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A helicopter tail rotor simulation system for wind tunnel test

A technology for a helicopter tail rotor and a simulation system is applied in the field of a helicopter tail rotor simulation system for wind tunnel tests, and can solve problems such as poor adaptability and single function.

Active Publication Date: 2020-10-16
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] However, the existing tail rotor simulation system can only realize a single function, has poor adaptability, and can only be tested on a single type of helicopter

Method used

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  • A helicopter tail rotor simulation system for wind tunnel test
  • A helicopter tail rotor simulation system for wind tunnel test
  • A helicopter tail rotor simulation system for wind tunnel test

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Embodiment Construction

[0017] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0018] refer to figure 1 with figure 2 , the wind tunnel test helicopter tail rotor simulation system of the embodiment of the present invention comprises a base 1, a drive mechanism 2, a support arm 3, a tilt adjustment mechanism 4 and a tail rotor transmission measurement and manipulation module 5, and one end of the support arm 3 is a fixed end , the other end is a tilting end, the fixed end of the support arm 3 is connected to the base 1 in rotation, the...

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Abstract

The invention relates to the technical field of wind tunnel tests, and discloses a helicopter tail rotor simulation system for wind tunnel tests, which includes a base, a drive mechanism, a support arm, a tilt adjustment mechanism, and a tail rotor transmission measurement and control module, and one end of the support arm The fixed end is the fixed end, and the other end is the tilting end. The fixed end of the support arm is rotatably connected to the base. The driving mechanism is used to drive the support arm to rotate around the base. The tilt adjustment mechanism is installed on the tilt end of the support arm. The mechanism can move along the axial direction of the support arm and rotate around the axial direction of the support arm, and the tail rotor transmission measurement manipulation module is rotationally connected with the tilt adjustment mechanism. The invention can simulate the flight states of different helicopters at different inclination angles.

Description

technical field [0001] The invention relates to the technical field of wind tunnel tests, in particular to a helicopter tail rotor simulation system for wind tunnel tests. Background technique [0002] In the helicopter wind tunnel test, it is necessary to study the aerodynamic performance of the rotor, fuselage, and tail rotor assembly under different inclination angles. The tail rotor simulation system needs to have: the relationship between the position of the rotor and the rotor at different inclinations during the test; it can simulate the position relationship between the rotor and the tail rotor of different types of helicopters; it can drive the rotation of the tail rotor, change the collective pitch angle of the tail rotor, and measure the aerodynamic force of the tail rotor. Load and other functions. [0003] However, the existing tail rotor simulation system can only realize a single function, has poor adaptability, and can only be tested on a single type of heli...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 黄志远杨永东彭先敏章贵川唐敏赵亮亮
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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