CN110641735A - Fatigue test loading device for tail rotor hub journal shaft sleeve assembly - Google Patents
Fatigue test loading device for tail rotor hub journal shaft sleeve assembly Download PDFInfo
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- CN110641735A CN110641735A CN201910931325.4A CN201910931325A CN110641735A CN 110641735 A CN110641735 A CN 110641735A CN 201910931325 A CN201910931325 A CN 201910931325A CN 110641735 A CN110641735 A CN 110641735A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a tail rotor hub journal shaft sleeve assembly fatigue test loading device, wherein a tail rotor hub journal shaft sleeve assembly is fixedly arranged on a tail rotor shaft fork assembly dummy piece (3), two ends of the tail rotor hub journal shaft sleeve assembly are connected with a blade dummy piece (4), the blade dummy piece (4) is connected with a centrifugal force actuator through a centrifugal force loading assembly (5), a swinging force loading assembly (8) is fixed on the blade dummy piece (4) at a first preset distance from the center position of a tail rotor hub, a swinging force loading assembly (10) is fixed on the blade dummy piece (4) at a second preset distance from the center position of the tail rotor hub, a swinging force loading joint (8-1) and a swinging force loading joint (10-1) are in small clearance fit with the blade dummy piece (4) by adopting a self-aligning roller bearing with a fastening sleeve, and an anti-torsion bar assembly (13) is lapped on the upper end face of a connecting joint of the blade dummy piece (4) and the tail rotor hub journal shaft sleeve assembly. The device provided by the invention is used for carrying out a fatigue test on the shaft sleeve component of the shaft neck of the tail rotor hub of the unmanned helicopter, so that the performance of the shaft sleeve component can be fully verified, and the fatigue life of the structure can be obtained.
Description
Technical Field
The invention belongs to the fatigue test technology of a tail rotor of an unmanned helicopter, and relates to a load loading device for a fatigue test of a tail rotor hub journal shaft sleeve assembly.
Background
The tail rotor hub journal shaft sleeve assembly is a key complex dynamic component used for balancing reaction torque and carrying out course control on a helicopter in a tail rotor system of an unmanned helicopter, can play a role in stabilizing the course of the unmanned helicopter, and bears all loads from blades through related force transmission components, including flapping force, shimmy force, centrifugal force generated when a tail transmission shaft rotates at a high speed and the like. In actual flight conditions, high cycle fatigue of the tail rotor hub journal shaft sleeve caused by high cycle vibration load is mainly considered, the fatigue stress level of the tail rotor hub journal shaft sleeve is obviously higher than that of an airframe structure, and the fatigue life of the tail rotor hub journal shaft sleeve is generally estimated by a high cycle fatigue calculation rule. Because the assembling structure and the force transmission mode of the shaft sleeve component of the shaft neck of the tail propeller hub of the unmanned helicopter are complex, the bearing load forms are complex and various, the structure is small, the weight is light, and the shaft sleeve component can not bear large load, an accurate fatigue test examination environment is provided, the fatigue performance and weak parts of the shaft sleeve component are obtained by performing test examination, the examination period and the maintenance method of the shaft sleeve component are determined, and the service life of the shaft sleeve component of the shaft neck of the tail propeller hub of the unmanned helicopter is estimated to be of great importance.
At present, because the fatigue test technology of the shaft sleeve assembly of the tail rotor hub shaft of the unmanned helicopter is insufficient in the aspects of boundary simulation, test loading technology and the like, a corresponding fatigue test loading device of the shaft sleeve assembly of the tail rotor hub shaft of the unmanned helicopter does not exist, and the fatigue test loading can not be carried out on the shaft sleeve assembly of the tail rotor hub shaft of the unmanned helicopter.
Disclosure of Invention
In view of the above situations in the prior art, an object of the present invention is to provide a tail rotor hub journal shaft sleeve assembly fatigue test loading device, which is used for an unmanned helicopter tail rotor hub journal shaft sleeve assembly fatigue test.
The above object of the present invention is achieved by the following technical solutions:
the technical scheme of the invention is as follows: the fatigue test loading device is characterized by comprising a tail rotor hub journal shaft sleeve assembly dummy piece, a blade dummy piece, a centrifugal force loading assembly, a flap force loading assembly, a shimmy force loading assembly and an anti-torsion rod assembly, wherein the tail rotor hub journal shaft sleeve assembly is fixedly arranged on the tail rotor shaft fork assembly dummy piece, two ends of the tail rotor hub journal shaft sleeve assembly dummy piece are connected with the blade dummy piece, the blade dummy piece is connected with a centrifugal force actuator through the centrifugal force loading assembly so as to apply centrifugal force Fc, the centrifugal force Fc can be loaded by a steel wire rope, the flap force loading assembly is fixed on the blade dummy piece at a first preset distance from the center of a tail rotor hub, the shimmy force loading assembly is fixed on the blade dummy piece at a second preset distance from the center of the tail rotor hub, the first preset distance and the second preset distance are different from each other, and the flap force loading joint in the flap force loading assembly and the shimmy force loading joint in the shimmy force loading assembly adopt a roller bearing with a tight fixed sleeve and an aligning dummy blade The piece carries out little clearance fit, adjusts the loading position of waving power and pendulum power through the tight fit nut of elasticity, and anti-torsion bar subassembly one end is taken and is pressed at the upper end face of the attach fitting of paddle dummy and tail-rotor hub journal axle sleeve subassembly, and the other end is fixed, for example fixes on the test bench bottom plate to wave the additional moment of flexure that the year caused during balance test, guarantee that experimental steady going on smoothly.
The fatigue test loading device for the tail rotor hub journal shaft sleeve assembly of the unmanned helicopter is combined with the assembly structure of the tail rotor hub journal shaft sleeve assembly of the unmanned helicopter and the load characteristics of a tail rotor blade, test boundary connection condition simulation and tail rotor hub journal shaft sleeve load loading design are carried out, and the fatigue test of the unmanned helicopter tail rotor hub journal shaft sleeve assembly can be carried out by adopting the fatigue test loading device for the tail rotor hub journal shaft sleeve assembly of the unmanned helicopter, so that the performance of the tail rotor hub journal shaft sleeve assembly of the unmanned helicopter can be fully verified, and the fatigue life of the structure can be obtained.
Drawings
Fig. 1 is a schematic general structural diagram of a fatigue test loading device for a tail rotor hub journal shaft sleeve assembly of the invention.
Fig. 2 is a centrifugal force loading schematic diagram of the fatigue test loading device for the tail rotor hub journal shaft sleeve assembly of the invention.
Fig. 3 is a schematic view of the loading device for fatigue test of the tail rotor hub journal shaft sleeve assembly of the invention.
Fig. 4 is a schematic view of shimmy force loading of the fatigue test loading device for the tail rotor hub journal shaft sleeve assembly of the invention.
FIG. 5 is a schematic view of a structure of a flap force and a shimmy force loading joint.
FIG. 6 is a front view of an anti-torque rod assembly in an embodiment of the present invention.
FIG. 7 is a top view of an anti-twist bar assembly in an embodiment of the present invention.
Detailed Description
The technical scheme of the invention is clearly and completely described in combination with the embodiment of the invention by referring to the attached drawings.
The fatigue test loading device for the tail rotor hub journal shaft sleeve assembly comprises a tail rotor shaft fork assembly dummy piece 3, a blade dummy piece 4 (a simulated blade 4-1 comprising a shaft sleeve connecting joint 4-2 and a steel wire rope connecting joint 4-3), a centrifugal force loading assembly 5 (comprising a steel wire rope 5-1, a centrifugal force loading joint 5-2 and a centrifugal force loading actuator), a flapping force loading assembly 8 (comprising a flapping force loading joint 8-1, a transition joint 8-2 and a flapping force loading actuator), a shimmy force loading assembly 10 (comprising a shimmy force loading joint 10-1, a transition rod 10-2 and a shimmy force loading actuator) and an anti-torsion rod assembly 13 (comprising an anti-torsion rod 13-1, an anti-torsion beam 13-2, an anti-torsion joint 13-3 and an anti-torsion support 13-4). The design of the interface of the tail rotor shaft fork assembly dummy 3, the blade dummy 4 and the tail rotor hub journal shaft sleeve assembly test piece is consistent with the installation state, the other parts are designed according to the strength requirement of a test bed without considering the operation function of a tail rotor transmission shaft, the pneumatic appearance of a tail rotor blade and the like, test loads are applied by various loading actuators, and are transmitted to the tail rotor hub journal shaft sleeve test piece through the swinging force loading joint 8-1, the swinging force loading joint 10-1, the steel wire rope 5-1 and the centrifugal force loading joint 5-2, so that the connection assembly and the load transmission relation of the fork, the tail rotor hub journal and the shaft sleeve are truly simulated.
The test device can realize fatigue test loading of the shaft sleeve assembly of the tail rotor hub journal of the unmanned helicopter. The test device can be designed into three parts, namely a centrifugal force loading design, a waving force and shimmy force loading design and an anti-torsion rod assembly design.
1. Centrifugal force loading design
The method includes the steps that the actual installation state of a tail rotor hub shaft neck shaft sleeve of the unmanned helicopter is simulated, a tail rotor hub shaft neck shaft sleeve assembly is installed and fixed on a tail rotor shaft forked assembly dummy 3 through forked bolts (wherein the tail rotor shaft forked assembly dummy 3 is fixed on a test bed floor 1 through a transition shaft 2, so that the height can be adjusted), two ends of the tail rotor hub shaft neck shaft sleeve assembly are connected with a blade dummy 4 through shaft sleeve connecting joints 4-2 through blade connecting bolts, and steel wire rope connecting joints 4-3 of the blade dummy 4 are connected with centrifugal force loading joints 5-2 through threads and then are connected with steel wire ropes through M45 bolts. The other end of the centrifugal force loading assembly 5 and the steel wire rope 5-1 are connected with the centrifugal force loading joint 5-2 through an M45 bolt and then connected with a centrifugal force actuator. The blade dummy 4 is connected with an actuator through a centrifugal force loading assembly 5 so as to apply a centrifugal force Fc, the centrifugal force actuator is fixedly installed on a centrifugal force actuator fixing bracket 7 through a first actuator support 6, and the centrifugal force loading height can be adjusted according to test requirements through the first actuator support 6, as shown in fig. 2. The centrifugal force Fc adopts the steel wire rope loading to ensure the centering and stable application of load, and because the steel wire rope is flexible, the test piece can be ensured not to be applied with reverse thrust when the test piece is unloaded, and the test piece is protected in a buffering way.
2. Flapping and shimmy force loading design
The flap force loading is mainly accomplished by applying a flap force Fb to a flap force loading assembly 8 (comprising a flap force loading joint 8-1, a transition joint 8-2 and a flap force loading actuator) fixed at a position L1 on the blade dummy 4 (from the center of the hub of the tail rotor). As shown in figure 3, after a simulated blade 4-1 in the blade dummy 4 is connected with a self-aligning roller bearing with a tight sleeve in the flapping force loading joint 8-1 by clearance fit (as shown in figure 5), the flapping force loading joint 8-1 is connected with a transition joint 8-2 through threads, the other end of the transition joint 8-2 is connected with a flapping force actuator, and the flapping force loading actuator is fixed on a flapping force loading support 9.
The shimmy force loading is mainly completed by applying a shimmy force Ft to a shimmy force loading assembly 10 (comprising a shimmy force loading joint 10-1, a transition rod 10-2 and a shimmy force loading actuator) fixed at the position L2 (from the central position of a tail rotor hub) on the blade dummy piece 4. As shown in fig. 4, after the simulated blade 4-1 in the blade dummy piece 4 is connected with the self-aligning roller bearing with the adapter sleeve in the shimmy force loading joint 10-1 by clearance fit (as shown in fig. 5), the shimmy force loading joint 10-1 is further connected with the transition rod 10-2 by screw threads, the other end of the transition rod 10-2 is further connected with the shimmy force actuator, the shimmy force loading actuator is fixed on the second actuator support 11, and the second actuator support 11 is fixed on the shimmy force actuator fixing support 12 by bolts. The L1 and L2 are adjustable and are unequal to each other. In the loading device, the swinging force loading support 9 is fixed on the test bed bottom plate 1, and the loading point positions of the swinging force and the swinging force can be adjusted by adjusting the horizontal mounting position of the swinging force loading support 9 on the test bed bottom plate 1 and the horizontal mounting position of the swinging force actuator fixing bracket 12 from left to right so as to meet the test loading requirement, as shown in fig. 3 and 4. After the loading point positions of the flapping force and the pendulum vibration force are determined, the limiting plate 14 needs to be fixed by screwing 4M 10 long bolts, and the installation loading positions of the flapping force loading assembly 8 and the pendulum vibration force loading assembly 10 are limited, see fig. 3 and 4.
The flapping force loading joint 8-1 and the shimmy force loading joint 10-1 are in small clearance fit with a simulated blade 4-1 in the blade dummy 4 by adopting a self-aligning roller bearing with a tightening sleeve, and the loading positions of the flapping force and the shimmy force are secondarily adjusted by tightening a tightening sleeve nut, as shown in figure 5, so that the load required by the test can be accurately applied, and the bending moment output of the monitoring section of the test piece can be adjusted.
The assembly structure between the flap force loading joint 8-1 and the drag force loading joint 10-1 and the dummy blade 4-1 of the blade dummy 4 will be described in detail. As shown in fig. 5, the adapter sleeve fitted with the bearing is mounted on the blade dummy 4 with a clearance fit, and the bearing is mounted inside the loadjoint by: one end of the bearing outer ring is arranged on an inner boss of the cavity groove in the loading joint, and the other end of the bearing outer ring limits the bearing to move in the outer direction through the bearing retaining ring. The bearing retainer ring is fixed on the loading joint through a bolt. During the experiment, self-aligning roller bearing can automatic aligning and can bear certain radial and axial load, and can freely install on paddle dummy 4 with tight fit assembly, conveniently adjusts and waves and pendulum vibration power load point position, guarantees that accurate the exerting wave and pendulum vibration load, satisfies the pendulum ratio of waving that experimental requirement.
3. Anti-twist bar assembly design
And anti-twisting devices are designed at two ends of the paddle dummy piece 4 connected with the shaft sleeve test piece. The anti-twist beam 13-7 in the anti-twist rod assembly 13 is abutted against the upper end face of the shaft sleeve connecting joint 4-1 of the blade dummy 4, the anti-twist beam 13-7 is fixed through the connecting short screw 13-5, the small pressing plate 13-6, the large pressing plate 13-8 and the connecting long screw 13-9 so as to press the blade dummy 4 to prevent the blade dummy 4 from moving during the test, and the anti-twist rod assembly 13 is integrally fixed on the test bed bottom plate 1 through the upper anti-twist support 13-1, the upper anti-twist joint 13-4, the anti-twist rod 13-3 and the lower anti-twist joint 13-2 so as to balance the additional bending moment caused by galloping during the test and ensure that the test is smoothly carried out, as shown in fig. 6 and 7.
When the device is used for testing, the boundary conditions of a test piece can be accurately simulated, the test bench is stable, the test environment is good, the load fluctuation amount is small, the total error of the test can be controlled within 3% by adopting the device for testing, and the performance of the device can be fully verified and the fatigue life of the structure can be obtained by adopting the test data obtained by the device for carrying out life analysis.
Claims (8)
1. A fatigue test loading device for a tail rotor hub journal shaft sleeve assembly is characterized by comprising a tail rotor hub fork assembly dummy piece (3), a blade dummy piece (4), a centrifugal force loading assembly (5), a flap force loading assembly (8), a shimmy force loading assembly (10) and an anti-torsion rod assembly (13), wherein the tail rotor hub journal shaft sleeve assembly is fixedly arranged on the tail rotor shaft fork assembly dummy piece (3), two ends of the tail rotor hub journal shaft sleeve are connected with the blade dummy piece (4), the blade dummy piece (4) is connected with a centrifugal force actuator through the centrifugal force loading assembly (5) so as to apply centrifugal force Fc, the flap force loading assembly (8) is fixedly arranged on the blade dummy piece (4) at a first preset distance from the center position of a tail rotor hub, the shimmy force loading assembly (10) is fixedly arranged on the blade dummy piece (4) at a second preset distance from the center position of the tail rotor hub, and the first preset distance and the second preset distance are different from each other, the flapping force loading joint (8-1) in the flapping force loading assembly (8) and the shimmy force loading joint (10-1) in the shimmy force loading assembly (10) are in small-clearance fit with the blade dummy piece (4) by adopting a self-aligning roller bearing with a fastening sleeve, one end of the anti-torsion rod assembly (13) is lapped and pressed on the upper end surface of the connecting joint of the blade dummy piece (4) and the tail rotor hub journal shaft sleeve assembly, and the other end of the anti-torsion rod assembly is fixed.
2. The tail rotor hub journal bushing assembly fatigue test loading device of claim 1, wherein centrifugal force Fc is loaded using a wire rope.
3. The tail rotor hub journal bushing assembly fatigue test loading device of claim 1, wherein the tail rotor shaft yoke assembly dummy (3) is fixed to the test bed floor (1) by the transition shaft (2).
4. The fatigue test loading device for the tail rotor hub journal sleeve assembly according to claim 1, wherein the centrifugal force actuator is fixedly arranged on the centrifugal force actuator fixing bracket (7) through a first actuator support (6), and the centrifugal force loading height can be adjusted through the first actuator support (6) according to test requirements.
5. The fatigue test loading device for the tail rotor hub journal shaft sleeve assembly according to claim 1, wherein a torsion-proof beam (13-7) in the torsion-proof rod assembly (13) is abutted against the upper end face of a shaft sleeve connecting joint (4-1) of the blade dummy 4, the torsion-proof beam (13-7) is fixed by connecting a short screw (13-5), a small pressing plate (13-6), a large pressing plate (13-8) and a connecting long screw (13-9) so as to press the blade dummy (4), and the torsion-proof rod assembly (13) is integrally fixed on a test bed bottom plate (1) by an upper torsion-proof support (13-1), a lower torsion-proof support (13-1), the upper torsion-proof joint (13-4), a torsion-proof rod (13-3) and a lower torsion-proof joint (13-2).
6. The tail rotor hub journal sleeve assembly fatigue test loading device according to claim 1, wherein the adapter sleeve is mounted on the blade dummy (4) by clearance fit, one end of the outer ring of the roller bearing is mounted on a boss in the cavity groove inside the loading joint, and the other end of the outer ring of the roller bearing limits the bearing from dislocating in the outer direction through the bearing retaining ring.
7. The tail rotor hub journal shaft sleeve assembly fatigue test loading device according to claim 1, further comprising a limiting plate (14) for limiting the installation loading positions of the flapping force loading assembly (8) and the shimmy force loading assembly (10) after the loading positions of the flapping force and the shimmy force are adjusted and determined.
8. The tail rotor hub journal sleeve assembly fatigue test loading device of claim 1, wherein the first predetermined distance and the second predetermined distance are both adjustable.
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| CN201910931325.4A CN110641735A (en) | 2019-09-29 | 2019-09-29 | Fatigue test loading device for tail rotor hub journal shaft sleeve assembly |
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| CN201910931325.4A CN110641735A (en) | 2019-09-29 | 2019-09-29 | Fatigue test loading device for tail rotor hub journal shaft sleeve assembly |
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Cited By (7)
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| CN107860565A (en) * | 2017-10-11 | 2018-03-30 | 昌河飞机工业（集团）有限责任公司 | A kind of loading device of helicopter simulating blade stress |
| CN112285555A (en) * | 2020-09-25 | 2021-01-29 | 北京二郎神科技有限公司 | Fatigue test device of unmanned aerial vehicle power system |
| CN112357114A (en) * | 2020-11-20 | 2021-02-12 | 昌河飞机工业（集团）有限责任公司 | Fatigue test platform for main hub of helicopter |
| CN112504589A (en) * | 2020-10-30 | 2021-03-16 | 哈尔滨飞机工业集团有限责任公司 | Helicopter composite material main blade airfoil section static strength test system and method |
| CN113335560A (en) * | 2021-06-04 | 2021-09-03 | 中国飞机强度研究所 | Complicated load box section or barrel section testing device and method |
| CN114162345A (en) * | 2021-11-25 | 2022-03-11 | 力源液压系统（贵阳）有限公司 | Rotor hub journal testing system and method |
| CN115479758A (en) * | 2021-06-15 | 2022-12-16 | 惠阳航空螺旋桨有限责任公司 | Centrifugal load test device and test method thereof |
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| CN107860565A (en) * | 2017-10-11 | 2018-03-30 | 昌河飞机工业（集团）有限责任公司 | A kind of loading device of helicopter simulating blade stress |
| CN112285555A (en) * | 2020-09-25 | 2021-01-29 | 北京二郎神科技有限公司 | Fatigue test device of unmanned aerial vehicle power system |
| CN112285555B (en) * | 2020-09-25 | 2024-05-17 | 北京二郎神科技有限公司 | Fatigue testing device of unmanned aerial vehicle power system |
| CN112504589A (en) * | 2020-10-30 | 2021-03-16 | 哈尔滨飞机工业集团有限责任公司 | Helicopter composite material main blade airfoil section static strength test system and method |
| CN112357114A (en) * | 2020-11-20 | 2021-02-12 | 昌河飞机工业（集团）有限责任公司 | Fatigue test platform for main hub of helicopter |
| CN113335560A (en) * | 2021-06-04 | 2021-09-03 | 中国飞机强度研究所 | Complicated load box section or barrel section testing device and method |
| CN113335560B (en) * | 2021-06-04 | 2024-01-30 | 中国飞机强度研究所 | Complex load box section or barrel section test device and method |
| CN115479758A (en) * | 2021-06-15 | 2022-12-16 | 惠阳航空螺旋桨有限责任公司 | Centrifugal load test device and test method thereof |
| CN114162345A (en) * | 2021-11-25 | 2022-03-11 | 力源液压系统（贵阳）有限公司 | Rotor hub journal testing system and method |
| CN114162345B (en) * | 2021-11-25 | 2023-09-08 | 贵州安飞精密制造有限公司 | Rotor hub journal testing system and method |
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Application publication date: 20200103 |