CN216734749U - Undercarriage structure - Google Patents
Undercarriage structure Download PDFInfo
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- CN216734749U CN216734749U CN202123232339.9U CN202123232339U CN216734749U CN 216734749 U CN216734749 U CN 216734749U CN 202123232339 U CN202123232339 U CN 202123232339U CN 216734749 U CN216734749 U CN 216734749U
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Abstract
The utility model discloses an undercarriage structure belongs to aircraft landing damper technical field, include: a cushion strut and a support assembly; the top fixedly connected with crossbeam auricle of buffering pillar, the rotatory lug of fixing of middle part fixedly connected with of buffering pillar, the lower extreme of buffering pillar rotates and is connected with the wheel tire, and a plurality of support ears of fixedly connected with on the side arm of rotatory lug of fixing, supporting component include: the aircraft comprises a front support rod assembly, a cross beam support rod assembly and a side support rod assembly, wherein one end of the front support rod assembly is rotatably connected with a support lug, the other end of the front support rod assembly is connected with a pod bottom pin of an aircraft, and one end of the cross beam support rod assembly is fixedly connected with a cross beam lug. The scheme can transmit course, vertical and transverse loads and bending and torsion loads from the ground through the unit buffer support columns, and convert the loads into shaft pins at two ends of the cross beam to be sheared, so that the degree of jolt of the airplane is smaller, and the airplane can run, rise and fall more stably.
Description
Technical Field
The utility model relates to an aircraft damping mechanism technical field that rises and falls, concretely relates to undercarriage structure.
Background
In the whole test period from the product design development stage to the identification stage of the undercarriage, in order to prevent structural elements of an airplane from being overloaded during landing impact, the undercarriage must effectively absorb energy generated by the landing impact, and the drop test is to verify whether the overload of the undercarriage, the strut and the tire use stroke meet the design requirements and whether the structure reaches the expected strength and rigidity while the undercarriage buffer system meets the absorption design work amount, so that the drop test of the undercarriage is particularly important for the whole development period process of the undercarriage.
When the aircraft lands, the existing landing gear has effective damping effect in the use process due to the fact that the self weight has larger impact force when landing, and the landing gear is easy to damage.
In view of this, a landing gear that facilitates shock absorption is devised.
SUMMERY OF THE UTILITY MODEL
To the above problem, the utility model provides an undercarriage structure.
The utility model discloses a technical scheme do: a landing gear structure comprising: a cushion strut and a support assembly;
the top end of the buffer strut is fixedly connected with a cross beam lug,
the middle part of the buffer strut is fixedly connected with a rotary fixing lug,
the lower end of the buffer strut is rotationally connected with an airplane wheel tire,
a plurality of supporting lugs are fixedly connected on the side arm of the rotary fixing lug,
the support assembly includes: a front stay bar component, a beam stay bar component and a side stay bar component,
one end of the front support rod component is rotatably connected with the support lug, the other end of the front support rod component is connected with a pod bottom pin of the airplane,
one end of the beam brace rod component is fixedly connected with the beam lug, the other end of the beam brace rod component is rotatably connected with one end of the side brace rod component,
the other end of the side stay bar component is rotatably connected with the supporting lug on the same side.
Further, the buffer strut includes: the device comprises a buffer, an upper anti-torsion arm, a lower anti-torsion arm, a rotary hoop and a wheel shaft;
the rotary hoop is rotationally connected to the outer arm of the buffer,
one end of the upper anti-torsion arm is rotationally connected with the outer arm of the rotary hoop,
the other end of the upper anti-twist arm is rotationally connected with one end of the lower anti-twist arm,
the other end of the lower torsion-proof arm is rotationally connected with the outer arm of the buffer,
the wheel shaft is rotationally connected to the tire of the airplane wheel and is fixedly connected with the lower end of the buffer;
wherein the cross beam lug is fixedly connected to the top end of the buffer,
the rotary fixing lug is fixedly connected to the middle of the buffer, and the rotary hoop is located at the lower end of the rotary fixing lug.
Still further, the front brace assembly includes: y-shaped support rods and a cross beam arranged between the Y-shaped support rods,
two ends of the head part of the Y-shaped stay bar are respectively provided with a pin shaft which is rotationally connected with the aircraft pod,
the tail part of the Y-shaped support rod is provided with a cross universal joint which is rotationally connected with the support lug.
Still further, the cross beam brace assembly comprises: a first and second post beam in opposing positions;
the side stay assembly includes: the first strut side supporting rod and the second strut side supporting rod are opposite in position;
one end of the first column cross beam is fixedly connected with one end of the cross beam lug, the other end of the first column cross beam is rotatably connected with one end of the first column side supporting rod,
the other end of the first support rod is rotatably connected with the support lug on the same side;
one end of the second strut beam is fixedly connected with the other end of the beam lug, the other end of the second strut beam is rotatably connected with one end of the second strut side supporting rod,
the other end of the second support column side support rod is rotatably connected with the support lug on the same side.
Furthermore, the other ends of the first pillar beam and the second pillar beam are fixedly connected with connecting lugs,
the connecting lug is provided with a pin hole, correspondingly, the connecting ends of the first strut side brace and the second strut side brace connected with the connecting lug are provided with pin holes,
the first column side supporting rod is connected with the connecting lug on the first column cross beam through a pin,
the second strut-side stay bar is connected with a connecting lug on the second strut cross beam through a pin;
connecting ends of the first strut side stay bar column and the second strut side stay bar connected with the supporting lugs are respectively provided with a connecting groove,
the connecting grooves are provided with pin holes, the corresponding supporting lugs connected with the first strut side supporting rod and the second strut side supporting rod are provided with pin holes,
the first strut side supporting rod and the second strut side supporting rod are connected with the supporting lug through pins respectively.
Furthermore, the cross section of the connecting lug and the cross section of the connecting groove are both U-shaped.
Furthermore, a first U-shaped connecting piece is fixedly connected to a side arm of the rotary clamp,
the bending end of the first U-shaped connecting piece is far away from the rotating hoop, and the bending end is provided with a first through hole,
a first pin shaft is rotatably connected in the first through hole, and the length of the first pin shaft is greater than that of the first through hole;
the upper end of the upper torsion-proof arm is provided with a first U-shaped notch, the width of the first U-shaped notch is larger than that of the first U-shaped connecting piece,
two sides of the first U-shaped notch are respectively provided with a first mounting hole,
two sides of the first U-shaped notch are respectively provided with a first threaded hole which is vertical to the arrangement direction of the first mounting hole,
the first threaded hole penetrates through the first mounting hole,
correspondingly, the first pin shaft is provided with a first connecting hole which is matched with the first threaded hole,
the first U-shaped notch is clamped at the outer side of the first U-shaped connecting piece, two ends of the first U-shaped notch are sleeved with two ends of the first pin shaft,
wherein the first U-shaped notch is fixedly connected with the first pin shaft through a bolt,
the first pin shaft is rotatably connected with the first through hole.
Furthermore, the connecting ends of the upper torsion-proof arm and the lower torsion-proof arm are provided with second through holes,
the upper anti-twist arm is provided with a second threaded hole which penetrates through the second through hole,
the arrangement direction of the second threaded hole is vertical to that of the second through hole;
the upper torsion-proof arm and the lower torsion-proof arm pass through the second through hole through a pin to realize connection, and the upper torsion-proof arm and the lower torsion-proof arm are connected through the second through hole and the second threaded hole through bolts to realize fixed connection of the upper torsion-proof arm and the pin,
wherein the upper torsion-proof arm is fixedly connected with the pin,
the lower torsion arm is rotatably connected with the pin.
Furthermore, a second U-shaped connecting piece is fixedly connected on the side arm of the buffer,
the bent end of the second U-shaped connecting piece is far away from the buffer, and the bent end is provided with a third through hole,
a second pin shaft is rotatably connected in the third through hole, and the length of the second pin shaft is greater than that of the third through hole;
the lower end of the lower torsion-proof arm is provided with a second U-shaped notch, the width of the second U-shaped notch is larger than that of the second U-shaped connecting piece,
two sides of the second U-shaped notch are provided with second mounting holes,
third threaded holes which are vertical to the arrangement direction of the second mounting holes are arranged on both sides of the second U-shaped notch,
the third threaded hole penetrates through the second mounting hole,
correspondingly, the second pin shaft is provided with a connecting hole which is matched with the third threaded hole,
the second U-shaped notch is clamped at the outer side of the second U-shaped connecting piece, and two ends of the second U-shaped notch are sleeved with two ends of the second pin shaft,
wherein the second U-shaped notch is fixedly connected with the second pin shaft through a bolt,
and the second pin shaft is rotatably connected with the third through hole.
The utility model has the advantages that:
1. the unit buffer support column is arranged, so that the course, vertical and transverse loads and bending and torsion loads from the ground can be transmitted through the support column, the loads are converted into shaft pins at two ends of the cross beam to be sheared, and the lug of the nacelle is pulled and bent to be transmitted, so that the airplane has smaller bumping degree, and the driving, landing and landing are more stable.
2. The pillar beam, the side stay bar component and the buffer pillar are connected by bolts in a combined structure, and a large-scale integral forging piece is not adopted, so that the material cost and the processing cost are greatly saved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification.
Fig. 1 is a schematic view of the overall structure of a landing gear according to an embodiment of the present invention;
fig. 2 is a partial structural schematic diagram of an embodiment of the present invention;
fig. 3 is a schematic structural view of a front stay bar according to an embodiment of the present invention.
Reference numerals:
1 is the buffering pillar, 101 is the crossbeam auricle, 102 is rotatory fixed auricle, 103 is last anti-torque arm, 104 is down anti-torque arm, 105 is rotatory clamp, 106 is the shaft, 2 is preceding vaulting pole subassembly, 201 is the Y type vaulting pole, 202 is the crossbeam, 3 is crossbeam vaulting pole subassembly, 301 is first pillar crossbeam, 302 is the second pillar crossbeam, 4 is the side vaulting pole subassembly, 401 is first pillar side vaulting pole, 402 is second pillar side vaulting pole.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention.
Referring to fig. 1 to 3, as shown in fig. 1 to 3, a landing gear structure includes: a cushion strut and a support assembly;
the top end of the buffer strut 1 is fixedly connected with a crossbeam lug 101,
the middle part of the buffer strut 1 is fixedly connected with a rotary fixing lug plate 102,
the lower end of the buffer strut 1 is rotatably connected with an airplane wheel tire,
a plurality of supporting lugs are fixedly connected to the side arms of the rotary fixing lug plate 102,
the support assembly includes: a front stay bar component 2, a beam stay bar component 3 and a side stay bar component 4,
one end of the front supporting rod component 2 is rotatably connected with the supporting lug, the other end of the front supporting rod component 2 is connected with a pod bottom pin of the airplane,
one end of the beam brace component 3 is fixedly connected with the beam lug 101, the other end of the beam brace component 3 is rotatably connected with one end of the side brace component 4,
the other end of the side stay bar component 4 is rotatably connected with the supporting lug on the same side.
It should be noted that the landing gear mainly bears the landing load of the airship, absorbs the landing work load, reduces the landing overload, and simultaneously reduces the jolt of the airship in the ground sliding process, thereby realizing the functions of ground traction, turning and moving. The undercarriage is arranged on the lower portion of the airship nacelle, the beam of the beam support rod assembly is connected with the width of 532mm, the distance between the front intersection point and the rear intersection point is 797mm, the undercarriage is connected with the nacelle through a pin shaft, and the pin shaft is fixed with the undercarriage beam through a bolt.
In an embodiment of the present invention, the buffer support 1 includes: the damper, the upper torsion-proof arm 103, the lower torsion-proof arm 104, the rotary hoop 105 and the wheel shaft 106;
the swivel yoke 105 is pivotally attached to the outer arm of the damper,
one end of the upper anti-twist arm 103 is rotatably connected to an outer arm of the swivel yoke 105,
the other end of the upper anti-twist arm 103 is rotatably connected with one end of the lower anti-twist arm 104,
the other end of the lower anti-twist arm 104 is rotatably connected to the outer arm of the damper,
the wheel shaft 106 is rotatably connected to the wheel tires, and the wheel shaft 106 is fixedly connected with the lower end of the buffer;
wherein the crossbeam lug plate 101 is fixedly connected at the top end of the buffer,
the rotary fixing lug 102 is fixedly connected to the middle of the buffer, and the rotary clamp 105 is located at the lower end of the rotary fixing lug 102.
It should be noted that the buffer strut is the main force-transmitting and functional component of the landing gear, and the heading, vertical and lateral loads from the ground, and bending and torsional loads are transmitted through the strut, and these loads are converted into the transmission of the shear of the shaft pin at the two ends of the crossbeam, and the tension and bending of the pod lug.
The buffer is an important functional part of the landing gear, and mainly comprises an outer barrel, a piston rod, an inner diffusion pipe, an inner support, a forward-stroke oil hole assembly, a reverse-stroke oil hole assembly, a sealing assembly and other structural assemblies. The buffer is filled with pure nitrogen and No. 15 aviation hydraulic oil. The oil level was about 55mm above the forward and reverse stroke damping oil pan.
The lower part of the piston rod and the wheel shaft assembly are connected with the tire of the airplane wheel, the airplane wheels are arranged in parallel with two wheels, the wheel distance of the airplane wheel is 320mm, the wheel shaft and the piston rod are fixed by bolts at the middle positions, and the grounding conductive brush is arranged at the middle positions and is used as a static electricity releasing device when the airship lands. Because the wheel is selected, the mounting interface cannot be changed, and because the load is larger, the material of the wheel shaft is selected to be 30CrMnSiNi2A so as to ensure the strength requirement.
The conductive brush is loose connection that can move about from top to bottom, can arrive the longest position under the action of gravity, if not long enough can adjust the elasticity screw in order to adjust length to satisfy the length adjustment after daily use wearing and tearing.
At the middle part position of undercarriage, rotatory clamp, go up prevent the knuckle arm, prevent the knuckle arm down and be the main part of follow-up turn function, rotatory clamp cover is continuous through the pivot in the lower part of the urceolus of buffer and last prevent the knuckle arm, and the pivot passes through the bolt fastening with rotatory clamp, prevents down that knuckle arm and piston rod lower part auricle pass through bolt assembly and link to each other, goes up to prevent the knuckle arm, prevents down that the knuckle arm passes through the bolt and links to each other.
A section of polish rod extends out of the connecting bolt between the upper anti-torsion arm and the lower anti-torsion arm to two sides to serve as a ground auxiliary traction and turning joint.
In the processes of taking off, landing and sliding, the lower airplane wheel drives the upper torsion-proof arm, the lower torsion-proof arm and the rotary hoop to realize follow-up turning at any angle.
The airplane wheel is provided with a stable distance of 100mm, and has a certain orientation function when the airship slides along any course. However, the following steering mechanism has small net weight of the airship, the friction force of the tire ground is naturally small, and the centering moment provided by the ground is not large as the friction moment in the undercarriage, so that the following characteristic is not good when the airship turns at a small angle or a small radius, and extra assistance is needed.
In addition, when the ground is towed, the towing points in the middle of the upper anti-twist arm and the lower anti-twist arm can be used for adding steering auxiliary torque to the airplane wheel through the towing rods, so that the auxiliary turning function is realized.
The rotary hoop is provided with a bolt lug, corresponding lugs are arranged at the relative position of the outer barrel and the positions of the positive and negative rotation angles of 90 degrees respectively, and when the airship is moored on the ground, the rotary hoop can be fixed at the course position and the positions of the positive and negative rotation angles of 90 degrees respectively through the shaft pins, so that the fixed-point two-direction rotation function of the airship along the mooring point is realized.
The rotary hoop is fixed on the outer cylinder through a lower locking nut. Lubricating oil injection nozzles are arranged on each revolute pair of the upper torsion-proof arm and the lower torsion-proof arm of the rotary hoop, so that the rotation is flexible and is not blocked. The upper and lower anti-twisting arms can also perform folding movement along with the extension and retraction of the piston rod of the buffer, and the realization of the rotation movement is not hindered.
Upper and lower torsion arms in the follow-up turning mechanism, 7050 aluminum alloy material is selected for the rotary hoop, 30CrMnSiA material is selected for the lock nut, and an aluminum bronze bushing is adopted between the rotary hoop and the outer barrel to improve the lubricating and wear-resisting properties.
The outer cylinder and the piston rod of the landing gear are the most important parts, and the ground load is transmitted to four connecting intersection points through the outer cylinder, the piston rod and the lug plates of the piston rod. Meanwhile, the outer cylinder and the piston rod are also part of the buffer and bear the load of internal gas compression.
The outer cylinder and the piston rod are complex in shape, dozens of interfaces are arranged on the outer cylinder, and the outer cylinder is provided with a cross beam, a side support rod, a front support rod, a rotary clamp and interfaces of internal components.
The piston rod is provided with a lower torsion-proof arm, a wheel shaft, a grounding wire and a sealing device interface. The outer cylinder and the piston rod are large in size, large in load and heavy in weight, account for nearly one half of the weight of the landing gear, and in order to reduce the weight, the outer cylinder and the piston rod are made of 30CrMnSiNi2A materials.
The outer cylinder has a plurality of interfaces, the requirement on relative position tolerance is high, the smoothness of the inner cylinder arm reaches more than Ra0.2, the outer arm of the piston rod has high smoothness and high wear-resistant hardness, and therefore, the smoothness reaches more than Ra0.2 by adopting a hard chromium plating surface treatment process.
In an embodiment of the present invention, the front stay bar assembly 2 includes: a Y-shaped brace 201 and a cross beam 202 arranged between the Y-shaped braces,
two ends of the head part of the Y-shaped support rod 201 are respectively provided with a pin shaft which is rotationally connected with the aircraft pod,
the tail of the Y-shaped support rod 201 is provided with a cross universal joint which is rotatably connected with the support lug.
It should be noted that the front stay bar component of the landing gear is a main force transmission structure of the course load, and is connected with the lug at the lower part of the outer barrel of the buffer cavity through the cross bidirectional joint, so that the front stay bar mainly bears the tension and compression load from the course, and meanwhile, the cross bidirectional joint can greatly reduce the transmission of the lateral load to the front stay bar.
The front support rod assembly and the nacelle are connected in the same mode as the main intersection point of the undercarriage, a pin shaft is also connected, and the pin shaft is connected with the front support rod through bolts.
The front support rod assembly is made of an integral piece, a 7050 aluminum alloy plate is selected, and a 30CrMnSiA material is selected as the cross bidirectional joint.
The landing gear main intersection point and the intersection point of the front support rod assembly and the pod are in butt joint large-gap structural design, 2mm butt joint gaps are reserved on two sides, and the gaps are compensated and adjusted through gaskets with different thicknesses so as to ensure that the final total gaps on the two sides do not exceed 0.1 mm.
In an embodiment of the present invention, the beam brace rod assembly 3 includes: first and second oppositely located post beams 301 and 302;
the side stay bar assembly 4 includes: a first strut-side stay 401 and a second strut-side stay 402 which are opposed in position;
one end of the first pillar beam 301 is fixedly connected with one end of the beam lug 101, the other end of the first pillar beam 301 is rotatably connected with one end of the first pillar side stay 401,
the other end of the first strut side supporting rod 401 is rotatably connected with the supporting lug on the same side;
one end of the second pillar beam 302 is fixedly connected with the other end of the beam lug 101, the other end of the second pillar beam 302 is rotatably connected with one end of the second pillar brace 402,
the other end of the second strut-side brace 402 is rotatably connected to the support ear on the same side.
It should be noted that the cross-beam brace assembly mainly bears vertical load, and the load mainly born by the cross-beam brace assembly is mainly from the heading direction of the ground, vertical and transverse loads and bending and torsion loads, which are transmitted through the first and second post cross-beams, and the loads are converted into the shearing of the shaft pins at the two ends of the cross-beam, so that the vertical load is completed.
The first and second strut side struts mainly bear lateral loads, when the first and second strut cross beams are stressed, the outer cylinder of the damper moves downwards, the first and second strut cross beams transmit the loads to the first and second strut side struts, the first and second strut side struts transmit the lateral loads to the damper, and the damper absorbs the loads.
In one embodiment of the present invention, the other ends of the first and second pillar beams 301 and 302 are fixedly connected with connecting lugs,
the connecting lug is provided with a pin hole, correspondingly, the connecting ends of the first strut side supporting rod 401 and the second strut side supporting rod 402 connected with the connecting lug are provided with pin holes,
the first pillar brace 401 is connected to the connecting lug of the first pillar brace 301 by a pin,
the second pillar side stay 402 is connected to the lug of the second pillar cross member 302 by a pin;
the connecting ends of the first strut side supporting rod 401 and the second strut side supporting rod 402 connected with the supporting lugs are respectively provided with a connecting groove,
pin holes are respectively arranged on the connecting grooves, the corresponding supporting lugs connected with the first strut side supporting rod 401 and the second strut side supporting rod 402 are respectively provided with pin holes,
wherein the first strut-side supporting rod 401 and the second strut-side supporting rod 402 are respectively connected with the supporting ears by pins.
It should be noted that, when the first pillar cross beam and the second pillar cross beam are stressed, the outer cylinder of the buffer moves downward to drive the first pillar cross beam and the second pillar cross beam to move downward, when the distance between the bottom of the outer cylinder and the bottom of the piston rod is the smallest, the included angles between the first pillar side supporting rod and the first pillar cross beam, and between the second pillar side supporting rod and the second pillar cross beam become smaller, and at this time, the load borne by the first pillar side supporting rod and the second side supporting rod is the largest.
In an embodiment of the present invention, the cross section of the connecting lug and the cross section of the connecting groove are U-shaped.
In one embodiment of the present invention, a first U-shaped connecting member is fixedly connected to the side arm of the rotating clamp 105,
the bending end of the first U-shaped connecting piece is far away from the rotating hoop, and the bending end is provided with a first through hole,
a first pin shaft is rotatably connected in the first through hole, and the length of the first pin shaft is greater than that of the first through hole;
the upper end of the upper anti-twisting arm 103 is provided with a first U-shaped notch, the width of the first U-shaped notch is larger than that of the first U-shaped connecting piece,
two sides of the first U-shaped notch are respectively provided with a first mounting hole,
two sides of the first U-shaped notch are respectively provided with a first threaded hole which is vertical to the arrangement direction of the first mounting hole,
the first threaded hole penetrates through the first mounting hole,
correspondingly, the first pin shaft is provided with a first connecting hole which is matched with the first threaded hole,
the first U-shaped notch is clamped at the outer side of the first U-shaped connecting piece, and the two ends of the first U-shaped notch are sleeved with the two ends of the first pin shaft,
wherein the first U-shaped notch is fixedly connected with the first pin shaft through a bolt,
the first pin shaft is rotatably connected with the first through hole.
It should be noted that the first pin connects the upper anti-twist arm and the lower anti-twist arm, and the two ends of the first pin are connected and connected with a section of polished rod extending outwards to serve as a ground auxiliary traction and turning joint. In the processes of taking off, landing and sliding, the lower airplane wheel drives the lower anti-torsion arm and the rotary hoop to realize follow-up turning at any angle.
In one embodiment of the present invention, the connecting ends of the upper torsion-proof arm 103 and the lower torsion-proof arm 104 are provided with second through holes,
a second threaded hole penetrating through the second through hole is formed on the upper torsion-proof arm 103,
the arrangement direction of the second threaded hole is vertical to that of the second through hole;
the connecting end of the lower anti-twist arm 104 and the upper anti-twist arm 103 is provided with a through hole,
the upper torsion-proof arm 103 and the lower torsion-proof arm 104 pass through the second through hole through a pin to realize connection, and the upper torsion-proof arm 103 and the lower torsion-proof arm 104 are connected through the second through hole and the second threaded hole through bolts to realize fixed connection of the upper torsion-proof arm 103 and the pin,
wherein the upper anti-twist arm 103 is fixedly connected with the pin,
the lower anti-twist arm 104 is rotatably connected to the pin.
In one embodiment of the utility model, the side arm of the buffer is fixedly connected with a second U-shaped connecting piece,
the bent end of the second U-shaped connecting piece is far away from the buffer, and the bent end is provided with a third through hole,
a second pin shaft is rotatably connected in the third through hole, and the length of the second pin shaft is greater than that of the third through hole;
the lower end of the lower torsion-proof arm 104 is provided with a second U-shaped notch, the width of the second U-shaped notch is larger than that of the second U-shaped connecting piece,
two sides of the second U-shaped notch are provided with second mounting holes,
both sides of the second U-shaped notch are provided with third threaded holes which are perpendicular to the arrangement direction of the second mounting hole,
the third threaded hole penetrates through the second mounting hole,
correspondingly, the second pin shaft is provided with a connecting hole which is matched with the third threaded hole,
the second U-shaped notch is clamped at the outer side of the second U-shaped connecting piece, and two ends of the second U-shaped notch are sleeved with two ends of the second pin shaft,
wherein the second U-shaped notch is fixedly connected with the second pin shaft through a bolt,
and the second pin shaft is rotatably connected with the third through hole.
It should be noted that the main functions of the lower torsion-proof arm and the upper torsion-proof arm are that, firstly, the lower torsion-proof arm bears a lateral load, when the outer cylinder of the buffer cavity moves downwards, the first pillar cross beam and the second pillar cross beam transmit a force to the first pillar side stay bar and the second pillar side stay bar, and then the first pillar side stay bar and the second pillar side stay bar transmit a force to the buffer, wherein a part of the force is dispersed by the upper torsion-proof arm and the lower torsion-proof arm;
and the second step is used for controlling the steering of the tire wheels, when the rotary hoop rotates on the outer barrel of the buffer, the upper torsion-proof arm is driven to rotate, then the lower torsion-proof arm is driven to rotate, and the lower torsion-proof arm ear connected with the lower torsion-proof arm pin is fixedly arranged on the piston rod of the buffer, so that the tire wheels rotate when the lower torsion-proof arm rotates.
The utility model provides a landing gear structure, when using, when the aircraft lands, the nacelle transmits the effort to buffering the pillar, and in this process, the buffer takes place the motion, and the urceolus moves down, makes the distance between urceolus bottom and the bottom of piston rod change, in the process of buffer motion, falls into horizontal load, vertical load, side direction load with the load;
wherein the nacelle transmits a portion of the load to the first and second post cross members, and transmits a portion of the load to the first and second post side stays and the bumper after the first and second post cross members are stressed,
the first strut side brace and the second strut side brace are stressed and transfer part of load to the buffer and the upper anti-torsion arm and the lower anti-torsion arm along with the downward movement of the outer cylinder,
finally, it is achieved that the first and second column beams bear lateral loads, the first and second column side struts bear lateral loads, and the bumpers and the tires bear vertical loads.
The above description is only for the preferred embodiment of the present invention, and is not intended to limit the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included within the protection scope of the present invention.
Claims (9)
1. A landing gear structure, comprising: a cushion strut and a support assembly;
the top end of the buffer strut is fixedly connected with a cross beam lug,
the middle part of the buffer strut is fixedly connected with a rotary fixing lug,
the lower end of the buffer strut is rotationally connected with an airplane wheel tire,
a plurality of supporting lugs are fixedly connected on the side arm of the rotary fixing lug,
the support assembly includes: a front stay bar component, a beam stay bar component and a side stay bar component,
one end of the front support rod component is rotatably connected with the support lug, the other end of the front support rod component is connected with a pod bottom pin of the airplane,
one end of the beam brace rod component is fixedly connected with the beam lug, the other end of the beam brace rod component is rotatably connected with one end of the side brace rod component,
the other end of the side stay bar component is rotatably connected with the supporting lug on the same side.
2. The landing gear structure of claim 1, wherein the buffer strut includes: the device comprises a buffer, an upper anti-torsion arm, a lower anti-torsion arm, a rotary hoop and a wheel shaft;
the rotating hoop is rotatably connected to the outer arm of the buffer,
one end of the upper anti-torsion arm is rotationally connected with the outer arm of the rotary hoop,
the other end of the upper anti-twist arm is rotationally connected with one end of the lower anti-twist arm,
the other end of the lower torsion-proof arm is rotationally connected with the outer arm at the lower part of the buffer,
the wheel shaft is rotationally connected to the tire of the airplane wheel and is fixedly connected with the lower end of the buffer;
wherein the cross beam lug is fixedly connected to the top end of the buffer,
the rotary fixing lug is fixedly connected to the middle of the buffer, and the rotary hoop is located at the lower end of the rotary fixing lug.
3. A landing gear structure according to claim 1, wherein the nose strut assembly includes: y-shaped support rods and a cross beam arranged between the Y-shaped support rods,
two ends of the head part of the Y-shaped stay bar are respectively and rotationally connected with the airplane pod through pin shafts,
the tail part of the Y-shaped support rod is rotatably connected with the support lug through a cross universal joint.
4. A landing gear structure according to claim 1, wherein the cross brace assembly includes: a first and second post beam in opposing positions;
the side stay assembly includes: the first strut side supporting rod and the second strut side supporting rod are positioned on two sides of the buffer strut;
one end of the first column cross beam is fixedly connected with one end of the cross beam lug, the other end of the first column cross beam is rotatably connected with one end of the first column side supporting rod,
the other end of the first support rod is rotatably connected with the support lug on the same side;
one end of the second pillar beam is fixedly connected with the other end of the beam lug plate, the other end of the second pillar beam is rotatably connected with one end of the second pillar side stay bar,
the other end of the second support column side support rod is rotatably connected with the support lug on the same side.
5. The landing gear structure of claim 4, wherein the other ends of the first and second strut beams are each fixedly connected with a lug,
the connecting lug is provided with a pin hole, correspondingly, the connecting ends of the first strut side supporting rod and the second strut side supporting rod connected with the connecting lug are provided with pin holes,
the first column side supporting rod is connected with the connecting lug on the first column cross beam through a pin,
the second strut-side stay bar is connected with a connecting lug on the second strut cross beam through a pin;
connecting ends of the first strut side stay bar column and the second strut side stay bar connected with the supporting lugs are respectively provided with a connecting groove,
the connecting grooves are provided with pin holes, the corresponding supporting lugs connected with the first strut side supporting rod and the second strut side supporting rod are provided with pin holes,
the first strut side supporting rod and the second strut side supporting rod are connected with the supporting lug through pins respectively.
6. A landing gear structure according to claim 5, wherein the cross-section of the attachment lugs and the cross-section of the attachment slots are both U-shaped.
7. A landing gear arrangement according to claim 2, wherein a first U-shaped connector is fixedly connected to the side arm of the swivel clip,
the bending end of the first U-shaped connecting piece is far away from the rotating hoop, and the bending end is provided with a first through hole,
a first pin shaft is rotatably connected in the first through hole, and the length of the first pin shaft is greater than that of the first through hole;
the upper end of the upper torsion-proof arm is provided with a first U-shaped notch, the width of the first U-shaped notch is larger than that of the first U-shaped connecting piece,
two sides of the first U-shaped notch are respectively provided with a first mounting hole,
two sides of the first U-shaped notch are respectively provided with a first threaded hole which is vertical to the arrangement direction of the first mounting hole,
the first threaded hole penetrates through the first mounting hole,
correspondingly, the first pin shaft is provided with a first connecting hole which is matched with the first threaded hole,
the first U-shaped notch is clamped at the outer side of the first U-shaped connecting piece, two ends of the first U-shaped notch are sleeved with two ends of the first pin shaft,
wherein the first U-shaped notch is fixedly connected with the first pin shaft through a bolt,
the first pin shaft is rotatably connected with the first through hole.
8. A landing gear structure according to claim 2, wherein the connection ends of the upper and lower anti-twist arms are each provided with a second through-hole,
the upper anti-twist arm is provided with a second threaded hole which penetrates through the second through hole,
the arrangement direction of the second threaded hole is vertical to that of the second through hole;
the upper torsion-proof arm and the lower torsion-proof arm pass through the second through hole through a pin to realize connection, and the upper torsion-proof arm and the lower torsion-proof arm are connected through the second through hole and the second threaded hole through bolts to realize fixed connection of the upper torsion-proof arm and the pin,
wherein the upper torsion arm is fixedly connected with the pin,
the lower torsion arm is rotatably connected with the pin.
9. A landing gear structure according to claim 7, wherein a second U-shaped connector is fixedly connected to the side arm of the bumper,
the bent end of the second U-shaped connecting piece is far away from the buffer, and the bent end is provided with a third through hole,
a second pin shaft is rotatably connected in the third through hole, and the length of the second pin shaft is greater than that of the third through hole;
the lower end of the lower torsion-proof arm is provided with a second U-shaped notch, the width of the second U-shaped notch is larger than that of the second U-shaped connecting piece,
two sides of the second U-shaped notch are provided with second mounting holes,
third threaded holes which are vertical to the arrangement direction of the second mounting holes are arranged on both sides of the second U-shaped notch,
the third threaded hole penetrates through the second mounting hole,
correspondingly, the second pin shaft is provided with a connecting hole which is matched with the third threaded hole,
the second U-shaped notch is clamped at the outer side of the second U-shaped connecting piece, and two ends of the second U-shaped notch are sleeved with two ends of the second pin shaft,
wherein the second U-shaped notch is fixedly connected with the second pin shaft through a bolt,
and the second pin shaft is rotatably connected with the third through hole.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123232339.9U CN216734749U (en) | 2021-12-22 | 2021-12-22 | Undercarriage structure |
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| CN202123232339.9U CN216734749U (en) | 2021-12-22 | 2021-12-22 | Undercarriage structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114771810A (en) * | 2022-06-24 | 2022-07-22 | 西安羚控电子科技有限公司 | Undercarriage system and unmanned aerial vehicle on warship |
| CN115923397B (en) * | 2023-03-09 | 2023-05-30 | 江苏星光发电设备有限公司 | Built-in lifting frame of mobile power station |
-
2021
- 2021-12-22 CN CN202123232339.9U patent/CN216734749U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114771810A (en) * | 2022-06-24 | 2022-07-22 | 西安羚控电子科技有限公司 | Undercarriage system and unmanned aerial vehicle on warship |
| CN115923397B (en) * | 2023-03-09 | 2023-05-30 | 江苏星光发电设备有限公司 | Built-in lifting frame of mobile power station |
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