CN112591137A - Horizontal tail large shaft test device for airplane - Google Patents
Horizontal tail large shaft test device for airplane Download PDFInfo
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- CN112591137A CN112591137A CN202011267970.XA CN202011267970A CN112591137A CN 112591137 A CN112591137 A CN 112591137A CN 202011267970 A CN202011267970 A CN 202011267970A CN 112591137 A CN112591137 A CN 112591137A
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- box section
- horizontal tail
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- large shaft
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- 238000012360 testing method Methods 0.000 title claims abstract description 67
- 230000005540 biological transmission Effects 0.000 claims abstract description 31
- 238000009434 installation Methods 0.000 claims abstract description 18
- 230000003014 reinforcing effect Effects 0.000 claims description 10
- 238000012546 transfer Methods 0.000 claims description 9
- 238000004088 simulation Methods 0.000 abstract description 4
- 230000003068 static effect Effects 0.000 abstract description 4
- 238000011160 research Methods 0.000 abstract description 3
- 238000005452 bending Methods 0.000 abstract description 2
- 238000006073 displacement reaction Methods 0.000 abstract description 2
- 238000012795 verification Methods 0.000 abstract description 2
- 230000006978 adaptation Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 210000005069 ears Anatomy 0.000 description 2
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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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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- 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 a horizontal tail large shaft test device for an airplane. The utility model provides an aircraft horizontal tail main shaft test device, it is fixed with the one end of test piece to adopt fixed box section and fixing support, the other end and the biography of test piece carry the box section fixedly, the transmission connects on being responsible for transmitting the moment of torsion that the loading produced to fixed box section through the connecting plate, be provided with joint bearing at the both ends of connecting plate, can provide the corner displacement for test piece loaded bending deformation, the transmission connects and passes to carry the box section to be connected, pass to carry the box section to pass through the connecting seat and be connected with the loading roof beam. The airplane horizontal tail large shaft test device can simulate the installation mode and the resultant force point position of a horizontal tail large shaft on an airplane, the force transmission route is clear, the authenticity of test piece loaded simulation is guaranteed, parts are few, the installation and the disassembly are convenient, the test complexity is greatly reduced, and the airplane horizontal tail large shaft test device can be suitable for static force, fatigue and other strength test research and verification work of various models of horizontal tail large shafts.
Description
Technical Field
The application belongs to the technical field of aviation strength tests, and particularly relates to a horizontal tail large shaft test device for an airplane.
Background
The big horizontal tail shaft is an important part of some military aircrafts, plays a key role in the structure, bears large load and is a vulnerable part. In order to research and verify the static strength and fatigue strength performance of the horizontal tail large shaft, a large number of static and fatigue strength tests need to be carried out. The key of the test is to simulate the stress state of the large horizontal tail shaft on the airplane, but the stress condition is complex, the conventional test method needs numerous loading points and loading channels, is difficult to install and disassemble, is not beneficial to test inspection, and can cause the problems of long test period and high cost.
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 application aims to provide an airplane horizontal tail large shaft testing device to solve at least one problem existing in the prior art.
The technical scheme of the application is as follows:
an aircraft horizontal tail large shaft test device comprises:
fixing the box section;
the fixing support comprises a fixing seat, a first mounting part and a second mounting part, wherein the first mounting part and the second mounting part are arranged on the fixing seat;
the connecting plate comprises a first connecting part and a second connecting part, the first connecting part is mounted 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 and is connected with the double-lug structure of the first connecting part;
a double-lug structure is arranged at one end of the transmission joint, the double-lug structure is matched with a pin shaft and is connected with the other joint bearing of the second connecting part, a second through hole is formed in the other end of the transmission joint, and a plurality of mounting holes are formed in the periphery of the second through hole;
the loading device comprises a loading box section, a first connecting seat and a second connecting seat, wherein one end of the loading box section is provided with a first through hole, a plurality of mounting holes are formed in the periphery of the first through hole, the mounting holes of the loading box section are connected with the mounting holes of the driving joint through fasteners, the other end of the loading box section is connected with a loading beam through the connecting seat, and a first mounting part is arranged in the loading box section;
the test piece, the one end of test piece with fixing support's first installation department fixed connection, 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 a bolt.
Optionally, the first connecting portion of the connecting plate is mounted on the fixed box section by a bolt.
Optionally, the cross-section of the drive joint is Z-shaped.
Optionally, a plurality of second reinforcing plates are arranged inside the load carrying box section, and through holes for the test pieces to pass through are formed in the second reinforcing plates.
Optionally, the third installation part of the transfer box section comprises a wedge-shaped base and a wedge-shaped sliding block, one end of the wedge-shaped base is fixed on the strip hole of the wall plate of the transfer box section in a detachable connection mode, and the other end of the wedge-shaped base is fixedly connected with the wedge-shaped sliding block.
Optionally, still include the tooth backing plate, pass the welding on the outer wall of year box section have with tooth backing plate looks adaptation's tooth gasket, the wedge base pass through bolt cooperation nut and tooth backing plate is fixed pass on the wallboard of year box section.
Optionally, the wedge base includes a plurality of pairs, and two wedge bases in each pair are respectively and fixedly connected with two sides of the wedge slider.
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 portion is arranged on the loading beam, and a second loading portion is arranged on the connecting seat.
The invention has at least the following beneficial technical effects:
the utility model provides an aircraft horizontal tail main shaft test device can simulate the mounting means and the resultant force point position of horizontal tail main shaft on the aircraft, and the biography power route is clear, has guaranteed the authenticity of test piece loaded simulation, and spare part is less, and the installation is dismantled conveniently, greatly reduced experimental complexity.
Drawings
FIG. 1 is a schematic overall view of a horizontal tail large shaft test device of an airplane according to an embodiment of the application;
FIG. 2 is a top view of an aircraft horizontal tail large shaft test device according to an embodiment of the present application;
FIG. 3 is a side view of an aircraft horizontal tail large axle test rig according to one embodiment of the present application;
FIG. 4 is a schematic view of a fixed support of the horizontal tail large shaft test device of the airplane according to one embodiment of the application;
FIG. 5 is a schematic illustration of a connection plate of an aircraft horizontal tail large shaft test device according to an embodiment of the present application;
FIG. 6 is a schematic view of a drive joint of an aircraft horizontal tail large shaft test device according to an embodiment of the present application;
FIG. 7 is a schematic view of a load carrying box section of the aircraft horizontal tail large shaft test device according to one embodiment of the present application;
FIG. 8 is a schematic view of a third mounting portion of an aircraft horizontal tail large axle test rig according to an embodiment of the present application;
FIG. 9 is a schematic view of a tooth pad plate of the horizontal tail large shaft test device of the airplane according to one embodiment of the present application;
fig. 10 is a schematic diagram of a position of a test resultant force point of an aircraft horizontal tail large shaft test device according to an embodiment of the present application.
Wherein:
1-fixing the box section; 2-fixing a support; 3-test piece; 4-connecting plates; 5-a transmission joint; 6-carrying box section; 7-a load beam; 8-a first loading section; 9-a second loading part; 10-a connecting seat; 11-a wedge-shaped base; 12-a wedge shaped slide; 13-tooth backing plate.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the 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 a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. 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 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 is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, 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 aircraft horizontal tail macroaxis test device includes: fixed box section 1, fixing support 2, connecting plate 4, transmission joint 5, pass and carry box section 6 and testpieces 3.
Specifically, as shown in fig. 1 to 3, the fixed box section 1 is a box-shaped structure, and is disposed on the ground, and a plurality of mounting holes are formed thereon. Fixing support 2 includes the fixing base and sets up first installation department and the second installation department on the fixing base, has seted up a plurality of mounting holes on the fixing base, installs on fixed box section 1 through the fastener, has seted up first through-hole on the second installation department. The connecting plate 4 comprises a first connecting part and a second connecting part, wherein a plurality of mounting holes are formed in the first connecting part, the first connecting part is mounted 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 and is connected with the double-lug structure of the first connecting part.
Further, the one end that transmission connects 5 is provided with the ears structure, and ears structure cooperation round pin axle is connected with another joint bearing of second connecting portion, and the second through-hole has been seted up to the other end that transmission connects 5, and has seted up a plurality of mounting holes around the second through-hole. A third through hole is formed in one end of the load transfer box section 6, a plurality of mounting holes are formed in the periphery of the third through hole, the mounting holes of the load transfer box section 6 are connected with the mounting holes of the transmission joint 5 through fasteners, the other end of the load transfer box section 6 is connected with the loading beam 7 through the connecting seat 10, and a third mounting part is arranged inside the load transfer box section 6; one end of the test piece 3 is fixedly connected with the first mounting part of the fixed support 2, and the other end of the test piece sequentially penetrates through the first through hole of the second mounting part of the fixed support 2, the second through hole of the transmission joint 5 and the third through hole of the transmission box section 6 and then is fixedly connected with the third mounting part of the transmission box section 6. Wherein, can be through offering the screw hole on the first installation department at fixing support 2 and the third installation department of biography year box section 6, the both ends of testpieces 3 are provided with the screw thread section, and the cooperation nut is connected the both ends of testpieces 3 and the installation department that corresponds.
The utility model provides an aircraft horizontal tail main shaft test device, adopt fixed box section 1 and fixing support 2 fixed with the one end of test piece 3, the other end and the biography of test piece 3 carry box section 6 fixedly, transmission joint 5 is responsible for transmitting the moment of torsion that the loading produced to fixed box section 1 through connecting plate 4, both ends at connecting plate 4 are provided with joint bearing, can be for test piece 3 born the weight of bending deformation and provide the corner displacement, transmission joint 5 carries box section 6 with the biography and is connected, biography year box section 6 is connected with loading roof beam 7 through connecting seat 10.
Advantageously, in one embodiment of the present application, a plurality of first reinforcing plates may be provided inside the stationary box section 1 for increasing the stability of the stationary box section 1.
In this embodiment, the fixing seat of the fixing support 2 is installed on the fixing box section 1 through a bolt, and the first connecting portion of the connecting plate 4 is also installed on the fixing box section 1 through a bolt.
In the present embodiment, the cross-section of the drive joint 5 is Z-shaped, as shown in fig. 6.
Advantageously, a plurality of second reinforcing plates may be disposed inside the carrying box section 6, in this embodiment, two second reinforcing plates are disposed, and a through hole for the test piece 3 to pass through is formed in each second reinforcing plate.
The utility model provides an aircraft horizontal tail main shaft test device, pass and carry the third installation department of box section 6 and include wedge base 11 and wedge slider 12, and the one end of wedge base 11 is fixed on passing the rectangular hole of carrying 6 wallboards of box section through the mode that can dismantle the connection, and the other end passes through bolt and wedge slider 12 fixed connection. The horizontal direction 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 large horizontal tail shaft sizes, the automatic centering of the wedge-shaped sliding block 12 can be achieved when a bolt in the horizontal direction is screwed, the axis of the wedge-shaped sliding block 12 is coaxial with the axis of the large horizontal tail shaft, and the design can ensure universality and assembly and load transmission. Advantageously, in this embodiment, still include tooth backing plate 13, weld on the outer wall of biography year box-section 6 and have the tooth gasket with tooth backing plate 13 looks adaptation, during the assembly, with tooth backing plate 13 and tooth gasket interlock, cooperate bolt and nut again to fix wedge base 11 on passing the wallboard of year box-section 6, prevent that wedge base 11 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 respectively and fixedly connected to two sides of the wedge slider 12.
The application discloses a horizontal tail large shaft test device for an airplane, a loading beam 7 is connected with a connecting seat 10 through a bolt, the connecting seat 10 is connected with a load transfer box section 6 through a bolt, a first loading part 8 is arranged on the loading beam 7, a second loading part 9 is arranged on the connecting seat 10, the first loading part 8 is in a handrail form, the second loading part 9 is in an ear piece form, the two loading parts are used as loading points and respectively correspond to the resultant force point positions of a case 2 and a case 1 shown in a figure 10, and test loads are applied through the two loading points. During testing, resultant loads of the situation 2 and the situation 1 are applied to the first loading part 8 and the second loading part 9 respectively, the loading loads are transmitted to the connecting seat 10 through the loading beam 7, then 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 redundant torsion is transmitted to the fixed box section 1 through the transmission joint 5.
The utility model provides an aircraft horizontal tail macroaxis test device, can simulate the mounting means and the resultant force point position of horizontal tail macroaxis on the aircraft, it is clear to pass the power route, the authenticity of test piece loaded simulation has been guaranteed, spare part is less, the installation is dismantled conveniently, only need apply load at 2 loading points, greatly reduced experimental complexity, and position control and aligning function that can have through wedge base 11 and wedge slider 12, guarantee the installation accuracy of not unidimensional horizontal tail macroaxis, the commonality is stronger. The method has the advantages of high loading simulation degree, low complexity and good universality, and can be suitable for strength test research and verification work of static force, fatigue and the like of the large horizontal tail shaft with various models.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides an aircraft horizontal tail macroaxis test device which characterized in that includes:
a stationary box section (1);
the fixing support (2) comprises a fixing seat, a first mounting part and a second mounting part, wherein the first mounting part and the second mounting part are arranged on the fixing seat, the fixing seat is mounted on the fixing box section (1) through a fastening piece, and a first through hole is formed in the second mounting part;
the connecting plate (4) comprises a first connecting part and a second connecting part, the first connecting part is mounted 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 and is connected with the double-lug structure of the first connecting part;
a double-lug structure is arranged at one end of the transmission joint (5), the double-lug structure is matched with a pin shaft and is connected with the other joint bearing of the second connecting part, a second through hole is formed in the other end of the transmission joint (5), and a plurality of mounting holes are formed in the periphery of the second through hole;
the transmission box section (6) is provided with a third through hole at one end, 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 inside the transmission box section (6);
the test piece (3), the one end of test piece (3) with the first installation department fixed connection of fixing support (2), 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 (6).
2. The aircraft flattail macroaxis test apparatus of claim 1, wherein a plurality of first reinforcing plates are provided inside the stationary box section (1).
3. The aircraft horizontal tail large shaft test device according to claim 1, wherein the fixed seat of the fixed support (2) is installed on the fixed box section (1) through a bolt.
4. The aircraft flattail macroaxis test apparatus of claim 1, characterized in that the first connection portion of the connection plate (4) is mounted on the fixed box section (1) by 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 aircraft horizontal tail large shaft test device according to claim 1, wherein a plurality of second reinforcing plates are arranged in the load transmission box section (6), and through holes for the test pieces (3) to pass through are formed in the second reinforcing plates.
7. The aircraft horizontal tail large shaft test device according to claim 1, wherein the third installation part of the load transmission 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 long hole of a wall plate of the load transmission 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 aircraft horizontal tail large shaft test device according to claim 7, further comprising a tooth backing plate (13), wherein a tooth gasket matched with the tooth backing plate (13) is welded on the outer wall surface of the load transmission box section (6), and the wedge-shaped base (11) is fixed on a wall plate of the load transmission 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, characterized in that the wedge-shaped bases (11) comprise a plurality of pairs, and two wedge-shaped bases (11) in each pair are respectively fixedly connected with two sides of the wedge-shaped sliding block (12).
10. The aircraft horizontal tail large shaft test device 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 true CN112591137A (en) | 2021-04-02 |
| CN112591137B CN112591137B (en) | 2023-11-28 |
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| 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 |
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| Country | Link |
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| CN (1) | CN112591137B (en) |
Cited By (1)
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| CN113654882A (en) * | 2021-06-18 | 2021-11-16 | 中国商用飞机有限责任公司 | Experimental loading device of horizontal tail |
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Also Published As
| Publication number | Publication date |
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| CN112591137B (en) | 2023-11-28 |
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