CN116754224A - Fatigue test device and method for rotor shaft of main speed reducer of helicopter - Google Patents
Fatigue test device and method for rotor shaft of main speed reducer of helicopter Download PDFInfo
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- 239000003638 chemical reducing agent Substances 0.000 title claims abstract description 45
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/02—Gearings; Transmission mechanisms
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- B—PERFORMING OPERATIONS; TRANSPORTING
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Abstract
The invention belongs to the field of fatigue tests, and particularly relates to a fatigue test device and method for a rotor shaft of a main speed reducer of a helicopter. The device comprises: six hydraulic cylinders, a casing false piece, a base, a rotor shaft hub false piece, six bearing devices and a switching disc, wherein the casing false piece is fixed on the base through the switching disc; the upper end of the receiver false part is connected with the middle lower end of the main reducer rotor shaft test piece through a roller bearing; the lower end of the receiver false part is connected with the spline end of the main speed reducer rotor shaft test part through a four-point contact ball bearing; the end face of the main speed reducer rotor shaft test piece is fixed with the rotor shaft hub dummy piece; the loading ends of the six hydraulic cylinders are respectively fixed with the rotor shaft hub dummy and are respectively positioned in the directions of 0 degree, 90 degrees, 180 degrees, 270 degrees, 30 degrees and 60 degrees; the fixed ends of the six hydraulic cylinders are respectively fixed on the six bearing devices.
Description
Technical Field
The invention belongs to the field of fatigue tests, and particularly relates to a fatigue test device and method for a rotor shaft of a main speed reducer of a helicopter.
Background
The main speed reducer rotor shaft of the helicopter transmission system is a key component of the helicopter transmission system and is also a safety guarantee unit for stable operation of the helicopter. The main speed reducer of the helicopter transmission system transmits engine power to all parts, wherein a transmission chain is transmitted to a rotor shaft, and the rotor shaft drives a propeller to provide power for the helicopter. The performance of the rotor shaft is a key factor for ensuring the safety of the helicopter, before formal batch production, the working life of the rotor shaft needs to be checked and evaluated, the corresponding replacement period is further determined, and the service life check needs to be performed with performance verification under the limiting working condition besides the related fatigue performance check, so that the service life of the rotor shaft is effectively evaluated.
According to the traditional fatigue test method, a rotor shaft is mounted on a complete machine for test, life assessment is carried out through a relevant fatigue test, the service life assessed by the test mode is relatively short, in the verification process of the test load of the complete machine, in view of comprehensive assessment, the load applied by the complete machine assessment is small, the performance of the rotor shaft cannot be fully verified, and the actual complex loading working condition of a rotor shaft simulation helicopter cannot be met.
Disclosure of Invention
The invention aims to: the fatigue test device and method for the rotor shaft of the main speed reducer of the helicopter transmission system are provided, and the aim of independently checking the performance of the rotor shaft is fulfilled.
The technical scheme is as follows:
a fatigue test device for a helicopter main reducer rotor shaft, comprising: the device comprises a first hydraulic cylinder 1, a second hydraulic cylinder 2, a third hydraulic cylinder 3, a fourth hydraulic cylinder 4, a fifth hydraulic cylinder 5, a sixth hydraulic cylinder 6, a casing false element 8, a base 9, a rotor shaft and propeller hub false element 10, six bearing devices 11 and a switching disc 12, wherein the casing false element 8 is fixed on the base 9 through the switching disc 12; the upper end of the receiver false part 8 is connected with the middle lower end of the main reducer rotor shaft test part 7 through a roller bearing; the lower end of the receiver false part 8 is connected with the spline end of the main reducer rotor shaft test part 7 through a four-point contact ball bearing; the end face of the main reducer rotor shaft test piece 7 is fixed with a rotor shaft hub dummy piece 10; the loading ends of the first hydraulic cylinder 1, the second hydraulic cylinder 2, the third hydraulic cylinder 3, the fourth hydraulic cylinder 4, the fifth hydraulic cylinder 5 and the sixth hydraulic cylinder 6 are respectively fixed with the rotor shaft hub prosthesis 10 and are respectively positioned in the directions of 0 degrees, 90 degrees, 180 degrees, 270 degrees, 30 degrees and 60 degrees; the fixed ends of the first hydraulic cylinder 1, the second hydraulic cylinder 2, the third hydraulic cylinder 3, the fourth hydraulic cylinder 4, the fifth hydraulic cylinder 5 and the sixth hydraulic cylinder 6 are respectively fixed on six bearing devices 11.
Further, the rotor shaft hub prosthesis 10 comprises a disc, four groups of long force arms and two groups of short force arms, wherein the four groups of long force arms and the two groups of short force arms are respectively fixed in the circumferential direction of the disc, the long force arms are used for being connected with the first hydraulic cylinder 1, the second hydraulic cylinder 2, the third hydraulic cylinder 3 and the fourth hydraulic cylinder 4, and the short force arms are used for being connected with the fifth hydraulic cylinder 5 and the sixth hydraulic cylinder 6.
Further, the long arm of force includes long splint and strengthen the long beam, strengthen the long beam and fix through long splint after the disc is docked; the short arm of force includes strengthening short beam and short splint, and the strengthening short beam is fixed through short splint after interfacing with the disc.
A fatigue test method for a rotor shaft of a main speed reducer of a helicopter comprises the following steps:
step 1: calculating initial loads of the first hydraulic cylinder 1, the second hydraulic cylinder 2, the third hydraulic cylinder 3, the fourth hydraulic cylinder 4, the fifth hydraulic cylinder 5 and the sixth hydraulic cylinder 6 respectively and loads of different angles alpha;
step 2: simulating test load spectrums according to initial loads and loads of different angles alpha;
step 3: and carrying out a loading test according to the test load spectrum to determine the service life of the test piece.
Further, the step 1 specifically includes: the load of the first hydraulic cylinder 1 is I1= (F/4+G/4) +h1/2L multiplied by cos alpha, wherein alpha is a phase angle, F is the lift force born by a rotor shaft test piece of the main speed reducer, G is the dead weight of a rotor shaft hub dummy piece, L is the length of a long force arm, h1 is the bending moment value born by the rotor shaft end face, h2 is the maximum value of the bending moment born by the rotor shaft, Δh is the difference between h2 and h1, L1 is the distance from a bending moment 0 point to the rotor shaft end face, and L2 is the distance from a rotor shaft supporting point to the rotor shaft end face.
Further, the step 1 specifically includes: the load of the second hydraulic cylinder 2 is I2= (F/4+G/4) +h1/2L×sin alpha, wherein alpha is a phase angle, F is the lifting force born by a rotor shaft test piece of the main speed reducer, G is the dead weight of a rotor shaft hub dummy piece, L is the length of a long force arm, h1 is the bending moment value born by the rotor shaft end face, h2 is the maximum value of the bending moment born by the rotor shaft, Δh is the difference between h2 and h1, L1 is the distance from a bending moment 0 point to the rotor shaft end face, and L2 is the distance from a rotor shaft supporting point to the rotor shaft end face.
Further, the step 1 specifically includes: the load of the third hydraulic cylinder 3 is I3= (F/4+G/4) -h1/2L multiplied by cos alpha, wherein alpha is a phase angle, F is the lifting force born by a rotor shaft test piece of the main speed reducer, G is the dead weight of a rotor shaft hub dummy piece, L is the length of a long force arm, h1 is the bending moment value born by the rotor shaft end face, h2 is the maximum value of the bending moment born by the rotor shaft, Δh is the difference between h2 and h1, L1 is the distance from a bending moment 0 point to the rotor shaft end face, and L2 is the distance from a rotor shaft supporting point to the rotor shaft end face.
Further, the step 1 specifically includes: the load of the fourth hydraulic cylinder 4 is I4= (F/4+G/4) -h1/2L multiplied by sin alpha, wherein alpha is a phase angle, F is the lifting force born by a rotor shaft test piece of the main speed reducer, G is the dead weight of a rotor shaft hub dummy piece, L is the length of a long force arm, h1 is the bending moment value born by the rotor shaft end face, h2 is the maximum value of the bending moment born by the rotor shaft, Δh is the difference between h2 and h1, L1 is the distance from a bending moment 0 point to the rotor shaft end face, and L2 is the distance from a rotor shaft supporting point to the rotor shaft end face.
Further, the step 1 specifically includes: the load of the fifth hydraulic cylinder 5 is i5=Δh/l2×cos (α+30°), wherein α is a phase angle, F is a lift force applied to the rotor shaft test piece of the main speed reducer, G is a dead weight of the rotor shaft hub dummy piece, L is a long arm length, h1 is a bending moment value applied to the rotor shaft end face, h2 is a maximum value of the bending moment applied to the rotor shaft, Δh is a difference between h2 and h1, L1 is a distance from a bending moment 0 point to the rotor shaft end face, and L2 is a distance from a rotor shaft supporting point to the rotor shaft end face.
Further, the step 1 specifically includes: the load i6=Δh/l2×sin (α+30°) of the sixth hydraulic cylinder 6, where α is a phase angle, F is a lift force applied to the rotor shaft test piece of the main speed reducer, G is a dead weight of the rotor shaft hub dummy piece, L is a long arm length, h1 is a bending moment value applied to the rotor shaft end face, h2 is a maximum value of the bending moment applied to the rotor shaft, Δh is a difference between h2 and h1, L1 is a distance from a bending moment 0 point to the rotor shaft end face, and L2 is a distance from a rotor shaft supporting point to the rotor shaft end face.
The beneficial effects are that:
the fatigue test device and method for the rotor shaft of the main speed reducer of the helicopter can apply lifting force and bending moment to the rotor shaft, and can meet the actual complex loading working condition requirement of the simulated helicopter. Meanwhile, the risk in the rotor shaft performance checking process is identified in advance, and the running safety of the helicopter is effectively ensured.
Drawings
FIG. 1 is a perspective view of a fatigue test apparatus for a helicopter main reducer rotor shaft of the present invention;
FIG. 2 is a top view of a fatigue test apparatus for a helicopter main reducer rotor shaft;
FIG. 3 is a cross-sectional view taken along line AA in FIG. 2;
the device comprises a first hydraulic cylinder 1, a second hydraulic cylinder 2, a third hydraulic cylinder 3, a fourth hydraulic cylinder 4, a fifth hydraulic cylinder 5, a sixth hydraulic cylinder 6, a main reducer rotor shaft test piece 7, a casing false piece 8, a base 9, a rotor shaft rotor hub false piece 10, a bearing device 11 and a switching disc 12;
FIG. 4 is a schematic representation of the rotor shaft load of a helicopter;
FIG. 5 is a load vector diagram of a fifth hydraulic cylinder, a sixth hydraulic cylinder;
FIG. 6 is a test load spectrum of the first hydraulic cylinder to the fourth hydraulic cylinder;
fig. 7 is a test load spectrum of the fifth and sixth cylinders, in which the abscissa indicates the phase angle α and the ordinate indicates the load.
Detailed Description
The main speed reducer rotor shaft test piece 7 is that a rotor hub drives the rotor shaft test piece to rotate 70-360 degrees on an aircraft. The end face connector of the main speed reducer rotor shaft test piece 7 is designed into a rotor shaft hub dummy piece 10 so as to simulate the actual working condition of the main speed reducer rotor shaft hub dummy piece. The long arm of force of the rotor shaft hub dummy 10 is set to be 1m, and the short arm of force is set to be 0.6m, so that the occupied space of the tester is reduced, and the calculation is convenient. The design is split structure, and the arm of force includes splint and reinforcing long beam to easy installation and lift off.
And calculating the maximum load borne by the first hydraulic cylinder 1 to the sixth hydraulic cylinder 6, wherein the force arm long clamping plates are set to be 80mm thick and 40mm wide according to the strength calculation formula sigma=F/S, the force arm reinforcing long beams are 40mm thick and 40mm wide on both sides respectively, the force arm short clamping plates are set to be 80mm thick and 60mm wide, and the force arm reinforcing short beams are 40mm thick and 60mm wide on both sides respectively. Through finite element stress analysis, the maximum bearing tension of the force arm is 30kN, the strength and displacement of the force arm are both within the allowable range of the material, and the maximum stress is 14MPa. Meets the test requirements.
Through calculation, simulation and verification, 6 hydraulic cylinders are determined to be used, 4 hydraulic cylinders are determined to be used for applying lifting force through stress analysis on the main reducer rotor shaft test piece 7, and 2 hydraulic cylinders are determined to be used for applying bending moment. In order to be closer to the real stress state of the main speed reducer rotor wing shaft test piece 7 on an airplane, the first hydraulic cylinder 1 to the fourth hydraulic cylinder 4 are symmetrically distributed on the vertical ground, the fifth hydraulic cylinder 5 and the sixth hydraulic cylinder 6 are symmetrically distributed on the parallel ground, through multi-angle practical verification, the included angle of the fifth hydraulic cylinder 5 is-30 degrees, the included angle of the sixth hydraulic cylinder 6 is 60 degrees, so that bending moment compensation is ensured, the range selection minimization of the hydraulic cylinders is facilitated, the test control precision is effectively improved, and the positions of the 6 hydraulic cylinders are determined.
The building block type force bearing device 11 can be set up at will according to test requirements, and the force bearing device 11 is adopted to fix the first hydraulic cylinder 1 to the sixth hydraulic cylinder 6, so that the tester runs stably.
The connecting piece of main reducer rotor shaft test piece 7 spline end is according to the installation state design to consolidate, reduce the change number of times.
The design of the structure reduces the occupied space, is easy to maintain daily and replace parts, and meets the test requirement.
Referring to fig. 1-3, the helicopter rotor shaft tester structure of the invention comprises a first hydraulic cylinder 1, a second hydraulic cylinder 2, a third hydraulic cylinder 3, a fourth hydraulic cylinder 4, a fifth hydraulic cylinder 5, a sixth hydraulic cylinder 6, a rotor shaft hub dummy 10, a main reducer rotor shaft test 7, a base 9, a switching disc 12, a bearing device 11 and a casing dummy 8, wherein a vector diagram of the fifth hydraulic cylinder 5 and the sixth hydraulic cylinder 6 is shown in fig. 5.
The first hydraulic cylinder 1, the second hydraulic cylinder 2, the third hydraulic cylinder 3, the fourth hydraulic cylinder 4, the fifth hydraulic cylinder 5 and the sixth hydraulic cylinder 6 are arranged on the action plane of X-O-Y force; the first hydraulic cylinder 1 to the fourth hydraulic cylinder 4 are connected to the rotor shaft hub dummy, the distance from the connecting point to the circle center O point is an acting force arm, the application of lifting force and torque is realized, the fifth hydraulic cylinder 5 and the sixth hydraulic cylinder 6 are positioned on the acting parting line, act on the circle center O point, and supplement the bending moment of the test piece.
Taking the rotor shaft load of a helicopter in fig. 4 as an example, the known moment at the position M is h2, the lifting force is F, the dead weight of a rotor shaft hub dummy is G, the distance from a connecting point to a circle center (namely a long moment arm) is L, the calculation formulas of the first hydraulic cylinder 1 to the sixth hydraulic cylinder 6 are shown in (1) to (6), and the load parameters are calculated by applying the formulas:
(1) 1# hydraulic cylinder load formula: i1 = (F/4+g/4) +h1/2l×cos α;
(2) 2# hydraulic cylinder load equation: i2 = (F/4+g/4) +h1/2l×sinα;
(3) 3# hydraulic cylinder load equation: i3 = (F/4+g/4) -h1/2l×cos α;
(4) Load formula of hydraulic cylinder # 4: i4 = (F/4+g/4) -h1/2l×sinα;
(5) Load formula of 5# hydraulic cylinder: i5 =Δh/l2×cos (α+30°);
(6) Load formula of 6# hydraulic cylinder: i6 =Δh/l2×sin (α+30°);
note that: alpha is the phase angle { change category (0-360) °, F is the lift force born by the rotor shaft, G is the dead weight of the rotor shaft hub false piece, L is the length of a long force arm, h1 is the bending moment value born by the rotor shaft end face, h2 is the maximum value of the bending moment born by the rotor shaft, Δh is the difference between h2 and h1, L1 is the distance from the bending moment 0 point to the rotor shaft end face, and L2 is the distance from the rotor shaft supporting point to the rotor shaft end face.
After the tester is installed and debugged, the loading of the rotor shaft can be realized, wherein the loading comprises bending moment compensation loading and lifting force single loading; and the systematic coordinated loading of the lift force and the bending moment of the rotor shaft can be realized. In the design process, a sufficient margin is reserved for selecting the mechanical accompanying test piece and the sensor, so that the tester can realize a load acceleration equivalent test. The invention meets the fatigue test and loading requirements of the rotor shaft, meets the actual complex loading working condition requirements of the simulated helicopter, and can be widely used for fatigue tests of other rotor shafts.
Moment compensation loading: the fifth hydraulic cylinder 5 and the sixth hydraulic cylinder 6 are provided with pressure by a pump source, and bending moment compensation is independently applied to the rotor shaft test piece 7.
Lift force single-phase loading: the first hydraulic cylinder 1, the second hydraulic cylinder 2, the third hydraulic cylinder 3 and the fourth hydraulic cylinder 4 are provided with pressure by pump sources, and lift load is independently applied to the rotor shaft test piece 7.
And (3) coordination loading: the first hydraulic cylinder 1, the second hydraulic cylinder 2, the third hydraulic cylinder 3 and the fourth hydraulic cylinder 4 apply lifting force and bending moment to the rotor shaft test piece 7, the fifth hydraulic cylinder 5 and the sixth hydraulic cylinder 6 provide pressure, and the bending moment supplement is applied to the rotor shaft test piece 7 through pump sources.
Examples:
and (3) testing the fatigue life of the rotor shaft of a certain helicopter.
The high cycle fatigue test steps are as follows:
(1) According to the technical file requirements, calculating the lift force born by each cylinder of the first hydraulic cylinder 1, the second hydraulic cylinder 2, the third hydraulic cylinder 3 and the fourth hydraulic cylinder 4 and the bending moment generated jointly, the bending moment compensated jointly by the fifth hydraulic cylinder 5 and the sixth hydraulic cylinder 6, wherein the sum of the lift forces of the first hydraulic cylinder 1 to the fourth hydraulic cylinder 4 is the lift force required by the technical requirement, the difference is the bending moment required by the technical requirement, and the sum of the bending moments of the fifth hydraulic cylinder 5 and the sixth hydraulic cylinder 6 is the bending moment compensation required by the technical requirement;
(2) Calculating the calculation formulas 1-6 according to the lift force and the bending moment by using theory;
(3) According to a calculation formula, calculating the loads of alpha at different angles, and thus drawing a test load spectrum, see fig. 6 and 7;
(4) The control system loads the test piece according to the load spectrum, and the service life of the test piece is determined.
(5) In the loading process, a strain gauge is stuck on a stress point of the rotor shaft test piece 7, the value of the strain gauge is measured through a test system and converted into load, and the loaded load spectrum is verified to be correct.
The mechanical system of the tester adopts a general structure and conventional materials, is convenient to process, manufacture and repair, has low overall cost, and ensures the effective implementation of a test scheme. The rotor shaft hub dummy adopts a split structure, so that the processing difficulty is reduced, and the structure is convenient to install and detach. And a servo hydraulic cylinder is selected, and the control precision is effectively and accurately improved through the feedback of related signals. The loading device performs limit protection, and the hardware protection is performed on the tested product in a structure optimization mode. The key parameter setting is carried out from the software control end, and when the test parameter is abnormal, a software protection program is triggered to carry out software protection on the tested product. The lower end of the tested product adopts a casing shell structure, so that the simulation degree/degree of the tested product under the real working condition is improved, a real casing piece is replaced, the manufacturing cost is low, the structural strength is superior to that of the real casing piece, and the stability of the test device is ensured. The 4 sets of vertical loading hydraulic devices adopt independent structures, so that the installation and the disassembly are facilitated, redundant structures can be removed, and the occupied space is saved. The 2 sets of transverse hydraulic cylinders are used for applying compensating load to the load with insufficient loading of the vertical hydraulic cylinders, so that the large tonnage selection of the vertical loading hydraulic cylinders is avoided, and the precision of the test device is improved. The bottom end of the rotor shaft is optimized and upgraded, the strength of the rotor shaft is improved, the wear resistance is enhanced, the replacement period is prolonged, and the running reliability of equipment is improved. And a theoretical model is built, modeling and calculation are carried out, the real working condition of the rotor shaft is highly simulated, and the implementation of a scheme is accurately guided.
Claims (10)
1. A fatigue test device of helicopter main reducer rotor shaft, characterized by comprising: the device comprises a first hydraulic cylinder (1), a second hydraulic cylinder (2), a third hydraulic cylinder (3), a fourth hydraulic cylinder (4), a fifth hydraulic cylinder (5), a sixth hydraulic cylinder (6), a casing false part (8), a base (9), a rotor shaft hub false part (10), six bearing devices (11) and a switching disc (12), wherein the casing false part (8) is fixed on the base (9) through the switching disc (12); the upper end of the receiver false part (8) is connected with the middle lower end of the main reducer rotor shaft test part (7) through a roller bearing; the lower end of the receiver false part (8) is connected with the spline end of the main speed reducer rotor shaft test part (7) through a four-point contact ball bearing; the end face of the main speed reducer rotor shaft test piece (7) is fixed with a rotor shaft hub dummy piece (10); the loading ends of the first hydraulic cylinder (1), the second hydraulic cylinder (2), the third hydraulic cylinder (3), the fourth hydraulic cylinder (4), the fifth hydraulic cylinder (5) and the sixth hydraulic cylinder (6) are respectively fixed with the rotor shaft hub dummy (10) and are respectively positioned in the directions of 0 DEG, 90 DEG, 180 DEG, 270 DEG, 30 DEG and 60 DEG; the fixed ends of the first hydraulic cylinder (1), the second hydraulic cylinder (2), the third hydraulic cylinder (3), the fourth hydraulic cylinder (4), the fifth hydraulic cylinder (5) and the sixth hydraulic cylinder (6) are respectively fixed on six force bearing devices (11).
2. The helicopter main reducer rotor shaft fatigue test apparatus of claim 1, wherein the rotor shaft rotor hub dummy (10) comprises a disc, four groups of long force arms and two groups of short force arms, wherein the four groups of long force arms and the two groups of short force arms are respectively fixed in the circumferential direction of the disc, the long force arms are used for being connected with the first hydraulic cylinder (1), the second hydraulic cylinder (2), the third hydraulic cylinder (3) and the fourth hydraulic cylinder (4), and the short force arms are used for being connected with the fifth hydraulic cylinder (5) and the sixth hydraulic cylinder (6).
3. The helicopter main reducer rotor shaft fatigue test apparatus of claim 1, wherein the long arm comprises a long clamping plate and a reinforcing long beam, and the reinforcing long beam is fixed by the long clamping plate after being butted with the disk; the short arm of force includes strengthening short beam and short splint, and the strengthening short beam is fixed through short splint after interfacing with the disc.
4. A fatigue test method for a rotor shaft of a main speed reducer of a helicopter is characterized by comprising the following steps:
step 1: calculating initial loads of the first hydraulic cylinder (1), the second hydraulic cylinder (2), the third hydraulic cylinder (3), the fourth hydraulic cylinder (4), the fifth hydraulic cylinder (5) and the sixth hydraulic cylinder (6) respectively and loads of different angles alpha;
step 2: simulating test load spectrums according to initial loads and loads of different angles alpha;
step 3: and carrying out a loading test according to the test load spectrum to determine the service life of the test piece.
5. The method according to claim 4, wherein step 1 specifically comprises:
the load of the first hydraulic cylinder (1) is I1= (F/4+G/4) +h1/2L multiplied by cos alpha, wherein alpha is a phase angle, F is the lift force born by a main speed reducer rotor shaft test piece, G is the dead weight of a rotor shaft rotor hub dummy piece, L is the length of a long force arm, h1 is the bending moment value born by the rotor shaft end face, h2 is the maximum value of the bending moment born by the rotor shaft, Δh is the difference between h2 and h1, L1 is the distance from a bending moment 0 point to the rotor shaft end face, and L2 is the distance from a rotor shaft supporting point to the rotor shaft end face.
6. The method according to claim 4, wherein step 1 specifically comprises:
the load of the second hydraulic cylinder (2) is I2= (F/4+G/4) +h1/2L multiplied by sin alpha, wherein alpha is a phase angle, F is the lifting force born by a rotor shaft test piece of the main speed reducer, G is the dead weight of a rotor shaft hub dummy piece, L is the length of a long force arm, h1 is the bending moment value born by the rotor shaft end face, h2 is the maximum value of the bending moment born by the rotor shaft, Δh is the difference between h2 and h1, L1 is the distance from a bending moment 0 point to the rotor shaft end face, and L2 is the distance from a rotor shaft supporting point to the rotor shaft end face.
7. The method according to claim 4, wherein step 1 specifically comprises: the load of the third hydraulic cylinder (3) is I3= (F/4+G/4) -h1/2L multiplied by cos alpha, wherein alpha is a phase angle, F is the lifting force born by a rotor shaft test piece of the main speed reducer, G is the dead weight of a rotor shaft hub dummy piece, L is the length of a long force arm, h1 is the bending moment value born by the rotor shaft end face, h2 is the maximum value of the bending moment born by the rotor shaft, Δh is the difference between h2 and h1, L1 is the distance from a bending moment 0 point to the rotor shaft end face, and L2 is the distance from a rotor shaft supporting point to the rotor shaft end face.
8. The method according to claim 4, wherein step 1 specifically comprises: the load of the fourth hydraulic cylinder (4) is I4= (F/4+G/4) -h1/2L multiplied by sin alpha, wherein alpha is a phase angle, F is the lifting force born by a rotor shaft test piece of the main speed reducer, G is the dead weight of a rotor shaft hub dummy piece, L is the length of a long force arm, h1 is the bending moment value born by the rotor shaft end face, h2 is the maximum value of the bending moment born by the rotor shaft, Δh is the difference between h2 and h1, L1 is the distance from a bending moment 0 point to the rotor shaft end face, and L2 is the distance from a rotor shaft supporting point to the rotor shaft end face.
9. The method according to claim 4, wherein step 1 specifically comprises: the load of the fifth hydraulic cylinder (5) is I5=delta h/L2×cos (alpha+30 DEG), wherein alpha is a phase angle, F is the lift force born by a rotor shaft test piece of the main speed reducer, G is the dead weight of a rotor shaft hub dummy piece, L is the length of a long force arm, h1 is the bending moment value born by the rotor shaft end face, h2 is the maximum value of the bending moment born by the rotor shaft, delta h is the difference between h2 and h1, L1 is the distance from a bending moment 0 point to the rotor shaft end face, and L2 is the distance from a rotor shaft supporting point to the rotor shaft end face.
10. The method according to claim 4, wherein step 1 specifically comprises: the load I6=Δh/L2xsin (alpha+30°) of the sixth hydraulic cylinder (6), wherein alpha is a phase angle, F is a lift force born by a rotor shaft test piece of the main speed reducer, G is a dead weight of a rotor shaft hub dummy piece, L is a long arm length, h1 is a bending moment value born by a rotor shaft end face, h2 is a maximum value of the bending moment born by the rotor shaft, Δh is a difference between h2 and h1, L1 is a distance from a bending moment 0 point to the rotor shaft end face, and L2 is a distance from a rotor shaft supporting point to the rotor shaft end face.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310706971.7A CN116754224A (en) | 2023-06-14 | 2023-06-14 | Fatigue test device and method for rotor shaft of main speed reducer of helicopter |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310706971.7A CN116754224A (en) | 2023-06-14 | 2023-06-14 | Fatigue test device and method for rotor shaft of main speed reducer of helicopter |
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| CN116754224A true CN116754224A (en) | 2023-09-15 |
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| CN202310706971.7A Pending CN116754224A (en) | 2023-06-14 | 2023-06-14 | Fatigue test device and method for rotor shaft of main speed reducer of helicopter |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117268739A (en) * | 2023-11-22 | 2023-12-22 | 西安蓝天维特航空科技有限公司 | Helicopter tail speed reducer casing fatigue test device |
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2023
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117268739A (en) * | 2023-11-22 | 2023-12-22 | 西安蓝天维特航空科技有限公司 | Helicopter tail speed reducer casing fatigue test device |
| CN117268739B (en) * | 2023-11-22 | 2024-04-02 | 西安翼为航空科技有限公司 | Helicopter tail speed reducer casing fatigue test device |
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