CN112591137B - Airplane horizontal tail large shaft test device - Google Patents
Airplane horizontal tail large shaft test device Download PDFInfo
- Publication number
- CN112591137B CN112591137B CN202011267970.XA CN202011267970A CN112591137B CN 112591137 B CN112591137 B CN 112591137B CN 202011267970 A CN202011267970 A CN 202011267970A CN 112591137 B CN112591137 B CN 112591137B
- Authority
- CN
- China
- Prior art keywords
- box section
- horizontal tail
- large shaft
- wedge
- test device
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 73
- 230000005540 biological transmission Effects 0.000 claims abstract description 41
- 238000009434 installation Methods 0.000 claims abstract description 33
- 238000012546 transfer Methods 0.000 claims description 10
- 230000003014 reinforcing effect Effects 0.000 claims description 9
- 238000004088 simulation Methods 0.000 abstract description 4
- 230000003068 static effect Effects 0.000 abstract description 4
- 238000005452 bending Methods 0.000 abstract description 2
- 238000006073 displacement reaction Methods 0.000 abstract description 2
- 238000011160 research Methods 0.000 abstract description 2
- 238000012795 verification Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009661 fatigue test Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The application belongs to the technical field of aviation strength tests, and particularly relates to an airplane horizontal tail large shaft test device. According to the plane horizontal tail large-shaft test device, one end of a test piece is fixed by adopting the fixed box section and the fixed support, the other end of the test piece is fixed with the load transmission box section, the transmission joint is responsible for transmitting torque generated by loading to the fixed box section through the connecting plate, the joint bearings are arranged at the two ends of the connecting plate and can provide corner displacement for the loaded bending deformation of the test piece, the transmission joint is connected with the load transmission box section, and the load transmission box section is connected with the load beam through the connecting seat. The device for testing the horizontal tail large shaft of the aircraft can simulate the installation mode and resultant force point position of the horizontal tail large shaft on the aircraft, has clear force transmission route, ensures the authenticity of loaded simulation of test pieces, has fewer parts, is convenient to install and detach, greatly reduces the complexity of the test, and can be suitable for static force, fatigue and other strength test research and verification work of the horizontal tail large shaft of various models.
Description
Technical Field
The application belongs to the technical field of aviation strength tests, and particularly relates to an airplane horizontal tail large shaft test device.
Background
The large horizontal tail shaft is an important part of some military aircraft, plays a key role in the structure, bears a large load and is a vulnerable part. In order to study and verify the static strength and fatigue strength performance of the large horizontal tail shaft, a large number of static force and fatigue strength tests need to be carried out. The key point of the test is to simulate the stress state of the horizontal tail large shaft on the airplane, but the conventional test method needs a plurality of loading points and loading channels due to complex stress conditions, is difficult to install and detach, is unfavorable for test and inspection, and can cause the problems of long test period and high cost.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide an airplane horizontal tail large shaft test device, which aims to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
an aircraft horizontal tail large shaft test device, comprising:
fixing the box section;
the fixing support comprises a fixing seat, a first installation part and a second installation part, wherein the first installation part and the second installation part are arranged on the fixing seat, the fixing seat is installed on the fixing box section through a fastener, and the second installation part is provided with a first through hole;
the connecting plate comprises a first connecting part and a second connecting part, the first connecting part is arranged on the fixed box section through a fastener, a double-lug structure is arranged on the first connecting part, joint bearings are respectively arranged at two ends of the second connecting part, and one joint bearing of the second connecting part is matched with a pin shaft to be connected with the double-lug structure of the first connecting part;
the transmission joint is provided with a double-lug structure at one end, the double-lug structure is matched with the pin shaft to be connected with the other joint bearing of the second connecting part, a second through hole is formed at the other end of the transmission joint, and a plurality of mounting holes are formed around the second through hole;
the device comprises a transmission box section, wherein one end of the transmission box section is provided with a third through hole, a plurality of mounting holes are formed in the periphery of the third through hole, the mounting holes of the transmission box section are connected with the mounting holes of the transmission joint through fasteners, the other end of the transmission box section is connected with a loading beam through a connecting seat, and a third mounting part is arranged in the transmission box section;
the test piece, the one end of test piece with the first installation department fixed connection of fixed bolster, the other end pass in proper order behind first through-hole, second through-hole and the third through-hole with pass and carry the third installation department fixed connection of box section.
Optionally, a plurality of first reinforcing plates are provided inside the fixed box section.
Optionally, the fixing seat of the fixing support is mounted on the fixing box section through bolts.
Optionally, the first connection portion of the connection plate is mounted on the fixed box section by a bolt.
Optionally, the cross section of the transmission joint is Z-shaped.
Optionally, a plurality of second reinforcing plates are arranged in the load transfer box section, and through holes for the test pieces to pass through are formed in the second reinforcing plates.
Optionally, the third installation department of carrying the box section includes wedge base and wedge slider, the one end of wedge base is fixed through detachable connection's mode on carrying the rectangular hole of box section wallboard, the other end with wedge slider fixed connection.
Optionally, the device further comprises a tooth backing plate, the outer wall surface of the load transfer box section is welded with a tooth pad matched with the tooth backing plate, and the wedge-shaped base is fixed on the wall plate of the load transfer box section through a bolt matched with a nut and the tooth backing plate.
Optionally, the wedge-shaped base comprises a plurality of pairs, and two wedge-shaped bases in each pair are respectively and fixedly connected with two sides of the wedge-shaped sliding block.
Optionally, the loading beam is connected with the connecting seat through a bolt, the connecting seat is connected with the load transfer box section through a bolt, a first loading part is arranged on the loading beam, and a second loading part is arranged on the connecting seat.
The application has at least the following beneficial technical effects:
the device for testing the horizontal tail large shaft of the aircraft can simulate the installation mode and the resultant force point position of the horizontal tail large shaft on the aircraft, has clear force transmission route, ensures the authenticity of loaded simulation of test pieces, has fewer parts, is convenient to install and detach, and greatly reduces the complexity of the test.
Drawings
FIG. 1 is an overall schematic diagram of an aircraft horizontal tail large shaft test apparatus according to one embodiment of the present application;
FIG. 2 is a top view of an aircraft horizontal tail large axis test rig according to one embodiment of the application;
FIG. 3 is a side view of an aircraft horizontal tail large axis test rig according to one embodiment of the application;
FIG. 4 is a schematic view of a stationary support of an aircraft horizontal tail large shaft test rig according to one embodiment of the application;
FIG. 5 is a schematic diagram of a connection plate of an aircraft horizontal tail large shaft test apparatus according to one embodiment of the application;
FIG. 6 is a schematic view of a drive joint of an aircraft horizontal tail large shaft test rig according to one embodiment of the application;
FIG. 7 is a schematic view of a transfer box section of an aircraft horizontal tail large shaft test apparatus according to one embodiment of the application;
FIG. 8 is a schematic view of a third mounting portion of an aircraft horizontal tail large shaft test rig according to one embodiment of the present application;
FIG. 9 is a schematic view of a tooth pad of an aircraft horizontal tail large shaft test apparatus according to one embodiment of the application;
FIG. 10 is a schematic diagram of the test resultant force point location of an aircraft horizontal tail large axis test apparatus according to one embodiment of the application.
Wherein:
1-fixing the box section; 2-fixing a support; 3-test piece; 4-connecting plates; 5-a transmission joint; 6-a loading box section; 7-loading beams; 8-a first loading section; 9-a second loading section; 10-connecting seats; 11-a wedge-shaped base; 12-wedge-shaped slide blocks; 13-tooth pad.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are illustrative and intended to explain the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely to facilitate describing the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of the present application.
The present application will be described in further detail with reference to fig. 1 to 10.
The application provides an airplane horizontal tail large shaft test device, which comprises: the test piece comprises a fixed box section 1, a fixed support 2, a connecting plate 4, a transmission joint 5, a load-transferring box section 6 and a test piece 3.
Specifically, as shown in fig. 1 to 3, the fixed box section 1 has a box-shaped structure, is disposed on the ground, and is provided with a plurality of mounting holes. The fixed support 2 comprises a fixed seat, a first installation part and a second installation part, wherein the first installation part and the second installation part are arranged on the fixed seat, a plurality of installation holes are formed in the fixed seat, the fixed support is installed on the fixed box section 1 through fasteners, and a first through hole is formed in the second installation part. The connecting plate 4 comprises a first connecting portion and a second connecting portion, wherein a plurality of mounting holes are formed in the first connecting portion, the connecting plate is mounted on the fixed box section 1 through fasteners, a double-lug structure is arranged on the first connecting portion, joint bearings are respectively arranged at two ends of the second connecting portion, and one joint bearing of the second connecting portion is matched with a pin shaft to be connected with the double-lug structure of the first connecting portion.
Further, one end of the transmission joint 5 is provided with a double-lug structure, the double-lug structure is matched with the pin shaft to be connected with the other joint bearing of the second connecting part, the other end of the transmission joint 5 is provided with a second through hole, and a plurality of mounting holes are formed in the periphery of the second through hole. A third through hole is formed in one end of the carrying box section 6, a plurality of mounting holes are formed in the periphery of the third through hole, the mounting holes of the carrying box section 6 are connected with the mounting holes of the transmission joint 5 through fasteners, the other end of the carrying box section 6 is connected with the loading beam 7 through a connecting seat 10, and a third mounting part is arranged in the carrying box section 6; one end of the test piece 3 is fixedly connected with the first installation part of the fixed support 2, and the other end of the test piece sequentially passes through the first through hole of the second installation part of the fixed support 2, the second through hole of the transmission joint 5 and the third through hole of the load transmission box section 6 and then is fixedly connected with the third installation part of the load transmission box section 6. Screw holes can be formed in the first installation portion of the fixed support 2 and the third installation portion of the load transfer box section 6, screw thread sections are arranged at two ends of the test piece 3, and two ends of the test piece 3 are connected with corresponding installation portions through matched nuts.
According to the plane horizontal tail large-shaft test device, one end of a test piece 3 is fixed by adopting the fixed box section 1 and the fixed support 2, the other end of the test piece 3 is fixed with the load-transferring box section 6, the transmission joint 5 is responsible for transmitting torque generated by loading to the fixed box section 1 through the connecting plate 4, the two ends of the connecting plate 4 are provided with the joint bearings, so that corner displacement can be provided for the loaded bending deformation of the test piece 3, the transmission joint 5 is connected with the load-transferring box section 6, and the load-transferring box section 6 is connected with the loading beam 7 through the connecting seat 10.
Advantageously, in one embodiment of the application, a plurality of first stiffening plates may be provided inside the fixed box segment 1 for increasing the stability of the fixed box segment 1.
In this embodiment, the fixing seat of the fixing support 2 is mounted on the fixing box section 1 through a bolt, and the first connection portion of the connection plate 4 is also mounted on the fixing box section 1 through a bolt.
In this embodiment, as shown in fig. 6, the transmission joint 5 has a Z-shaped cross section.
Advantageously, a plurality of second reinforcing plates may be provided inside the load transfer box section 6, in this embodiment, two second reinforcing plates are provided, and through holes for the test pieces 3 to pass through are provided on the second reinforcing plates.
According to the airplane horizontal tail large-shaft test device, the third installation part of the carrying box section 6 comprises the wedge-shaped base 11 and the wedge-shaped sliding block 12, one end of the wedge-shaped base 11 is fixed on a strip hole of a wall plate of the carrying box section 6 in a detachable connection mode, and the other end of the wedge-shaped base is fixedly connected with the wedge-shaped sliding block 12 through a bolt. The horizontal position of the wedge-shaped sliding block 12 can be finely adjusted through the wedge-shaped base 11, the wedge-shaped sliding block is suitable for different horizontal tail large shaft sizes, automatic centering of the wedge-shaped sliding block 12 can be realized when bolts in the horizontal direction are screwed, the axis of the wedge-shaped sliding block 12 and the horizontal tail large shaft axis are coaxial, and the universality and the assembly and the load transfer can be guaranteed through the design. Advantageously, in this embodiment, the wedge-shaped base 11 is fixed on the wall plate of the carrying box section 6 by matching the bolt and the nut, and the wedge-shaped base 11 is prevented from sliding in the horizontal direction. In this embodiment, the wedge base 11 may include a plurality of pairs, and two wedge bases 11 in each pair are fixedly connected to two sides of the wedge slider 12.
According to the airplane horizontal tail large-shaft test device, the loading beam 7 is connected with the connecting seat 10 through bolts, the connecting seat 10 is connected with the load transmission box section 6 through bolts, the loading beam 7 is provided with the first loading part 8, the connecting seat 10 is provided with the second loading part 9, the first loading part 8 is in the form of an armrest, the second loading part 9 is in the form of an ear piece, the two loading parts are used as loading points, the two loading parts respectively correspond to the resultant force point positions of the condition 2 and the condition 1 shown in fig. 10, and test loads are applied by the two loading points. In the test, the first loading part 8 and the second loading part 9 are respectively applied with resultant loads of the condition 2 and the condition 1, the loading loads are transmitted to the connecting seat 10 through the loading beam 7, then are transmitted to the test piece 3 through the load transmission box section 6, the wedge-shaped base 11 and the wedge-shaped sliding block 12, and the redundant torsion is transmitted to the fixed box section 1 through the transmission joint 5.
The device for testing the horizontal tail large shaft of the aircraft can simulate the installation mode and the resultant force point position of the horizontal tail large shaft on the aircraft, has clear force transmission route, ensures the authenticity of loaded simulation of a test piece, has fewer parts, is convenient to install and detach, only needs to apply load at 2 loading points, greatly reduces the complexity of the test, and can ensure the installation precision of the horizontal tail large shaft with different sizes and has stronger universality through the position adjustment and the aligning functions of the wedge-shaped base 11 and the wedge-shaped slide block 12. The application has the advantages of high loaded simulation degree, low complexity and good universality, and can be suitable for static force test research, fatigue test and other strength test work of various types of horizontal tail large shafts.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. An aircraft horizontal tail large shaft test device, which is characterized by comprising:
a fixed box section (1);
the fixing support (2) comprises a fixing seat, a first installation part and a second installation part, wherein the first installation part and the second installation part are arranged on the fixing seat, the fixing seat is installed on the fixing box section (1) through a fastener, and a first through hole is formed in the second installation part;
the connecting plate (4), the connecting plate (4) comprises a first connecting part and a second connecting part, the first connecting part is installed on the fixed box section (1) through a fastener, a double-lug structure is arranged on the first connecting part, joint bearings are respectively arranged at two ends of the second connecting part, and one joint bearing of the second connecting part is matched with a pin shaft to be connected with the double-lug structure of the first connecting part;
the transmission joint (5), one end of the transmission joint (5) is provided with a double-lug structure, the double-lug structure is matched with a pin shaft to be connected with the other joint bearing of the second connecting part, the other end of the transmission joint (5) is provided with a second through hole, and a plurality of mounting holes are formed around the second through hole;
the device comprises a transmission box section (6), wherein a third through hole is formed in one end of the transmission box section (6), a plurality of mounting holes are formed in the periphery of the third through hole, the mounting holes of the transmission box section (6) are connected with the mounting holes of the transmission joint (5) through fasteners, the other end of the transmission box section (6) is connected with a loading beam (7) through a connecting seat (10), and a third mounting part is arranged in the transmission box section (6);
the test piece (3), one end of test piece (3) with the first installation department fixed connection of fixed bolster (2), the other end pass behind first through-hole, second through-hole and the third through-hole in proper order with pass and carry the third installation department fixed connection of box section (6).
2. The aircraft horizontal tail large shaft test device according to claim 1, characterized in that a plurality of first reinforcing plates are arranged inside the fixed box section (1).
3. The aircraft horizontal tail large shaft test device according to claim 1, wherein the fixing seat of the fixing support (2) is mounted on the fixing box section (1) through bolts.
4. The aircraft horizontal tail large shaft test device according to claim 1, characterized in that the first connection part of the connection plate (4) is mounted on the fixed box section (1) by means of bolts.
5. The aircraft horizontal tail large shaft test device according to claim 1, wherein the cross section of the transmission joint (5) is Z-shaped.
6. The horizontal tail large shaft test device of the airplane according to claim 1, wherein a plurality of second reinforcing plates are arranged in the load transfer box section (6), and through holes for the test pieces (3) to pass through are formed in the second reinforcing plates.
7. The airplane horizontal tail large shaft test device according to claim 1, wherein the third installation part of the carrying box section (6) comprises a wedge-shaped base (11) and a wedge-shaped sliding block (12), one end of the wedge-shaped base (11) is fixed on a strip hole of a wall plate of the carrying box section (6) in a detachable connection mode, and the other end of the wedge-shaped base is fixedly connected with the wedge-shaped sliding block (12).
8. The airplane horizontal tail large shaft test device according to claim 7, further comprising a tooth backing plate (13), wherein the tooth backing plate (13) is matched with the tooth backing plate (13) in a matched mode is welded on the outer wall surface of the carrying box section (6), and the wedge-shaped base (11) is fixed on the wall plate of the carrying box section (6) through a bolt matched nut and the tooth backing plate (13).
9. The aircraft horizontal tail large shaft test device according to claim 7, wherein the wedge-shaped bases (11) comprise a plurality of pairs, and two wedge-shaped bases (11) in each pair are fixedly connected with two sides of the wedge-shaped sliding block (12) respectively.
10. The horizontal tail large shaft test device of the airplane according to claim 1, wherein the loading beam (7) is connected with the connecting seat (10) through a bolt, the connecting seat (10) is connected with the load transfer box section (6) through a bolt, a first loading part (8) is arranged on the loading beam (7), and a second loading part (9) is arranged on the connecting seat (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011267970.XA CN112591137B (en) | 2020-11-13 | 2020-11-13 | Airplane horizontal tail large shaft test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011267970.XA CN112591137B (en) | 2020-11-13 | 2020-11-13 | Airplane horizontal tail large shaft test device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112591137A CN112591137A (en) | 2021-04-02 |
| CN112591137B true CN112591137B (en) | 2023-11-28 |
Family
ID=75182993
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011267970.XA Active CN112591137B (en) | 2020-11-13 | 2020-11-13 | Airplane horizontal tail large shaft test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112591137B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113654882B (en) * | 2021-06-18 | 2022-04-26 | 中国商用飞机有限责任公司 | Experimental loading device of horizontal tail |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012013137A1 (en) * | 2010-07-26 | 2012-02-02 | 西安理工大学 | Full load static characteristics testing device for bolt joint surface unit and testing method thereof |
| CN203350040U (en) * | 2013-07-02 | 2013-12-18 | 吉林大学 | Multiple unit train transmission system axle box bearing radial and axial static-state loading test stand |
| CN107685876A (en) * | 2017-07-28 | 2018-02-13 | 中国航空工业集团公司西安飞机设计研究所 | Adjustable wheel loaded member for articulated landing gear |
| CN108169015A (en) * | 2017-12-01 | 2018-06-15 | 中国直升机设计研究所 | A kind of tail-rotor flexible beam torque load testing machine |
| CN207570942U (en) * | 2017-12-03 | 2018-07-03 | 中国直升机设计研究所 | A kind of tail undercarriage damper leg erection joint fatigue experimental device |
| US10053238B1 (en) * | 2017-02-21 | 2018-08-21 | The Boeing Company | Fixture, system, and method for testing loads in a flexible aerodynamic member |
| CN109506911A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Load testing machine |
| CN210258874U (en) * | 2019-05-29 | 2020-04-07 | 陕西飞机工业（集团）有限公司 | Outer wing butt joint face loading simulation piece |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3239055B1 (en) * | 2016-04-25 | 2019-01-30 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Extracting device for extracting a trim weight from a rotor blade |
-
2020
- 2020-11-13 CN CN202011267970.XA patent/CN112591137B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012013137A1 (en) * | 2010-07-26 | 2012-02-02 | 西安理工大学 | Full load static characteristics testing device for bolt joint surface unit and testing method thereof |
| CN203350040U (en) * | 2013-07-02 | 2013-12-18 | 吉林大学 | Multiple unit train transmission system axle box bearing radial and axial static-state loading test stand |
| US10053238B1 (en) * | 2017-02-21 | 2018-08-21 | The Boeing Company | Fixture, system, and method for testing loads in a flexible aerodynamic member |
| CN107685876A (en) * | 2017-07-28 | 2018-02-13 | 中国航空工业集团公司西安飞机设计研究所 | Adjustable wheel loaded member for articulated landing gear |
| CN108169015A (en) * | 2017-12-01 | 2018-06-15 | 中国直升机设计研究所 | A kind of tail-rotor flexible beam torque load testing machine |
| CN207570942U (en) * | 2017-12-03 | 2018-07-03 | 中国直升机设计研究所 | A kind of tail undercarriage damper leg erection joint fatigue experimental device |
| CN109506911A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Load testing machine |
| CN210258874U (en) * | 2019-05-29 | 2020-04-07 | 陕西飞机工业（集团）有限公司 | Outer wing butt joint face loading simulation piece |
Non-Patent Citations (1)
| Title |
|---|
| 一种民机静力试验平尾加载假件的设计;刘佳;;工程与试验(第03期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112591137A (en) | 2021-04-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110726541B (en) | Large-bypass-ratio aero-engine intermediate casing strength test device | |
| CN112591137B (en) | Airplane horizontal tail large shaft test device | |
| CN113138070B (en) | Static test device for frame and floor beam connecting structure | |
| US11511846B2 (en) | Aircraft with multi spar box connection to fuselage | |
| CA3049803C (en) | Method and apparatus for attaching a fuselage frame to a wing box | |
| CN109297724B (en) | Composite fatigue testing device and method for V-shaped thrust rod assembly | |
| CN112141360A (en) | Vertical fin box section test support dummy and test equipment | |
| WO2023029146A1 (en) | Testing device and method for simulating static force on wall panel structure of cylindrical cabin | |
| US7380463B2 (en) | Assembly for testing panels under shear-compression loads | |
| US20180148153A1 (en) | Fuselage Skin Panel Connection System and Method for Connecting Skin Panels | |
| US20220017205A1 (en) | Method and System for Coupling a Vertical Stabilizer to an Aircraft Fuselage | |
| CN202138224U (en) | Novel gearbox auxiliary suspension device | |
| CN112504594B (en) | Impact and vibration fatigue coupling loading device for floating friction plate | |
| US11714025B1 (en) | Pseudo-static test device and method for seismic behavior of connection joints of wallboard | |
| CN113654882B (en) | Experimental loading device of horizontal tail | |
| CN213974522U (en) | Vertical fin box section test support dummy and test equipment | |
| CN113465856B (en) | Cabin body frequency modulation tool | |
| CN114013266B (en) | Power assembly suspension system, installation method and vehicle | |
| US20210371079A1 (en) | Aircraft with multi spar box connection to fuselage | |
| CN110595806B (en) | Loading method and loading device for loads of monorail framework and axle | |
| CN118190371A (en) | Variable stiffness wing test supporting device | |
| CN112763312A (en) | Tension-shear composite bolt fatigue test clamp and method | |
| CN221147949U (en) | Fixing device and test system | |
| CN215794525U (en) | Machine carries equipment cabinet strength test spare structure | |
| CN212458896U (en) | Vehicle body test equipment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |