CN205209758U - Aircraft vertical fin dynamic load loading device - Google Patents
Aircraft vertical fin dynamic load loading device Download PDFInfo
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- CN205209758U CN205209758U CN201521009119.1U CN201521009119U CN205209758U CN 205209758 U CN205209758 U CN 205209758U CN 201521009119 U CN201521009119 U CN 201521009119U CN 205209758 U CN205209758 U CN 205209758U
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Abstract
The utility model discloses an aircraft vertical fin dynamic load loading device, including electric magnetic vibration platform, the extension bar, the static pressure ball pivot, the keysets, the sensor, the connecting plate, loading aluminium pig and load plate, electricity magnetic vibration platform is fixed on frame construction or ground, the mesa of electricity magnetic vibration platform and the one end fixed connection of extension bar, the extension bar other end is equipped with the spherical shell and is connected with the sphere end of static pressure ball pivot, the other end of static pressure ball pivot passes through the one end fixed connection of keysets and sensor, the other end and the connecting plate fixed connection of sensor, the one end fixed connection of connecting plate and loading aluminium pig, the fast other end of loading bonds with the bonding agent with load plate's first bottom surface, second bottom surface with load plate bonds in aircraft vertical fin airfoil at last. Provide the dynamic load through electric magnetic vibration platform, transmit aircraft vertical fin airfoil with the dynamic load through extension bar, sensor, loading aluminium pig and load plate etc. Adopt the static pressure ball pivot can guarantee dynamic load vertical force in aircraft vertical fin airfoil all the time in the transmission.
Description
Technical field
The utility model belongs to aircraft structure strength experimental technique field, particularly relates to a kind of aircraft vertical fin dynamic load loading device.
Background technology
In aircraft structure test, the plain fatigue experimental technique of complete aircraft is ripe, but during the flight of present generation aircraft large attack angle, the air-flow flowing through wing can produce powerful eddy current sharp blow aircraft vertical fin, thus causes the vibration of aircraft vertical fin and buffeting to cause dynamic fatigue to destroy.
In this case, the fatigure failure of fuselage and vertical fin thereafter can not have effectively been verified and solved in the plain fatigue test of complete aircraft.Therefore, for effectively verifying the fatigure failure of the aircraft rear body that vibration and buffeting cause and vertical fin, the dynamic fatigue test of aircraft vertical fin under Dynamic Loading need be carried out.Therefore, a kind of equipment or device is needed can to carry out dynamic load load test to aircraft vertical fin.
Utility model content
The purpose of this utility model is to provide a kind of aircraft vertical fin dynamic load loading device, does not have the problem of relevant device or device during in order to solve and to carry out dynamic fatigue test to aircraft vertical fin at present.
For achieving the above object, the technical solution adopted in the utility model is: a kind of aircraft vertical fin dynamic load loading device, comprise electromagnetic vibration generator system, extension rod, static-pressure spherical hinge, card extender, sensor, web joint, load aluminium block and load plate, described electromagnetic vibration generator system is fixed in framed structure or ground, the table top of electromagnetic vibration generator system is fixedly connected with one end of extension rod, the extension rod other end is provided with spherical shell and is connected with the sphere end of described static-pressure spherical hinge, the rod end of static-pressure spherical hinge is fixedly connected with one end of sensor by card extender, the other end end of sensor is fixedly connected with web joint, web joint is fixedly connected with the one end loading aluminium block, loading the fast other end carries out bonding with the first bottom surface bonding agent of load plate, recently the second bottom surface of load plate is adhered to aircraft vertical fin aerofoil.
Further, described load plate is truncated cone shape, the described loading aluminium block face bonding with described load plate is the first bottom surface of the frustum of a cone, and the face that described load plate acts on aircraft vertical fin is the second bottom surface of the frustum of a cone, and described first bottom surface is less than described second bottom surface.
Further, along described frustum of a cone axis place plane, described load plate is divided into 4 secter pats, the segment angle of described secter pat is 90 degree.
Further, the material of described load plate is polyurethane.
Further, described load bar is that duralumin, hard alumin ium alloy is made.
Further, described sensor is dynamic force sensor.
A kind of aircraft vertical fin dynamic load loading device of the present utility model, dynamic load is provided by electromagnetic vibration generator system, through extension rod, sensor, loading aluminium block and load plate etc., dynamic load is delivered to aircraft vertical fin aerofoil, adopt in transmission static-pressure spherical hinge can ensure dynamic load all the time vertical loading in aircraft vertical fin, solve and do the problem that aircraft vertical fin dynamic loading test does not have testing equipment at present.
Accompanying drawing explanation
Accompanying drawing to be herein merged in instructions and to form the part of this instructions, shows and meets embodiment of the present utility model, and is used from instructions one and explains principle of the present utility model.
Fig. 1 is the structural representation of a kind of aircraft vertical fin dynamic load loading device according to the utility model one embodiment;
Fig. 2 is the structural representation of the load plate according to the utility model one embodiment;
Fig. 3 is the load application schematic diagram of a kind of aircraft vertical fin dynamic load loading device according to the utility model one embodiment.
Wherein, 1 is electromagnetic vibration generator system, and 2 is extension rods, and 3 is static-pressure spherical hinges, and 4 is card extenders, and 5 is sensors, and 6 is web joints, and 7 is load aluminium block, and 8 is load plate, and 81 is secter pats, and 801 is first bottom surfaces, and 802 is second bottom surfaces.
Embodiment
The object implemented for making the utility model, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the utility model embodiment, are further described in more detail the technical scheme in the utility model embodiment.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the utility model part embodiment, instead of whole embodiments.Be exemplary type below by the embodiment be described with reference to the drawings, be intended to for explaining the utility model, and can not be interpreted as restriction of the present utility model.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creation type work prerequisite, all belong to the scope of the utility model protection.Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail.
In description of the present utility model, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore the restriction to the utility model protection domain can not be interpreted as.
Be illustrated in figure 1 a kind of aircraft vertical fin dynamic load loading device of the present utility model, comprise electromagnetic vibration generator system 1, extension rod 2, static-pressure spherical hinge 3, card extender 4, sensor 5, web joint 6, load aluminium block 7 and load plate 8, electromagnetic vibration generator system 1 is fixed in framed structure or ground, the table top of electromagnetic vibration generator system 1 and one end of extension rod 2 are bolted to connection, extension rod 2 other end is provided with spherical shell and is connected with the sphere end of static-pressure spherical hinge 3, the other end of static-pressure spherical hinge 3 is fixedly connected with by card extender 4 one end with sensor 5, the other end of sensor 5 is fixedly connected with web joint 6, web joint 6 is fixedly connected with by screw with the one end loading aluminium block 7, loading the fast other end carries out bonding with the one side bonding agent of load plate 8, finally another face of load plate 8 is adhered to aircraft vertical fin aerofoil.
Demand is pointed out that, as shown in Figure 2, the material of load plate 8 is polyurethane, and global shape is taper platform shape, the less bottom surface of taper platform is that the first bottom surface connects with loading aluminium block 7 AB is gluing, and the larger bottom surface of taper platform is the second bottom surface is also carry out bonding with AB glue with the vertical fin aerofoil of aircraft.Load plate 8 forms by the secter pat 81 that 4 sizes are identical is bonding, it along taper platform axis place plane, taper platform is divided into 4 secter pats 81 uniformly by the load plate 8 of the taper platform of monoblock, the fan angle of each secter pat 81 is 90 °, again these 4 secter pats 81 is spliced into an entirety afterwards.The load plate 8 be spliced by the secter pat 81 of 4 polyurethane is not like this rigid material due to it and be divided into 4 pieces, can fit with the arc-shaped curved surface of aircraft vertical fin aerofoil to greatest extent when carrying out bonding to aircraft vertical fin.
Concrete, the step that load plate 8 bonds to aircraft vertical fin aerofoil is:
1) polyurethane load plate is divided into four pieces, each block is 90 ° fan-shaped, high performance structures AB glue is smeared in each block bottom surface and surrounding, block-by-block is bonded in vertical fin aerofoil surfaces, and by the center of circle centering aerofoil loading Position of every block, after four pieces all bonding, four pieces are compressed respectively, AB glue is overflowed along the seam of each piece and periphery, smear AB glue in right amount to again polyurethane load plate circumferential edge and make its edge sealing, after one hour, reach 70% of its final bonding strength;
2) polish flat with the less bottom surface (i.e. the first bottom surface) of emery wheel by the taper platform of polyurethane load plate;
3) high performance structures AB glue is smeared in the face (the first bottom surface) that loading aluminium block 7 contacts with load plate 8, Shi Qi center is facing to the center of polyurethane load plate, loading aluminium block 7 compressed and uses high performance structures AB adhesive edge, waiting for after adhesive curing and reach maximum to make its bonding strength in 24 hours;
4) bonding strength of each bond reach maximum after could be connected with other parts, and carry out oscillating load loading.
It is pointed out that load bar 2 of the present utility model adopts duralumin, hard alumin ium alloy material to make, adopt duralumin, hard alumin ium alloy both can ensure that the strength and stiffness of extension rod 2, reduce additional mass and moment of flexure again as far as possible.In addition, what sensor 5 of the present utility model adopted is dynamic force sensor.
Concrete, a kind of aircraft vertical fin dynamic load loading device principle of work of the present utility model and process are: when vibrating loading, the signal of dynamic force sensor can be used as control signal and controls shaking table loading, be be rigidly connected between each, the oscillating load that therefore shaking table produces can accurately be loaded on vertical fin aerofoil.When vertical fin stress deformation, because polyurethane load plate and loading aluminium sheet 7 are bonded in vertical fin aerofoil, club and the dynamic force sensor of static-pressure spherical hinge 3 and load aluminium sheet 7 and be all fixed with bolts, each with vertical fin without translation or rotational freedom, its axis direction is exactly loading direction.And the club of static-pressure spherical hinge 3 and spherical shell are hinged, relatively rotate degree of freedom, therefore, when the distortion of vertical fin aerofoil produces angle of deflection, loaded member can make loading direction all the time perpendicular to vertical fin aerofoil with its deflection, each the drift angle α produced with shaking table axle center is then compensated by static-pressure spherical hinge 3, as shown in Figure 3 (electromagnetic vibration generator system 1 does not draw).
A kind of aircraft vertical fin dynamic load loading device of the present utility model, adopts the oscillating load load mode of ball pivot, when can ensure vertical fin stress deformation, loads all the time in vertical fin aerofoil vertical direction; Adopt the desk-top polyurethane load plate of circular cone, namely expand the bond area of polyurethane load plate and vertical fin thus improve bonding strength, be of value to again the stress dispersion of vertical fin aerofoil covering, be unlikely to covering stress concentrate and destroy, and adopt the bonding mode of polyurethane load plate to fix charger at vertical fin aerofoil, therefore under the prerequisite of vertical fin not being carried out to physical damage, oscillating load can be applied to vertical fin set point.
The above; be only optimum embodiment of the present utility model; but protection domain of the present utility model is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the utility model discloses; the change that can expect easily or replacement, all should be encompassed within protection domain of the present utility model.Therefore, protection domain of the present utility model should be as the criterion with the protection domain of described claim.
Claims (6)
1. an aircraft vertical fin dynamic load loading device, it is characterized in that, comprise electromagnetic vibration generator system (1), extension rod (2), static-pressure spherical hinge (3), card extender (4), sensor (5), web joint (6), load aluminium block (7) and load plate (8), described electromagnetic vibration generator system (1) is fixed in framed structure or ground, the table top of electromagnetic vibration generator system (1) is fixedly connected with one end of extension rod (2), extension rod (2) other end is provided with spherical shell and is connected with the sphere end of described static-pressure spherical hinge (3), the rod end of static-pressure spherical hinge (3) is fixedly connected with by card extender (4) one end with sensor (5), the other end end of sensor (5) is fixedly connected with web joint (6), web joint (6) is connected surely with the one end loading aluminium block (7), the other end loading aluminium block (7) carries out bonding with the first bottom surface bonding agent of load plate (8), second bottom surface of load plate (8) is adhered to aircraft vertical fin aerofoil.
2. a kind of aircraft vertical fin dynamic load loading device according to claim 1, it is characterized in that, described load plate (8) is truncated cone shape, the face that described loading aluminium block (7) is bonding with described load plate (8) is first bottom surface (801) of the frustum of a cone, the face that described load plate (8) is adhered to aircraft vertical fin aerofoil is second bottom surface (802) of the frustum of a cone, and described first bottom surface (801) area is less than described second bottom surface (802) area.
3. a kind of aircraft vertical fin dynamic load loading device according to claim 2, it is characterized in that, along described frustum of a cone axis place plane, described load plate (8) is divided into 4 secter pats (81), the segment angle of described secter pat (81) is 90 degree.
4. a kind of aircraft vertical fin dynamic load loading device according to claim 3, is characterized in that, the material of described load plate (8) is polyurethane.
5. a kind of aircraft vertical fin dynamic load loading device according to claim 1, is characterized in that, described extension rod (2) is made for duralumin, hard alumin ium alloy.
6. a kind of aircraft vertical fin dynamic load loading device according to claim 1, is characterized in that, described sensor (5) is dynamic force sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521009119.1U CN205209758U (en) | 2015-12-08 | 2015-12-08 | Aircraft vertical fin dynamic load loading device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521009119.1U CN205209758U (en) | 2015-12-08 | 2015-12-08 | Aircraft vertical fin dynamic load loading device |
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| CN205209758U true CN205209758U (en) | 2016-05-04 |
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| CN201521009119.1U Active CN205209758U (en) | 2015-12-08 | 2015-12-08 | Aircraft vertical fin dynamic load loading device |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163227A (en) * | 2017-11-30 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of turning joint pressure-bearing joint |
| CN109655245A (en) * | 2018-10-31 | 2019-04-19 | 中国飞机强度研究所 | A kind of four vertical fin load loading methods |
| CN114674547A (en) * | 2022-05-30 | 2022-06-28 | 中国飞机强度研究所 | Boundary rigidity simulation system in full-motion vertical fin buffeting test of airplane strength test |
| CN114778049A (en) * | 2022-06-22 | 2022-07-22 | 中国飞机强度研究所 | Vibration testing device and vibration simulation method for airplane airfoil surface structure |
| CN114813000A (en) * | 2022-06-23 | 2022-07-29 | 中国飞机强度研究所 | Load monitoring device and method for buffeting test of aircraft key structure |
-
2015
- 2015-12-08 CN CN201521009119.1U patent/CN205209758U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163227A (en) * | 2017-11-30 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of turning joint pressure-bearing joint |
| CN109655245A (en) * | 2018-10-31 | 2019-04-19 | 中国飞机强度研究所 | A kind of four vertical fin load loading methods |
| CN114674547A (en) * | 2022-05-30 | 2022-06-28 | 中国飞机强度研究所 | Boundary rigidity simulation system in full-motion vertical fin buffeting test of airplane strength test |
| CN114674547B (en) * | 2022-05-30 | 2022-08-05 | 中国飞机强度研究所 | Boundary rigidity simulation system in full-motion vertical fin buffeting test of airplane strength test |
| CN114778049A (en) * | 2022-06-22 | 2022-07-22 | 中国飞机强度研究所 | Vibration testing device and vibration simulation method for airplane airfoil surface structure |
| CN114813000A (en) * | 2022-06-23 | 2022-07-29 | 中国飞机强度研究所 | Load monitoring device and method for buffeting test of aircraft key structure |
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