CN112061416A - Aviation is system of marcing with pulling - Google Patents
Aviation is system of marcing with pulling Download PDFInfo
- Publication number
- CN112061416A CN112061416A CN202010996452.5A CN202010996452A CN112061416A CN 112061416 A CN112061416 A CN 112061416A CN 202010996452 A CN202010996452 A CN 202010996452A CN 112061416 A CN112061416 A CN 112061416A
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- Prior art keywords
- trailer
- bucket
- landing gear
- plate
- hydraulic cylinder
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- 230000007246 mechanism Effects 0.000 claims description 21
- 238000003466 welding Methods 0.000 claims description 20
- 238000013016 damping Methods 0.000 claims description 19
- 238000010521 absorption reaction Methods 0.000 claims description 12
- 230000035939 shock Effects 0.000 claims description 12
- 235000017166 Bambusa arundinacea Nutrition 0.000 claims description 10
- 235000017491 Bambusa tulda Nutrition 0.000 claims description 10
- 241001330002 Bambuseae Species 0.000 claims description 10
- 235000015334 Phyllostachys viridis Nutrition 0.000 claims description 10
- 239000011425 bamboo Substances 0.000 claims description 10
- 230000011218 segmentation Effects 0.000 claims description 3
- 239000000725 suspension Substances 0.000 claims description 3
- 238000004088 simulation Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 description 14
- 230000008569 process Effects 0.000 description 12
- 230000009471 action Effects 0.000 description 8
- 238000005553 drilling Methods 0.000 description 7
- 230000000875 corresponding effect Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000003137 locomotive effect Effects 0.000 description 2
- 230000001960 triggered effect Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Images
Classifications
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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
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/22—Ground or aircraft-carrier-deck installations installed for handling aircraft
- B64F1/225—Towing trucks
- B64F1/227—Towing trucks adapted for directly connecting to aircraft, e.g. trucks without tow-bars
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/22—Operating mechanisms fluid
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
- G09B9/085—Special purpose teaching, e.g. alighting on water, aerial photography
Abstract
The invention belongs to the field of aircraft dragging devices, relates to an auxiliary tool for a trailer, and particularly relates to a dragging and traveling system for an aviation simulator. The towing and traveling system for the aviation simulator is reasonable in structure, is applied to the ground towing operation simulation of the aviation simulator, and has wide adaptability.
Description
Technical Field
The invention belongs to the field of aircraft dragging devices, relates to an auxiliary tool for a trailer, and particularly relates to a dragging and advancing system for an aviation simulator.
Background
The aviation simulator is a facility for simulating the aircraft as the name implies, is an important simulation drilling prop, and can be respectively applied to various posts related to the aircraft, such as simulated flight, fire drilling, rescue drilling, ground service drilling and the like according to different functions.
At present, a common truss or steel bar structure of a ground aviation simulator used in China builds a demonstration space which is the same as that of a corresponding machine type. However, such simulators are fixed and have a very limited application range, i.e., cannot simulate the lifting and lowering of the nose landing gear of an aircraft, and cannot simulate ground taxiing, passive towing and other actions of the aircraft.
Therefore, the simulation operation generally requires a real machine for drilling, but such a drilling mode has a high risk, and may cause damage to the aircraft itself during drilling, which is potentially too high cost.
In order to solve the above problems, some research institutions or manufacturers develop movable flight simulators, and for example, a movable simulated aircraft is disclosed in patent No. 2014104865443. The aircraft is different from the prior art, a simulation undercarriage and a traveling wheel are installed in a cabin body, and operations such as in-situ large-angle turning of the aircraft are simulated through the matching of the nose undercarriage and the traveling wheel. Compared with the prior art, the problem of movement of the aviation simulator is solved, but the structure of the aviation simulator is not enough. The document disclosed in the patent is a comprehensive aviation simulator, which can be applied to matching various special vehicles such as an object vehicle, a garbage truck, a conveyor belt vehicle, a platform vehicle and the like with the aviation simulator, and although the application fields are various, the pertinence is not strong. Although the problem of movement of an aviation simulator can be solved, the structure of a nose landing gear of the aircraft simulator is greatly different from that of a real aircraft, so that actions such as lifting and descending cannot be realized, and the process of matching with a traction vehicle cannot be simulated.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a towing and advancing system for an aviation simulator, which is reasonable in structure, is applied to ground towing operation simulation of the aviation simulator and has wide adaptability.
A trailing travel system for an aviation simulator, comprising an aircraft body, characterized in that: the aircraft is characterized by further comprising a front landing gear mechanism and a mobile trailer, wherein the front landing gear mechanism is installed at the bottom of the aircraft body and can be movably installed with the mobile trailer, the front landing gear mechanism comprises wheels, the mobile trailer can be hung with the wheels and can drive the front landing gear mechanism under the driving of the mobile trailer, and the aircraft body synchronously moves.
Furthermore, the front landing gear mechanism comprises a mounting frame, a damping support column tube and a wheel assembly, the mounting frame is mounted at the upper end of the damping support column tube, the upper end part of the damping support column tube penetrates upwards from the inside of the mounting frame, and the wheel assembly comprises a wheel which is mounted at the lower end of the damping support column tube; the utility model discloses an aircraft wheel suspension device, including undercarriage hydraulic cylinder, damping strut section of thick bamboo, mounting bracket, upper strut torsion arm cover, support frame, undercarriage hydraulic cylinder, a connecting plate is installed to the tip position that damping strut section of thick bamboo was worn out in by the mounting bracket, and the upper end of this connecting plate is connected with the piston rod tip hinge dress of the hydraulic cylinder that falls together, damping strut section of thick bamboo outside cover between mounting bracket and the wheel subassembly is equipped with an upper strut torsion arm cover, and the support frame is installed to one side of this upper strut torsion arm cover, the support frame is two segmentation structures, including the upper strut frame and the under bracing frame of middle part hinge dress, under undercarriage hydraulic cylinder lift and upper strut torsion arm cover hinge dress, upper strut frame and mounting bracket all with aircraft body fixed.
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 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.
Furthermore, a towing bucket is hinged at the rear end of the mobile trailer, an opening is formed in one side, back to the mobile trailer, of the towing bucket, a bottom plate of the towing bucket is flatly formed, swing components are mounted on two sides of the towing bucket and can drive the bottom plate of the towing bucket to swing, the bottom surface of the bottom plate on the opening side of the towing bucket is in contact with the ground in a low position state, a slope is formed on the upper end surface of the bottom plate, and an electric winch, a towing belt and a driving assembly are mounted in the towing bucket.
Furthermore, a side plate is respectively installed on the left side and the right side of the rear end of the mobile trailer, a connecting shaft is transversely installed between the two side plates, and the two ends of the trailer are sleeved and connected with the connecting shaft in a rotating mode.
Furthermore, an inner bucket is installed in the trailer bucket, a back plate is installed on one side of the inner bucket facing the opening of the trailer bucket, a limit switch is installed in the back plate and connected with a driving assembly of the electric winch, and after the limit switch is started, a motor in the driving assembly can be controlled to be turned off, and the electric winch is stopped to take up the wire.
Furthermore, the swing part comprises two hydraulic cylinders which are respectively arranged at two sides of the rear end of the mobile trailer, a cylinder seat of the hydraulic cylinder is hinged with the mobile trailer, and the end part of a piston rod of the hydraulic cylinder is hinged and fixed with the outer walls of two sides of the trailer bucket.
Furthermore, wear-resisting plates are mounted at the edge positions, close to the openings, in the bottom surface of the trailer bucket and are fixed with the trailer bucket in a movable mounting mode.
The invention has the advantages and positive effects that:
according to the invention, the nose landing gear structure is arranged at the bottom of the aircraft body and matched with the mobile trailer, so that the real process of connecting and towing the mobile trailer and the aircraft in the moving operation can be simulated. Compared with the prior art, the nose landing gear mechanism disclosed by the patent is more similar to the nose landing gear structure of practical application of an aircraft in principle or structure, and meanwhile, the lifting and descending processes of the nose landing gear can be simulated, so that the combination process of the mobile trailer and the nose landing gear structure is close to practical operation.
In the invention, a trailer bucket is arranged at the rear end of the mobile trailer, and an opening formed by the trailer bucket is used for guiding in a nose landing gear of an aircraft. Because the swinging components arranged on the two sides of the front landing gear adjust the low position and the high position of the opening of the trailer bucket, the bottom surface of the bottom plate of the front landing gear is contacted with the bottom surface under the low position state, so that the front landing gear can be guided in without clearance; under the high position state, the opening position swings upwards, the airplane wheel of the nose landing gear is lifted and limited, and falling off in the moving process is prevented. The electric winch and the components thereof are used for fixing the front landing gear for connection and fixation and traction.
In the invention, the connection between the mobile trailer and the trailer bucket is realized by adopting two side plates, and the swinging and the rotation of the trailer bucket can be realized by taking a connecting shaft arranged in the trailer as a shaft. The limit switch installed in the back plate is used for controlling the action of the electric winch, and when the locomotive contacts with the back plate, the limit switch is actively triggered, so that the electric winch is controlled to be closed, and the overload is prevented.
According to the invention, the hydraulic cylinder is used as the swing part to control the height of the opening side of the trailer bucket, the technology is mature, the operation is simple and convenient, and the bottom surface of the bottom plate of the trailer bucket is in contact with the ground, so that the wear-resisting plate is preferably arranged in the second bottom surface to prolong the service life of the trailer bucket.
The designed nose landing gear structure comprises a mounting frame, a damping column barrel, a turbine assembly and other structures, can realize basic actions of descending, lifting and the like of the landing gear through the structural cooperation, and can be connected and fixed with an external moving device.
In the invention, the mounting frame is used as a basic carrier, and the damping support cylinder and the turbine assembly which are mounted in the mounting frame are matched for mounting the wheel and simulating the contact vibration process of the wheel after the wheel contacts the ground. A connecting plate integrally manufactured in the mounting frame is matched with a hydraulic cylinder of the undercarriage 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.
In the invention, the connecting plates on the two sides of the mounting rack are matched with the upper supporting rack to form a multi-point fixed connecting structure, so that the mounting rack not only can be suitable for an aircraft body researched and developed according to functions of the mounting rack, but also can be expanded and applied to other aviation simulators used in the market at present, and corresponding actions of the undercarriage can be realized as long as the mounting is carried out through the structure.
In the invention, the wheel assembly and the torsion arm assembly are matched to simulate the landing gear structure of an aircraft and realize the steering action of the landing gear, and the wheel assembly and the traction assembly are matched to simulate the connection and fixation of the landing gear structure and finally realize the traction operation of the mobile trailer and the aviation simulator.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of the nose landing gear mechanism;
FIG. 3 is a left side view of FIG. 2;
fig. 4 is a right side view of fig. 2.
1. Moving trailer 2, connecting shaft 3, side plate 4, trailer hopper 5, inner hopper 6, bottom plate (bottom surface) 7, nose landing gear 8, electric winch 9, back plate 10, hydraulic cylinder 11, connecting plate 12, mounting frame 13, piston rod 14, hydraulic cylinder seat 15, landing gear hydraulic cylinder 16, torque arm sleeve 17, upper torque arm 18, lower torque arm 19, wheel 20, limit stop tube 21, shock-absorbing support cylinder 22, upper support torque arm sleeve 23, lower support frame 24, upper support frame 25, side connecting plate 26, traction pin 27, welding plate 28, connecting rod 29 and connecting pin 29
Detailed Description
The present invention is illustrated in detail below by means of examples, which are illustrative and not limitative, and the scope of protection of the present invention is not limited thereby.
The invention relates to a towing and traveling system for an aviation simulator, which comprises an aircraft body, and the towing and traveling system is characterized by further comprising a front landing gear mechanism and a movable trailer 1, wherein the front landing gear mechanism is arranged at the bottom of the aircraft body and can be movably arranged with the movable trailer, the front landing gear mechanism comprises wheels, and the movable trailer can be hung with the wheels and can drive the front landing gear mechanism to move synchronously under the driving of the movable trailer, namely the aircraft body.
The aircraft comprises an aircraft body, a mounting frame 12, a shock absorption column tube 21 and an airplane wheel assembly, wherein the mounting frame is mounted at the upper end of the shock absorption column tube, the upper end part of the shock absorption column tube penetrates upwards from the mounting frame, and the airplane wheel assembly internally comprises an airplane wheel 19 which is mounted at the lower end of the shock absorption column tube; the utility model discloses an aircraft wheel suspension device, including undercarriage hydraulic cylinder, damping strut section of thick bamboo, mounting bracket, upper strut support torque arm cover, undercarriage hydraulic cylinder, lower strut support and mounting bracket, a connecting plate 11 is installed to the tip position that damping strut section of thick bamboo was worn out in by the mounting bracket, and the upper end of this connecting plate is connected with the piston rod 13 tip hinge dress of the hydraulic cylinder 15 that falls together, an upper strut support torque arm cover 22 is equipped with to the damping strut section of thick bamboo outside cover between mounting bracket and the wheel subassembly, and the support frame is installed to one side of this upper strut support torque arm cover, the support frame is two segmentation structures, including the upper strut support 24 and the under strut support 23 of middle part hinge dress, under undercarriage hydraulic cylinder exit and return stroke effect, piston rod tip drives damping strut section of thick bamboo.
In this embodiment, the landing gear mechanism can be disassembled and assembled for different models, namely, the aircraft body, and the connection mode between different models and the mobile trailer can be simulated by replacing the landing gear mechanisms with different models and sizes.
In this embodiment, the landing gear hydraulic cylinder is fixed within the aircraft body by a hydraulic cylinder mount 14.
In this embodiment, the connecting plates are integrally fixed to the middle of the upper end surface of the mounting frame, and a set of side connecting plates 25 are integrally formed at both ends of the mounting frame, respectively, and the mounting plate is hinged to the aircraft body via the side connecting plates.
In this embodiment, the wheel assembly includes a wheel shaft, welding plates 27, wheels, and a connecting rod 28, the wheels are rotatably mounted at two axial ends of the wheel shaft, the welding plates are integrally welded at 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 on the outside of the shock-absorbing strut cylinder above the wheel assembly, and the torsion arm assembly comprises a torsion arm sleeve 16, an upper torsion arm 17 and a lower torsion arm 18, wherein the torsion arm sleeve is sleeved on the outside of 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 29, and the upper torsion arm and the lower torsion arm are hinged with each other.
In this embodiment, the damping strut cylinder is sleeved with a limiting stop tube 20 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 26, the pulling heads are integrally formed with the welding plate on both sides of the welding plate, and the pulling pins are inserted between the pulling heads.
In the embodiment, the mobile trailer comprises a mobile trailer 1, the innovation of the invention is that a trailer bucket 4 is hinged at the rear end of the mobile trailer, an opening is formed in one side of the trailer bucket, which is back to the mobile trailer, a bottom plate of the trailer bucket is flatly formed, swing parts are arranged on two sides of the trailer bucket, the bottom plate of the trailer bucket can be driven to swing, in a low state, the bottom surface 6 of the bottom plate on the opening side of the trailer bucket is in contact with the ground, the upper end surface of the bottom plate forms a slope, and an electric winch 8, a towing belt and a driving assembly are arranged in the trailer bucket.
In this embodiment, a curb plate 3 is installed respectively to the rear end left and right sides of mobile trailer, transversely installs a connecting axle 2 between this both sides board, the outside suit of rotating of connecting axle drags the both ends of hanging the fill.
In this embodiment, an inner bucket 5 is installed in the trailer bucket, a back plate 9 is installed on one side of the inner bucket facing the opening of the trailer bucket, a limit switch is installed in the back plate, the limit switch is connected with a driving assembly of the electric winch, and after the limit switch starts, a motor in the driving assembly can be controlled to be turned off, and the electric winch is stopped to take up the wire.
In this embodiment, the swing component includes two hydraulic cylinders 10, and these two hydraulic cylinders are installed respectively in the rear end both sides of trailer, the cylinder seat of hydraulic cylinder and trailer hinge dress, the piston rod tip of hydraulic cylinder and the both sides outer wall hinge dress of trailer fill are fixed.
In this embodiment, wear-resisting plates are installed at the edge positions close to the opening in the bottom surface of the trailer bucket, and the wear-resisting plates are fixed with the trailer bucket in a movable installation mode.
The using process of the invention is as follows:
when the airplane wheel landing gear is used, firstly, the hydraulic cylinder of the landing gear is controlled to lower the airplane wheel to a proper state, and the proper state can be a ground contact state and can also simulate different horizontal heights when the landing gear fails.
Then, as shown in fig. 1, the opening of the trailer bucket is adjusted by the hydraulic cylinder to be in a low position, and then the operator connects the hook at the towing terminal of the electric winch to the towing shaft of the nose landing gear 7. After the tires of the nose landing gear touch the limit switches arranged in the back plate, the nose landing gear is indicated to be dragged to a limited position, and the electric winch is turned off at the moment. A piston rod of the hydraulic cylinder extends out to push the towing bucket to be lifted to a high position by taking the connecting shaft as a rotating shaft, and at the moment, the bottom surface of the towing bucket is separated from the ground. And then guarantee to move the trailer and go the in-process, nose landing gear can not the landing, and the pneumatic cylinder has the pressurize effect at the in-process that advances.
According to the invention, the nose landing gear structure is arranged at the bottom of the aircraft body and matched with the mobile trailer, so that the real process of connecting and towing the mobile trailer and the aircraft in the moving operation can be simulated. Compared with the prior art, the nose landing gear mechanism disclosed by the patent is more similar to the nose landing gear structure of practical application of an aircraft in principle or structure, and meanwhile, the lifting and descending processes of the nose landing gear can be simulated, so that the combination process of the mobile trailer and the nose landing gear structure is close to practical operation.
In the invention, a trailer bucket is arranged at the rear end of the mobile trailer, and an opening formed by the trailer bucket is used for guiding in a nose landing gear of an aircraft. Because the swinging components arranged on the two sides of the front landing gear adjust the low position and the high position of the opening of the trailer bucket, the bottom surface of the bottom plate of the front landing gear is contacted with the bottom surface under the low position state, so that the front landing gear can be guided in without clearance; under the high position state, the opening position swings upwards, the airplane wheel of the nose landing gear is lifted and limited, and falling off in the moving process is prevented. The electric winch and the components thereof are used for fixing the front landing gear for connection and fixation and traction.
In the invention, the connection between the mobile trailer and the trailer bucket is realized by adopting two side plates, and the swinging and the rotation of the trailer bucket can be realized by taking a connecting shaft arranged in the trailer as a shaft. The limit switch installed in the back plate is used for controlling the action of the electric winch, and when the locomotive contacts with the back plate, the limit switch is actively triggered, so that the electric winch is controlled to be closed, and the overload is prevented.
According to the invention, the hydraulic cylinder is used as the swing part to control the height of the opening side of the trailer bucket, the technology is mature, the operation is simple and convenient, and the bottom surface of the bottom plate of the trailer bucket is in contact with the ground, so that the wear-resisting plate is preferably arranged in the second bottom surface to prolong the service life of the trailer bucket.
The designed nose landing gear structure comprises a mounting frame, a damping column barrel, a turbine assembly and other structures, can realize basic actions of descending, lifting and the like of the landing gear through the structural cooperation, and can be connected and fixed with an external moving device.
In the invention, the mounting frame is used as a basic carrier, and the damping support cylinder and the turbine assembly which are mounted in the mounting frame are matched for mounting the wheel and simulating the contact vibration process of the wheel after the wheel contacts the ground. 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.
In the invention, the connecting plates on the two sides of the mounting rack are matched with the upper supporting rack to form a multi-point fixed connecting structure, so that the mounting rack not only can be suitable for an aircraft body researched and developed according to functions of the mounting rack, but also can be expanded and applied to other aviation simulators used in the market at present, and corresponding actions of the undercarriage can be realized as long as the mounting is carried out through the structure.
In the invention, the wheel assembly and the torsion arm assembly are matched to simulate the landing gear structure of an aircraft and realize the steering action of the landing gear, and the wheel assembly and the traction assembly are matched to simulate the connection and fixation of the landing gear structure and finally realize the traction operation of the mobile trailer and the aviation simulator.
Claims (10)
1. A trailing travel system for an aviation simulator, comprising an aircraft body, characterized in that: the aircraft is characterized by further comprising a front landing gear mechanism and a mobile trailer, wherein the front landing gear mechanism is installed at the bottom of the aircraft body and can be movably installed with the mobile trailer, the front landing gear mechanism comprises wheels, the mobile trailer can be hung with the wheels and can drive the front landing gear mechanism under the driving of the mobile trailer, and the aircraft body synchronously moves.
2. The towed travel system for an aerial simulator of claim 1, wherein: the front landing gear mechanism comprises a mounting frame, a shock absorption support column tube and an airplane wheel assembly, the mounting frame is mounted at the upper end of the shock absorption support column tube, the upper end part of the shock absorption support column tube penetrates upwards from the inside of the mounting frame, and the airplane wheel assembly comprises an airplane wheel which is mounted at the lower end of the shock absorption support column tube; the utility model discloses an aircraft wheel suspension device, including undercarriage hydraulic cylinder, damping strut section of thick bamboo, mounting bracket, upper strut torsion arm cover, support frame, undercarriage hydraulic cylinder, a connecting plate is installed to the tip position that damping strut section of thick bamboo was worn out in by the mounting bracket, and the upper end of this connecting plate is connected with the piston rod tip hinge dress of the hydraulic cylinder that falls together, damping strut section of thick bamboo outside cover between mounting bracket and the wheel subassembly is equipped with an upper strut torsion arm cover, and the support frame is installed to one side of this upper strut torsion arm cover, the support frame is two segmentation structures, including the upper strut frame and the under bracing frame of middle part hinge dress, under undercarriage hydraulic cylinder lift and upper strut torsion arm cover hinge dress, upper strut frame and mounting bracket all with aircraft body fixed.
3. The towed travel system for an aerial simulator of claim 2, 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. The towed travel system for an aerial simulator of 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.
5. The towed travel system for an aerial simulator of claim 4, 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.
6. The towed travel system for an aerial simulator of claim 1, wherein: the rear end of the mobile trailer is hinged with a trailer bucket, one side of the trailer bucket, which faces away from the mobile trailer, is provided with an opening, a bottom plate of the trailer bucket is flatly arranged, swing parts are arranged on two sides of the trailer bucket and can drive the bottom plate of the trailer bucket to swing, the bottom surface of the bottom plate on the opening side of the trailer bucket is in contact with the ground in a low state, the upper end surface of the bottom plate forms a slope, and an electric winch, a towing belt and a driving assembly are arranged in the trailer bucket.
7. The towed travel system for an aerial simulator of claim 6, wherein: a side plate is respectively installed on the left side and the right side of the rear end of the mobile trailer, a connecting shaft is transversely installed between the two side plates, and the two ends of the trailer are sleeved in a rotating mode outside the connecting shaft.
8. The towed travel system for an aerial simulator of claim 6, wherein: the internal bucket of the trailer bucket is installed, a back plate is installed on one side of the internal bucket facing the opening of the trailer bucket, a limit switch is installed in the back plate, the limit switch is connected with a driving assembly of the electric winch, a motor in the driving assembly can be controlled to be turned off after the limit switch is turned off, and the electric winch is stopped to take up the wire.
9. The towed travel system for an aerial simulator of claim 6, wherein: the swing component comprises two hydraulic cylinders which are respectively arranged on two sides of the rear end of the mobile trailer, a cylinder seat of the hydraulic cylinder is hinged with the mobile trailer, and the end part of a piston rod of the hydraulic cylinder is hinged and fixed with the outer walls of two sides of the trailer bucket.
10. The towed travel system for an aerial simulator of claim 6, wherein: wear-resisting plates are mounted at the edge positions, close to the openings, in the bottom surface of the trailer bucket and are fixed with the trailer bucket in a movable mounting mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010996452.5A CN112061416A (en) | 2020-09-21 | 2020-09-21 | Aviation is system of marcing with pulling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010996452.5A CN112061416A (en) | 2020-09-21 | 2020-09-21 | Aviation is system of marcing with pulling |
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| CN112061416A true CN112061416A (en) | 2020-12-11 |
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| CN202010996452.5A Pending CN112061416A (en) | 2020-09-21 | 2020-09-21 | Aviation is system of marcing with pulling |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106738296A (en) * | 2017-03-31 | 2017-05-31 | 德州海天机电科技有限公司 | A kind of ground actuator for light wall board product line |
| CN114446112A (en) * | 2022-02-09 | 2022-05-06 | 安胜（天津）飞行模拟系统有限公司 | Undercarriage handle fault simulation method and locking device |
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| CN202038455U (en) * | 2011-04-29 | 2011-11-16 | 李磊 | Multifunctional shovel-wheel-type aircraft tractor |
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| CN106738296A (en) * | 2017-03-31 | 2017-05-31 | 德州海天机电科技有限公司 | A kind of ground actuator for light wall board product line |
| CN106738296B (en) * | 2017-03-31 | 2022-07-12 | 德州海天机电科技有限公司 | Ground dragging device for light wallboard production line |
| CN114446112A (en) * | 2022-02-09 | 2022-05-06 | 安胜（天津）飞行模拟系统有限公司 | Undercarriage handle fault simulation method and locking device |
| CN114446112B (en) * | 2022-02-09 | 2024-01-23 | 安胜（天津）飞行模拟系统有限公司 | Landing gear handle fault simulation method and locking device |
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