The invention discloses a three-rotor-wing main rotor hub of an unmanned helicopter. The three-rotor-wing main rotor hub comprises a main shaft, an inclinator static disc, a middle connector, an inclinator movable disc, rotor clamps, bulb head connecting rods, rocker arm connecting rods, an inclinator bearing, connecting shaft blocks and a static disc lower connecting rod. The middle connector is assembled at the top end of the main shaft and connected with all transverse shafts through the multiple connecting shaft blocks to be assembled. Each transverse shaft is provided with the corresponding rotor clamp. The rotor clamps are used for installation of helicopter rotor wings. Each rotor clamp rocker arm is provided with the corresponding rocker arm connecting rod used for installation of a lower inclinator. The inclinator movable disc and the inclinator static disc are assembled at the lower end of the main shaft. The inclinator bearing is assembled in the inclinator static disc. The inclinator movable disc is triangular. The three corners of the inclinator movable disc are connected with the bulb head connecting rods correspondingly. The bulb head connecting rods are connected with the rotor clamp rocker arms. The main shaft drives the rotor clamps to rotate, then the inclinator movable disc is driven to rotate, the screw pith is controlled, and the posture of the helicopter is changed.

Three-rotor-wing main rotor hub of unmanned helicopter

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.

Aerodynamic interference measuring method for helicopter coaxial rigid rotor model

The invention provides an automatic inclinator suitable for multiple propeller hub configurations. The automatic inclinator suitable for the multiple propeller hub configurations comprises an immobilering component, a moving ring component, a spherical hinge component, a variable pitch pull rod component, a torque arm component and a guide cylinder, wherein a rotor shaft is rotationally arrangedin the guide cylinder; the immobile ring component sleeves outside the guide cylinder and is connected with the guide cylinder through the spherical hinge component; an annular step extends from the immobile ring component in the axial direction of the guide cylinder; the moving ring component rotationally sleeves outside the step; a plurality of fork lugs are arranged in the circumferential direction of the moving ring component; one end of the torque arm component is selectively connected with the fork lug; the other end of the torque arm component is connected with a propeller hub; one endof the variable pitch pull rod component is selectively connected with the fork lug; and the other end of the variable pitch pull rod component is connected to a supporting arm of the propeller hub. The structural design of the automatic inclinator in the form of a multi-fork-lug moving ring is skillful, and the propeller hub configurations placed at multiple angles can be met only by changing themounting positions of the variable pitch pull rod, a torque arm and an anti-torque arm.

Automatic inclinator suitable for multiple propeller hub configurations

The invention provides a wind tunnel test rotor operation mechanism. The wind tunnel test rotor operation mechanism comprises a plurality of linear drivers (1), a non-rotating ring (3), a spherical hinge (5), and a rotating ring (8). The linear drivers (1) are movably connected with the non-rotating ring (3) in a hinged manner. The non-rotating ring (3) is connected with the spherical hinge (5), and rotates around the center of the spherical hinge (5). The rotating ring (8) is movably connected with the non-rotating ring (3), and rotates with respect to the non-rotating ring (3). The rotating ring (8) is movably connected with one end of a pull rod (4), and the other end of the pull rod (4) is movably connected with a rotor installation part (6) of a rotor transmission shaft (7), and the rotor transmission shaft (7) penetrates the spherical hinge (5). The wind tunnel test rotor operation mechanism is advantageous in that the collective pitch of the rotor and the cyclic pitch of the rotor are operated, and operation is simple, safe, and reliable; a dynamic characteristic is good, and operation precision is high; a structure is compact, and a size is small; during the use in a wind tunnel test, the data of the wind tunnel test is more reliable.

Wind tunnel test rotor operating mechanism

The invention relates to the field of helicopter propeller pitch angle measuring, and especially relates to a difference calculation method of helicopter propeller pitch angles. The difference calculation method of helicopter propeller pitch angles comprises following steps: a first angle sensor and a second angle sensor are arranged on a blade installation surface A1 and a central member plane B1respectively; a rectangular coordinate system is established, and a model is established and simplified; the rotating directions of the blade installation surface A1 and the central member plane B1 on the rectangular coordinate system X axis, Y axis, and Z axis are controlled to simulate main rotor shaft non-vertical situations, and calculate a corresponding propeller pitch angle. The differencecalculation method of helicopter propeller pitch angles is capable of realizing measurement on helicopter propeller pitch angles when the main rotor shafts are not designed to be vertical. Compared with the prior art, the advantages are that: the precision is high, the guarantee efficiency is high, the personal safety of measuring personnel is ensured, and labor intensity is reduced.

Difference calculation method of helicopter propeller pitch angles

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 rotors

Hong Yongjun

Papers

Simple rotor mechanism of coaxial dual-rotor helicopter test stand