CN110758768B - Loading device for stiffness test of flexible beam of bearingless rotor wing - Google Patents
Loading device for stiffness test of flexible beam of bearingless rotor wing Download PDFInfo
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- CN110758768B CN110758768B CN201910981662.4A CN201910981662A CN110758768B CN 110758768 B CN110758768 B CN 110758768B CN 201910981662 A CN201910981662 A CN 201910981662A CN 110758768 B CN110758768 B CN 110758768B
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0016—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings of aircraft wings or blades
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Abstract
The invention belongs to the technical field of helicopter bearingless rotor flexible beam rigidity tests, and relates to a bearingless rotor flexible beam rigidity test loading device. The device includes centre gripping frame (A) and bracing piece (B), wherein, centre gripping frame (A) includes the clamping part, wave the bending moment and apply the portion, the portion is applyed to the shimmy bending moment, torsion bar (A5), wave the bending moment and apply the portion and set up the below at the clamping part, the portion sets up the one side at the clamping part is applyed to the shimmy bending moment, torsion bar (A5) includes straight line portion and arc portion, wherein the straight line portion of torsion bar (A5) is fixed with the opposite side of clamping part, the arc structure of torsion bar (A5) for using straight line portion as the diameter, and the outer tip of this arc structure is provided with the screw hole, bracing piece (B) and centre gripping frame (A) fixed connection.
Description
Technical Field
The invention belongs to the technical field of helicopter bearingless rotor flexible beam rigidity tests, and relates to a bearingless rotor flexible beam rigidity test loading device.
Background
The flexible beam of the bearingless rotor wing is a key component of a helicopter rotor wing system, and the design of the flexible beam not only needs to meet the strength requirement of a structure, but also needs to meet reasonable rigidity characteristics.
The results of the bearing-free rotor flexible beam stiffness test are mainly used for evaluating the conformance of the section characteristics of the bearing-free rotor flexible beam to theoretical calculated values, the test results provide important data support for rotor dynamics calculation, load calculation, strength check and the like, and meanwhile, a powerful basis is provided for the structural design of a rotor system.
The stiffness test of the flexible beam of the bearingless rotor mainly comprises the test of waving bending stiffness, shimmy bending stiffness and torsional stiffness, the test requires that waving bending moment, shimmy bending moment and torque are applied to the same section of the flexible beam, and a pure torque around the direction of a torsional center line is applied. In order to realize that loads in different directions and pure torque are applied to the flexible beam and ensure the precision and reliability of test loading, a special loading device is required. However, the prior art has no proper loading device for the stiffness test of the flexible beam of the bearingless rotor, and cannot be replaced by other loading devices.
Disclosure of Invention
In view of the above-mentioned state of the art, the object of the invention is: the utility model provides a simple structure, convenient equipment, and same loading section can apply respectively and wave the flexural beam rigidity test loading device of moment of flexure, shimmy moment of flexure and pure moment of torsion of rotor without bearing.
The technical scheme of the invention is as follows:
in a first aspect, the bearing-free rotor flexible beam rigidity test loading device comprises a clamping frame A and a supporting rod B, wherein the clamping frame A comprises a clamping part, a waving bending moment applying part, a shimmy bending moment applying part and a torsion rod A5,
waving bending moment applying part is arranged below the clamping part, swinging bending moment applying part is arranged on one side of the clamping part, the torsion bar A5 comprises a straight line part and an arc-shaped part, wherein the straight line part of the torsion bar A5 is fixed with the other side of the clamping part, the arc-shaped part of the torsion bar A5 is of an arc-shaped structure taking the straight line part as the diameter, the outer end part of the arc-shaped structure is provided with a threaded hole, and the support bar B is fixedly connected with the clamping frame A.
Optionally, the clamping portion specifically includes a clamping groove a1 and a cover plate a2, the cover plate a2 is disposed above the clamping groove a1, and an opening for placing a loading end of the flexible beam of the bearingless rotor is disposed on a side surface of the clamping groove a 1.
Optionally, the flapping-moment imparting part comprises a monaural a 3.
Optionally, the shimmy bending moment application part comprises a double lug A4.
Optionally, a groove is provided on the outer side of the arc portion of torsion bar a 5.
Optionally, the support rod B includes an adapter B1, a deep groove ball bearing B2, and a fixed support double ear B3, where the adapter B1 is connected to the fixed support double ear B3 through a deep groove ball bearing B2, and the fixed support double ear B3 is fixed to the upper end of the support rod.
Optionally, the adapter B1 is connected to the fixed branch double lug B3 through a deep groove ball bearing B2, and specifically includes: the adapter B1 is in interference fit with the deep groove ball bearing B2, and the deep groove ball bearing B2 is in interference fit with the fixed support double lugs B3.
Optionally, the support rod includes an upper screw B5, a lower support rod B6 and a middle screw B7, wherein the middle screw B7 is a circular tube structure, and a first thread is provided on an inner surface of an upper end of the middle screw B7, a second thread is provided on an inner surface of a lower end of the middle screw B7, the first thread is opposite to the second thread, a thread matching the first thread is provided on an outer surface of a lower end of the upper screw B5, and a thread matching the second thread is provided on an outer surface of an upper end of the lower support rod B6.
Optionally, the side wall of the clamping groove a1 is provided with a hollow structure.
Optionally, the outer surface of the middle screw B7 is provided with groove-shaped openings which are symmetrical up and down
The invention has the technical effects that: centre gripping frame and bracing piece package assembly simple structure just can apply respectively at same loading section and wave the moment of flexure, shimmy moment of flexure and pure moment of torsion, and a moment of torsion is applyed through the circular arc structure on the torsion bar, can guarantee in certain torsion angle within range, and the moment of torsion of applying on no bearing rotor flexible beam is unchangeable.
Drawings
FIG. 1 is a block diagram of a bearingless rotor flex beam stiffness test loading unit according to an embodiment of the present invention;
FIG. 2 is a block diagram of a clamping frame of a bearingless rotor flexible beam stiffness test loading device according to an embodiment of the invention;
fig. 3 is a structural diagram of a support rod of a stiffness test loading device of a bearingless rotor flexible beam according to an embodiment of the invention.
The clamping frame A, the clamping groove A1, the cover plate A2, the single lug A3, the double lugs A4, the torsion rod A5, the first bolt A6, the second bolt A7, the third bolt A8, the support rod B, the adapter B1, the deep groove ball bearing B2, the fixed support double lugs B3, the fourth bolt B4, the upper screw B5, the lower support rod B6 and the middle screw B7.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention discloses a bearing-free rotor wing flexible beam rigidity test loading device which comprises a clamping frame A and a supporting rod B as shown in figure 1.
Specific structure of clamping frame a referring to fig. 2, the clamping frame a includes a clamping groove a1, a cover plate a2, a single lug A3, two lugs a4, a torsion bar a5, a first bolt a6, a second bolt a7, a third bolt A8, and a nut.
The clamping groove A1 is a U-shaped groove structure, two threaded holes are respectively arranged on two sides of the upper surface, four threaded holes are arranged on the left outer side, one threaded hole is arranged on the right outer side, and two circular through holes are arranged on the lower surface.
The cover plate A2 is a rectangular flat plate, two ends of the flat plate are respectively provided with four small through holes, and the positions of the four small through holes correspond to the four holes on the upper surface of the clamping groove.
The single lug A3 is in T-shaped structure when viewed from the side, two through holes are symmetrically arranged on the transverse plane of the single lug A3, the through holes correspond to the through holes on the lower surface of the clamping groove A1, and a round hole is arranged on the vertical plane.
The double-lug A4 is formed by a U-shaped structure and a rod when viewed from the side surface, both sides of the U-shaped structure are provided with a circular through hole, and the rod is a circular rod with threads.
The torsion bar A5 is composed of three structures of arc, bar and plate, its left side has an arc structure connected with the bar, the side of the arc has a groove, the groove surface has a round hole, the right side of the torsion bar A5 has a thin plate connected with the bar, the thin plate has four through holes, the positions of the holes correspond to the positions of the holes at the left and outer sides of the holding groove A1.
During test installation, a first bolt A6 penetrates through a through hole in the cover plate and is screwed into a threaded hole of the clamping groove A1, the clamping groove A1 and the cover plate A2 clamp the loading end of the bearingless rotor flexible beam, meanwhile, two round holes are arranged in the middle of the cover plate A2, the hole centers of the hole center of the hole of the loading end of the bearingless rotor flexible beam and the hole centers of two holes in the lower portion of the clamping groove A1 are matched with the hole centers of holes in the transverse surface of the single lug A3, the cover plate A2, the bearingless rotor flexible beam, the clamping groove A1 and the single lug A3 are fixedly connected through a second bolt A7 and a nut, the four hole centers on the torsion rod A5 are matched with the hole centers of four threaded holes in the left side of the clamping groove, the torsion rod A5 is fixed on the left side of the clamping groove A1 through a third bolt A8, and a threaded rod A4 is screwed into the right threaded hole of the clamping groove A1.
During test loading, after installation is finished according to the flow, the bearing-free rotor wing flexible beam can be connected with the bolt and the steel cable through the single lug A3 or the double lugs A4 respectively, so that swinging or shimmy bending moment is applied to the loading end of the bearing-free rotor wing flexible beam, and after the supporting rod B is additionally arranged when pure torque is applied, the bearing-free rotor wing flexible beam is connected with the bolt through the torsion rod A5 and the steel cable.
The structure of the support rod B is described in detail below, and referring to fig. 3, the support rod B is composed of an adapter B1, a deep groove ball bearing B2, a fixed support double lug B3, a fourth bolt B4, an upper screw B5, a lower support rod B6, and a middle screw B7.
Adapter B1 is similar "U" style of calligraphy groove structure, and U type groove both sides respectively have two through-holes, and the position in hole corresponds with the position of centre gripping groove lower surface hole. A circular through hole is formed in the bottom of the U-shaped groove, and a deep groove ball bearing B2 is embedded in the through hole.
The fixed support double lugs B3 are composed of a U-shaped groove and a round rod, two through holes are respectively arranged on two sides of the U-shaped groove, and the round rod is arranged in the middle of the bottom of the U-shaped groove and is in interference fit with the round hole of the deep groove ball bearing.
Go up screw rod B5 and constitute by cylinder and cuboid, the cylinder surface has one section screw thread, and the cuboid side has two circular through-holes, and the position in hole corresponds with the position of solid support ears upper hole.
The lower stay bar B6 is composed of a cylinder, a reinforcing rib and a cuboid, and the outer surface of the cylinder is provided with a section of screw thread.
Well screw rod B7 is round tube structure, and the pipe both ends internal surface has reverse screw thread, cooperates with last screw rod B5 and lower vaulting pole B6 respectively, realizes flexible function, and the pipe outside has two kidney slots through-holes, conveniently looks over the screw rod position.
This device can exert respectively at the same loading section of no bearing rotor flexible beam through the equipment of difference and wave bending moment, shimmy bending moment and pure moment of torsion.
Centre gripping frame and bracing piece equipment, wherein the height-adjustable of bracing piece, the accommodation is about half a meter, can satisfy the requirement of different mounting heights, the adapter on the bracing piece is embedded to have a deep groove ball bearing, the bearing center is supported admittedly, apply a moment of torsion through the circular arc groove on the torsion bar, can guarantee in certain torsion angle scope, it is unchangeable to apply the moment of torsion on no bearing rotor flexible beam, rotate round its torsion central line, the bracing piece is placed on ground, it is unchangeable to have guaranteed that the centre of torsion is fixed.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any modifications or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (6)
1. The utility model provides a no bearing rotor flexible beam rigidity test loading device, a serial communication port, including centre gripping frame (A) and bracing piece (B), wherein, centre gripping frame (A) includes the clamping part, wave the moment of flexure and exert the portion, the pendulum vibration moment of flexure is exerted the portion, torsion bar (A5), wave the moment of flexure and exert the portion and set up in the below of clamping part, the pendulum vibration moment of flexure is exerted the portion and is set up in one side of clamping part, torsion bar (A5) includes straight line portion and arc portion, wherein the straight line portion of torsion bar (A5) is fixed with the opposite side of clamping part, the arc portion of torsion bar (A5) is the arc structure with straight line portion as the diameter, and the outer tip of this arc structure is provided with the screw hole, bracing piece (B) and centre gripping frame (A) fixed connection, the clamping part specifically includes centre gripping groove (A1), apron (A2), apron (A2) sets up above centre gripping groove (A1), centre gripping groove (A1) side is provided with the opening and is used for placing the flexible loading end of no bearing rotor beam, the swing bending moment applying part comprises a single lug (A3), the shimmy bending moment applying part comprises double lugs (A4), the single lug (A3) is arranged below the clamping groove (A1), and the double lugs (A4) are arranged on one side surface of the clamping groove (A1); the support rod (B) comprises an adapter (B1), a deep groove ball bearing (B2) and a fixed support double ear (B3), the adapter (B1) is connected with the fixed support double ear (B3) through the deep groove ball bearing (B2), and the fixed support double ear (B3) is fixed with the upper end of the support rod.
2. The device of claim 1, wherein the outer side of the arc of the torsion bar (a5) is provided with a groove.
3. The device according to claim 1, characterized in that the adapter (B1) is connected to the fixed support ears (B3) by deep groove ball bearings (B2), and specifically comprises: the adapter (B1) is in interference fit with the deep groove ball bearing (B2), and the deep groove ball bearing (B2) is in interference fit with the fixed support double lugs (B3).
4. The apparatus of claim 1, wherein the support bar comprises an upper screw (B5), a lower support bar (B6) and a middle screw (B7), wherein the middle screw (B7) has a circular tube structure and is provided with a first thread on an inner surface of an upper end of the middle screw (B7), and a second thread on an inner surface of a lower end of the middle screw (B7), the first thread being opposite to the second thread, wherein the outer surface of the lower end of the upper screw (B5) is provided with a thread matching the first thread, and the outer surface of the upper end of the lower support bar (B6) is provided with a thread matching the second thread.
5. The device according to claim 1, characterized in that the side walls of the clamping groove (A1) are provided with hollow structures.
6. The device according to claim 1, characterized in that the outer surface of the middle screw (B7) is provided with a slot-shaped opening which is symmetrical up and down.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910981662.4A CN110758768B (en) | 2019-10-15 | 2019-10-15 | Loading device for stiffness test of flexible beam of bearingless rotor wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910981662.4A CN110758768B (en) | 2019-10-15 | 2019-10-15 | Loading device for stiffness test of flexible beam of bearingless rotor wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110758768A CN110758768A (en) | 2020-02-07 |
| CN110758768B true CN110758768B (en) | 2022-07-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910981662.4A Active CN110758768B (en) | 2019-10-15 | 2019-10-15 | Loading device for stiffness test of flexible beam of bearingless rotor wing |
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| US4676720A (en) * | 1984-07-10 | 1987-06-30 | Kawasaki Jukogyo Kabushiki Kaisha | Bearingless hub structure for rotary-wing aircrafts |
| US4864863A (en) * | 1988-04-22 | 1989-09-12 | United Technologies Corporation | Mechanism for testing helicopter rotor blade fatigue properties |
| JP3839983B2 (en) * | 1999-02-05 | 2006-11-01 | 株式会社鷺宮製作所 | Combined torsion / bending load testing machine |
| FR2871440B1 (en) * | 2004-06-15 | 2006-09-08 | Airbus France Sas | METHOD AND DEVICE FOR DETECTING EXCEEDING SIZING LOADS OF THE DRIFT OF AN AIRCRAFT |
| US7434328B2 (en) * | 2005-01-21 | 2008-10-14 | Sikorsky Aircraft Corporation | Rotor blade cuff measuring tool |
| GB2489263A (en) * | 2011-03-23 | 2012-09-26 | Rolls Royce Plc | Device for fatigue testing a specimen |
| JP5804469B2 (en) * | 2011-03-31 | 2015-11-04 | 学校法人立命館 | Multi-axis load test apparatus and method |
| EP2554475B1 (en) * | 2011-08-04 | 2016-03-23 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Planar flexbeam unit |
| JP5856462B2 (en) * | 2011-12-08 | 2016-02-09 | 国際計測器株式会社 | Torsion testing machine |
| CN105716839A (en) * | 2014-12-03 | 2016-06-29 | 中国直升机设计研究所 | Anti-twist device for rotor hub attachment fatigue test |
| CN204495642U (en) * | 2015-04-07 | 2015-07-22 | 中国直升机设计研究所 | A kind of flexible beam stiffness measurement device |
| CN106314790B (en) * | 2015-06-24 | 2018-12-04 | 湖南大学 | A kind of helicopter rotor system with flexible girder construction |
| CN106802234A (en) * | 2015-11-26 | 2017-06-06 | 中国直升机设计研究所 | A kind of main oar center piece three-dimensional loading device of bearingless rotor |
| CN106240840B (en) * | 2016-07-05 | 2018-12-11 | 中国飞机强度研究所 | A kind of wing-box experimental rig of bending loading |
| CN106248322B (en) * | 2016-07-05 | 2018-11-13 | 中国飞机强度研究所 | A kind of wing-box experimental rig of curved scissors loading |
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| CN108839818B (en) * | 2018-06-26 | 2021-08-13 | 中国直升机设计研究所 | Air resonance test method for bearingless rotor |
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- 2019-10-15 CN CN201910981662.4A patent/CN110758768B/en active Active
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