CN212966631U - Nose landing gear for aviation simulator - Google Patents
Nose landing gear for aviation simulator Download PDFInfo
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- CN212966631U CN212966631U CN202022075339.1U CN202022075339U CN212966631U CN 212966631 U CN212966631 U CN 212966631U CN 202022075339 U CN202022075339 U CN 202022075339U CN 212966631 U CN212966631 U CN 212966631U
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- torsion arm
- thick bamboo
- shock attenuation
- landing gear
- wheel
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Abstract
The utility model belongs to the aircraft structural design field relates to the undercarriage design of aviation simulator, especially a nose landing gear for aviation simulator, including mounting bracket, shock attenuation prop section of thick bamboo and wheel subassembly, the mounting bracket is installed in the upper end of shock attenuation prop section of thick bamboo, and the upper end of this shock attenuation prop section of thick bamboo is worn out from the mounting bracket is inside to the top, includes the wheel in the wheel subassembly, and it installs at the lower extreme of shock attenuation prop section of thick bamboo; the utility model discloses a damping strut section of thick bamboo, including shock attenuation strut section of thick bamboo, the tip position of wearing out in by the mounting bracket installs a connecting plate, and the upper end of this connecting plate is connected with the tailpiece of the piston rod portion hinge dress of a pneumatic cylinder, the outside cover of damping strut section of thick bamboo between mounting bracket and the wheel subassembly is equipped with an upper bracket torsion arm cover, and the support frame is installed to one side of this upper bracket torsion arm cover, the support frame is two segmentation structures, including the upper bracket and the under bracing frame of middle part hinge dress, under bracing frame and upper bracket torsion arm cover hinge dress, upper bracket and mounting bracket all with aircraft body fixed connection.
Description
Technical Field
The utility model belongs to airborne vehicle structural design field relates to the undercarriage design of aviation simulator, especially a nose landing gear for aviation simulator.
Background
The aviation simulator is a facility for simulating aircrafts as the name implies, and can be applied to different simulation purposes of flying, fire fighting, ground service and the like according to different functions.
The currently used non-flight simulator is generally applied to the demonstration training process of flight crew practice, fire-fighting operation, rescue operation and various ground service operations. At present, the simulators generally adopt truss or steel bar structures to build a demonstration space which is the same as that of a corresponding airplane type, but the simulators cannot move or simulate airplane actions when in use, and the application range is very limited.
For this purpose, a new flight simulator should be designed, which, in addition to being identical in shape and internal structure to the simulator type, should also be extended in function, for example, to simulate the operations of jacking, pulling, moving and the like of an aircraft. However, the above-mentioned operation needs to be performed by not only reconstructing the internal and external structures of the aviation simulator, but also designing the structure of the landing gear to simulate the lifting process of the landing gear and the traction operation related to the landing gear.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome prior art's is not enough, provides an undercarriage structure to aviation simulator is used, and this undercarriage can realize the lift operation to can be connected with removing auxiliary facilities such as car, be used for simulating the fire control of airborne vehicle, remove the aircraft nose landing gear for the aviation simulator of ground operation such as shifting.
A nose landing gear for an aviation simulator comprises an aircraft body, and is characterized in that: the airplane wheel assembly comprises an airplane wheel which is arranged at the lower end of the shock absorption column barrel; the utility model discloses an aircraft wheel damping support, including shock attenuation support section of thick bamboo, wheel subassembly, support frame, lower carriage and upper carriage torsion arm cover, the tip position that a shock attenuation support section of thick bamboo was worn out in by the mounting bracket installs a connecting plate, and the upper end of this connecting plate is connected with the tailpiece of the piston rod portion hinge dress of a pneumatic cylinder, shock attenuation support section of thick bamboo outside cover between mounting bracket and the wheel subassembly is equipped with an upper bracket torsion arm cover, and the support frame is installed to one side of this upper bracket torsion arm cover, the support frame is two segmentation structures, including the upper bracket and the under bracing frame of middle part hinge dress, under pneumatic cylinder lift and return stroke effect, the tip of the piston rod drives shock attenuation support section of thick bamboo pendulum and changes the.
Furthermore, the connecting plates and the middle part of the upper end face of the mounting frame are integrally fixed, a group of side connecting plates are respectively integrally manufactured at two ends of the mounting frame positioned beside the connecting plates, and the mounting plate and the aircraft body are hinged through the two side connecting plates.
Furthermore, the airplane wheel assembly comprises an axle, welding plates, airplane wheels and a connecting rod, the airplane wheels are rotatably mounted at two axial ends of the axle respectively, the welding plates are integrally welded on two radial sides of the axle between the two airplane wheels respectively, a through hole is formed in the middle of one welding plate, the lower end part of the connecting rod penetrates through the through hole, the upper end part of the connecting rod penetrates through the lower end part of the shock absorption support column barrel, and the connecting plate can coaxially rotate with the shock absorption support column barrel.
Furthermore, a torsion arm assembly is sleeved outside the shock absorption support column barrel above the airplane wheel assembly, the torsion arm assembly comprises a torsion arm sleeve, an upper torsion arm and a lower torsion arm, the torsion arm sleeve is sleeved outside the shock absorption support column barrel, the upper torsion arm is hinged with the torsion arm sleeve through a connecting pin, the lower torsion arm is hinged with a welding plate through a connecting pin, and the upper torsion arm is hinged with the lower torsion arm.
Furthermore, the damping strut cylinder is sleeved with a limiting baffle pipe outside the lower part of the torsion arm sleeve.
Furthermore, a traction assembly is arranged in the end face of the welding plate on the same side as the support frame.
Furthermore, the traction assembly comprises traction heads and traction pins, the traction heads are positioned on two sides of the welding plate and are integrally manufactured with the welding plate, and the traction pins penetrate between the two traction heads.
The utility model has the advantages that:
the utility model discloses in, designed an undercarriage for aviation simulator, it includes the mounting bracket, and shock attenuation column casing and turbine subassembly isotructure can realize the decline of undercarriage through the cooperation of above-mentioned structure, basic action such as lifting to can be connected fixedly with outside moving the device.
The utility model discloses in to the mounting bracket is as basic carrier, and the cooperation of its inside installation's shock attenuation column section of thick bamboo and turbine subassembly is used for installing the wheel, and the process of simulation wheel contact vibrations after touching to earth. A connecting plate integrally manufactured in the mounting frame is matched with a hydraulic cylinder to output and transmit power, and the position change output by a piston rod of the hydraulic cylinder is linked through a hinged mechanism of the upper supporting frame and the lower supporting frame, so that the wheels are lowered and lifted.
The utility model discloses in, the connecting plate and the cooperation of upper bracket of mounting bracket both sides form the fixed connection structure of a multiple spot, and it not only can be applicable to the airborne vehicle body to its function research and development, also can extend to use in other aviation simulators that use on the market at present, as long as can install the corresponding action that also can realize the undercarriage through above structure.
The utility model discloses in, the undercarriage structure of aircraft is not only simulated in wheel subassembly and the cooperation of torsion arm subassembly, still can realize the action that turns to of undercarriage, and wheel subassembly and traction assembly cooperation then are used for the simulation to be connected fixedly to the undercarriage structure to finally realize the operation of pulling to the aviation simulator.
Drawings
Fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a left side view of FIG. 1;
fig. 3 is a right side view of fig. 1.
1. Connecting plate 2, mounting frame 3, piston rod 4, hydraulic cylinder seat 5, hydraulic cylinder 6, torque arm sleeve 7, upper torque arm 8, lower torque arm 9, wheel 10, limit stop tube 11, damping support cylinder 12, upper support frame torque arm sleeve 13, lower support frame 14, upper support frame 15, side connecting plate 16, traction pin 17, welding plate 18, connecting rod 19 and connecting pin
Detailed Description
The present invention is described in detail below with reference to examples, which are illustrative and not restrictive, and the scope of the invention is not limited thereto.
The utility model provides a nose landing gear for aviation simulator, includes the aircraft body, the innovation of the utility model lies in, including mounting bracket 2, shock attenuation prop section of thick bamboo 11 and wheel subassembly, the mounting bracket is installed in the upper end of shock attenuation prop section of thick bamboo, and the upper end of this shock attenuation prop section of thick bamboo is worn out from the mounting bracket is inside to the top, includes wheel 9 in the wheel subassembly, and it installs in the lower extreme of shock attenuation prop section of thick bamboo; a connecting plate 1 is installed to the tip position that a shock attenuation pillar section of thick bamboo was worn out in by the mounting bracket, and the upper end of this connecting plate is connected with the 3 tip hinges of piston rod of a pneumatic cylinder 5, shock attenuation pillar section of thick bamboo outside cover between mounting bracket and the wheel subassembly is equipped with an upper bracket torsion arm cover 12, and the support frame is installed to one side of this upper bracket torsion arm cover, the support frame is two segmentation structures, including upper bracket 14 and bottom suspension fagging 13 of middle part hinge dress, bottom suspension fagging and upper bracket torsion arm cover hinge dress, upper bracket and mounting bracket all with aircraft body fixed connection, under pneumatic cylinder lift and return stroke effect, the tip of piston rod drives the swing of shock attenuation pillar section of thick bamboo and realizes the decline and the rising of wheel.
In this embodiment, the hydraulic cylinder is fixed in the aircraft body by means of a cylinder block 4.
In this embodiment, the connecting plates are integrally fixed to the middle of the upper end surface of the mounting frame, a set of side connecting plates 15 are integrally formed at two ends of the mounting frame, and the mounting plate is hinged to the aircraft body through the side connecting plates.
In this embodiment, the wheel assembly includes a wheel shaft, welding plates 17, wheels, and a connecting rod 18, the wheels are rotatably mounted at two axial ends of the wheel shaft, the welding plates are integrally welded to two radial sides of the wheel shaft between the two wheels, a through hole is formed in the middle of one of the welding plates, the lower end of the connecting rod penetrates through the through hole, the upper end of the connecting rod penetrates through the lower end of the shock-absorbing strut cylinder, and the connecting plate can rotate coaxially with the shock-absorbing strut cylinder.
In this embodiment, a torsion arm assembly is sleeved outside the shock-absorbing strut cylinder above the wheel assembly, and the torsion arm assembly comprises a torsion arm sleeve 6, an upper torsion arm 7 and a lower torsion arm 8, wherein the torsion arm sleeve is sleeved outside the shock-absorbing strut cylinder, the upper torsion arm is hinged with the torsion arm sleeve through a connecting pin, the lower torsion arm is hinged with a welding plate through a connecting pin 18, and the upper torsion arm is hinged with the lower torsion arm.
In this embodiment, the damping strut cylinder is sleeved with a limiting baffle tube 10 outside the torsion arm sleeve.
In this embodiment, install in the terminal surface of welding plate and support frame homonymy and pull the subassembly.
In this embodiment, the pulling assembly comprises pulling heads and pulling pins 16, the pulling heads are integrally formed with the weld plate on both sides of the weld plate, and the pulling pins are inserted between the pulling heads.
The utility model discloses a use is:
when the aircraft landing simulator is used, the aircraft can move out of the way through the hydraulic cylinder when the aircraft landing state is simulated, and then the aircraft wheel descends; when the simulation is used for dragging the aircraft, the towing pin can be fixed through an external rigging, and then the undercarriage is connected with an external working vehicle, so that the whole simulated aircraft is moved.
In addition, the actions of the landing gear can be applied to the simulation process of the actions of a plurality of types of designed landing gear parts such as jacking an aviation simulator, connecting and moving a trailer, connecting a traction hanger, cushioning a sleeper and the like.
The utility model discloses in, designed an undercarriage for aviation simulator, it includes the mounting bracket, and shock attenuation column casing and turbine subassembly isotructure can realize the decline of undercarriage through the cooperation of above-mentioned structure, basic action such as lifting to can be connected fixedly with outside moving the device.
The utility model discloses in to the mounting bracket is as basic carrier, and the cooperation of its inside installation's shock attenuation column section of thick bamboo and turbine subassembly is used for installing the wheel, and the process of simulation wheel contact vibrations after touching to earth. A connecting plate integrally manufactured in the mounting frame is matched with a hydraulic cylinder to output and transmit power, and the position change output by a piston rod of the hydraulic cylinder is linked through a hinged mechanism of the upper supporting frame and the lower supporting frame, so that the wheels are lowered and lifted.
The utility model discloses in, the connecting plate and the cooperation of upper bracket of mounting bracket both sides form the fixed connection structure of a multiple spot, and it not only can be applicable to the airborne vehicle body to its function research and development, also can extend to use in other aviation simulators that use on the market at present, as long as can install the corresponding action that also can realize the undercarriage through above structure.
The utility model discloses in, the undercarriage structure of aircraft is not only simulated in wheel subassembly and the cooperation of torsion arm subassembly, still can realize the action that turns to of undercarriage, and wheel subassembly and traction assembly cooperation then are used for the simulation to be connected fixedly to the undercarriage structure to finally realize the operation of pulling to the aviation simulator.
Claims (7)
1. A nose landing gear for an aviation simulator comprises an aircraft body, and is characterized in that: the airplane wheel assembly comprises an airplane wheel which is arranged at the lower end of the shock absorption column barrel; the utility model discloses an aircraft wheel damping support, including shock attenuation support section of thick bamboo, wheel subassembly, support frame, lower carriage and upper carriage torsion arm cover, the tip position that a shock attenuation support section of thick bamboo was worn out in by the mounting bracket installs a connecting plate, and the upper end of this connecting plate is connected with the tailpiece of the piston rod portion hinge dress of a pneumatic cylinder, shock attenuation support section of thick bamboo outside cover between mounting bracket and the wheel subassembly is equipped with an upper bracket torsion arm cover, and the support frame is installed to one side of this upper bracket torsion arm cover, the support frame is two segmentation structures, including the upper bracket and the under bracing frame of middle part hinge dress, under pneumatic cylinder lift and return stroke effect, the tip of the piston rod drives shock attenuation support section of thick bamboo pendulum and changes the.
2. A nose landing gear for an aircraft simulator according to claim 1, wherein: the connecting plates are integrally fixed with the middle of the upper end face of the mounting frame, a group of side connecting plates are integrally manufactured at two ends of the mounting frame located beside the side, and the mounting plate and the aircraft body are hinged through the two side connecting plates.
3. A nose landing gear for an aircraft simulator according to claim 1, wherein: the airplane wheel assembly comprises an axle, welding plates, airplane wheels and a connecting rod, the airplane wheels are rotatably mounted at two axial ends of the axle respectively, the welding plates are integrally welded on two radial sides of the axle between the two airplane wheels respectively, a through hole is formed in the middle of one welding plate, the lower end of the connecting rod penetrates through the through hole, the upper end of the connecting rod penetrates through the lower end of a shock absorption support column barrel, and the connecting plate can rotate coaxially with the shock absorption support column barrel.
4. A nose landing gear for an aircraft simulator according to claim 3, wherein: the wheel assembly is characterized in that a torsion arm assembly is sleeved outside the shock absorption support column barrel above the wheel assembly, the torsion arm assembly comprises a torsion arm sleeve, an upper torsion arm and a lower torsion arm, the torsion arm sleeve is sleeved outside the shock absorption support column barrel, the upper torsion arm is hinged with the torsion arm sleeve through a connecting pin, the lower torsion arm is hinged with a welding plate through a connecting pin, and the upper torsion arm is hinged with the lower torsion arm.
5. A nose landing gear for an aircraft simulator according to claim 4, wherein: and a limiting baffle pipe is sleeved outside the damping strut cylinder below the torsion arm sleeve.
6. A nose landing gear for an aircraft simulator according to claim 3, wherein: and a traction assembly is arranged in the end face of the welding plate at the same side as the support frame.
7. A nose landing gear for an aircraft simulator according to claim 6, wherein: the traction assembly comprises traction heads and traction pins, the traction heads are positioned on two sides of the welding plate and are integrally manufactured with the welding plate, and the traction pins penetrate between the two traction heads.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022075339.1U CN212966631U (en) | 2020-09-21 | 2020-09-21 | Nose landing gear for aviation simulator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022075339.1U CN212966631U (en) | 2020-09-21 | 2020-09-21 | Nose landing gear for aviation simulator |
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| Publication Number | Publication Date |
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| CN212966631U true CN212966631U (en) | 2021-04-13 |
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| CN202022075339.1U Active CN212966631U (en) | 2020-09-21 | 2020-09-21 | Nose landing gear for aviation simulator |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112061416A (en) * | 2020-09-21 | 2020-12-11 | 航大联合航空设备有限公司 | Aviation is system of marcing with pulling |
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2020
- 2020-09-21 CN CN202022075339.1U patent/CN212966631U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112061416A (en) * | 2020-09-21 | 2020-12-11 | 航大联合航空设备有限公司 | Aviation is system of marcing with pulling |
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