CN117871093A - Helicopter main reducer propeller hub load simulation loading device - Google Patents
Helicopter main reducer propeller hub load simulation loading device Download PDFInfo
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- CN117871093A CN117871093A CN202311602392.4A CN202311602392A CN117871093A CN 117871093 A CN117871093 A CN 117871093A CN 202311602392 A CN202311602392 A CN 202311602392A CN 117871093 A CN117871093 A CN 117871093A
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- 239000003638 chemical reducing agent Substances 0.000 title claims abstract description 36
- 238000004088 simulation Methods 0.000 title claims abstract description 25
- 238000005452 bending Methods 0.000 claims abstract description 23
- 230000008878 coupling Effects 0.000 claims abstract description 21
- 238000010168 coupling process Methods 0.000 claims abstract description 21
- 238000005859 coupling reaction Methods 0.000 claims abstract description 21
- 230000000712 assembly Effects 0.000 claims description 5
- 238000000429 assembly Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 2
- 238000010008 shearing Methods 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 3
- 230000003068 static effect Effects 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000009661 fatigue test Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 206010034719 Personality change Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
Abstract
A helicopter main reducer hub load simulation loading device comprises a lift loading assembly, a shear loading assembly, a rotor wing loading bearing seat assembly and a bending moment loading assembly; the rotor wing loading bearing seat assembly comprises a bearing seat body, a lifting force loading outer ring, a lifting force loading inner ring, an inner ring rotary joint assembly and an outer ring rotary joint assembly; the lifting force loading outer ring is connected with the lifting force loading inner ring through the outer ring rotary joint assembly, and the lifting force loading inner ring is connected with the bearing seat body through the inner ring rotary joint assembly; the bending moment loading assembly comprises a universal coupling, a torque meter, a swinging hydraulic cylinder assembly and a fixed plate, one end of the universal coupling is connected with the connecting shaft, and the swinging hydraulic cylinder assembly is connected with the other end of the universal coupling through the torque meter, so that moment load is applied to the bearing seat body, and bending moment loading of the rotor shaft is realized. The invention reduces the influence of the gesture change on the precision of the force loading assembly and improves the loading stability and operability.
Description
Technical Field
The invention relates to the technical field of helicopter main reducer tests, in particular to a helicopter main reducer hub load simulation loading device.
Background
The main speed reducer of the helicopter is a transmission device for connecting an engine and a main rotor wing, and is a core component of the helicopter. When the main speed reducer of the helicopter runs, besides the torque loads of an engine input shaft, a rotor output shaft and accessory shafts, the rotor shaft also bears aerodynamic loads from the rotor, such as vertical lifting force, lateral shearing force, lateral bending moment and the like, and the loads are transmitted to a transmission part and a support part of the main speed reducer through the rotor shaft, so that the load simulation loading of the hub load of the main speed reducer of the helicopter is an important part of the main speed reducer test of the helicopter, and the simulation coincidence of the load simulation loading to the real working condition is directly related to the effectiveness of the simulation test.
At present, in the field of helicopter test, a method combining a static fatigue test and a dynamic working condition simulation test is generally adopted to carry out a helicopter main speed reducer hub load simulation loading test: the strength of the rotor shaft of the main speed reducer of the helicopter is mainly checked through static fatigue tests in the modes of hydraulic servo loading and the like; the dynamic working condition simulation test is mainly used for checking the overall dynamic performance of the main speed reducer. The ground helicopter iron bird test is an effective dynamic test, and because the helicopter is operated with a real rotor, the lift load condition of the main rotor is high in consistency with the actual flight condition, but the main purpose is to carry out the complete machine test of a helicopter flight control system and the like, and the cost is high. At present, a rotor hub load test of a main speed reducer of a helicopter generally needs to be carried out on an independent main speed reducer test bed, a rolling bearing rotor loading bearing seat is generally adopted to carry out simulated loading on a rotor shaft, a rotor loading bearing seat rotating shaft is connected with the main rotor shaft of the helicopter, and a static bearing seat shell of the rotor loading bearing seat is used for applying loads such as tension, shearing force, bending moment and the like through a force loading device such as a hydraulic cylinder.
Helicopter models are numerous, the form of its main reducer is various, wherein have some main reducer to adopt the flexible supporting mode of damping to fix, installation rigidity is lower, can lead to rotor loading bearing frame to appear rocking, especially the helicopter main reducer of twin-rotor, its internal rotation wing axle is longer relatively, rotor loading bearing frame's range of rocking can be bigger, rotor loading bearing frame's gesture change can lead to the control precision of force loading device such as pneumatic cylinder to descend, rotor loading bearing frame's design needs to consider rotor bearing frame and force loading device's motion decoupling. In addition, for a high-speed helicopter with a rigid rotor, the bending moment load of the rotor is quite large, the conventional mode of indirectly generating bending moment by making difference of the loading value of a lifting force loading device is not suitable any more, a pair of hydraulic cylinders are generally adopted to provide lifting force, the other pair of hydraulic cylinders provide pressure, and the loading stability and operability are poor.
Disclosure of Invention
The invention provides a helicopter main reducer hub load simulation loading device for overcoming the prior art. The device carries out optimal design to rotor loading bearing frame subassembly to adopt direct moment loading design, replaced conventional mode that produces the moment indirectly through lift loading device loading value difference, reduced the influence of gesture change to force loading device with the device, can realize the loading of big moment load, improved loaded stability and operability.
The helicopter main reducer hub load simulation loading device comprises a lift loading assembly, a shear loading assembly and a rotor loading bearing seat assembly, wherein the rotor loading bearing seat assembly is supported by a pair of tapered roller bearings in a back-to-back combination manner;
the bending moment loading assembly is also included; the rotor wing loading bearing seat assembly comprises a bearing seat body, a lifting force loading outer ring, a lifting force loading inner ring, an inner ring rotary joint assembly and an outer ring rotary joint assembly;
the lift force loading outer ring is connected with the lift force loading inner ring through the outer ring rotary joint assembly, the lift force loading outer ring can rotate around the outer ring rotary joint assembly, the lift force loading inner ring is connected with the bearing seat body through the inner ring rotary joint assembly, the lift force loading inner ring can rotate around the inner ring rotary joint assembly, the inner ring rotary joint assembly is orthogonally arranged with the outer ring rotary joint assembly, the lift force loading outer ring is perpendicular to the axial direction of a rotary shaft of the lift force loading inner ring, so that the lift force loading outer ring is always kept in a horizontal state, the lift force loading assembly is connected to the lift force loading outer ring, the shear force loading assembly penetrates through the lift force loading outer ring and is rotationally connected with the inner ring rotary joint assembly, and the axial direction of the rotational connection is parallel to the axial direction of the outer ring rotary joint assembly;
the bending moment loading assembly comprises a universal coupling, a torque meter, a swinging hydraulic cylinder assembly and a fixed plate, one end of the universal coupling is connected with a connecting shaft, the connecting shaft penetrates through a lifting force loading outer ring to be connected with an inner ring rotary joint assembly, the swinging hydraulic cylinder assembly is connected with the other end of the universal coupling through the torque meter, so that moment load is applied to a bearing seat body, bending moment loading of a rotor shaft is achieved, the swinging hydraulic cylinder assembly and the torque meter are subjected to closed-loop control, and balance moment is applied by the fixed plate.
Further, the universal coupling is a spline housing universal coupling.
Compared with the prior art, the invention has the beneficial effects that:
according to the rotor loading bearing seat assembly, the rotor loading bearing seat assembly is optimally designed, and the motion decoupling design of the joint of the rotor loading bearing seat assembly and the force loading device is adopted, so that the influence of the posture change of the rotor loading bearing seat on the precision of the force loading assembly is solved, and the loading precision of the lifting load is improved; through moment loading assembly innovation design, realize the application of bigger rotor moment load to loaded stability and operability have been improved.
The technical scheme of the invention is further described below with reference to the accompanying drawings and examples:
drawings
The drawings that form a part of this application are intended to illustrate embodiments of the present invention and, therefore, not to limit the invention in any way.
FIG. 1 is an isometric view of a helicopter main reducer hub load simulator loader of the present invention; to illustrate construction details;
FIG. 2 is a front cross-sectional view of a helicopter main reducer hub load simulation loading apparatus illustrating the main components according to an embodiment of the invention;
FIG. 3 is a side view of a helicopter main reducer hub load simulation loading apparatus in accordance with an embodiment of the present invention illustrating side structural details;
FIG. 4 is a top view, C, of a helicopter main reducer hub load simulation loading apparatus illustrating details of a top view structure in accordance with an embodiment of the present invention;
figure 5 is an isometric view of a helicopter main reducer hub load simulation loading apparatus in a deflected state illustrating the rotor loading bearing housing assembly in a deflected state and in a motion decoupling mode of operation in accordance with an embodiment of the present invention.
The main speed reducer of the 10-helicopter, a 20-rotor power loading crowned tooth coupler, a 30-lift loading assembly, a 40-shear loading assembly, a 50-bending moment loading assembly, a 51-universal coupler, a 52-torque meter, a 53-swing hydraulic cylinder assembly, a 54-fixed plate, a 60-rotor loading bearing seat assembly, a 61-bearing seat shell, a 62-lift loading outer ring, a 63-lift loading inner ring, a 64-inner ring rotary joint assembly and a 65-outer ring rotary joint assembly.
Detailed Description
Embodiments of the technical scheme of the present invention will be described in detail below with reference to the accompanying drawings. Unless otherwise defined, technical or scientific terms used herein should be given the ordinary meaning as understood by one of ordinary skill in the art to which this invention belongs.
From fig. 1, 2 and 3, fig. 4 can be seen that the helicopter main reducer hub load simulation loading device of the invention comprises a lift loading assembly 30, a shear loading assembly 40, a bending moment loading assembly 50 and a rotor loading bearing seat assembly 60, wherein the rotor loading bearing seat assembly 60 is supported by a pair of tapered roller bearings in a back-to-back combination;
in order to solve the problem that the attitude change of the rotor loading bearing seat affects the precision of the force loading device, the common rotor loading bearing seat needs to be optimally designed in order to realize larger bending moment load.
Preferably, the rotor loading bearing seat assembly 60 is supported by a pair of tapered roller bearings in a back-to-back combination way, the bearing group can bear large axial force, radial force, bending moment and other combined loads, the installation and the allocation are simple, the bearing capacity is extremely strong, and the rotor loading bearing seat assembly is suitable for the working condition of low speed and large load of a rotor shaft of a main speed reducer of a helicopter; the upper part of the rotating shaft of the rotor loading bearing seat assembly 60 is connected through the rotor power loading crowned tooth coupling 20, so that the transmission of the rotor rotating speed n and the torque T can be realized, and the power loading of the rotor shaft can be realized.
Preferably, the lift loading assembly 30 and the shear loading assembly 40 are servo-controlled hydraulic cylinder assemblies, and the application of the lift load Fa and the shear load Ft can be realized through closed-loop feedback control of a force sensor and a servo valve.
The rotor loading bearing seat assembly 60 comprises a bearing seat body 61, a lift loading outer ring 62, a lift loading inner ring 63, an inner ring rotary joint assembly 64 and an outer ring rotary joint assembly 65, wherein the lift loading outer ring 62 is connected with the lift loading inner ring 63 through the outer ring rotary joint assembly 65, the lift loading outer ring 62 can rotate around the outer ring rotary joint assembly 65, the lift loading inner ring 63 is connected with the bearing seat body 61 through the inner ring rotary joint assembly 64, the lift loading inner ring 63 can rotate around the inner ring rotary joint assembly 64, the inner ring rotary joint assembly 64 is orthogonally arranged with the outer ring rotary joint assembly 65, the axial direction of a rotating shaft of the lift loading outer ring 62 and the lift loading inner ring 63 is perpendicular, and the two orthogonal rotating directions are combined to realize the inclination of any space angle, so that the lift loading outer ring 62 always keeps a horizontal state under the inclination condition of any angle of the rotor loading bearing seat assembly 60, the lift loading outer ring 30 is ensured not to generate large displacement expansion, the servo control hydraulic cylinder assembly is prevented from keeping constant force output in a larger displacement range, and the control precision of the lift loading outer ring 62 is improved;
the lift loading assembly 30 is connected to the lift loading outer ring 62, the shear loading assembly 40 passes through the hole of the lift loading outer ring 62 and is rotationally connected with the pin shaft on the inner ring rotary joint assembly 64, and the axial direction of the rotational connection is parallel to the axial direction of the outer ring rotary joint assembly 65, so that the shearing force is directly applied to the bearing seat body 61 of the rotor loading bearing seat assembly 60, and the force is transmitted to the rotating rotor shaft of the main speed reducer 10 of the helicopter through the internal bearing assembly, so that the shearing force loading of the rotor shaft is realized.
Wherein, two lift loading assemblies 30 of symmetrical arrangement are connected to lift loading outer loop 62 through the joint bearing connection bearing frame, the lift load of exerting is transmitted to bearing frame body 61 through lift loading outer loop 62 by quadrature inner ring revolute joint assembly 64 and outer ring revolute joint assembly 65, bearing frame body 61 contains the bearing frame casing, bearing frame rotation axis 66 and rotor adapter flange 67, thereby directly apply the lift to the shell of rotor simulation loading bearing frame 60, transmit the lift on the rotatory rotor shaft of helicopter main reducer 10 through inside bearing assembly, thereby realize the lift loading of rotor shaft, the loading of lift is simpler because not used as the difference synthetic moment of flexure, the loading operation is simpler, two lift loading assemblies 30 do the equivalent loading more be favorable to the atress balance of lift loading outer loop 62 and lift loading inner loop 63.
The helicopter main reducer 10 is a test piece, is generally flexibly supported by a pull rod, is connected with a rotor when a rotor shaft flies, bears the pneumatic load of the rotor, comprises lift force, shearing force, bending moment and the like, and is connected with a bearing seat rotating shaft 66 of the rotor loading bearing seat assembly 60 through a rotor adapter flange 67 during a simulated loading test.
Preferably, the bending moment loading assembly 50 comprises a universal coupling 51, a torque meter 52, a swinging hydraulic cylinder assembly 53 and a fixed plate 54, one end of the universal coupling 51 is connected with a connecting shaft, the connecting shaft passes through a hole of a lifting force loading outer ring 62 and is connected with a pin shaft of an inner ring rotary joint assembly 64, the swinging hydraulic cylinder assembly 53 is connected with the other end of the universal coupling 51 through the torque meter 52, so that moment load is applied on a bearing seat body 61, bending moment loading of a rotor shaft is realized, the swinging hydraulic cylinder assembly 53 and the torque meter 52 are subjected to closed-loop control, and balance moment is applied by the fixed plate 54. The moment load M is applied to the rotor simulated loading bearing seat body 61, the bending moment load is directly applied through a separate bending moment loading assembly, and the loading operation is simpler.
In addition, the universal coupling 51 of the bending moment loading assembly 50 is a spline housing universal coupling, the universal couplings are arranged at two ends of the universal coupling 51, the intermediate shaft is an axially telescopic spline housing tooth, the posture change of the rotor loading bearing seat assembly 60 can be compensated at the same time, and the moment load M is ensured to be applied to the rotor simulation loading bearing seat body 61.
In summary, through the motion decoupling design of the joint of the rotor wing bearing seat assembly and the force loading device, the influence of the posture change of the rotor wing loading bearing seat on the precision of the force loading device is solved, and the loading precision of the lifting load is improved; through moment loading subassembly innovation design, realize the application of bigger rotor moment load to improve loaded stability and operability.
The present invention has been described in terms of preferred embodiments, but is not limited to the invention, and any equivalent embodiments can be made by those skilled in the art without departing from the scope of the invention, as long as the equivalent embodiments are possible using the above-described structures and technical matters.
Claims (5)
1. A helicopter main reducer hub load simulation loading device comprises a lift loading assembly (30), a shear loading assembly (40) and a rotor loading bearing seat assembly (60), wherein the rotor loading bearing seat assembly (60) is supported by a pair of tapered roller bearings in a back-to-back combination manner;
the method is characterized in that: also comprises a bending moment loading assembly (50);
the rotor loading bearing seat assembly (60) comprises a bearing seat body (61), a lifting force loading outer ring (62), a lifting force loading inner ring (63), an inner ring rotary joint assembly (64) and an outer ring rotary joint assembly (65); the lift force loading outer ring (62) is connected with the lift force loading inner ring (63) through the outer ring rotary joint assembly (65), the lift force loading outer ring (62) can rotate around the outer ring rotary joint assembly (65), the lift force loading inner ring (63) is connected with the bearing seat body (61) through the inner ring rotary joint assembly (64), the lift force loading inner ring (63) can rotate around the inner ring rotary joint assembly (64), the inner ring rotary joint assembly (64) is orthogonally arranged with the outer ring rotary joint assembly (65), the axial directions of the rotation shafts of the lift force loading outer ring (62) and the lift force loading inner ring (63) are perpendicular, so that the lift force loading outer ring (62) always keeps a horizontal state, the lift force loading assembly (30) is connected to the lift force loading outer ring (62), the shear force loading assembly (40) penetrates through the lift force loading outer ring (62) and is rotationally connected with the inner ring rotary joint assembly (64), and the axial direction of the rotational connection is parallel to the axial direction of the outer ring rotary joint assembly (65);
the bending moment loading assembly (50) comprises a universal coupling (51), a torque meter (52), a swinging hydraulic cylinder assembly (53) and a fixed plate (54), one end of the universal coupling (51) is connected with a connecting shaft, the connecting shaft penetrates through a lifting force loading outer ring (62) to be connected with an inner ring rotary joint assembly (64), the swinging hydraulic cylinder assembly (53) is connected with the other end of the universal coupling (51) through the torque meter (52) so that moment load is applied on a bearing seat body (61), the bending moment loading of a rotor shaft is achieved, the swinging hydraulic cylinder assembly (53) and the torque meter (52) are subjected to closed-loop control, and balance moment is applied by the fixed plate (54).
2. The helicopter main reducer hub load simulation loading device of claim 1, wherein: the universal coupling (51) is a spline housing universal coupling.
3. The helicopter main reducer hub load simulation loading device of claim 1, wherein: the upper part of the rotating shaft of the rotor simulated loading bearing seat (60) is connected with a rotor power loading crowned tooth coupler (20).
4. The helicopter main reducer hub load simulation loading device of claim 1, wherein: the lift force loading assembly (30) and the shear force loading assembly (40) are servo-controlled hydraulic cylinder assemblies.
5. The helicopter main reducer hub load simulation loading device of claim 1, wherein: two symmetrically arranged lift force loading assemblies (30) are connected to a lift force loading outer ring (62) through a knuckle bearing connecting bearing seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311602392.4A CN117871093A (en) | 2023-11-28 | 2023-11-28 | Helicopter main reducer propeller hub load simulation loading device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311602392.4A CN117871093A (en) | 2023-11-28 | 2023-11-28 | Helicopter main reducer propeller hub load simulation loading device |
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| Publication Number | Publication Date |
|---|---|
| CN117871093A true CN117871093A (en) | 2024-04-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311602392.4A Pending CN117871093A (en) | 2023-11-28 | 2023-11-28 | Helicopter main reducer propeller hub load simulation loading device |
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| CN (1) | CN117871093A (en) |
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- 2023-11-28 CN CN202311602392.4A patent/CN117871093A/en active Pending
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