CN112461526A - Fatigue test loading device for main starting rocker arm joint of unmanned helicopter - Google Patents
Fatigue test loading device for main starting rocker arm joint of unmanned helicopter Download PDFInfo
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- CN112461526A CN112461526A CN202011316951.1A CN202011316951A CN112461526A CN 112461526 A CN112461526 A CN 112461526A CN 202011316951 A CN202011316951 A CN 202011316951A CN 112461526 A CN112461526 A CN 112461526A
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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
- G01M13/00—Testing of machine parts
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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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- Manufacturing & Machinery (AREA)
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- Aviation & Aerospace Engineering (AREA)
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention belongs to a helicopter fatigue test technology, and discloses a fatigue test loading device for a main starting rocker arm joint of an unmanned helicopter, which comprises: the device comprises a portal frame, a servo actuator fixing seat, a servo actuator, a single fork lug assembly, a transfer block, a double fork lug, an undercarriage dummy part, a double-head fork lug assembly, a rack, a horizontal fixing seat, a test part connector, a main lifting rocker arm connector test part, a bottom plate, a supporting seat and a fork lug fixing seat; x, Y, Z, the loading in three directions can be transmitted to the switching block, the switching block is connected to the undercarriage dummy piece through a bolt, the undercarriage dummy piece is connected to the main starting rocker arm joint test piece through a tubular shaft bolt, the main starting rocker arm joint test piece is fixed on the test piece connector through a bolt, the test piece connector is fixed on the rack through a bolt, and the rack is fixed on the bottom plate through a bolt.
Description
Technical Field
The invention belongs to the technical field of helicopter fatigue tests, and relates to a loading device for a fatigue test of a main starting rocker arm joint of an unmanned helicopter.
Background
The landing gear is an important component of a helicopter structure, is a helicopter landing device, has the capacity of absorbing the impact on the helicopter in the landing process and can reduce the impact on the helicopter in the landing process. The main starting rocker arm joint is connected to a main landing gear of the helicopter and fixed on a front fuselage, the fatigue performance of the main starting rocker arm joint plays a vital role, and in order to explore the fatigue performance of the main starting rocker arm joint of the unmanned helicopter, a fatigue test loading device for the main starting rocker arm joint of the unmanned helicopter is designed.
Disclosure of Invention
In view of the above situation in the prior art, the invention provides a fatigue test loading device for a main starting rocker arm joint of an unmanned helicopter, and the purpose of solving the problem that the fatigue test loading device for the main starting rocker arm joint of the unmanned helicopter is lack and researching the fatigue performance of the main starting rocker arm joint is achieved.
The technical scheme of the invention is as follows:
the utility model provides an unmanned helicopter owner plays rocker arm joint fatigue test loading device, includes: the device comprises an undercarriage dummy part, a main starting rocker arm joint test part, a test part joint, a transfer block, an X-direction loading unit, a Y-direction loading unit, a Z-direction loading unit, a rack and a bottom plate;
the bottom plate is arranged on the ground, and the rack is fixed on the bottom plate;
one end of the main starting rocker joint test piece is fixed with the rack through a test piece connector; the other end of the main lifting rocker joint test piece is connected with one end of the undercarriage dummy piece, and the other end of the undercarriage dummy piece is connected with the transfer block;
the switching block is respectively connected with the loading units in the X \ Y \ Z directions; the transfer block is used for transferring the load applied by the X \ Y \ Z direction loading unit to the undercarriage dummy piece so as to load the main starting rocker arm joint test piece.
Furthermore, an X-direction loading hole, a Y-direction double ear and a Z-direction double ear are arranged on the switching block.
Further, the X-direction loading unit includes: the X-direction servo actuator is arranged on the X-direction horizontal fixing seat;
x passes through the bolt fastening to horizontal fixing base the bottom plate, X to servo actuator stiff end with X is connected to horizontal fixing base, X passes through threaded connection to servo actuator loading end X to single-prong ear subassembly one end, X to the single-prong ear subassembly other end pass through the bolt with the double-prong ear is connected, the double-prong ear through end axle with X is fixed to the loading hole on the switching piece.
Further, the Y-direction loading unit includes: the Y-direction servo actuator is arranged on the Y-direction horizontal fixing seat;
y is fixed in to horizontal fixing base through the bolt the bottom plate, Y to servo actuator stiff end with Y is connected to horizontal fixing base, Y passes through threaded connection to servo actuator loading end Y to single-fork ear subassembly one end, Y to single-fork ear subassembly other end pass through the bolt with the double-fork ear is connected, the double-fork ear through end shaft with Y is fixed to the ears on the switching piece.
Further, the Z-direction loading unit includes: the device comprises a Z-direction fixing seat, a Z-direction servo actuator, a Z-direction single fork ear assembly and a portal frame;
the portal frame is fixed on the bottom plate, and the Z-direction servo actuator is fixed at the top end of the portal frame through the Z-direction fixing seat; the loading end of the Z-direction servo actuator is connected with one end of the Z-direction single-fork ear assembly through threads, and the other end of the Z-direction single-fork ear assembly is connected with the Z-direction double lugs of the transfer block through bolts.
Furthermore, the device also comprises a double-head fork lug assembly, a fork lug fixing seat and a supporting seat;
one end of the double-end fork ear assembly is connected with the middle part of the undercarriage dummy part; the other end is connected with a fork ear fixing seat; the fork lug fixing seat is fixed on the rack through a supporting seat; the double-ended yoke assembly is adjustable in length for adjusting the position of the landing gear dummy.
Further, the dual-headed fork ear assembly comprises: two monaural structural members and a tubular shaft; one end of each of the two single lug structural parts is a single lug, and the other end of each of the two single lug structural parts is a threaded end; the tubular shaft is provided with an internal thread matched with the threaded end of the single-lug structural part, and the two single-lug structural parts are connected through the tubular shaft.
Further, the undercarriage dummy part is connected to the main lifting rocker arm joint test part through a pipe shaft bolt.
The fatigue test device is simple and practical, has lower processing and maintenance cost, solves the problem that the fatigue test loading device of the main starting rocker arm joint of the unmanned helicopter is lack, and realizes the purpose of checking the fatigue property of the fatigue test of the main starting rocker arm joint.
Drawings
FIG. 1 is an isometric view of a fatigue test loading device for a main starting rocker arm joint of an unmanned helicopter;
FIG. 2 is an isometric view of a hidden base plate;
FIG. 3 is a schematic view of the connection of a landing gear dummy, a rack and a test piece connector;
FIG. 4 is an isometric view of a portion of a fatigue test loading end structure of a main lift rocker joint;
FIG. 5 is an isometric view of a main lift rocker joint trial;
FIG. 6 is an isometric view of an adapter block;
FIG. 7 is an isometric view of a servo actuator assembly;
in the figure, 1-a portal frame, 2-a servo actuator fixing seat, 3-a servo actuator, 4-a single fork lug assembly, 5-a transfer block, 6-a double fork lug, 7 landing gear dummy pieces, 8-a double-head fork lug assembly, 9-a rack, 10-a horizontal fixing seat, 11-a test piece connector, 12-a main lifting rocker arm connector test piece, 13-a bottom plate, 14-a supporting seat and 15-a fork lug fixing seat.
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.
A fatigue test loading device for a main starting rocker arm joint of an unmanned helicopter is shown in figures 1 and 2, and comprises: portal frame 1, servo actuator fixing base 2, servo actuator 3, single fork ear subassembly 4, switching piece 5, double fork ear 6, undercarriage dummy 7, double-end fork ear subassembly 8, rack 9, horizontal fixing base 10, test piece connector 11, the main rocking arm joint test piece 12 that plays, bottom plate 13, supporting seat 14, fork ear fixing base 15.
Above-mentioned unmanned helicopter owner plays rocker arm joint fatigue test loading device can realize X, Y, Z three direction loading, servo actuator is shown in fig. 7, the 3 stiff ends of servo actuator on the Z side are fixed in servo actuator fixing base 2 at first in the loading process, servo actuator fixing base 2 adopts four bolt fastening in portal frame 1, 3 loading ends of servo actuator on the Z side adopt threaded connection in single-fork ear subassembly 4, single-fork ear subassembly 4 adopts bolted connection on the piece 5 that connects that changes, consequently change and connect 5 and receive 3 loading powers of servo actuator from the Z side. On 3 stiff ends of servo actuator in X and the Y direction were fixed in horizontal fixing base 10, fixing base 10 passed through the bolt fastening on bottom plate 13, 3 loading ends of servo actuator in the X direction adopted threaded connection in single fork ear subassembly 4, and single fork ear subassembly 4 adopts bolted connection in double fork ear 6, and double fork ear 6 is directly fixed in the hole of the 5 processing of switching piece through end shaft to on, thereby. The loading end of the servo actuator 3 in the Y direction is connected to the single-prong assembly 4 by screw threads, the single-prong assembly 4 is directly connected to the end shaft of the double-prong 6, the loading force is transmitted to the double-prong 6, and the double-prong 6 is connected to the transfer block 5, as shown in FIG. 4, so that X, Y, Z loading in three directions can be transmitted to the transfer block 5.
The transfer block 5 is shown in fig. 6, the transfer block 5 is connected to the undercarriage dummy piece 7 through a bolt, the undercarriage dummy piece 7 is connected to the main starting rocker arm joint test piece 12 through a pipe shaft bolt, as shown in fig. 3, the main starting rocker arm joint test piece 12 is shown in fig. 5, the main starting rocker arm joint test piece is fixed to the test piece connector 11 through a bolt, the test piece connector 11 is fixed to the rack 9 through a bolt, and the rack 9 is fixed to the bottom plate 13 through a bolt.
The double-end fork ear assembly 8 is connected to the undercarriage dummy part 7 through one end of a bolt, the other end of the double-end fork ear assembly 8 is connected to a fork ear fixing seat 15, the fork ear fixing seat 15 is connected to a supporting seat 14, and the supporting seat 14 is connected to the rack 9. The double-end fork ear assembly 8 is provided with a left thread structure assembly and a right thread structure assembly, and can be adjusted to a certain length, so that the position of the undercarriage dummy part 7 is adjusted, and the correctness of a test loading scheme is ensured.
Claims (8)
1. The utility model provides an unmanned helicopter owner plays rocker arm joint fatigue test loading device which characterized in that: the device comprises: the device comprises an undercarriage dummy part, a main starting rocker arm joint test part, a test part joint, a transfer block, an X-direction loading unit, a Y-direction loading unit, a Z-direction loading unit, a rack and a bottom plate;
the bottom plate is arranged on the ground, and the rack is fixed on the bottom plate;
one end of the main starting rocker joint test piece is fixed with the rack through a test piece connector; the other end of the main lifting rocker joint test piece is connected with one end of the undercarriage dummy piece, and the other end of the undercarriage dummy piece is connected with the transfer block;
the switching block is respectively connected with the loading units in the X \ Y \ Z directions; the transfer block is used for transferring the load applied by the X \ Y \ Z direction loading unit to the undercarriage dummy piece so as to load the main starting rocker arm joint test piece.
2. The fatigue test loading device for the main starting rocker arm joint of the unmanned helicopter of claim 1, characterized in that: and the switching block is provided with an X-direction loading hole, Y-direction double ears and Z-direction double ears.
3. The fatigue test loading device for the main starting rocker arm joint of the unmanned helicopter of claim 2, characterized in that: the X-direction loading unit includes: the X-direction servo actuator is arranged on the X-direction horizontal fixing seat;
x passes through the bolt fastening to horizontal fixing base the bottom plate, X to servo actuator stiff end with X is connected to horizontal fixing base, X passes through threaded connection to servo actuator loading end X to single-prong ear subassembly one end, X to the single-prong ear subassembly other end pass through the bolt with the double-prong ear is connected, the double-prong ear through end axle with X is fixed to the loading hole on the switching piece.
4. The fatigue test loading device for the main starting rocker arm joint of the unmanned helicopter of claim 2, characterized in that: the Y-direction loading unit includes: the Y-direction servo actuator is arranged on the Y-direction horizontal fixing seat;
y is fixed in to horizontal fixing base through the bolt the bottom plate, Y to servo actuator stiff end with Y is connected to horizontal fixing base, Y passes through threaded connection to servo actuator loading end Y to single-fork ear subassembly one end, Y to single-fork ear subassembly other end pass through the bolt with the double-fork ear is connected, the double-fork ear through end shaft with Y is fixed to the ears on the switching piece.
5. The fatigue test loading device for the main starting rocker arm joint of the unmanned helicopter of claim 2, characterized in that: the Z-direction loading unit includes: the device comprises a Z-direction fixing seat, a Z-direction servo actuator, a Z-direction single fork ear assembly and a portal frame;
the portal frame is fixed on the bottom plate, and the Z-direction servo actuator is fixed at the top end of the portal frame through the Z-direction fixing seat; the loading end of the Z-direction servo actuator is connected with one end of the Z-direction single-fork ear assembly through threads, and the other end of the Z-direction single-fork ear assembly is connected with the Z-direction double lugs of the transfer block through bolts.
6. The fatigue test loading device for the main starting rocker arm joint of the unmanned helicopter of claim 1, characterized in that: the device also comprises a double-head fork lug assembly, a fork lug fixing seat and a supporting seat;
one end of the double-end fork ear assembly is connected with the middle part of the undercarriage dummy part; the other end is connected with a fork ear fixing seat; the fork lug fixing seat is fixed on the rack through a supporting seat; the double-ended yoke assembly is adjustable in length for adjusting the position of the landing gear dummy.
7. The fatigue test loading device for the main starting rocker arm joint of the unmanned helicopter of claim 1, characterized in that: the double-ended fork ear assembly comprises: two monaural structural members and a tubular shaft; one end of each of the two single lug structural parts is a single lug, and the other end of each of the two single lug structural parts is a threaded end; the tubular shaft is provided with an internal thread matched with the threaded end of the single-lug structural part, and the two single-lug structural parts are connected through the tubular shaft.
8. The fatigue test loading device for the main starting rocker arm joint of the unmanned helicopter of claim 1, characterized in that: the undercarriage dummy part is connected to the main starting rocker arm joint test part through a pipe shaft bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011316951.1A CN112461526B (en) | 2020-11-20 | 2020-11-20 | Fatigue test loading device for main starting rocker arm joint of unmanned helicopter |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011316951.1A CN112461526B (en) | 2020-11-20 | 2020-11-20 | Fatigue test loading device for main starting rocker arm joint of unmanned helicopter |
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| CN112461526A true CN112461526A (en) | 2021-03-09 |
| CN112461526B CN112461526B (en) | 2022-06-21 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU207625U1 (en) * | 2021-07-30 | 2021-11-08 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Московский авиационный институт (национальный исследовательский университет)" | Roll swing frame of a helicopter crash-resistant fuel system test rig |
| RU207631U1 (en) * | 2021-07-30 | 2021-11-08 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Московский авиационный институт (национальный исследовательский университет)" | Base for the turntable of the helicopter crash-resistant fuel system test rig |
| CN114166488A (en) * | 2021-11-23 | 2022-03-11 | 中国直升机设计研究所 | Fatigue test loading device for helicopter main landing gear |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011116966A1 (en) * | 2010-03-26 | 2011-09-29 | Messier-Bugatti-Dowty | Method for producing an arm made from composite material, comprising a transverse bearing intended to receive a fixed or rotary shaft |
| CN102917948A (en) * | 2010-06-16 | 2013-02-06 | 梅西耶-布加蒂-道提公司 | Main landing gear of an aircraft, comprising two walking beams joined to the structure of the aircraft in an articulated manner |
| KR20130073167A (en) * | 2011-12-23 | 2013-07-03 | 현대위아 주식회사 | Device for testing of endurance of landing gear |
| CN104215443A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Torque loading device of main lifting rocker joint |
| CN105651495A (en) * | 2014-11-12 | 2016-06-08 | 广州汽车集团股份有限公司 | Swing arm part durability test stand |
| CN106441857A (en) * | 2016-11-29 | 2017-02-22 | 中国直升机设计研究所 | Fatigue testing apparatus for mounting joint of damper post of main gear |
| CN106768921A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of tail undercarriage rocking arm erection joint fatigue experimental device |
| CN206573385U (en) * | 2017-03-30 | 2017-10-20 | 兰州理工大学 | A kind of axial workpiece fatigue test clamper |
| CN108082454A (en) * | 2017-12-03 | 2018-05-29 | 中国直升机设计研究所 | A kind of undercarriage rocking arm joint mounting structure and method based on self-lubricating bushing |
| CN108827657A (en) * | 2018-08-03 | 2018-11-16 | 合肥百川自动化科技有限公司 | Durable test stand is opened in a kind of arrangements for automotive doors |
| CN209008890U (en) * | 2019-01-24 | 2019-06-21 | 西安建卓航空机械制造有限公司 | A kind of undercarriage rotating arm testboard |
| CN111003200A (en) * | 2019-11-20 | 2020-04-14 | 中国飞机强度研究所 | Fatigue test device for outer front flap and joint test piece |
| CN210834116U (en) * | 2019-09-29 | 2020-06-23 | 中国直升机设计研究所 | Main rocker joint loading device |
-
2020
- 2020-11-20 CN CN202011316951.1A patent/CN112461526B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011116966A1 (en) * | 2010-03-26 | 2011-09-29 | Messier-Bugatti-Dowty | Method for producing an arm made from composite material, comprising a transverse bearing intended to receive a fixed or rotary shaft |
| CN102917948A (en) * | 2010-06-16 | 2013-02-06 | 梅西耶-布加蒂-道提公司 | Main landing gear of an aircraft, comprising two walking beams joined to the structure of the aircraft in an articulated manner |
| KR20130073167A (en) * | 2011-12-23 | 2013-07-03 | 현대위아 주식회사 | Device for testing of endurance of landing gear |
| CN104215443A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Torque loading device of main lifting rocker joint |
| CN105651495A (en) * | 2014-11-12 | 2016-06-08 | 广州汽车集团股份有限公司 | Swing arm part durability test stand |
| CN106768921A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of tail undercarriage rocking arm erection joint fatigue experimental device |
| CN106441857A (en) * | 2016-11-29 | 2017-02-22 | 中国直升机设计研究所 | Fatigue testing apparatus for mounting joint of damper post of main gear |
| CN206573385U (en) * | 2017-03-30 | 2017-10-20 | 兰州理工大学 | A kind of axial workpiece fatigue test clamper |
| CN108082454A (en) * | 2017-12-03 | 2018-05-29 | 中国直升机设计研究所 | A kind of undercarriage rocking arm joint mounting structure and method based on self-lubricating bushing |
| CN108827657A (en) * | 2018-08-03 | 2018-11-16 | 合肥百川自动化科技有限公司 | Durable test stand is opened in a kind of arrangements for automotive doors |
| CN209008890U (en) * | 2019-01-24 | 2019-06-21 | 西安建卓航空机械制造有限公司 | A kind of undercarriage rotating arm testboard |
| CN210834116U (en) * | 2019-09-29 | 2020-06-23 | 中国直升机设计研究所 | Main rocker joint loading device |
| CN111003200A (en) * | 2019-11-20 | 2020-04-14 | 中国飞机强度研究所 | Fatigue test device for outer front flap and joint test piece |
Non-Patent Citations (1)
| Title |
|---|
| 陶宪斌等: "某型机摇臂接头疲劳试验失效分析", 《金属加工(热加工)》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU207625U1 (en) * | 2021-07-30 | 2021-11-08 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Московский авиационный институт (национальный исследовательский университет)" | Roll swing frame of a helicopter crash-resistant fuel system test rig |
| RU207631U1 (en) * | 2021-07-30 | 2021-11-08 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Московский авиационный институт (национальный исследовательский университет)" | Base for the turntable of the helicopter crash-resistant fuel system test rig |
| CN114166488A (en) * | 2021-11-23 | 2022-03-11 | 中国直升机设计研究所 | Fatigue test loading device for helicopter main landing gear |
| CN114166488B (en) * | 2021-11-23 | 2023-05-23 | 中国直升机设计研究所 | Fatigue test loading device for main landing gear of helicopter |
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| CN112461526B (en) | 2022-06-21 |
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