Patent
Simple rotor mechanism of coaxial dual-rotor helicopter test stand
TLDR
In this article, a simple rotor mechanism of a coaxial dual-rotor helicopter test stand is described, where the actuator group is connected with the lower control system to control synchronous motion of the first paddle arm and second paddle arm.Abstract:
The invention relates to a simple rotor mechanism of a coaxial dual-rotor helicopter test stand The rotor mechanism comprises an inner shaft, an outer shaft, an actuator group, a lower control system, an upper control system, an upper rotor propeller hub and a lower rotor propeller hub, wherein the upper rotor propeller hub comprises a first propeller hub seat, and a first paddle arm arranged on the first propeller hub seat in a full articulation manner; the lower rotor propeller hub comprises a second propeller hub seat and a second paddle arm arranged on the second propeller hub seat in a full articulation manner; the upper control system is connected with the first paddle arm; the lower control system is connected with the second paddle arm; the upper control system is connected with the lower control system via an intermediate draw bar; and the actuator group is connected with the lower control system to control synchronous motion of the first paddle arm and the second paddle arm The mechanism can achieve collective pitch control and cyclic pitch change of coaxial dual rotors, and effectively achieves various dynamic tests of the helicopter such as upper and lower rotor aerodynamic characteristics of the coaxial dual rotors, dynamic stability of the rotors, and moving part loads of the rotorsread more
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Patent
Three-rotor-wing main rotor hub of unmanned helicopter
Wang Chuan,Yang Wei +1 more
TL;DR: In this paper, a three-rotor-wing main rotor hub of an unmanned helicopter is described, which consists of a main shaft, an inclinator static disc, a middle connector, a movable disc, rotor clamps, bulb head connecting rods, and a rocker arm connecting rods.
Patent
Aerodynamic interference measuring method for helicopter coaxial rigid rotor model
Abstract: The invention discloses an aerodynamic interference measuring method for a helicopter coaxial rigid rotor model, and belongs to the technical field of wind tunnel test. The measuring method is mainlyrelying on a twin rotors wind tunnel test platform, and can be used for conducting the aerodynamic load and aerodynamic interference test of the coaxial rigid rotor model with large forward ratio. According to the measuring method, the aerodynamic load of the upper hub model, the lower hub model, the upper rotor model, the lower rotor model and the different combinations of the four models are respectively measured by the upper and lower rotor measuring systems, and the problem of separately measuring the aerodynamic performance of the upper and lower hub models and the upper and lower rotor models by acquiring the separate aerodynamics of the four models and the aerodynamic interference laws in different combinations. The method can be used for the study of the aerodynamic interference characteristics of twin rotors.
Patent
Automatic inclinator suitable for multiple propeller hub configurations
Zhang Fei,Wang Jie,Pan Zhujin,Wang Jian,Song Haijuan,Li Lei,Lu Yuhui,Yang Guangyong,Dong Jinshan,Li Yongxin +9 more
TL;DR: In this paper, an automatic inclinator suitable for multiple propeller hub configurations is presented, which consists of an immobilering component, a moving ring component, spherical hinge component, variable pitch pull rod component, torque arm component and a guide cylinder.
Patent
Wind tunnel test rotor operating mechanism
TL;DR: In this paper, a wind tunnel test rotor operation mechanism consisting of a plurality of linear drivers (1), a non-rotating ring (3), a spherical hinge (5), and a rotating ring (8) is presented.
Patent
Difference calculation method of helicopter propeller pitch angles
He Chenfei,Chen Yujin,Wu Hangwei +2 more
TL;DR: In this article, a difference calculation method of helicopter propeller pitch angles is proposed, where a first angle sensor and a second angle sensor are arranged on a blade installation surface A1 and a central member plane B1respectively.
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Patent
Coaxial drive and control structure for coaxial contrarotation rotor helicopter
TL;DR: In this paper, the authors proposed a coaxial drive and control structure for the coaxial contrarotation rotor helicopter, which can provide more upper rotors and more lower rotors, lifting power can be improved, full differentiating control can be realized, and manufacturing and processing costs of the spindle also can be reduced.
Patent
Standalone control system of coaxial double-rotor unmanned helicopter control system
TL;DR: In this paper, the authors presented a standalone control system of a double-rotor unmanned helicopter control system consisting of a rotor system, a control system, and a transmission system.
Patent
Device for testing coaxial inversion rotor wing of helicopter
TL;DR: In this article, a device for testing a coaxial inversion rotor wing of a helicopter is presented, where a motor is installed on a base and connected to an inner shaft transmission and an outer shaft transmission in series.
Patent
Dynamic balance testing machine
TL;DR: In this article, the authors propose to close a solenoid valve when the number of rotations reached the upper limit value of a comparing circuit and to open the same when reached the lower limit value thereof.