A Design Method of Helicopter Rear Mounted Flat Tail Rudder Surface Angle Control

A helicopter, rear-mounted technology, applied in the design field of helicopter rear-mounted flat tail rudder deflection angle control, can solve problems such as repeated design and influence on development progress, achieve the effect of reducing the number of test points and improving design efficiency

Active Publication Date: 2022-02-11
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Application Information

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Problems solved by technology

[0003] The purpose of the present invention is to overcome the deficiencies in the prior art, to provide a design method for the control of the deflection angle of the rear-mounted flat tail rudder surface of a helicopter, which improves the design efficiency and avoids solving such problems in the flight test process after the development of the helicopter is completed. And the resulting repeated design, affecting the development progress and other issues

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  • A Design Method of Helicopter Rear Mounted Flat Tail Rudder Surface Angle Control

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Embodiment Construction

[0029] All features disclosed in this specification, or all methods or processes implicated in the disclosure, in addition to the features and / or steps other than each other, can be combined and / or extended, replaced in any manner.

[0030] like figure 1 As shown, a design method of a helicopter rear type tail rudder surface decision angle control, including steps:

[0031] S1, a flat wind tunnel test is performed on the non-mounted helicopter model, obtaining the helicopters of the helicopters in different wind speeds and the torque and attitude angle of the pitching moment in the case of un installed.

[0032] S2, the helicopter model in step S1 is equipped with a flat tail, and the tail-tail angle can be adjusted, and the helicopter model of the plus tail is tested.

[0033] In an alternative embodiment, in step S1, the sub-step:

[0034] S11, adjust the wind speed to a given wind speed;

[0035] S12, the resistance of the body is measured;

[0036] S13, adjust the axial ti...

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Abstract

The invention discloses a method for designing the deflection angle control of the rear-mounted flat tail rudder surface of a helicopter, which includes the step of: S1, performing a trim wind tunnel test on a helicopter model without a flat tail, and obtaining the full range of the helicopter without a flat tail at different wind speeds. aircraft pitching moment and attitude angle; S2, add a horizontal tail to the helicopter model in step S1, and the horizontal tail deflection angle can be adjusted, and carry out a trim wind tunnel test on the helicopter model equipped with a horizontal tail. The invention improves the design efficiency, avoids solving such problems during the flight test process after the development of the helicopter is completed, and thus brings about problems such as repeated design and influence on the development progress.

Description

Technical field [0001] The present invention relates to the field of helicopter flight control, and more specifically, involving a design method of a helicopter rear type tail rudder vectic angle control. Background technique [0002] The rear-type width layout facilitates increasing the longitudinal stability of the helicopter, but as the flight speed changes, the interference effect of the rotor tail on the tail is changed. For example, when the low speed is flying, the down-down rotor tail is impacted to the tail, so that the tail is stronger downward, causing the helicopter to take up. As the speed increases, the rotor tail flow is moved upward. The rotor tail flow is gradually reduced, so that the lift of the tail-tail is gradually recover, causing the helicopter to take a head. The sudden down and lingering of the helicopter will cause the pilot visual observation difficult, and the risk of flight is increased, and the comfort is limited. Inventive content [0003] It is a...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/00B64F5/60G01M9/00
CPCB64F5/00B64F5/60G01M9/00
Inventor 王畅黄明其徐栋霞彭先敏袁红刚杨永东
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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