CN109533387A - A kind of Helicopter Main Hub support arm restraint lock fatigue experimental device - Google Patents
A kind of Helicopter Main Hub support arm restraint lock fatigue experimental device Download PDFInfo
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- CN109533387A CN109533387A CN201811346511.3A CN201811346511A CN109533387A CN 109533387 A CN109533387 A CN 109533387A CN 201811346511 A CN201811346511 A CN 201811346511A CN 109533387 A CN109533387 A CN 109533387A
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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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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The application belongs to Helicopter Main Hub support arm restraint and locks tired experimental technique field, and in particular to a kind of Helicopter Main Hub support arm restraint lock fatigue experimental device, comprising: the fixed device of testpieces locks testpieces to fixed restraint；Displacement loading device, for being connect with restraint lock testpieces, to apply displacement load to restraint lock testpieces；Shimmy loading device, for being connect with restraint lock testpieces, to apply shimmy load to restraint lock testpieces；Flight loading device, for being connect with restraint lock testpieces, to apply flight load to restraint lock testpieces.Those skilled in the art can lock testpieces to main hub support arm restraint using the device and apply displacement load, shimmy load and flight load, obtain its fatigue properties and its weak part to assess its service life and its structure optimization improvement and providing authentic data.
Description
Technical Field
The application belongs to the technical field of helicopter main propeller hub support arm limiting lock fatigue tests, and particularly relates to a helicopter main propeller hub support arm limiting lock fatigue test device.
Background
The helicopter main hub support arm limiting lock is a part for folding and locking a helicopter main rotor, can save the parking space of a helicopter on a ship, provides reliable data for evaluating the service life of the helicopter and improving and optimizing the structure of the helicopter, needs to be subjected to experimental research, is subjected to ground experimental loading, and obtains the fatigue characteristic and the weak part of the helicopter.
The structure of the helicopter main hub support arm limit lock experimental part is shown in figure 1, and comprises: the fixed part 1, the long fork lug 2, the short fork lug 3 and the two damper connecting bosses 4 are mainly used for bearing variable pitch load, shimmy load and flight load during working. At present, lack the experimental apparatus that can accurate simulation helicopter main propeller hub support arm limit lock installation and carry out the load boundary condition, the skilled person in the art can not be effectual carries out fatigue test to it.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The present application is directed to a helicopter main hub arm limit lock fatigue test apparatus to overcome or alleviate at least one of the above problems.
The technical scheme of the application is as follows:
a helicopter main hub support arm limiting lock fatigue test device comprises:
the test piece fixing device is used for fixing the limit lock test piece;
the variable-pitch loading device is used for being connected with the motion-limiting lock test piece so as to apply variable-pitch load to the motion-limiting lock test piece;
the shimmy loading device is used for being connected with the limited lock test piece so as to apply shimmy load to the limited lock test piece;
and the flight loading device is used for being connected with the motion-limiting lock test piece so as to apply flight load to the motion-limiting lock test piece.
According to at least one embodiment of the present application, a test piece fixing device includes:
a base plate;
the two upright posts are fixedly arranged on one side wall surface of the bottom plate;
when the test piece fixing device is used for fixing the limit lock test piece, the fixing part of the limit lock test piece is fixedly connected with the wall surfaces of the two stand columns, and the axis of the long fork lug through hole of the limit lock test piece and the axis of the short fork lug through hole of the limit lock test piece are perpendicular to the bottom plate.
According to at least one embodiment of the application, the axis of the long fork lug through hole of the motion limiting lock test piece is called a long fork lug axis;
the axis of the short fork lug through hole of the limiting lock test piece is called as the axis of the short fork lug;
the pitch-variable loading device comprises:
one end of the long fork lug variable-pitch loading device is connected with the long fork lug so as to apply a long fork lug variable-pitch force to the long fork lug along the long fork lug line;
and one end of the short fork lug variable-pitch loading device is used for being connected with the short fork lug so as to apply short fork lug variable-pitch force to the short fork lug along the short fork lug line.
According to at least one embodiment of the present application, a long fork lug variable pitch loading apparatus comprises:
one end of the long fork lug adapter is of a double-lug structure and is used for being connected with the long fork lug;
the piston rod of the long fork ear actuating cylinder is connected with the other end of the long fork ear joint; wherein,
when the long fork lug adapter is connected with the long fork lug, the long fork lug is positioned between double lug structures of the long fork lug adapter, and the axis of the long fork lug adapter is superposed with the axis of the through hole on the long fork lug;
short fork ear displacement loading attachment includes:
one end of the short fork lug adapter is of a double-lug structure and is used for being connected with the short fork lug;
the piston rod of the short fork ear actuating cylinder is connected with the other end of the short fork ear joint; wherein,
when the short fork lug adapter is connected with the short fork lug, the short fork lug is positioned between double lug structures of the short fork lug adapter, and the axis of the short fork lug adapter coincides with the axis of the through hole in the short fork lug.
According to at least one embodiment of the present application, the pitch loading apparatus further comprises:
two struts;
the cross beam is erected between the two upright posts, and the wall surface of the cross beam is provided with two U-shaped through holes;
two lifting lugs, wherein,
one end of a lifting lug is connected with one end of the long fork ear actuator cylinder, which is far away from the long fork ear adapter, and the other end of the lifting lug penetrates through a U-shaped through hole and can move in the U-shaped through hole along the axial direction of the cross beam;
one end of the other lifting lug is connected with one end, far away from the short fork lug adapter, of the short fork lug actuating cylinder, and the other end of the other lifting lug penetrates through the other U-shaped through hole and can move in the U-shaped through hole along the axial direction of the cross beam.
According to at least one embodiment of the present application, a shimmy loading device comprises:
one end of the shimmy joint is used for being connected with the long fork lug of the motion limiting lock test piece;
the piston rod of the shimmy actuating cylinder is connected with the other end of the shimmy joint;
wherein,
when the shimmy joint is connected with the long fork lug, the axis of the shimmy joint is superposed with a preset shimmy loading line.
According to at least one embodiment of the application, the shimmy loading device further comprises a shimmy joint bearing, and the outer ring wall surface of the shimmy joint bearing is connected with the end surface of one end of the shimmy joint, which is far away from the shimmy actuating cylinder;
when the pendulum vibration joint is connected with the long fork lug, the pendulum vibration joint bearing is positioned between the lug plates of the long fork lug, and the inner ring of the pendulum vibration joint bearing is connected with the lug plates penetrating through the long fork lug through bolts.
According to at least one embodiment of the application, the shimmy loading device further comprises a shimmy support, and one end, far away from the shimmy joint, of the shimmy actuating cylinder is connected with the shimmy support; according to at least one embodiment of the present application, a flight loading apparatus comprises:
one end of the flight loading joint is used for being connected with a bolt on a damper connecting boss on the motion limiting lock test piece;
the piston rod of the flight loading actuating cylinder is connected with the other end of the flight loading joint;
wherein,
when the flying loading joint is connected with the bolts on the connecting bosses of the two dampers, the axis of the flying loading joint is superposed with the preset flying loading line.
According to at least one embodiment of this application, flight loading device still includes:
the outer ring wall surface of the flight loading joint bearing is connected with the end surface of the flight loading joint, which is far away from one end of the flight loading actuating cylinder;
the flying loading support is connected with one end of the flying loading actuator cylinder, which is far away from the flying loading joint;
the flight loading support can be fixedly arranged at one of a plurality of preset flight loading positions;
wherein,
when the flying loading joint is connected with the bolt on the damper connecting boss, the inner ring of the flying loading joint bearing is connected with the bolt on the damper connecting boss.
The application has at least the following beneficial technical effects: the fatigue test device can accurately simulate the installation and loading boundary conditions of the helicopter main hub support arm limit lock, and can apply variable-pitch load, shimmy load and flight load to a main hub support arm limit lock test piece to obtain the fatigue characteristic and weak parts thereof so as to provide reliable data for evaluating the service life of the test piece and improving and optimizing the fatigue characteristic and the weak parts.
Drawings
FIG. 1 is a schematic structural diagram of a helicopter main hub arm limit lock test piece provided by an embodiment of the present application;
FIG. 2 is a schematic diagram of an operation of a pitch-variable loading device according to an embodiment of the present disclosure;
FIG. 3 is a schematic structural diagram of a part of a pitch-variable loading device provided in the embodiment of the present application;
FIG. 4 is a schematic diagram of the operation of a shimmy loading device provided in the embodiments of the present application;
FIG. 5 is a schematic structural diagram of a portion of a shimmy loading device provided in an embodiment of the present application;
FIG. 6 is a schematic view of an exemplary embodiment of a flight loading apparatus;
fig. 7 is a schematic structural diagram of a part of a flight loading device provided by an embodiment of the application.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.
The present application is described in further detail below with reference to fig. 1 to 7.
A helicopter main hub support arm limiting lock fatigue test device comprises:
the test piece fixing device is used for fixing the limit lock test piece;
the variable-pitch loading device is used for being connected with the motion-limiting lock test piece so as to apply variable-pitch load to the motion-limiting lock test piece;
the shimmy loading device is used for being connected with the limited lock test piece so as to apply shimmy load to the limited lock test piece;
and the flight loading device is used for being connected with the motion-limiting lock test piece so as to apply flight load to the motion-limiting lock test piece.
In some alternative embodiments, the test piece holding device comprises:
a bottom plate 5;
two upright columns 6 are fixedly arranged on one side wall surface of the bottom plate 5;
when the test piece fixing device is used for fixing the motion-limiting lock test piece, the fixing part 1 of the motion-limiting lock test piece is fixedly connected with the wall surfaces of the two stand columns 6, and the axis of the through hole 2 of the long fork lug of the motion-limiting lock test piece and the axis of the through hole 3 of the short fork lug of the motion-limiting lock test piece are perpendicular to the bottom plate 5.
In some alternative embodiments, the axis of the through hole of the long fork lug 2 of the motion-limiting lock test piece is called the long fork lug axis; the axis of the through hole of the short fork lug 3 of the limiting lock test piece is called as the axis of the short fork lug;
the pitch-variable loading device comprises: one end of the long fork lug variable-pitch loading device is connected with the long fork lug 2 so as to apply a long fork lug variable-pitch force to the long fork lug 2 along the long fork lug line; one end of the short fork lug variable-pitch loading device is connected with the short fork lug 3 so as to apply short fork lug variable-pitch force to the short fork lug 3 along the short fork lug line; the pitch load comprises: long fork lug displacement force and short fork lug displacement force.
In some optional embodiments, the long fork lug variable pitch loading device comprises: a long fork lug adapter 7, one end of which is of a double-lug structure and is used for being connected with the long fork lug 2; a long fork ear actuator cylinder 8, the piston rod of which is connected with the other end of the long fork ear joint 7; when the long fork lug adapter 7 is connected with the long fork lug 2, the long fork lug 7 is positioned between double lug structures of the long fork lug adapter 7, and the axis of the long fork lug adapter 7 is superposed with the axis of the through hole of the long fork lug 2;
short fork ear displacement loading attachment includes: a short fork lug adapter 9, one end of which is of a double-lug structure and is used for being connected with the short fork lug 3; a short fork ear actuating cylinder 10, the piston rod of which is connected with the other end of the short fork ear joint 9; wherein, when short fork ear adapter 9 is connected with short fork ear 3, short fork ear 3 is located between the double-lug structure of short fork ear adapter 9, and the axis of short fork ear adapter 9 and the coincidence of short fork ear 3 through-hole axis.
When the long fork lug adapter 7 is connected with the long fork lug 2, a person skilled in the art can select the connection within a range known in the art, for example, a screw or a bolt penetrating through the double lug pieces of the long fork lug adapter 7 can be used to connect with the long fork lug 2, and one end of the long fork lug adapter 7 is designed into a double lug structure, mainly to facilitate the connection with the long fork lug 2, and to easily adjust the axis to coincide with the axis of the through hole of the long fork lug 2, so as to accurately apply the long fork lug variable-pitch force to the main paddle hub support arm limiting lock. The end of the short fork lug adapter 9 for connection with the short fork lug 3 is designed to be of a binaural structure for similar reasons and purposes.
In some optional embodiments, the pitch-variable loading device further comprises: two struts 11; a beam 12, which is erected between the two upright posts 11, and the wall surface of which is provided with two U-shaped through holes 13; one end of each lifting lug is connected with one end, far away from the long fork lug adapter 7, of the long fork lug actuating cylinder 8, and the other end of each lifting lug penetrates through a U-shaped through hole 13 and can move in the U-shaped through hole 13 along the axial direction of the cross beam 12; one end of the other lifting lug is connected with one end of the short fork lug actuating cylinder 10 far away from the short fork lug adapter 9, and the other end of the other lifting lug penetrates through the other U-shaped through hole 13 and can move in the U-shaped through hole 13 along the axial direction of the cross beam 12. By the arrangement, on one hand, the position directions of the long fork ear actuator cylinder 8 and the short fork ear actuator cylinder 10 can be conveniently adjusted, so that the axis of the long fork ear adapter 7 is superposed with the axis of the through hole in the long fork ear 2, and the axis of the short fork ear adapter 9 is superposed with the axis of the through hole in the short fork ear 3; on the other hand, when the long fork-ear cylinder 8 and the short fork-ear cylinder 10 are operated, the degrees of freedom are restricted to prevent the occurrence of displacement.
In some alternative embodiments, the shimmy loading device comprises: one end of the shimmy joint 14 is used for being connected with the long fork lug 2 of the limited lock test piece; a pendulum actuating cylinder 15, the piston rod of which is connected with the other end of the pendulum joint 14; when the shimmy joint 14 is connected with the long fork ear 2, the axis of the shimmy joint coincides with a preset shimmy loading line. It will be readily appreciated by those skilled in the art that the predetermined shimmy load line described above can be determined based on the shimmy load actually experienced by the helicopter main hub yoke limit lock.
In some optional embodiments, the shimmy loading device further comprises a shimmy joint bearing, and the wall surface of the outer ring of the shimmy joint bearing is connected with the end surface of the end, far away from the shimmy actuator cylinder 15, of the shimmy joint 14; when the shimmy joint 14 is connected with the long fork ear 2, the shimmy joint bearing is positioned between the lug plates of the long fork ear 2, and the inner ring of the shimmy joint bearing is connected with the lug plate penetrating through the long fork ear 2 through a bolt. The arrangement can coordinate the shimmy load loading displacement and adjust the loading angle.
In some optional embodiments, the shimmy loading device further comprises a shimmy support 18, and one end of the shimmy actuator cylinder 15, which is far away from the shimmy joint 14, is connected with the shimmy support 18; the shimmy mount 18 can be fixedly disposed at one of a plurality of predetermined shimmy positions. It will be readily appreciated by those skilled in the art that the shimmy mount 18 can be easily adjusted to be close to the axis of the shimmy joint 14 and the predetermined shimmy load line by fixing the shimmy mount at a predetermined shimmy position and adjusting the height of the base thereof in coordination with the need for testing.
In some optional embodiments, the flight loading apparatus comprises: one end of the flight loading joint 19 is used for being connected with a bolt on the limiting lock test piece damper connecting boss 4; a flying loading actuator cylinder 16, the piston rod of which is connected with the other end of the flying loading joint 19; when the flying loading joint 19 is connected with the bolts on the two damper connecting bosses 4, the axis of the flying loading joint coincides with the preset flying loading line.
In some optional embodiments, the flight loading device further comprises: the outer ring wall surface of the flight loading joint bearing is connected with the end surface of one end of the flight loading joint 19 far away from the flight loading actuating cylinder 16; the flight loading support 17 is provided with a flight loading connection point, and one end of the flight loading actuating cylinder 16, which is far away from the flight loading joint 19, is connected with the position of the flight loading connection point on the flight loading support 17; the flight loading support 17 can be fixedly arranged at one of a plurality of preset flight loading positions and can adjust the height of a flight loading connection point on the flight loading support; when the flying loading joint 19 is connected with the bolt on the damper connecting boss 4, the inner ring of the flying loading joint bearing is connected with the bolt on the damper connecting boss 4.
In some optional embodiments, the testing apparatus further includes a testing platform, the bottom plate 5 and the two pillars 11 are fixedly disposed on the testing platform, and the plurality of preset shimmy positions and the plurality of preset flight loading positions are located on the testing platform, and when the testing apparatus is used, a person skilled in the art can determine which preset shimmy position the shimmy support 18 is located and which preset flight loading position the flight loading support 17 is fixed at according to actual needs.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.
Claims (10)
1. The utility model provides a helicopter owner propeller hub support arm limit lock fatigue test device which characterized in that includes:
the test piece fixing device is used for fixing the limit lock test piece;
the variable-pitch loading device is connected with the motion-limiting lock test piece so as to apply variable-pitch load to the motion-limiting lock test piece;
the shimmy loading device is used for being connected with the limited lock test piece so as to apply shimmy load to the limited lock test piece;
and the flight loading device is used for being connected with the motion-limiting lock test piece so as to apply flight load to the motion-limiting lock test piece.
2. The test device of claim 1, wherein the test piece fixture comprises:
a base plate (5);
two upright posts (6) fixedly arranged on one side wall surface of the bottom plate (5);
when the test piece fixing device fixes the limit lock test piece, the fixing part (1) of the limit lock test piece is fixedly connected with the wall surface of the stand column (6), and the axis of the through hole of the long fork upper lug (2) of the limit lock test piece and the axis of the through hole of the short fork lug (3) of the limit lock test piece are perpendicular to the bottom plate (5).
3. Testing device according to claim 1,
the axis of the through hole on the limiting lock test piece long fork lug (2) is called as a long fork lug axis;
the axis of the through hole on the short fork lug (3) of the limiting lock test piece is called as the axis of the short fork lug;
the pitch-variable loading device comprises:
one end of the long fork lug variable-pitch loading device is connected with the long fork lug (2) so as to apply a long fork lug variable-pitch force to the long fork lug (2) along the long fork lug line;
and one end of the short fork lug variable-pitch loading device is used for being connected with the short fork lug (3) so as to apply short fork lug variable-pitch force to the short fork lug (3) along the short fork lug axis.
4. Testing device according to claim 3,
the long fork lug variable-pitch loading device comprises:
a long fork lug adapter (7), one end of which is of a double-lug structure and is used for being connected with the long fork lug (2);
the piston rod of the long fork ear actuating cylinder (8) is connected with the other end of the long fork ear joint (7); wherein,
when the long fork lug adapter (7) is connected with the long fork lug (2), the long fork lug (7) is positioned between double lug structures of the long fork lug adapter (7), and the axis of the long fork lug adapter (7) is superposed with the axis of the through hole in the long fork lug (2);
the short fork lug variable-pitch loading device comprises:
one end of the short fork lug adapter (9) is of a double-lug structure and is used for being connected with the short fork lug (3);
the piston rod of the short fork ear actuating cylinder (10) is connected with the other end of the short fork ear joint (9); wherein,
short fork ear adapter (9) with when short fork ear (3) are connected, short fork ear (3) are located between the double ear structure of short fork ear adapter (9), just the axis of short fork ear adapter (9) with the axis coincidence of through-hole on the short fork ear 3.
5. The testing apparatus of claim 4, wherein the pitch loading apparatus further comprises:
two struts (11);
the cross beam (12) is erected between the two upright posts (11), and the wall surface of the cross beam is provided with two U-shaped through holes (13);
two lifting lugs, wherein,
one end of the lifting lug is connected with one end of the long fork lug actuator cylinder (8) far away from the long fork lug adapter (7), and the other end of the lifting lug penetrates through one U-shaped through hole (13) and can move in the U-shaped through hole (13) along the axial direction of the cross beam (12);
one end of the other lifting lug is connected with one end, far away from the short fork lug adapter (9), of the short fork lug actuating cylinder (10), and the other end of the lifting lug penetrates through the other U-shaped through hole (13) and can move in the U-shaped through hole (13) along the axial direction of the cross beam (12).
6. The test device of claim 1, wherein the shimmy loading device comprises:
one end of the shimmy joint (14) is used for being connected with the long fork lug (2) of the limited lock test piece;
the piston rod of the shimmy actuating cylinder (15) is connected with the other end of the shimmy joint (14);
wherein,
when the shimmy joint (14) is connected with the long fork ear (2), the axis of the shimmy joint coincides with a preset shimmy loading line.
7. The test device according to claim 6, wherein the shimmy loading device further comprises a shimmy joint bearing, and an outer ring wall surface of the shimmy joint bearing is connected with an end surface of the end of the shimmy joint (14) far away from the shimmy actuating cylinder (15);
when the shimmy joint (14) is connected with the long fork lug (2), the shimmy joint bearing is positioned between the lug pieces of the long fork lug (2), and the inner ring of the shimmy joint bearing is connected with the lug pieces penetrating through the long fork lug (2) through bolts.
8. The test device according to claim 6, wherein the shimmy loading device further comprises a shimmy support (18), and one end of the shimmy actuating cylinder (15) far away from the shimmy joint (14) is connected with the shimmy support (18);
the shimmy mount (18) can be fixedly arranged at one of a plurality of preset shimmy positions.
9. The test rig of claim 1, wherein the flight loading device comprises:
one end of the flight loading joint (19) is used for being connected with a bolt on a damper connecting boss (4) on the motion limiting lock test piece;
a flying loading actuator cylinder (16), the piston rod of which is connected with the other end of the flying loading joint (19);
wherein,
when the flight loading joint (19) is connected with the bolts on the two damper connecting bosses (4), the axis of the flight loading joint coincides with a preset flight loading line.
10. The test rig of claim 9, wherein the flying loading unit further comprises:
the outer ring wall surface of the flight loading joint bearing is connected with the end surface of one end, away from the flight loading actuating cylinder (16), of the flight loading joint (19);
a flight loading support (17), wherein one end of the flight loading actuator cylinder (16) far away from the flight loading joint (19) is connected with the flight loading support (17);
the flight loading support (17) can be fixedly arranged at one of a plurality of preset flight loading positions;
wherein,
when the flying loading joint (19) is connected with the bolt on the damper connecting boss (4), the inner ring of the flying loading joint bearing is connected with the bolt on the damper connecting boss (4).
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| CN201811346511.3A CN109533387A (en) | 2018-11-13 | 2018-11-13 | A kind of Helicopter Main Hub support arm restraint lock fatigue experimental device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811346511.3A CN109533387A (en) | 2018-11-13 | 2018-11-13 | A kind of Helicopter Main Hub support arm restraint lock fatigue experimental device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111099036A (en) * | 2019-11-22 | 2020-05-05 | 南京航空航天大学 | Fatigue test device and test method for landing gear ejection main force transmission structure |
| CN112161861A (en) * | 2020-10-23 | 2021-01-01 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Loading device and loading method for airplane stabilizer control load test |
| CN112179787A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Torsion test device for main paddle central part and support arm limited lock |
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Application publication date: 20190329 |