CN114252262B - Helicopter main reducer hub load simulation loading device considering balanced static dead weight - Google Patents

Abstract

The present invention provides a helicopter main reducer propeller load simulation loading device that considers the balance of static self-weight. The present invention uses a force balance component combined with a pulley component and a tower force balancer to achieve static and dynamic large axial displacements. Provide constant balanced lift to ensure that the helicopter reducer is not subject to abnormal downward axial force throughout the entire process; through the split design of loading the axial force and shear force on the load bearing arm and the rotor load bearing seat, the force can be passed through The replacement of the support arm assembly can adapt to the propeller hub loading center position requirements of different main reducers. The entire device has strong versatility and simple structure. It cleverly overcomes the adverse effects of the weight of the simulated loading device on the main reducer, improves the versatility of the simulated loading device, and improves the switching efficiency of different types of test pieces.

Description

A simulated loading of helicopter main reducer blade load considering balanced static self-weight device

Technical field

The invention belongs to the technical field of helicopter main reducer simulation tests, and specifically relates to a helicopter main reducer propeller load simulation loading device that considers balanced static self-weight.

Background technique

The helicopter's main decelerator transmits the engine's speed and torque to the main rotor, tail rotor, hydraulic pump, generator and other accessories according to a certain transmission ratio. It is the core component of the helicopter. It needs to be subjected to load simulation loading tests during its research and development and production stages. . During the actual operation of the helicopter's main deceleration, in addition to the torque load of each shaft system, the main rotor shaft also bears loads from the rotor tension, shear force, bending moment, etc. These loads are transmitted to the rotor support bearings, transmission gears, and deceleration through the main rotor shaft. The reducer housing, etc., has an important impact on the bearing life, gear meshing and reducer housing deformation. Therefore, the helicopter main reducer propeller load simulation loading is an important part of the helicopter main reducer test, and its simulation of real working conditions Compliance is directly related to the success of the simulation test.

At present, for the simulated loading test of the helicopter main reducer blade load, the industry generally uses a method that combines static fatigue testing with dynamic working condition simulation tests: the static fatigue test mainly assesses the strength of the rotor shaft of the helicopter main reducer; dynamic working condition simulation The test mainly evaluates the overall dynamic performance of the main reducer. The dynamic test of the helicopter main reducer can be carried out in the ground helicopter iron bird test. The iron bird test is carried out directly with the rotor. The main rotor shaft is subject to loads such as rotor lift, shear force, bending moment, etc. The load conditions are consistent with the actual flight conditions. The consistency is high, but its cost is high. Most of the industry currently uses rolling bearing rotor loading bearing seats to simulate loading of the rotor shaft. The rotating axis of the rotor loading bearing seat is connected to the main rotor shaft of the helicopter, and its stationary outer shell applies tension, shear force, bending moment and other loads through hydraulic cylinder and other force loading devices. . Generally speaking, simulation test equipment requires a long design life, and due to the rotor shaft torque loading shaft of the helicopter main reducer, the rotor loading bearing seat will use a large diameter rolling bearing, resulting in a large mass of the entire simulation loading device, which will Abnormal downward axial load is applied to the main reducer rotor shaft in the non-operating state. However, the main reducer rotor shaft of some types of helicopters has strict restrictions on the downward axial load. Abnormal downward axial load may cause Causes damage to some structural parts, so the helicopter main reducer propeller load simulation loading test must consider overcoming the influence of the larger self-weight of the loading device. In addition, helicopter main reducer test benches are often compatible with the test functions of multi-type main reducers. Different types of reducers have different propeller hub centers and rotor shaft connection interfaces. In order to improve the rapid switching of different test pieces, the propeller hub load needs to be increased. Simulates the versatility of loading devices.

Contents of the invention

The purpose of the present invention is to solve the adverse effects of the larger self-weight of the loading device in the helicopter main reducer propeller load simulation loading test and to provide a helicopter main reducer propeller load simulation loading device that considers the balanced static self-weight.

A helicopter main reducer propeller load simulation loading device that considers balanced static self-weight, including a rotor loading bearing seat assembly, a lift loading assembly, a shear loading assembly and a force balance assembly. The rotor loading bearing seat assembly includes an output flange assembly, a tapered roller bearing, an inner bearing spacer ring, a bearing injection outer spacer ring, a bearing seat shell, a bearing seat rotating shaft, a rotor adapter flange, an axial force and Shear forces load the stressed arm assembly. The rotor loading bearing seat assembly is supported by a pair of tapered roller bearings in a back-to-back combination. The inner spacer ring of the bearing cooperates with the outer spacer ring of the bearing to adjust the preload force. A bearing seat rotation shaft is installed on the rotor loading bearing seat assembly. The upper part of the bearing seat rotation axis is connected to the output flange assembly through drum-shaped teeth, and the lower part of the bearing seat rotation axis is connected to the rotor adapter flange through end face teeth. The lift loading component and the shear loading component are connected to the bearing housing through the axial force and shear force loading force-bearing arm components. The force balancing component is connected to the shear loading component.

Further, the force balance assembly includes a lifting pulley assembly, a wire rope and a tower force balancer assembly. The lifting pulley assembly is connected to the tower force balancer assembly through a wire rope.

The beneficial effects of the present invention are:

By using a force balance component combined with a pulley component and a tower force balancer, a constant balanced lift can be provided during static and dynamic large axial displacements, ensuring that the helicopter reducer is not subject to abnormal downward axial force throughout the entire process; The split design of the axial force and shear force loading force supporting arm and the rotor loading bearing seat can be adapted to the propeller hub loading center position requirements of different main reducers by replacing the force supporting arm. The entire device has strong versatility and simple structure. It cleverly overcomes the adverse effects of the weight of the simulated loading device on the main reducer, improves the versatility of the simulated loading device, and improves the switching efficiency of different types of test pieces.

Description of the drawings

Figure 1 is a schematic structural diagram of the present invention;

Figure 2 is a schematic structural diagram of the present invention as seen from the top in direction A.

Detailed ways

The present invention will be further described below in conjunction with the accompanying drawings.

Figure 1 is a schematic structural diagram of a helicopter main reducer propeller load simulation loading device that considers balancing static self-weight in the preferred implementation of the invention. It mainly consists of a rotor loading bearing seat assembly 10, a lift loading assembly 20, a shear loading assembly 30 and a force balance. Composed of 40 components. The rotor loading bearing seat assembly 10 mainly includes an output flange assembly 11, a tapered roller bearing 12, a bearing inner spacer ring 13, a bearing injection outer spacer ring 14, a bearing housing 15, a bearing seat rotation shaft 16, and a rotor adapter. Flange 17, axial force and shear force loading force arm assembly 18; the lift loading assembly 20 and the shear loading assembly 30 are servo hydraulic cylinder loaders; the force balance assembly 40 consists of a lift pulley assembly 41, a wire rope 42 and It is composed of tower force balancer assembly 43.

The rotor loading bearing seat assembly 10 is supported by a pair of tapered roller bearings 12 in a back-to-back combination. The inner spacer ring 13 of the bearing cooperates with the outer spacer ring 14 of the bearing injection oil to adjust the preload force. The bearing group can withstand large axial force and radial force. and bending moment and other combined loads, the installation and deployment are simple, the load-bearing capacity is extremely strong, and it is suitable for the low-speed and large load conditions of the helicopter main reducer rotor shaft; the upper part of the bearing seat rotation axis 16 of the rotor loading bearing seat assembly 10 is connected to the output through drum-shaped teeth The flange assembly 11 is connected, which can realize the transmission of large rotor loading torque, and can realize the deviation of the torque loading axis and the rated coaxiality of the rotor loading bearing seat assembly 10 by 4'. It has a simple structure, easy installation and large compensation amount, and is suitable for helicopters. After the main reducer rotor shaft is in operation, the attitude changes due to tie rod deformation and temperature; the lower part of the bearing seat rotation axis 16 of the rotor loading bearing seat assembly 10 is connected to the rotor adapter flange 17 through end teeth, and the rotor adapter flange 17 is connected to the rotor shaft of the main reducer. By replacing the rotor adapter flange 17, the connection with the main reducer of different types of helicopters is realized; the inner diameter of the bearing seat rotating shaft 16 is larger, which is suitable for the main reducer of the double-rotor helicopter. Space is reserved for the inner rotor shaft to increase the versatility of the device.

The lift loading assembly 20 and the shear loading assembly 30 are connected to the bearing housing 15 through the axial force and shear loading force-bearing arm assembly 18 . The lift loading component 20 and the shear loading component 30 can be replaced according to the change of the rotor loading center point A on the helicopter main reducer test piece and the change of the simulated loading load, so as to adapt to the test requirements of different types of test rooms. The overall combined force of the four sets of lift cylinders provides the rotor lift simulation load. The lift loading components arranged symmetrically at 180° can achieve the rotor bending moment simulation load by applying different lift loads; the action axis of the shear loading component passes through the loading center point A, providing the rotor with a simulated load. Front and side shear simulated loads. The lift loading component 20 and the shear loading component 30 are both controlled by a hydraulic servo control system and can be loaded according to the helicopter's specific main reducer blade load spectrum.

The force balance component 40 is composed of a lift pulley component 41, a steel wire rope 42 and a tower force balancer component 43. The lift pulley component 41 can multiply the constant pulling force provided by the tower force balancer component 43, as shown in Figure 1 For example, the tower force balancer assembly 43 is set to a pulling force of 200kg. Finally, each force balance assembly 40 provides a pulling force of 800kg for the rotor loading bearing seat assembly 10. As shown in Figure 2, if 4 tower force balancer assemblies 43 are evenly distributed. , then the force balance assembly 40 provides a total pulling force of 3200kg to the rotor loading bearing seat assembly 10. Different layout methods of the force balance assembly 40 can be set according to the helicopter main reducer blade load to simulate the self-weight of the loading device and the actual test bench layout. Tension setting. The tower force balancer assembly 43 can maintain a constant balanced tension within a certain telescopic length range of the wire rope 42 .

In summary, the present invention provides a helicopter main reducer propeller load simulation loading device that considers balancing the static self-weight, which can balance the self-weight of the simulated loading device under static and dynamic conditions, thereby ensuring that the helicopter main reducer The test piece can be safely and reliably simulated propeller hub load on the test bench; the split design of the load-bearing arm through axial force and shear force loading and the design of the rotor adapter flange improve the versatility of simulated propeller hub load. performance and ease of use.

The present invention considers the static self-weight balance of the helicopter main reducer propeller load simulation loading device and uses a pair of rotors to load the bearing seat assembly 10. The bearing seat rotation axis 16 can be connected to different types of main reducer through the rotor adapter flange 17. The connection, and the bearing seat rotor has a larger inner diameter, which can adapt to the test connection requirements of the main reducer with double rotors; the axial force and shear force loading force-bearing arm and the rotor loading bearing seat are designed as two bodies, which can Through the replacement of the force-bearing arm, the propeller loading center position requirements of different main reducers can be adapted; the axial force and shear force load of the helicopter main reducer propeller load simulation loading device are evenly distributed on the force-bearing arm. The component adopts a pulley component and a tower force balancer combination, which can amplify the pulling force of the tower force balancer according to different pulley combinations, and balance the self-weight of the helicopter main reducer propeller load simulation loading device within a larger force range. In addition, Taking advantage of the constant force within the large telescopic stroke of the tower force balancer, it can still provide constant balanced lift when the main reducer is subjected to large axial tension and undergoes large axial displacement.

The above descriptions are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and changes. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention shall be included in the protection scope of the present invention.

Claims (1)

1. A balanced static self-weight helicopter main reducer propeller load simulation loading device, which is characterized by: including a rotor loading bearing seat assembly (10), a lift loading assembly (20), a shear loading assembly (30) and a force balance assembly (40); The rotor loading bearing seat assembly (10) includes an output flange assembly (11), a tapered roller bearing (12), a bearing inner spacer ring (13), a bearing oil injection outer spacer ring (14), a bearing The seat housing (15), the bearing seat rotation axis (16), the rotor adapter flange (17), the axial force and shear force loading force-bearing arm assembly (18); the rotor loading bearing seat assembly (10) is composed of A pair of tapered roller bearings (12) are supported in a back-to-back combination. The inner bearing spacer ring (13) cooperates with the bearing oil injection outer spacer ring (14) to adjust the preload force; the rotor loading bearing seat assembly (10) is equipped with a bearing. The upper part of the bearing seat rotating axis (16) is connected to the output flange assembly (11) through drum-shaped teeth, and the lower part of the bearing seat rotating axis (16) is connected to the rotor adapter flange (17) through end face teeth. ; The lift loading component (20) and shear loading component (30) are connected to the bearing housing (15) through the axial force and shear force loading force-bearing arm component (18), and the lift loading component (20) And the shear loading component (30) can be replaced according to the change of the rotor loading center point A on the helicopter main reducer test piece and the change of the simulated loading load; the force balance component (40) is connected to the shear loading component (30) ; The force balance component (40) includes a lift pulley component (41), a wire rope (42) and a tower force balancer component (43); the lift pulley component (41), the wire rope (42) and the tower force balancer component (43) CONNECTION.