CN213083527U - Auxiliary device for vibration test of aircraft suspension device - Google Patents
Auxiliary device for vibration test of aircraft suspension device Download PDFInfo
- Publication number
- CN213083527U CN213083527U CN202021024161.1U CN202021024161U CN213083527U CN 213083527 U CN213083527 U CN 213083527U CN 202021024161 U CN202021024161 U CN 202021024161U CN 213083527 U CN213083527 U CN 213083527U
- Authority
- CN
- China
- Prior art keywords
- plate
- aircraft
- clamp
- auxiliary device
- aircraft suspension
- 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
Images
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model discloses an aircraft linkage auxiliary device for vibration test, including hanging anchor clamps, simulant, sectional fixture, through hanging anchor clamps simulation aircraft linkage last one-level joint, simulant simulation lower one-level linkage, sectional fixture will hang anchor clamps, aircraft linkage, simulant integral erection on the vibration test bench. The device simple structure, convenient operation has fine practicality.
Description
Technical Field
The utility model belongs to experimental auxiliary device field of using, concretely relates to aircraft linkage auxiliary device for vibration test.
Background
The aircraft suspension device is a device which is suspended below the wing or belly of the aircraft and used for suspending a secondary fuel tank, a missile or a next-stage suspension device. The aircraft suspension device is used as a part of an aircraft and is also subjected to a series of test examinations to ensure the safety of the aircraft suspension device. One of the tests is a vibration test, namely, the aircraft suspension device is fixed on a vibration test bed, and the vibration test is carried out according to relevant test parameters. The test is one of the most important verification tests in aircraft suspension systems, and its importance is self-evident. When the vibration test is carried out, the airplane suspension device is not fixed on the vibration table, but the vibration test is carried out under the condition that the airplane suspension device is simulated. Therefore, an auxiliary device needs to be designed to help the aircraft suspension device simulate a real installation state and then be fixed on a vibration test bed.
SUMMERY OF THE UTILITY MODEL
Purpose of the utility model
In order to solve the technical problem, the utility model provides an aircraft linkage auxiliary device for vibration test.
Technical solution of utility model
In order to realize the purpose of the utility model, the utility model adopts the following technical scheme:
the utility model provides an aircraft linkage auxiliary device for vibration test, includes suspension fixture, simulation thing, sectional fixture, through suspension fixture simulation aircraft linkage last level joint, simulation thing simulation next level suspension device, sectional fixture with suspension fixture, aircraft linkage, simulation thing integral erection on the vibration test platform.
Preferably, the sectional fixture comprises a base and two upper connecting components which are horizontally arranged, the two upper connecting components are positioned right above the base and are parallel to each other and positioned on the same horizontal position, and the base and the two upper connecting components are connected through a plurality of connecting columns and reinforcing ribs respectively.
Preferably, the upper connecting assembly comprises an upper connecting plate and a lower connecting plate which are horizontally arranged, the upper connecting plate and the lower connecting plate are connected through a plurality of reinforcing plates, the side surfaces of the upper connecting plate and the lower connecting plate are connected through a vertical plate, a plurality of round holes are uniformly distributed on the upper connecting plate and the lower connecting plate, and the upper connecting assembly is connected with the suspension clamp; the base is connected with the vibration test bed.
Preferably, the suspension clamp consists of a front clamp body and a rear clamp body which are independent, and the front clamp body and the rear clamp body of the suspension clamp are respectively connected with a front joint and a rear joint of the aircraft suspension device; the front clamp body and the rear clamp body respectively comprise a horizontally arranged bottom plate and an upper plate, the side surface of the upper plate, which is vertical to the course, is fixedly connected together through a reinforced vertical plate and a reinforcing rib II, a positioning block is fixed in the middle of the bottom surface of the upper plate, the upper vertical plate, which is vertical to the upper plate, is fixed on the top surface of the upper plate, and a cover plate is fixed on the top surface of the upper vertical; the corresponding positions of the bottom plate and the upper plate are provided with a plurality of waist-shaped holes, the symmetrical axes of the waist-shaped holes are parallel to the course, and the positioning block is connected with the airplane suspension device.
Preferably, the waist-shaped holes are uniformly distributed, and the suspension clamp is fixed on the mounting clamp through mounting bolts and nuts at the waist-shaped holes.
Preferably, the locating piece includes connecting portion I and two vertical settings of being connected with the upper plate and the connecting portion II of riser is strengthened to the perpendicular to, and the locating hole has been seted up to corresponding position on connecting portion II, is connected with aircraft linkage through the last location bolt that passes two connecting portion II go up the locating hole, goes up location bolt tip and has seted up the round hole, connects aircraft linkage good back, prevents through the split pin I that sets up in the round hole that aircraft linkage from droing from the location bolt when vibration test.
Preferably, the simulant includes the main part, connects locating piece, balancing weight, and the balancing weight is connected in the main part and is made the weight and the focus of simulant and next stage suspender weight, focus identical, connects the locating piece and installs and be connected with aircraft linkage at the main part upper surface.
Preferably, the main body or the counterweight is provided with an eyebolt.
Preferably, the simulator is connected with the airplane suspension device through the lower positioning bolt arranged on the connecting positioning block, the end part of the lower positioning bolt is provided with a round hole, after the simulator is connected, the cotter pin II is inserted into the round hole in the lower positioning bolt, and the simulator is prevented from falling off from the lower positioning bolt during vibration test after being arranged.
Preferably, the upper connecting plate, the lower connecting plate, the reinforcing plate and the vertical plate are fixed by welding between the base and the connecting column and between the base and the reinforcing rib.
The advantages of the utility model
The utility model has the advantages that: the device utilizes a suspension clamp to simulate a primary connector on an airplane suspension device, a simulator to simulate a secondary suspension device, and an installation clamp to integrally install the suspension clamp, the airplane suspension device and the simulator on a vibration test bed; the suspension clamp is divided into independent front and rear clamp bodies which are respectively connected with the front and rear joints of the airplane suspension device, so that the mounting difficulty is reduced; the waist-shaped holes uniformly distributed on the upper plate and the bottom plate in the suspension fixture can be used for adjusting the suspension fixture, the airplane suspension device and a simulation object along the course of an airplane during installation; the split pin is inserted into the round holes at the front ends of the upper positioning bolt and the lower positioning bolt to limit the plane suspension device and the simulation object from falling off from the upper positioning bolt and the lower positioning bolt during vibration; the round holes uniformly distributed along the course on the connecting and positioning assembly on the mounting fixture are utilized to realize adjustment during mounting and enable the mounting fixture to be used for mounting different hanging fixtures. The device simple structure, convenient operation has fine practicality.
Drawings
Fig. 1 is an assembly view of the auxiliary device for vibration test of an aircraft suspension device of the present invention.
Fig. 2 is a front view of the mounting fixture.
Fig. 3 is a top view of the mounting clip.
Fig. 4 is a front view of a front/rear clamp body in the suspension clamp.
Fig. 5 is a top view of the front/rear clamp body of the suspension clamp.
Fig. 6 is a schematic view of a structure of a suspension.
In the figure: 1 mounting clamp, 1-1 connecting column, 1-2 reinforcing ribs I, 1-3 vertical plates, 1-4 reinforcing plates, 1-5 lower connecting plates, 1-6 upper connecting plates, 1-7 bases, 2 aircraft suspension devices, 3 suspension clamps, 3-1 bottom plates, 3-2 reinforcing vertical plates, 3-3 upper plates, 3-4 reinforcing ribs II, 3-5 cotter pins I, 3-6 upper positioning bolts, 3-7 upper vertical plates, 3-8 cover plates, 3-9 screws, 3-10 cylindrical pins, 3-11 positioning blocks, 4 simulators, 4-1 balancing weights 1, 4-2 bolts, 4-3 nuts, 4-4 lifting eye bolts, 4-5 front connectors, 4-6 main bodies, 4-7 balancing weights 2, 4-8 rear connectors, 4-9 supporting blocks, 4-10 lower positioning bolts and 4-11 cotter pins II.
Detailed Description
The detailed description of the embodiments of the present invention is provided with the summary of the present invention and the accompanying drawings.
The utility model provides an aircraft linkage auxiliary device for vibration test, includes hang anchor clamps 3, simulant 4, sectional fixture 1, through hang anchor clamps 3 simulation aircraft linkage last level connect, simulant 4 simulation next level linkage, sectional fixture 1 with hang anchor clamps 3, aircraft linkage 2, simulant 4 integral erection on the vibration test platform.
The mounting fixture 1 comprises bases 1-7 and two upper connecting assemblies, wherein the bases 1-7 are horizontally arranged, the two upper connecting assemblies are located right above the bases 1-7 and are parallel to each other and located at the same horizontal position, and the bases 1-7 and the two upper connecting assemblies are connected through a plurality of connecting columns 1-1 and reinforcing ribs 1-2 respectively.
The upper connecting assembly comprises an upper connecting plate 1-6 and a lower connecting plate 1-5 which are horizontally arranged, a plurality of vertically arranged reinforcing plates 1-4 are welded between the upper connecting plate 1-6 and the lower connecting plate 1-5, vertical plates 1-3 are welded on the side surfaces of the upper connecting plate 1-6 and the lower connecting plate 1-5, a plurality of uniformly distributed round holes are formed in the same positions of the upper connecting plate 1-6 and the lower connecting plate 1-5, and the upper connecting assembly is connected with the hanging clamp 3 through bolts and nuts; the bases 1-7 are provided with a plurality of concentric circular and evenly distributed round holes, and the bases 1-7 are fixed with the vibration test bed through screws arranged in the round holes, so that the position of the mounting fixture 1 on the vibration test bed can be adjusted.
The suspension clamp 3 consists of a front clamp body and a rear clamp body which are independent, and the front clamp body and the rear clamp body of the suspension clamp 3 are respectively connected with an upper front joint and an upper rear joint of the airplane suspension device 2; the front clamp body and the rear clamp body respectively comprise a bottom plate 3-1 and an upper plate 3-3 which are horizontally arranged, the side surface perpendicular to the course is welded together through a reinforced vertical plate 3-2 and a reinforcing rib II 3-4, a positioning block 3-11 is fixed in the middle of the bottom surface of the upper plate 3-3, and the positioning block 3-11 is fixed on the upper plate 3-3 through a positioning pin hole and a screw and then welded, so that the strength of the positioning block is ensured. Two upper vertical plates 3-7 vertical to the upper plate 3-3 are welded on the top surface of the upper plate 3-3, and a cover plate 3-8 is welded on the top surface of the upper vertical plates 3-7; a plurality of uniformly distributed waist-shaped holes are formed in corresponding positions on the bottom plate 3-1 and the upper plate 3-3, the hanging clamp 3 is fixed on the mounting clamp 1 through mounting bolts and nuts at the waist-shaped holes, and the position of the hanging clamp 3 can be adjusted properly along the course direction according to the mounting condition.
The positioning block 3-11 comprises a connecting portion I connected with the upper plate 3-3 and two connecting portions II which are vertically arranged and perpendicular to the reinforced vertical plate 3-2, positioning holes are formed in corresponding positions of the connecting portions II, the connecting portions II are connected with the aircraft suspension device 2 through upper positioning bolts 3-6 penetrating through the positioning holes in the two connecting portions II, round holes are formed in the end portions of the upper positioning bolts 3-6, and after the aircraft suspension device 2 is connected, the aircraft suspension device 2 is prevented from falling off from the positioning bolts during vibration tests through split pins I3-5 arranged in the round holes.
The simulator 4 comprises a main body 4-6, a connecting positioning block and a balancing weight 4-1, wherein the balancing weight 4-1 is connected to the main body 4-6 through welding or bolts, so that the weight and the gravity center of the simulator 4 are completely the same as those of a next-stage suspension, the connecting positioning block is installed on the upper surface of the main body 4-6 through a positioning pin hole and a screw and is connected with the aircraft suspension device 2, and the strength of the connecting positioning block can be enhanced through welding after the connecting positioning block is installed. The main body 4-6 or the counterweight 4-1 is provided with an eyebolt 4-4. In the embodiment, the connecting and positioning block comprises a front joint 4-5 and a rear joint 4-8, wherein the front joint 4-5 is connected with a front lower joint in the aircraft suspension device 2, and the front joint 4-6 is connected with a rear lower joint in the aircraft suspension device 2.
The simulator 4 is connected with the airplane suspension device 2 by installing the lower positioning bolt 4-10 on the connecting positioning block, the end part of the lower positioning bolt 4-10 is provided with a round hole, and after the simulator 4 is connected, the cotter pin II 4-11 is inserted into the round hole on the lower positioning bolt 4-10, so that the simulator 4 is prevented from falling off from the lower positioning bolt 4-10 during vibration test after being installed. The 4-9 supporting blocks are used for supporting channel steel on the main body 4-6, the lower ends of the channel steel are connected with the lower ends of the main body 4-6, and the upper ends of the channel steel are connected with the lower surfaces of the channel steel on the main body 4-6 and are all connected in a welding mode.
The installation process is as follows: aligning an upper front connector positioning hole on an airplane suspension device 2 with a positioning hole on a positioning block 3-11, fixing the airplane suspension device 2 on a suspension clamp 3 by using an upper positioning bolt 3-6, and then inserting an opening pin I3-5 into the upper positioning bolt 3-6 to prevent the airplane suspension device 2 from falling off; then the suspension clamp 3 and the airplane suspension device 2 are integrally fixed by bolts and nuts through the waist-shaped holes on the bottom plate 3-1 and the upper plate 3-3 and the mounting holes on the lower connecting plate 1-5 and the upper connecting plate 1-6; then, the suspension clamp 3, the airplane suspension device 2 and the mounting clamp 1 are integrally fixed on a vibration test bed through round holes in the bases 1-7 by screws; finally, connecting holes of a front joint 4-5 and a rear joint 4-8 on the simulant 4 are aligned with positioning holes of a lower rear joint on the aircraft suspension device 2, the simulant is fixedly installed by using a lower positioning bolt 4-10, and then a cotter pin II 4-11 is inserted into the lower positioning bolt 4-10 to prevent the simulant 4 from falling off. And finishing the installation work before the test.
The above embodiments are only for illustrating the technical conception and features of the present invention, and the purpose thereof is to enable those skilled in the art to understand the contents of the present invention and to implement the same, so as not to limit the protection scope of the present invention, and all the equivalent changes or modifications made according to the spirit of the present invention should be covered in the protection scope of the present invention. The technology, shape and construction parts which are not described in detail in the present invention are all known technology.
Claims (10)
1. The utility model provides an aircraft linkage auxiliary device for vibration test which characterized in that: the device comprises a hanging clamp (3), a simulation object (4) and a mounting clamp (1), wherein the hanging clamp (3), the simulation object (2) and the simulation object (4) are integrally mounted on a vibration test bed through the hanging clamp (3) for simulating a first-stage joint on an airplane hanging device, the simulation object (4) for simulating a second-stage hanging device and the mounting clamp (1).
2. An auxiliary device for vibration testing of an aircraft suspension unit, as claimed in claim 1, wherein: the mounting fixture (1) comprises bases (1-7) and two upper connecting assemblies, wherein the bases (1-7) are horizontally arranged, the two upper connecting assemblies are located right above the bases (1-7) and are parallel to each other and located at the same horizontal position, and the bases (1-7) and the two upper connecting assemblies are connected through a plurality of connecting columns (1-1) and reinforcing ribs (1-2) respectively.
3. An auxiliary device for vibration testing of an aircraft suspension unit, as claimed in claim 2, wherein: the upper connecting assembly comprises an upper connecting plate (1-6) and a lower connecting plate (1-5) which are horizontally arranged, the upper connecting plate (1-6) and the lower connecting plate (1-5) are connected through a plurality of reinforcing plates (1-4), the side surfaces of the upper connecting plate (1-6) and the lower connecting plate (1-5) are connected through a vertical plate (1-3), a plurality of round holes are uniformly distributed at the same positions of the upper connecting plate (1-6) and the lower connecting plate (1-5), and the upper connecting assembly is connected with the hanging clamp (3); the base (1-7) is connected with the vibration test bed.
4. An auxiliary device for vibration testing of an aircraft suspension unit, as claimed in claim 1, wherein: the suspension clamp (3) consists of a front clamp body and a rear clamp body which are independent, and the front clamp body and the rear clamp body of the suspension clamp (3) are respectively connected with the aircraft suspension device (2); the front clamp body and the rear clamp body respectively comprise a bottom plate (3-1) and an upper plate (3-3) which are horizontally arranged, the side surfaces perpendicular to the course direction of the upper plate (3-3) are fixedly connected together through a reinforced vertical plate (3-2) and a reinforcing rib II (3-4), a positioning block (3-11) is fixed in the middle of the bottom surface of the upper plate (3-3), an upper vertical plate (3-7) perpendicular to the upper plate (3-3) is fixed on the top surface of the upper plate (3-3), and a cover plate (3-8) is fixed on the top surface of the upper vertical plate (3-7); a plurality of waist-shaped holes are formed in corresponding positions on the bottom plate (3-1) and the upper plate (3-3), and the symmetry axes of the waist-shaped holes are parallel to the course; the positioning blocks (3-11) are connected with the aircraft suspension device (2).
5. An auxiliary device for vibration testing of an aircraft suspension unit, as defined in claim 4, wherein: the waist-shaped holes are uniformly distributed, and the suspension clamp (3) is fixed on the mounting clamp (1) through mounting bolts and nuts at the waist-shaped holes.
6. An auxiliary device for vibration testing of an aircraft suspension unit, as defined in claim 4, wherein: the positioning block (3-11) comprises a connecting part I connected with the upper plate (3-3) and two connecting parts II which are vertically arranged and perpendicular to the reinforced vertical plate (3-2), positioning holes are formed in corresponding positions of the connecting parts II, an upper positioning bolt (3-6) penetrating through the positioning holes in the two connecting parts II is connected with the aircraft suspension device (2), a round hole is formed in the end part of the upper positioning bolt (3-6), and after the aircraft suspension device (2) is connected, the aircraft suspension device (2) is prevented from falling off from the positioning bolt through a split pin I (3-5) arranged in the round hole.
7. An auxiliary device for vibration testing of an aircraft suspension unit, as claimed in claim 1, wherein: the simulator (4) comprises a main body (4-6), a connecting positioning block and a balancing weight (4-1), wherein the balancing weight (4-1) is connected to the main body (4-6) so that the weight and the gravity center of the simulator (4) are completely the same as the weight and the gravity center of a next-stage suspension object, and the connecting positioning block is installed on the upper surface of the main body (4-6) and connected with the aircraft suspension device (2).
8. An auxiliary device for vibration testing of an aircraft suspension unit, as defined in claim 7, wherein: the main body (4-6) or the counterweight block (4-1) is provided with an eyebolt (4-4).
9. An auxiliary device for vibration testing of an aircraft suspension unit, as defined in claim 7, wherein: a lower positioning bolt (4-10) is arranged on the connecting positioning block to enable the simulation object (4) to be connected with the airplane suspension device (2), a round hole is formed in the end portion of the lower positioning bolt (4-10), after the simulation object (4) is connected, the cotter pin II (4-11) is inserted into the round hole in the lower positioning bolt (4-10), and the simulation object (4) is prevented from falling off from the lower positioning bolt (4-10) during a vibration test after being installed.
10. An auxiliary device for vibration testing of an aircraft suspension unit, as claimed in claim 3, wherein: the base (1-7), the connecting column (1-1) and the reinforcing ribs (1-2) are fixed by welding, and the upper connecting plate (1-6), the lower connecting plate (1-5), the reinforcing plate (1-4) and the vertical plate (1-3) are fixed by welding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021024161.1U CN213083527U (en) | 2020-06-05 | 2020-06-05 | Auxiliary device for vibration test of aircraft suspension device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021024161.1U CN213083527U (en) | 2020-06-05 | 2020-06-05 | Auxiliary device for vibration test of aircraft suspension device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213083527U true CN213083527U (en) | 2021-04-30 |
Family
ID=75619161
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021024161.1U Active CN213083527U (en) | 2020-06-05 | 2020-06-05 | Auxiliary device for vibration test of aircraft suspension device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213083527U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113335561A (en) * | 2021-06-04 | 2021-09-03 | 中国飞机强度研究所 | Undercarriage test supporting clamp |
| CN115649476A (en) * | 2022-09-30 | 2023-01-31 | 成都飞机工业（集团）有限责任公司 | Pin type finished product bottom plate installation method based on vibration environment |
| CN115649476B (en) * | 2022-09-30 | 2024-05-14 | 成都飞机工业（集团）有限责任公司 | Bolt finished product bottom plate mounting method based on vibration environment |
-
2020
- 2020-06-05 CN CN202021024161.1U patent/CN213083527U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113335561A (en) * | 2021-06-04 | 2021-09-03 | 中国飞机强度研究所 | Undercarriage test supporting clamp |
| CN113335561B (en) * | 2021-06-04 | 2024-04-09 | 中国飞机强度研究所 | Landing gear test support clamp |
| CN115649476A (en) * | 2022-09-30 | 2023-01-31 | 成都飞机工业（集团）有限责任公司 | Pin type finished product bottom plate installation method based on vibration environment |
| CN115649476B (en) * | 2022-09-30 | 2024-05-14 | 成都飞机工业（集团）有限责任公司 | Bolt finished product bottom plate mounting method based on vibration environment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN213083527U (en) | Auxiliary device for vibration test of aircraft suspension device | |
| CN209023161U (en) | A kind of aircraft slow test nose-gear loaded member | |
| CN113740181A (en) | Wing oil tank wall plate impact test system and test method thereof | |
| CN109752239A (en) | A kind of reaction frame for blower embedded foundation load carrying capacity test | |
| CN108639947B (en) | Hanging type electric hoist test bed lifting device | |
| CN102680333B (en) | Lamp testing device, lamp testing framework and lamp testing method | |
| CN110631791A (en) | Testing device for battery device | |
| CN216386636U (en) | Wing oil tank wallboard impact test system | |
| CN214066453U (en) | Vibration test tool for guiding electromagnet of high-speed maglev train | |
| CN206208480U (en) | Vibration impact experiment fixture | |
| CN112082865B (en) | Novel device for buckling test of inclined strut | |
| CN214472281U (en) | Auxiliary device for draught fan embedded part drawing test detection | |
| WO2023123732A1 (en) | Loading device and method for multi-point hoisting static testing of spacecraft cabin body | |
| CN211899779U (en) | A lifeline support for construction | |
| CN209394622U (en) | One kind repairing experiment supporting device for WWER nuclear power unit spring loaded safety valve | |
| CN111487027A (en) | Airborne external longitudinal vibration test platform | |
| CN202507014U (en) | Handling frame for welder qualification test | |
| CN206140333U (en) | A frock clamp that is used for seven people's seat vibration test in subway | |
| CN109356612A (en) | The assembling method of stand-type prototype structure test shield duct piece | |
| CN210616260U (en) | Fatigue test fixture for typical angle-shaped connecting piece of bulkhead | |
| CN213319698U (en) | Automatic locking clamp for assembling and detecting hook latch | |
| RU216683U1 (en) | Rolling Frame Test Rig for Helicopter Crash Resistant Fuel System | |
| CN214407958U (en) | Battery pack fixing tool for impact test and battery pack impact testing device | |
| CN210955586U (en) | Simulation teaching device for elevator door system installation and adjustment and linkage | |
| CN217897930U (en) | Counter weight frock base |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |