CN104280241A - Helicopter rotor system elastic bearing load measuring device - Google Patents
Helicopter rotor system elastic bearing load measuring device Download PDFInfo
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- CN104280241A CN104280241A CN201410541592.8A CN201410541592A CN104280241A CN 104280241 A CN104280241 A CN 104280241A CN 201410541592 A CN201410541592 A CN 201410541592A CN 104280241 A CN104280241 A CN 104280241A
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Abstract
The invention relates to a helicopter rotor system elastic bearing load measuring device. The helicopter rotor system elastic bearing load measuring device comprises a measurement base, an X axis direction testing mechanism, a Y axis direction bending testing mechanism, a Z axis direction bending testing mechanism, an alignment locking mechanism and a torsion testing mechanism in the X axis direction. The measurement base is composed of a detecting platform base, a rotating shaft and a bearing large-end clamp and arranged at the bottom of the helicopter rotor system elastic bearing load measuring device. The X axis direction testing mechanism is arranged on the top of the helicopter rotor system elastic bearing load measuring device, and the torsion testing mechanism in the X axis direction, the alignment locking mechanism, the Y axis direction bending testing mechanism and the Z axis bending testing mechanism are correspondingly arranged on the lower layer, the middle layer and the upper layer of the helicopter rotor system elastic bearing load measuring device in sequence from bottom to top along the axis lead in the X direction. Through the helicopter rotor system elastic bearing load measuring device, the rigidity characteristic detection on different models of helicopter rotor system elastic bearings can be performed on one detecting platform, and university is good. The detecting efficiency and the safety of personnel in the detecting process are improved, the detecting strength is reduced, the elastic bearings can be clamped on one detecting platform at a time, and force (torque) in multi-dimensional directions can be loaded and measured.
Description
Technical field
The present invention relates to a kind of loading Measurement and analysis equipment, specifically a kind of helicopter rotor system resilient bearing loads measuring equipment.
Background technology
Resilient bearing is one of three large technology of third generation rotor system, is the important composition parts of rotor system, its stiffness characteristics and quality most important to Helicopter Safety, directly affect the quality of helicopter.Resilient bearing stiffness characteristics weighs one of most important characteristic of resilient bearing, so be necessary that it detects accurately.But the load mode loading measurement resilient bearing should be the comprehensive force application system of multidimensional wind tunnel, thus make the designing technique loading measuring equipment particularly complicated.Domestic at present not yet have the disposable equipment simultaneously carrying out loading and measure of helicopter resilient bearing multidimensional wind tunnel.It is that the loading carrying out certain individual event on different loading equipemtn is respectively measured that resilient bearing means are measured in the loading of prior art, and this causes detection efficiency low, and the working strength of testing staff is large, testing process poor stability, the shortcomings such as testing result precision is low.
Summary of the invention
For the deficiency that above-mentioned current condition exists, the invention provides a kind of helicopter rotor system resilient bearing and load measuring equipment.
A kind of helicopter rotor system resilient bearing loads measuring equipment, comprises measurement pedestal, X axis mechanism for testing, Y-axis and Z-axis direction crooked test mechanism, to lock locking mechanism, reverses mechanism for testing around X axis.
Measure pedestal and form by monitor station base 1, rotation axis 2, the large end fixture 3 of bearing the bottom being arranged on this equipment.
Monitor station base 1 upper surface is provided with bearing seat.The axis body core of rotation axis 2 is provided with splined hole, and rotation axis 2 axis body waist is provided with rotating disk, and rotating disk is provided with a pair pan symmetrically.Large its afterbody of end fixture 3 of bearing is splined shaft, and its head is provided with U-shaped jaw, and jaw both sides external is provided with mounting hole.
Rotation axis 2 axis body bottom is set in monitor station base 1 bearing saddle bore by thrust bearing.The axis body spline joint of rotation axis 2 afterbody of the large end fixture 3 of bearing.The U-shaped jaw of the large end fixture 3 of bearing upward.
X axis mechanism for testing is arranged on the top of this equipment.The mounting center of X axis mechanism for testing and monitor station base 1 bearing saddle bore central coaxial, and both form the X of loading measurement system to axial line.
Mechanism for testing, lower floor lock locking mechanism, Y-axis and Z-axis direction crooked test mechanism being arranged on respectively with being corresponding in turn to from the bottom to top to this equipment along X to axial line, middle level and upper strata is reversed around X axis.
Comprising reversing test fluid cylinder pressure A24 and reversing test fluid cylinder pressure B18 around X axis torsion mechanism for testing is power source, the couple force application system of coplanar horizontal is made up of connecting rod D26, force snesor C25 and connecting rod E28, force snesor D 27, and the lower floor of the equipment that is arranged on that linked together by rotation axis 2.
Described torsion test fluid cylinder pressure A24 piston flange end is arranged on the left back of rotation axis 2 towards the right side, and is connected to the flange end of ring flange and connecting rod D26 successively by bolt.Force snesor C25 chuck is between the core of two mounting flanges.Connecting rod D26 connecting-rod head is hinged on one end pan of rotation axis 2 rotating disk.
Reverse test fluid cylinder pressure B18 piston flange end is arranged on rotation axis 2 right front towards a left side, and be connected to the flange end of ring flange and connecting rod E28 by bolt successively.Force snesor D 27 chuck is between the core of two mounting flanges.Connecting rod E28 connecting-rod head is hinged on the other end pan of rotation axis 2 rotating disk.
The X axis mechanism for testing being arranged on equipment top comprises with compression verification hydraulic cylinder 10 for power source, forms force application system straight down by connecting rod A9, force snesor A21.
Its upper end of connecting rod A9 is bulb end, and its lower end is ring flange.
Compression verification hydraulic cylinder 10 is bolted to connection on the support of this equipment, and the piston head of compression verification hydraulic cylinder 10 straight down, and is connected with the bulb end of connecting rod A9 by spherical hinge A11.The ring flange end of connecting rod A9 is connected to the flange end of ring flange and connecting rod A9 successively by bolt, force snesor A21 chuck is between the core of two mounting flanges.
Y-axis and Z-axis direction crooked test mechanism comprise with crooked test hydraulic cylinder B14 and crooked test hydraulic cylinder A6 for power source, form by coupling shaft 8, connecting rod C22, force snesor B23, connecting rod B12 and connecting rod F30, force snesor E32, connecting rod G31 the force application system that the orthogonal both direction of coplanar horizontal acts on same point.
Its top of the square body of coupling shaft 8 is provided with flange, and the circular bosses core of its underpart is provided with splined hole, and coupling shaft 8 square body just above and right flank be respectively equipped with a vertical chute.
Connecting rod F30 is identical with connecting rod B12 contour structures, and one end is ring flange, and the other end is bulb end.
Connecting rod G31 is identical with connecting rod C22 contour structures, and one end is round pin head, and the other end is ring flange.
Coupling shaft 8 flange end by ring flange with the flange end of connecting rod A9 of X axis mechanism for testing be connected.
Y-axis and Z-axis direction crooked test mechanism are by being connected the upper strata of the equipment of being arranged on coupling shaft 8.
The piston axle bowl of crooked test hydraulic cylinder A6 is corresponding just above with coupling shaft 8 square body.The piston axle bowl of crooked test hydraulic cylinder A6 by spherical hinge C29 and connecting rod G30 bulb end hinged, connecting rod G30 flange end is connected to ring flange and connecting rod G31 ring flange end successively by bolt, force snesor E32 chuck between the core of two mounting flanges, connecting rod G31 round pin head end embed coupling shaft 8 square body just before chute in.
The piston axle bowl of crooked test hydraulic cylinder B14 is corresponding with coupling shaft 8 square body right flank.The piston axle bowl of crooked test hydraulic cylinder B14 with by spherical hinge B13 and connecting rod B12 bulb end hinged, connecting rod B12 flange end is connected to ring flange and connecting rod C22 ring flange end successively by bolt, force snesor B23 chuck is between the core of two mounting flanges, and connecting rod C22 round pin head end embeds in the chute of coupling shaft 8 square body right flank.
Locking hydraulic cylinder A7, locking hydraulic cylinder B15 and bearing small end fixture 5 are comprised to lock locking mechanism.
The waist of bearing small end fixture 5 is flat-square shaped, and the top of flat-square shaped is provided with splined shaft, and the bottom of flat-square shaped is bar blocks, and bar blocks is provided with mounting hole.
Locking hydraulic cylinder A7, locking hydraulic cylinder B15 piston head end are equipped with stick U-shaped jaw.
Middle level lock locking mechanism being arranged on to equipment is with locking hydraulic cylinder A7 and locking hydraulic cylinder B15 for power source, and forms coplanar horizontal with bearing small end fixture 5 and the both direction of conllinear acts on the force application system of same point.
Bearing small end fixture 5 top spline joint is in the splined hole of the coupling shaft 8 of Y-axis and Z-axis direction crooked test mechanism.
Locking hydraulic cylinder A7 piston head end and locking hydraulic cylinder B15 piston head end are oppositely arranged on the left and right side of bearing small end fixture 5, and the U-shaped jaw of the U-shaped jaw of locking hydraulic cylinder A7 and locking hydraulic cylinder B15 is clamped on the left and right limit of the flat-square shaped of bearing small end fixture 5 respectively.
Technique effect of the present invention is embodied in following several aspect:
1. the movement interference problem when carrying out different-stiffness Characteristics Detection respectively and the coupling of multiple stiffness characteristics detects has been taken into full account from design organization aspect, and by arranging that in the bearing small end fixture left and right sides hydraulic cylinder eliminates the degree of freedom of resilient bearing small end around X-axis, thus improve in the degree of accuracy of carrying out detecting when resilient bearing is tested around X-axis torsional rigidity;
2. can detect by changing the resilient bearing of resilient bearing fixture to different model, achieving the detection to different model helicopter rotor system resilient bearing stiffness characteristics on a monitor station, universal good;
3. from practical operation aspect, the present invention meets resilient bearing clamped one time, can carry out the difference of resilient bearing three-dimensional force and moment or load simultaneously, the detection of whole multidimensional stiffness characteristics can realize on a monitor station, eliminate the process changing experiment table when carrying out different-stiffness Characteristics Detection of prior art, improve detection efficiency, reduce the detected intensity of testing staff, improve the security of testing process personnel;
4. from holistic approach, by application of the present invention, resilient bearing once clamping on a monitor station can be realized, carry out loading and the measurement of multi-dimensional direction power (moment) simultaneously, make the detection efficiency of product can improve about 20%, testing staff's working strength reduces about 60%.
Accompanying drawing explanation
Fig. 1 is schematic three dimensional views of the present invention.
Fig. 2 is the front view of proving installation of the present invention.
Fig. 3 is the exploded view of the present invention along X to each critical piece of direction of axis line pick-up unit.
Fig. 4 is measurement pedestal of the present invention and reverses mechanism for testing exploded view around X axis.
Fig. 5 is Y-axis of the present invention and Z-axis direction crooked test mechanism exploded view.
Sequence number in figure: 1 monitor station base, 2 rotation axiss, the large end fixture of 3 bearing, 4 laser displacement sensor A, 5 bearing small end fixtures, 6 crooked test hydraulic cylinder A, 7 locking hydraulic cylinder A, 8 coupling shafts, 9 connecting rod A, 10 compression verification hydraulic cylinders, 11 spherical hinge A 12 connecting rod B, 13 spherical hinge B, 14 crooked test hydraulic cylinder B, 15 locking hydraulic cylinder B, 16 laser displacement sensor B, 17 laser displacement sensor C, 18 reverse test fluid cylinder pressure B, 19 laser displacement sensor D, 20 resilient bearings, 21 force snesor A, 22 connecting rod C, 23 force snesor B, 24 reverse test fluid cylinder pressure A, 25 force snesor C, 26 connecting rod D, 27 force snesor D, 28 connecting rod E, 29 spherical hinge C, 30 connecting rod F, 31 connecting rod G, 32 force snesor E.
Embodiment
Below in conjunction with accompanying drawing, by embodiment, the utility model is further described.
See Fig. 1.A kind of helicopter rotor system resilient bearing loads measuring equipment, comprises measurement pedestal, X axis mechanism for testing, Y-axis and Z-axis direction crooked test mechanism, to lock locking mechanism, reverses mechanism for testing around X axis.
See Fig. 4.Measure pedestal and form by monitor station base 1, rotation axis 2, the large end fixture 3 of bearing the bottom being arranged on this equipment; Monitor station base 1 upper surface is provided with bearing seat.Monitor station base 1 to be fixed on ground and to have enough intensity, can ensure the security of test process and the stability of test result.The axis body core of rotation axis 2 is provided with splined hole, and rotation axis 2 axis body waist is provided with rotating disk, and rotating disk is provided with a pair pan symmetrically.Large its afterbody of end fixture 3 of bearing is splined shaft, and its head is provided with U-shaped jaw, and jaw both sides external is provided with mounting hole; Rotation axis 2 axis body bottom is set in monitor station base 1 bearing saddle bore by thrust bearing.The axis body spline joint of rotation axis 2 afterbody of the large end fixture 3 of bearing.The U-shaped jaw of the large end fixture 3 of bearing upward.
See Fig. 2.Resilient bearing 20 is square body bottom it, and its waist is the frustum of a cone, and its top is provided with U-shaped mouth.The square body of resilient bearing 20 is arranged on the U-shaped jaw of the large end fixture 5 of bearing, and is bolted; X axis mechanism for testing is arranged on the top of this equipment.The mounting center of X axis mechanism for testing and monitor station base 1 bearing saddle bore central coaxial, and both form the X of loading measurement system to axial line; Mechanism for testing, lower floor lock locking mechanism, Y-axis and Z-axis direction crooked test mechanism being arranged on respectively with being corresponding in turn to from the bottom to top to this equipment along X to axial line, middle level and upper strata is reversed around X axis.
See Fig. 4.Comprising reversing test fluid cylinder pressure A24 and reversing test fluid cylinder pressure B18 around X axis torsion mechanism for testing is power source, the couple force application system of coplanar horizontal is made up of connecting rod D26, force snesor C25 and connecting rod E28, force snesor D 27, and the lower floor of the equipment that is arranged on that linked together by rotation axis 2; Reverse test fluid cylinder pressure A24 piston flange end is arranged on rotation axis 2 left back towards the right side, and be connected to the flange end of ring flange and connecting rod D26 by bolt successively.Force snesor C25 chuck is between the core of two mounting flanges.Connecting rod D26 connecting-rod head is hinged on one end pan of rotation axis 2 rotating disk.
Reverse test fluid cylinder pressure B18 piston flange end is arranged on rotation axis 2 right front towards a left side, and be connected to the flange end of ring flange and connecting rod E28 by bolt successively.Force snesor D 27 chuck is between the core of two mounting flanges.Connecting rod E28 connecting-rod head is hinged on the other end pan of rotation axis 2 rotating disk; Reverse test fluid cylinder pressure A24 identical with torsion test fluid cylinder pressure B18 specifications and models.The force snesor of this group puts on the clockwise or anticlockwise power on rotation axis 2 in order to mensuration torsion test fluid cylinder pressure A24 and torsion test fluid cylinder pressure B18, and then converses the clockwise or counter clockwise direction moment put on rotation axis 2 according to rotating disk radius.
Monitor station base 1 is provided with laser displacement sensor D19, when reversing test fluid cylinder pressure A24 and promoting dial rotation with torsion test fluid cylinder pressure B18 and then apply certain moment of torsion by rotation axis 2 and the large end fixture 5 of bearing to resilient bearing 20, laser displacement sensor D19 can measure the angle that rotating disk turns over, thus determines the angle that resilient bearing 20 turns over.
See Fig. 3.The X axis mechanism for testing being arranged on equipment top comprises with compression verification hydraulic cylinder 10 for power source, forms force application system straight down by connecting rod A9, force snesor A21; Its upper end of connecting rod A9 is bulb end, and its lower end is ring flange; Compression verification hydraulic cylinder 10 is bolted to connection on the support of this equipment, and the piston head of compression verification hydraulic cylinder 10 straight down, and is connected with the bulb end of connecting rod A9 by spherical hinge A11.Described connection by spherical hinge can ensure that connecting rod A9 has the degree of freedom of Y-axis and Z-axis direction, avoids the flexural deformation of connecting rod A9 in Y-axis and Z-axis direction and interferes.The ring flange end of connecting rod A9 is connected to the flange end of ring flange and connecting rod A9 successively by bolt.Force snesor A21 chuck is between the core of two mounting flanges, and this pressure transducer puts on pressure on resilient bearing 20 in order to measure compression verification hydraulic cylinder 10.
Be provided with laser displacement sensor C17 from Z axis forward bias to Y-axis forward 45 degree of directions, when compression verification hydraulic cylinder 10 applies X axis certain pressure to resilient bearing 20, laser displacement sensor C17 can measure the decrement of resilient bearing 20 at X axis.
See Fig. 5.Y-axis and Z-axis direction crooked test mechanism comprise with crooked test hydraulic cylinder B14 and crooked test hydraulic cylinder A6 for power source, form by coupling shaft 8, connecting rod C22, force snesor B23, connecting rod B12 and connecting rod F30, force snesor E32, connecting rod G31 the force application system that the orthogonal both direction of coplanar horizontal acts on same point.
Its top of the square body of coupling shaft 8 is provided with flange, and the circular bosses core of its underpart is provided with splined hole, and coupling shaft 8 square body just above and right flank be respectively equipped with a vertical chute.Coupling shaft 8 just above and the vertical chute of right flank its role is to ensure the degree of freedom of coupling shaft 8 at X axis, resilient bearing X axis compression displacement amount (maximum 2 millimeters) can be met, avoid movement interference, this chute can ensure that connecting rod C22 and connecting rod connecting rod G31 is all the time perpendicular to coupling shaft 8 plane simultaneously; Connecting rod F30 is identical with connecting rod B12 contour structures, and one end is ring flange, and the other end is bulb end; Connecting rod G31 is identical with connecting rod C22 contour structures, and one end is round pin head, and the other end is ring flange; Coupling shaft 8 flange end by ring flange with the flange end of connecting rod A9 of X axis mechanism for testing be connected.
Y-axis and Z-axis direction crooked test mechanism are by being connected the upper strata of the equipment of being arranged on coupling shaft 8.
The piston axle bowl of crooked test hydraulic cylinder A6 is corresponding just above with coupling shaft 8 square body.The piston axle bowl of crooked test hydraulic cylinder A6 by spherical hinge C29 and connecting rod G30 bulb end hinged, connecting rod G30 flange end is connected to ring flange and connecting rod G31 ring flange end successively by bolt, and force snesor E32 chuck is between the core of two mounting flanges.Connecting rod G31 round pin head end embed coupling shaft 8 square body just before chute in, in chute, above-below direction short distance can slide (being no more than 3 millimeters).Force snesor E32 can measure crooked test hydraulic cylinder A6 and act on Z axis power forward or backwards on coupling shaft 8; The piston axle bowl of crooked test hydraulic cylinder B14 is corresponding with coupling shaft 8 square body right flank.The piston axle bowl of crooked test hydraulic cylinder B14 with by spherical hinge B13 and connecting rod B12 bulb end hinged, connecting rod B12 flange end is connected to ring flange and connecting rod C22 ring flange end successively by bolt, and force snesor B23 chuck is between the core of two mounting flanges.Connecting rod C22 round pin head end embeds in the chute of coupling shaft 8 square body right flank, above-below direction short distance can slide (being no more than 3 millimeters) in chute.Force snesor B23 can measure crooked test hydraulic cylinder B14 and act on Y-axis power forward or backwards on coupling shaft 8.
See Fig. 3.Locking hydraulic cylinder A7, locking hydraulic cylinder B15 and bearing small end fixture 5 are comprised to lock locking mechanism.
The waist of bearing small end fixture 5 is flat-square shaped, and the top of flat-square shaped is provided with splined shaft, and the bottom of flat-square shaped is bar blocks, and bar blocks is provided with mounting hole; Locking hydraulic cylinder A7, locking hydraulic cylinder B15 piston head end are equipped with stick U-shaped jaw; Middle level lock locking mechanism being arranged on to equipment is with locking hydraulic cylinder A7 and locking hydraulic cylinder B15 for power source, and forms coplanar horizontal with bearing small end fixture 5 and the both direction of conllinear acts on the force application system of same point; Bearing small end fixture 5 top spline joint is in the splined hole of the coupling shaft 8 of Y-axis and Z-axis direction crooked test mechanism.
Locking hydraulic cylinder A7 piston head end and locking hydraulic cylinder B15 piston head end are oppositely arranged on the left and right side of bearing small end fixture 5, and the U-shaped jaw of the U-shaped jaw of locking hydraulic cylinder A7 and locking hydraulic cylinder B15 is clamped on the left and right limit of the flat-square shaped of bearing small end fixture 5 respectively; The U-shaped mouth of resilient bearing 20 is stuck in the bar blocks of bearing small end fixture 5, by and be bolted.
When mounted, ensure that resilient bearing 20 is coaxial to axial line with X.
Bearing small end fixture about 5 two ends are arranged symmetrically with locking hydraulic cylinder A7 and locking hydraulic cylinder B15 and its role is to carry out being fixed on bearing small end fixture 5, to ensure accuracy resilient bearing 20 being applied to moment of torsion when torsional rigidity detects at resilient bearing 20.
Resilient bearing 20 or when bearing crooked test hydraulic cylinder A6 or bear the acting force of crooked test hydraulic cylinder B14 and bend, whole resilient bearing 20 and coupling shaft 8 can extend because of bending, but because elongation is very little, key connects and can slide a little to compensate this elongation on keyway, thus prevent movement interference, with the security of the accuracy and equipment that improve test; Be provided with laser displacement sensor A4 in the dead ahead of resilient bearing 20, when resilient bearing 20 bears the power of crooked test hydraulic cylinder A6 applying at Z axis, laser displacement sensor A4 can measure the side-play amount of resilient bearing 20 in Z-direction.
Be provided with laser displacement sensor B16 on the right side of resilient bearing 20, when resilient bearing 20 bears the power of crooked test hydraulic cylinder B28 applying in Y-axis, laser displacement sensor B16 can measure the side-play amount of resilient bearing 20 in Y direction.
Principle of work of the present invention:
1, the test of X axis stiffness characteristics is carried out to resilient bearing
See Fig. 2.Pressure is applied to resilient bearing 20 when keeping compression verification hydraulic cylinder 10 to work, remaining fluid cylinder pressure does not work, the pressure that resilient bearing 20 bears directly can be measured by pressure transducer A21, measure the X axis compress variation of resilient bearing 20 under this pressure by laser displacement sensor C17 simultaneously, by the pressure measured and compress variation, calculate X axis compression stiffness;
2, resilient bearing is carried out to the bending stiffness characteristic test of Z-axis direction
See Fig. 5.Keep crooked test hydraulic cylinder A6 work, remaining fluid cylinder pressure does not work, the bending force of resilient bearing 20 suffered by Z-direction directly can be measured by force snesor E32, and calculate moment of flexure further, calculate the angle of bend of resilient bearing 20 under this bending force by laser displacement sensor A4 simultaneously, by the Z-axis direction moment of flexure measured and angle of bend, the bending stiffness of Z-axis direction can be calculated.In this test, under the effect by control desk operation valve, crooked test hydraulic cylinder A6 can apply the power in Z-axis direction direction respectively to resilient bearing 20, measure pressure by force snesor E32, finally can calculate the bending stiffness of resilient bearing 20 in Z-axis direction direction;
3, resilient bearing is carried out to the bending stiffness characteristic test of Y-axis
See Fig. 5.Keep crooked test hydraulic cylinder B14 work, remaining fluid cylinder pressure does not work, the bending force of resilient bearing 20 suffered by Y direction directly can be measured by force snesor B23, and calculate moment of flexure further, calculate the angle of bend of resilient bearing 20 under this bending force by laser displacement sensor B16 simultaneously, by the Y-axis moment of flexure measured and angle of bend, the bending stiffness of Y-axis can be calculated.In this test, under the effect by control desk operation valve, crooked test hydraulic cylinder B14 can apply the power in Y-axis direction respectively to resilient bearing 20, measure pressure by force snesor B23, finally can calculate the bending stiffness of resilient bearing 20 in Y-axis direction;
4, carry out testing around X axis torsional rigidity to resilient bearing
See Fig. 2, Fig. 4.Locking hydraulic cylinder A7 and locking hydraulic cylinder B15 works and to be fixed by resilient bearing 20, reverse test fluid cylinder pressure A24 to work with torsion test fluid cylinder pressure B18 simultaneously, acting force is applied to rotation axis 2 by rotating disk, measured by force snesor C25 and force snesor D27 and now reverse test fluid cylinder pressure A24 and reverse test fluid cylinder pressure B18 and act on power on rotation axis 2, because rotating disk radius is certain and known, therefore draw the moment of torsion suffered by resilient bearing 20 by torsion test fluid cylinder pressure A24 and the torsion test fluid cylinder pressure B18 power acted on rotation axis 2.Simultaneously calculate by laser displacement sensor D19 the angle that resilient bearing 20 deflects around X-axis, by the moment of torsion measured and rotational angle, the torsional rigidity of resilient bearing 20 around X-axis can be calculated.In this test, under effect by control desk operation valve, reverse test fluid cylinder pressure A24 with reverse test fluid cylinder pressure B18 can to resilient bearing 20 provide clockwise with the moment of torsion of counterclockwise both direction, so can calculate resilient bearing 20 around X-axis clockwise with the torsional rigidity of counterclockwise both direction;
5, above-mentioned four kinds of stiffness test methods carry out simultaneously, can testing elastic bearing at the stiffness characteristics bearing each dimension under compression, torsion, the coupling simultaneously such as bending.
Claims (5)
1. helicopter rotor system resilient bearing loads a measuring equipment, it is characterized in that: comprise measurement pedestal, X axis mechanism for testing, Y-axis and Z-axis direction crooked test mechanism, to lock locking mechanism, reverse mechanism for testing around X axis;
Described measurement pedestal forms by monitor station base (1), rotation axis (2), the large end fixture (3) of bearing the bottom being arranged on this equipment;
Described monitor station base (1) upper surface is provided with bearing seat; The axis body core of described rotation axis (2) is provided with splined hole, and rotation axis (2) axis body waist is provided with rotating disk, and rotating disk is provided with a pair pan symmetrically; Its afterbody of the large end fixture (3) of described bearing is splined shaft, and its head is provided with U-shaped jaw, and jaw both sides external is provided with mounting hole;
Described rotation axis (2) axis body bottom is set in monitor station base (1) bearing saddle bore by thrust bearing; The axis body spline joint of described rotation axis (2) the afterbody of the large end fixture (3) of bearing; The U-shaped jaw of the large end fixture (3) of described bearing upward;
Described X axis mechanism for testing is arranged on the top of this equipment; The mounting center of X axis mechanism for testing and monitor station base (1) bearing saddle bore central coaxial, and both form the X of loading measurement system to axial line;
Described around X axis torsion mechanism for testing, lower floor lock locking mechanism, Y-axis and Z-axis direction crooked test mechanism being arranged on respectively with being corresponding in turn to from the bottom to top to this equipment along X to axial line, middle level and upper strata.
2. a kind of helicopter rotor system resilient bearing according to claim 1 loads measuring equipment, it is characterized in that: describedly reverse mechanism for testing around X axis and comprise reversing test fluid cylinder pressure A(24) and torsion test fluid cylinder pressure B(18) be power source, by connecting rod D(26), force snesor C(25) and connecting rod E(28), force snesor D (27) forms the couple force application system of coplanar horizontal, and the lower floor of the equipment that is arranged on that linked together by rotation axis (2);
Described torsion test fluid cylinder pressure A(24) piston flange end is arranged on the left back of rotation axis (2), and is connected to ring flange and connecting rod D(26 successively by bolt towards the right side) flange end; Described force snesor C(25) chuck is between the core of two mounting flanges; Described connecting rod D(26) connecting-rod head is hinged on one end pan of rotation axis (2) rotating disk;
Described torsion test fluid cylinder pressure B(18) piston flange end is arranged on the right front of rotation axis (2), and is connected to ring flange and connecting rod E(28 successively by bolt towards a left side) flange end; Described force snesor D (27) chuck is between the core of two mounting flanges; Described connecting rod E(28) connecting-rod head is hinged on the other end pan of rotation axis (2) rotating disk.
3. a kind of helicopter rotor system resilient bearing according to claim 1 loads measuring equipment, it is characterized in that: described in be arranged on equipment top X axis mechanism for testing comprise with compression verification hydraulic cylinder (10) for power source, by connecting rod A(9), force snesor A(21) form force application system straight down;
Described connecting rod A(9) its upper end is bulb end, its lower end is ring flange;
Described compression verification hydraulic cylinder (10) is bolted to connection on the support of this equipment, the piston head of compression verification hydraulic cylinder (10) straight down, and by spherical hinge A(11) with connecting rod A(9) bulb end be connected; Described connecting rod A(9) ring flange end be connected to ring flange and connecting rod A(9 successively by bolt) flange end, described force snesor A(21) chuck is between the core of two mounting flanges.
4. a kind of helicopter rotor system resilient bearing according to claim 1 loads measuring equipment, it is characterized in that: described Y-axis and Z-axis direction crooked test mechanism comprise with crooked test hydraulic cylinder B(14) and crooked test hydraulic cylinder A(6) for power source, by coupling shaft (8), connecting rod C(22), force snesor B(23), connecting rod B(12) and connecting rod F(30), force snesor E(32), connecting rod G(31) form the force application system that the orthogonal both direction of coplanar horizontal acts on same point;
Its top of square body of described coupling shaft (8) is provided with flange, and the circular bosses core of its underpart is provided with splined hole, and described coupling shaft (8) square body just above and right flank be respectively equipped with a vertical chute;
Described connecting rod F(30) with connecting rod B(12) contour structures is identical, one end is ring flange, and the other end is bulb end; Described connecting rod G(31) with connecting rod C(22) contour structures is identical, one end is round pin head, and the other end is ring flange;
Described coupling shaft (8) flange end by ring flange with the connecting rod A(9 of X axis mechanism for testing) flange end be connected;
Described Y-axis and Z-axis direction crooked test mechanism are by being connected the upper strata of the equipment of being arranged on coupling shaft (8);
Described crooked test hydraulic cylinder A(6) piston axle bowl and coupling shaft (8) square body corresponding just above; Crooked test hydraulic cylinder A(6) piston axle bowl by spherical hinge C(29) with connecting rod G(30) bulb end is hinged, described connecting rod G(30) flange end is connected to ring flange and connecting rod G(31 successively by bolt) ring flange end, described force snesor E(32) chuck between the core of two mounting flanges, described connecting rod G(31) round pin head end embed coupling shaft (8) square body just before chute in;
Described crooked test hydraulic cylinder B(14) piston axle bowl corresponding with coupling shaft (8) square body right flank; Crooked test hydraulic cylinder B(14) piston axle bowl with by spherical hinge B(13) with connecting rod B(12) bulb end is hinged, described connecting rod B(12) flange end is connected to ring flange and connecting rod C(22 successively by bolt) ring flange end, described force snesor B(23) chuck between the core of two mounting flanges, described connecting rod C(22) round pin head end embed coupling shaft (8) square body right flank chute in.
5. a kind of helicopter rotor system resilient bearing according to claim 1 loads measuring equipment, it is characterized in that: describedly comprise locking hydraulic cylinder A(7 to lock locking mechanism), locking hydraulic cylinder B(15) and bearing small end fixture (5);
The waist of described bearing small end fixture (5) is flat-square shaped, and the top of flat-square shaped is provided with splined shaft, and the bottom of flat-square shaped is bar blocks, and bar blocks is provided with mounting hole;
Described locking hydraulic cylinder A(7), locking hydraulic cylinder B(15) piston head end is equipped with stick U-shaped jaw;
The described middle level being arranged on equipment to lock locking mechanism is with locking hydraulic cylinder A(7) and locking hydraulic cylinder B(15) for power source, and form coplanar horizontal with bearing small end fixture (5) and the both direction of conllinear acts on the force application system of same point;
Described bearing small end fixture (5) top spline joint is in the splined hole of the coupling shaft (8) of Y-axis and Z-axis direction crooked test mechanism;
Described locking hydraulic cylinder A(7) piston head end and locking hydraulic cylinder B(15) piston head end is oppositely arranged on the left and right side of bearing small end fixture (5), and locking hydraulic cylinder A(7) U-shaped jaw and locking hydraulic cylinder B(15) U-shaped jaw be clamped in respectively on the left and right limit of the flat-square shaped of bearing small end fixture (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410541592.8A CN104280241B (en) | 2014-10-14 | A kind of helicopter rotor system resilient bearing loads measurement equipment |
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| CN201410541592.8A CN104280241B (en) | 2014-10-14 | A kind of helicopter rotor system resilient bearing loads measurement equipment |
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| CN104280241A true CN104280241A (en) | 2015-01-14 |
| CN104280241B CN104280241B (en) | 2017-01-04 |
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| CN105699078A (en) * | 2016-04-21 | 2016-06-22 | 青岛科技大学 | Angle-adjustable multifunctional testing stand for universal coupling |
| CN106092583A (en) * | 2016-08-12 | 2016-11-09 | 浙江万向精工有限公司 | Hub bearing unit torque rigidity test system and method |
| CN107907333A (en) * | 2017-11-29 | 2018-04-13 | 中国直升机设计研究所 | A kind of cylindrical elastomeric bearing fatigue experimental rig |
| CN108760309A (en) * | 2018-06-29 | 2018-11-06 | 燕山大学 | A kind of Helicopter Main rotor system forms a complete set of bearing tester |
| CN110017987A (en) * | 2019-04-09 | 2019-07-16 | 深圳市骁阳工程咨询有限公司 | High speed roller bearing testing stand |
| CN110243687A (en) * | 2019-06-06 | 2019-09-17 | 中国人民解放军总参谋部第六十研究所 | A kind of elastic shaft that environment temperature is controllable pressure-bearing-torsion combination experiment system |
| CN110849566A (en) * | 2019-10-28 | 2020-02-28 | 南通大学 | Magnetostrictive material driven torsional fatigue test device and method |
| CN110895184A (en) * | 2019-12-04 | 2020-03-20 | 中国直升机设计研究所 | Ground test system for unidirectional vibration reduction efficiency of helicopter vibration active control system |
| CN112461464A (en) * | 2020-11-20 | 2021-03-09 | 中国直升机设计研究所 | Torsion rigidity test loading device for central elastic bearing |
| CN113340546A (en) * | 2021-04-28 | 2021-09-03 | 重庆大学 | Bearing dismounting and rigidity testing integrated device |
| CN113551910A (en) * | 2021-08-27 | 2021-10-26 | 中浙高铁轴承有限公司 | Helicopter rotor system matched bearing testing machine and method |
| CN114320870A (en) * | 2021-12-07 | 2022-04-12 | 中国航发控制***研究所 | Vibration clamp with rotary motion transmission |
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| CN105699078A (en) * | 2016-04-21 | 2016-06-22 | 青岛科技大学 | Angle-adjustable multifunctional testing stand for universal coupling |
| CN105699078B (en) * | 2016-04-21 | 2018-02-02 | 青岛科技大学 | A kind of multifunctional universal of adjustable angle is coupler test-bed |
| CN106092583A (en) * | 2016-08-12 | 2016-11-09 | 浙江万向精工有限公司 | Hub bearing unit torque rigidity test system and method |
| CN107907333A (en) * | 2017-11-29 | 2018-04-13 | 中国直升机设计研究所 | A kind of cylindrical elastomeric bearing fatigue experimental rig |
| CN107907333B (en) * | 2017-11-29 | 2020-02-21 | 中国直升机设计研究所 | Cylindrical elastic bearing fatigue test device |
| CN108760309A (en) * | 2018-06-29 | 2018-11-06 | 燕山大学 | A kind of Helicopter Main rotor system forms a complete set of bearing tester |
| CN108760309B (en) * | 2018-06-29 | 2019-08-02 | 燕山大学 | A kind of Helicopter Main rotor system forms a complete set of bearing tester |
| CN110017987A (en) * | 2019-04-09 | 2019-07-16 | 深圳市骁阳工程咨询有限公司 | High speed roller bearing testing stand |
| CN110017987B (en) * | 2019-04-09 | 2022-04-12 | 深圳市骁阳工程咨询有限公司 | High-speed rolling bearing test bed |
| CN110243687A (en) * | 2019-06-06 | 2019-09-17 | 中国人民解放军总参谋部第六十研究所 | A kind of elastic shaft that environment temperature is controllable pressure-bearing-torsion combination experiment system |
| CN110243687B (en) * | 2019-06-06 | 2022-01-07 | 中国人民解放军总参谋部第六十研究所 | Environmental temperature controllable elastic bearing pressure-torsion combined experiment system |
| CN110849566B (en) * | 2019-10-28 | 2021-11-30 | 南通大学 | Magnetostrictive material driven torsional fatigue test device and method |
| CN110849566A (en) * | 2019-10-28 | 2020-02-28 | 南通大学 | Magnetostrictive material driven torsional fatigue test device and method |
| CN110895184B (en) * | 2019-12-04 | 2021-09-21 | 中国直升机设计研究所 | Ground test system for unidirectional vibration reduction efficiency of helicopter vibration active control system |
| CN110895184A (en) * | 2019-12-04 | 2020-03-20 | 中国直升机设计研究所 | Ground test system for unidirectional vibration reduction efficiency of helicopter vibration active control system |
| CN112461464A (en) * | 2020-11-20 | 2021-03-09 | 中国直升机设计研究所 | Torsion rigidity test loading device for central elastic bearing |
| CN113340546A (en) * | 2021-04-28 | 2021-09-03 | 重庆大学 | Bearing dismounting and rigidity testing integrated device |
| CN113551910A (en) * | 2021-08-27 | 2021-10-26 | 中浙高铁轴承有限公司 | Helicopter rotor system matched bearing testing machine and method |
| CN113551910B (en) * | 2021-08-27 | 2024-04-05 | 中浙高铁轴承有限公司 | Helicopter rotor system matched bearing testing machine and method |
| CN114320870A (en) * | 2021-12-07 | 2022-04-12 | 中国航发控制***研究所 | Vibration clamp with rotary motion transmission |
| CN114320870B (en) * | 2021-12-07 | 2023-07-14 | 中国航发控制***研究所 | Vibration fixture with rotary motion transmission function |
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