aircraft is between 20km and 30km, making full use of the characteristics of strong solar radiation and low wind speed in the high-altitude stratosphere atmosphere, and can fly higher and longer. It is low-cost, flexible, and can fly in a circle over a certain area, or fly globally as needed, which helps to solve the problems of limited flying height and endurance of traditional air platforms. This type of aircraft can stay in the air for a long time for military reconnaissance. It can search, intercept and analyze the signals sent by the e...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/04
Inventor 吴文华段焰辉余雷岳姝
Owner AERODYNAMICS NAT KEY LAB
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