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Wind tunnel test data correction method for near-space high-aspect ratio flexible spacecraft

A wind tunnel test and large aspect ratio technology, applied in the field of aerodynamics, can solve the problems of large difference, uncontrollable rate design and flight simulation to provide aerodynamic data, and inability to accurately simulate the aerodynamic characteristics of solar drones, etc., to achieve stability The effect of flying

Active Publication Date: 2017-06-13
CHINA ACAD OF AEROSPACE AERODYNAMICS
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AI Technical Summary

Problems solved by technology

However, conventional low-speed wind tunnel test methods cannot accurately simulate the aerodynamic characteristics of solar-powered UAVs after being subjected to aerodynamic loads. The results of wind tunnel tests are quite different from actual results, and cannot provide accurate aerodynamic data for control rate design and flight simulation.

Method used

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  • Wind tunnel test data correction method for near-space high-aspect ratio flexible spacecraft
  • Wind tunnel test data correction method for near-space high-aspect ratio flexible spacecraft
  • Wind tunnel test data correction method for near-space high-aspect ratio flexible spacecraft

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Embodiment Construction

[0037] At present, the domestic wind tunnel test is to carry out the conventional force measurement test of the rigid body model through the design of a reasonable scale model of the aircraft. The pilot projects mainly include three items:

[0038] 1) Empennage installation angle test: find the appropriate empennage installation angle through the test method.

[0039] 2) Basic state test: measure the aerodynamic force c at different angles of attack α and sideslip angle β x , c y , c z and aerodynamic distance m x , m y , m z . where c x is the drag coefficient, c y is the lift coefficient, c z is the lateral force coefficient, m x is the rolling moment coefficient, m y is the yaw moment coefficient, m z is the pitching moment coefficient.

[0040] 3) Rudder effect test: when the deflection angle of the control rudder surface is measured, c under different α and β x , c y , c z , m x , m y , m z amount of change.

[0041] The invention corrects the wind tun...

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Abstract

The invention discloses a wind tunnel test data correction method for a near-space high-aspect ratio flexible spacecraft. The wind tunnel test data correction method comprises a basic state data correction of wind tunnel test, a horizontal tail installation angle adjustment and a data correction of wind tunnel test pilot. The wind tunnel test data correction method combines the prior test conditions for wind tunnel tests in China and completes the correction of the wind tunnel test data of rigid body shape by means of aeroelastic and fluid mechanics analysis. The wind tunnel test data correction method can provide accurate aerodynamic data for near-space high-aspect ratio flexible spacecraft control rate design and flight simulation and ensure that the aircraft can stably flight under the condition of large deformation near the space.

Description

technical field [0001] The invention relates to a method for correcting wind tunnel test data of a flexible aircraft with a large aspect ratio in an adjacent space, which is used for the control rate design and flight simulation of a flexible aircraft with a large aspect ratio in an adjacent space, and belongs to the field of aerodynamics. Background technique [0002] With the continuous development of scientific theory, engineering design and manufacturing technology, ultra-long airborne capability has become an important direction for the development of modern UAVs. Flexible aircraft with large aspect ratios in adjacent spaces are typically represented by solar-powered UAVs, such as European UAVs. Zephyr, Heliplat, Solar Impulse, Vulture, SolarEagle in the United States, CH-T3, CH-T4 in China, etc., their primary design goals in general are to increase the cruising altitude of the aircraft and realize the ultra-long airborne capability of the aircraft, and use this Based ...

Claims

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Application Information

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IPC IPC(8): G01M9/00
CPCG01M9/00
Inventor 付义伟孙凯军包晓翔
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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