CN116729624A - Telescopic aircraft landing gear - Google Patents

Telescopic aircraft landing gear Download PDF

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Publication number
CN116729624A
CN116729624A CN202310828178.4A CN202310828178A CN116729624A CN 116729624 A CN116729624 A CN 116729624A CN 202310828178 A CN202310828178 A CN 202310828178A CN 116729624 A CN116729624 A CN 116729624A
Authority
CN
China
Prior art keywords
rocker arm
connecting rod
transmission
hinged
landing gear
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202310828178.4A
Other languages
Chinese (zh)
Inventor
印寅
陈博文
黄汉麟
李茂清
魏小辉
聂宏
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nanjing University of Aeronautics and Astronautics
Original Assignee
Nanjing University of Aeronautics and Astronautics
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Nanjing University of Aeronautics and Astronautics filed Critical Nanjing University of Aeronautics and Astronautics
Priority to CN202310828178.4A priority Critical patent/CN116729624A/en
Publication of CN116729624A publication Critical patent/CN116729624A/en
Pending legal-status Critical Current

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Classifications

    • 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
    • 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
    • B64C25/26—Control or locking systems therefor
    • 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 
    • B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface  wheeled type, e.g. multi-wheeled bogies
    • B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transmission Devices (AREA)

Abstract

The invention discloses a telescopic aircraft landing gear, which comprises a driving assembly, a buffer and a wheel assembly, wherein the wheel assembly comprises a connecting rocker arm and a telescopic rod, the connecting rocker arm is connected with a wheel, and the connecting rocker arm is connected with a torque arm to ensure the normal operation of a device; the telescopic link is articulated with connecting the rocking arm for drive assembly can utilize drive mechanism to drive the telescopic link motion, so that connect the rocking arm and can rotate for the buffer, thereby change the whole length of connecting the angle of rocking arm and buffer adjustment telescopic aircraft undercarriage, when the aircraft takes off and lands, the undercarriage is put down and the length increases, make the ground clearance of aircraft satisfy the flight requirement, when the undercarriage is packed up, when packing up the undercarriage through drive assembly, make the whole length of undercarriage shorten simultaneously, and drive mechanism sets up in the buffer, the telescopic link also stretches into in the buffer with the one end that drive mechanism links to each other, when the undercarriage is packed up, satisfy the collection space requirement of aircraft.

Description

Telescopic aircraft landing gear
Technical Field
The invention relates to the technical field of aircrafts and parts thereof, in particular to a telescopic aircraft landing gear.
Background
In order to meet the increasing demands of air transportation, high capacity and low fuel consumption are targets for current passenger aircraft development pursuit. In order to reduce the development costs, many aircraft manufacturers develop multiple derivative models based on their mature products, increasing the duct ratio and lengthening the fuselage size are common ways to increase the transport capacity and reduce the operating costs, but can present a series of problems for the flight safety of the aircraft. For example: the increase in engine size can result in insufficient ground clearance of the engine housing, and the fuselage lengthening can result in limited aircraft takeoff head-up angle of attack (wiping the ground at the tail of the fuselage). Such problems can be addressed by lengthening the landing gear lift aircraft ground clearance, but are limited by the structure and stowage space of the aircraft itself, and most aircraft cannot stow landing gear mechanisms of increased size. Thus being forced to raise the mounting height of the engine, but this changes the aerodynamic characteristics of the aircraft, which brings hidden danger to the flight safety of the aircraft.
Disclosure of Invention
The invention aims to provide a telescopic aircraft landing gear, which solves the problems in the prior art, enables the size of the aircraft landing gear to be increased, ensures that the aircraft takes off and lands smoothly, and simultaneously enables the aircraft landing gear to meet the requirement of a storage space.
In order to achieve the above object, the present invention provides the following solutions: the invention provides a retractable aircraft landing gear comprising:
a drive assembly;
the buffer comprises a main support outer cylinder and a main support piston rod, wherein the main support piston rod is connected with the main support outer cylinder through a sliding pair, and the main support outer cylinder is also in transmission connection with the driving assembly;
the machine wheel assembly comprises a connecting rocker arm and a telescopic rod, the connecting rocker arm can be connected with a machine wheel, one end of the telescopic rod extends out of a main support piston rod and is hinged to the connecting rocker arm, the other end of the telescopic rod is connected with a driving assembly in a transmission mode through a transmission mechanism, the transmission mechanism is arranged in a buffer, the connecting rocker arm is rotatably connected with the main support outer cylinder through a torque arm, and the driving assembly can drive the telescopic rod to move through the transmission mechanism so that the connecting rocker arm rotates relative to the buffer.
Preferably, the wheel assembly further comprises a transmission cylinder arranged in the main strut piston rod, the transmission cylinder comprises a transmission sleeve and a transmission piston, the transmission sleeve is connected with the transmission piston through a sliding pair, one end of the transmission piston is hinged with the telescopic rod, the other end of the transmission piston stretches into the transmission sleeve and is connected with the transmission mechanism, and a piston cavity of the transmission cylinder is communicated with a piston cavity of the buffer.
Preferably, the transmission mechanism comprises an upper connecting rod, a middle sleeve and a lower connecting rod which are sequentially connected, wherein the upper connecting rod and the lower connecting rod are both slidably connected with the middle sleeve, one end, far away from the middle sleeve, of the upper connecting rod is connected with the driving assembly, and one end, far away from the middle sleeve, of the lower connecting rod is connected with the transmission piston.
Preferably, the torque arm comprises an upper torque arm and a lower torque arm, one end of the upper torque arm is hinged with the main support outer cylinder, the other end of the upper torque arm is hinged with the lower torque arm, and one end of the lower torque arm, which is far away from the upper torque arm, is hinged with the connecting rocker arm.
Preferably, when the retractable aircraft landing gear is in the stowed condition, the wheel assembly is in the retracted condition, the connecting rocker arm is in abutment with the main strut piston rod.
Preferably, the driving assembly comprises an actuator and a first connecting rod, the length of the actuator can be adjusted, the movable end of the actuator is hinged with the main support outer cylinder, the fixed end of the actuator is hinged with the first connecting rod, and the first connecting rod is also hinged with the main support outer cylinder.
Preferably, the driving assembly further comprises a second connecting rod, a third connecting rod, a first rocker arm and a second rocker arm, one end of the second connecting rod is hinged to the first connecting rod, the other end of the second connecting rod is hinged to one end of the first rocker arm, the hinged surface of the second connecting rod and the first rocker arm is spherical, the other end of the first rocker arm is hinged to one end of the third connecting rod, the other end of the third connecting rod is hinged to one end of the second rocker arm, and the other end of the second rocker arm is connected with the transmission mechanism.
Preferably, the second rocker arm is connected with a cam, the cam is located in the main support outer cylinder, the transmission mechanism is rotationally connected with the cam, and the second rocker arm can drive the cam to rotate, so that the cam drives the telescopic rod to move by using the transmission mechanism.
Preferably, the cam has a guide slot, the transmission mechanism has a guide block matched with the guide slot, and the guide block is slidably arranged in the guide slot.
The invention also provides an aircraft, comprising the telescopic aircraft landing gear.
Compared with the prior art, the invention has the following technical effects: the telescopic aircraft landing gear comprises a driving assembly, a buffer and a wheel assembly, wherein the buffer comprises a main support outer cylinder and a main support piston rod, the main support piston rod is connected with the main support outer cylinder through a sliding pair, and the main support outer cylinder is also in transmission connection with the driving assembly; the machine wheel assembly comprises a connecting rocker arm and a telescopic rod, the connecting rocker arm can be connected with the machine wheel, one end of the telescopic rod extends out of a main strut piston rod and is hinged to the connecting rocker arm, the other end of the telescopic rod is connected with a driving assembly in a transmission mode through a transmission mechanism, the transmission mechanism is arranged in a buffer, the connecting rocker arm is rotatably connected with a main strut outer cylinder through a torque arm, and the driving assembly can drive the telescopic rod to move through the transmission mechanism so that the connecting rocker arm rotates relative to the buffer.
The invention also provides an aircraft, which comprises the telescopic aircraft landing gear, and the aircraft ground clearance is improved, so that the aircraft flight performance is ensured.
According to the telescopic aircraft landing gear, the main strut piston rod of the buffer can slide relative to the main strut outer cylinder so as to absorb vibration and impact load in the sliding and landing processes of an aircraft, and the driving assembly is in transmission connection with the buffer, so that the normal retraction and release of the device are ensured; in the wheel assembly, the connecting rocker arm is connected with the wheel, and the connecting rocker arm is connected with the torque arm, so that the normal operation of the device is ensured; meanwhile, the telescopic link is articulated with connecting the rocking arm for drive assembly can utilize drive mechanism to drive the telescopic link motion, so that connect the rocking arm and can rotate for the buffer, thereby change the whole length of connecting the angle of rocking arm and buffer adjustment scalable aircraft undercarriage, when the aircraft takes off and lands, the undercarriage is put down and the length increases, make the ground clearance of aircraft satisfy the flight requirement, when the undercarriage is packed up, when packing up the undercarriage through drive assembly, make the whole length of undercarriage shorten simultaneously, and drive mechanism sets up in the buffer, the telescopic link also stretches into in the buffer with the continuous one end of drive mechanism, when the undercarriage is packed up, satisfy the collection space requirement of aircraft.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is an isometric view of a retractable aircraft landing gear disclosed in an embodiment of the present invention;
FIG. 2 is a schematic front view of a retractable aircraft landing gear disclosed in an embodiment of the present invention;
FIG. 3 is a schematic side view of a retractable aircraft landing gear disclosed in an embodiment of the present invention;
FIG. 4 is a schematic top view of a retractable aircraft landing gear disclosed in an embodiment of the present invention;
FIG. 5 is an enlarged schematic view of a portion of the structure of a retractable aircraft landing gear disclosed in an embodiment of the present invention;
FIG. 6 is a schematic illustration of the internal structure of a retractable aircraft landing gear disclosed in an embodiment of the present invention;
FIG. 7 is a schematic view of a portion of a retractable aircraft landing gear disclosed in an embodiment of the present invention when stowed;
FIG. 8 is a schematic view of a portion of a retractable aircraft landing gear disclosed in an embodiment of the present invention in its lowered configuration;
fig. 9 is a schematic diagram showing the internal structure of the retractable landing gear of the retractable aircraft disclosed in the embodiment of the present invention.
Wherein 100 is a driving component, 200 is a buffer, and 300 is a wheel component;
1 is a main post outer cylinder, 2 is a main post piston rod, 3 is a connecting rocker, 4 is a telescopic rod, 5 is a transmission mechanism, 6 is a transmission sleeve, 7 is a transmission piston, 8 is an upper connecting rod, 9 is a middle sleeve, 10 is a lower connecting rod, 11 is an upper torque arm, 12 is a lower torque arm, 13 is an actuator, 14 is a first connecting rod, 15 is a second connecting rod, 16 is a third connecting rod, 17 is a first rocker, 18 is a second rocker, 19 is a cam, 20 is a guide groove, 21 is a guide block, and 22 is an oil limiting needle rod.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a telescopic aircraft landing gear, which solves the problems in the prior art, enables the size of the aircraft landing gear to be increased, ensures that the aircraft takes off and lands smoothly, and simultaneously enables the aircraft landing gear to meet the requirement of a storage space.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
The invention provides a telescopic aircraft landing gear, which comprises a driving assembly 100, a buffer 200 and an aircraft wheel assembly 300, wherein the buffer 200 comprises a main support outer cylinder 1 and a main support piston rod 2, the main support piston rod 2 is connected with the main support outer cylinder 1 through a sliding pair, and the main support outer cylinder 1 is also in transmission connection with the driving assembly 100; the wheel assembly 300 comprises a connecting rocker arm 3 and a telescopic rod 4, wherein the connecting rocker arm 3 can be connected with the wheel, one end of the telescopic rod 4 extends out of the main support piston rod 2 and is hinged with the connecting rocker arm 3, the other end of the telescopic rod 4 is in transmission connection with the driving assembly 100 through a transmission mechanism 5, the transmission mechanism 5 is arranged in the buffer 200, the connecting rocker arm 3 is rotatably connected with the main support outer cylinder 1 through a torque arm, and the driving assembly 100 can drive the telescopic rod 4 to move through the transmission mechanism 5 so that the connecting rocker arm 3 rotates relative to the buffer 200.
According to the telescopic aircraft landing gear disclosed by the invention, the main strut piston rod 2 of the buffer 200 can slide relative to the main strut outer cylinder 1 so as to absorb vibration and impact load in the process of sliding and landing of an aircraft, and the driving assembly 100 is in transmission connection with the buffer 200, so that the normal retraction and release of the device are ensured; in the wheel assembly 300, the connecting rocker arm 3 is connected with the wheels, and the connecting rocker arm 3 is connected with a torque arm, so that the normal operation of the device is ensured; meanwhile, telescopic link 4 is articulated with connecting rocking arm 3 for actuating assembly 100 can utilize drive mechanism 5 to drive telescopic link 4 motion, so that connecting rocking arm 3 can rotate for buffer 200, thereby change the angle of connecting rocking arm 3 and buffer 200 and adjust telescopic aircraft landing gear's overall length, when the aircraft takes off and lands, landing gear is put down and the length increases, the ground clearance of machine satisfies the flight requirement, when the landing gear is packed up, make landing gear overall length shorten simultaneously when packing up the landing gear through actuating assembly 200, fly and drive mechanism 5 sets up in buffer 200, telescopic link 4 also stretches into in buffer 200 with the continuous one end of drive mechanism 5, when the landing gear is packed up, satisfy the collection space requirement of aircraft. The driving assembly 200 is responsible for the whole retraction of the landing gear, and can drive the wheel assembly 300 to extend and retract, so that the whole occupied space of the device is reduced, and the energy consumption is reduced.
It should be further noted that, the wheel assembly 300 further includes a transmission cylinder disposed in the main strut piston rod 2, the transmission cylinder includes a transmission sleeve 6 and a transmission piston 7, the transmission sleeve 6 and the transmission piston 7 are connected through a sliding pair (the sliding pair is formed at a sliding connection position of the transmission sleeve and the transmission piston 7), one end of the transmission piston 7 is hinged with the telescopic rod 4, the other end of the transmission piston 7 extends into the transmission sleeve 6 and is connected with the transmission mechanism 5, and a piston cavity of the transmission cylinder is communicated with a piston cavity of the buffer 200. The telescopic rod 4 utilizes the drive cylinder to link to each other with drive mechanism 5, specifically, drive mechanism 5 utilizes drive piston 7 to drive telescopic rod 4 motion, adjusts telescopic rod 4 by the length that stretches out in the main stay piston rod 2, and drive piston 7 cooperatees with transmission sleeve 6 can restrict telescopic rod 4's extreme position, avoids telescopic rod 4 to stretch out the length overlength, improves the operational reliability of device.
In this embodiment, the drive mechanism 5 includes upper connecting rod 8, middle sleeve 9 and lower connecting rod 10 that link to each other in order, upper connecting rod 8 and lower connecting rod 10 all slidably link to each other with middle sleeve 9, upper connecting rod 8 keeps away from middle sleeve 9's one end and drive assembly 100 link to each other, lower connecting rod 10 keeps away from middle sleeve 9's one end and links to each other with drive piston 7, and upper connecting rod 8 and lower connecting rod 10 all have the fixture block with middle sleeve 9 tip slide hole looks adaptation, avoid upper connecting rod 8 and lower connecting rod 10 to slip in by middle sleeve 9 for drive assembly 100 can drive telescopic link 4 through pulling drive mechanism 5 and move, avoid buffer 200 buffering in-process promotion drive mechanism 5 to influence telescopic link 4's normal work simultaneously, improve the operational reliability of drive mechanism 5 and telescopic link 4 under the prerequisite of guaranteeing buffer 200 normal work. In this embodiment, the middle sleeve 9 passes through the main strut piston rod 2 to be connected with the driving assembly 100, the transmission mechanism 5 does not affect the operation of the buffer 200, the whole occupied space of the device can be saved, and the device can be smoothly stored by an airplane. Here, the limiting collar is provided on the inner wall of the main strut outer tube 1, so that the limiting position of the main strut piston rod 2 can be limited, and the working safety factor of the damper 200 can be improved.
The torque arm comprises an upper torque arm 11 and a lower torque arm 12, one end of the upper torque arm 11 is hinged with the main support outer cylinder 1, the other end of the upper torque arm 11 is hinged with the lower torque arm 12, one end of the lower torque arm 12, which is far away from the upper torque arm 11, is hinged with the connecting rocker arm 3, the torque arm can ensure normal steering of the machine wheel, the hinge point of the connecting rocker arm 3 and the telescopic rod 4 is positioned between the connecting point of the connecting rocker arm 3 and the machine wheel and the hinge point of the connecting rocker arm 3 and the lower torque arm 12, the telescopic rod 4 is ensured to drive the connecting rocker arm 3 to rotate, and the whole height of the device is adjusted.
In addition, when the retractable landing gear of the invention is in the retracted state, the wheel assembly 300 is in the retracted state, and at the moment, the connecting rocker arm 3 is propped against the main strut piston rod 2, and at the moment, the length direction of the connecting rocker arm 3 is vertical to the axial direction of the buffer 100, and the whole length of the landing gear is reduced; when the landing gear is put down, the wheel assembly 300 is in an extended state, at this time, the connecting rocker arm 3 rotates, one end, connected with the wheels, of the connecting rocker arm 3 turns downwards, the whole length of the landing gear is increased, and the ground clearance requirement of the aircraft is met. Specifically, in the aircraft take-off and head-up process, the lift force is gradually increased, when the lift force is increased to a certain degree, the space occupied by gas in the piston cavity of the buffer 200 is increased, so that oil enters the piston cavity of the transmission cylinder, the transmission piston 7 is utilized to push the telescopic rod 4, and the telescopic rod 4 is utilized to push the connecting rocker arm 3 to rotate, so that the whole length of the device is increased. Because the transmission cylinder is arranged in the main support piston rod 2, the sectional area of the piston cavity of the buffer 200 is larger than that of the transmission piston 7 cavity, and the extension rod 4 extends out of the main support piston rod 2 for a longer distance, so that the ground clearance of the airplane meets the requirement, and the ground wiping of the tail of the airplane is avoided. When the aircraft lands, the damping hole is arranged above the main support outer cylinder 1, the piston cavity of the buffer 200 is communicated with the damping hole by utilizing the oil limiting needle rod 22, the telescopic rod 4 is used for bearing partial load and slowly retracting the main support piston rod 2, the connecting rocker arm 3 is propped against the main support outer cylinder 1, the buffer 200 is used for bearing main load, and effective protection is provided for the telescopic rod 4, so that the situation that the bearing load is overlarge and failure is avoided. In addition, the damper 200 is provided with a damping hole and the oil restricting needle bar 22, which are common knowledge of those skilled in the art, and will not be described herein.
Specifically, the driving assembly 100 includes an actuator 13 and a first link 14, the length of the actuator 13 can be adjusted, the movable end of the actuator 13 is hinged to the main support outer cylinder 1, the fixed end of the actuator 13 is hinged to the first link 14, the first link 14 is also hinged to the main support outer cylinder 1, the hinge point of the actuator 13 and the main support outer cylinder 1 is not overlapped with the hinge point of the first link 14 and the main support outer cylinder 1, the length of the actuator 13 is changed, the main support outer cylinder 1 can be driven to rotate by using the first link 14, and the whole retraction of the device is smoothly realized. In practical application, the actuator 13 can select structures such as an air cylinder or a telescopic rod 4, and the like, can be selected according to practical working conditions, meets different working requirements, and improves the flexibility and adaptability of the device.
In order to enable the driving assembly 100 to drive the telescopic rod 4 to act simultaneously, the whole structure of the device is simplified, the driving assembly 100 further comprises a second connecting rod 15, a third connecting rod 16, a first rocker arm 17 and a second rocker arm 18, one end of the second connecting rod 15 is hinged with the first connecting rod 14, the other end of the second connecting rod 15 is hinged with one end of the first rocker arm 17, the hinged surface of the two is a spherical surface, the other end of the first rocker arm 17 is hinged with one end of the third connecting rod 16, the other end of the third connecting rod 16 is hinged with one end of the second rocker arm 18, and the other end of the second rocker arm 18 is connected with the transmission mechanism 5. When the actuator 13 drives the first connecting rod 14 to rotate, the first connecting rod 14 drives the second rocker arm 18 to rotate by using the second connecting rod 15, the first rocker arm 17 and the third connecting rod 16, and the second rocker arm 18 drives the transmission piston 7 to move by using the transmission mechanism 5, so that the purpose of driving the telescopic rod 4 to move is achieved. In this embodiment, the second rocker utilizes the upper connecting rod 8 to drive the transmission piston 7 to move, the first connecting rod 14 utilizes the second connecting rod 15, the first rocker arm 17 and the third connecting rod 16 to drive the second rocker arm 18 to move, the connecting rod mechanism has simple structure and reliable transmission, and the whole occupied space of the device is reduced as completely as possible while the telescopic rod 4 is smoothly driven to move, so that the device can be smoothly stored. In practical application, the second connecting rod 15 may be hinged to one end of the first rocker arm 17 by using a fisheye spherical hinge.
More specifically, the second rocker arm 18 is connected with a cam 19, the cam 19 is located in the main strut outer cylinder 1, the upper connecting rod 8 of the transmission mechanism 5 is rotationally connected with the cam 19, and the second rocker arm 18 can drive the cam 19 to rotate, so that the cam 19 drives the telescopic rod 4 to move by using the transmission mechanism 5. The structure and the size of the cam 19 are reasonably set, so that the cam 19 can drive the transmission mechanism 5 to move through the upper connecting rod 8 when rotating, and then drive the transmission piston 7 and the telescopic rod 4 connected with the transmission mechanism 5 to move. In practical application, the second connecting rod 15 can be connected with the cam 19 through a connecting rod, and the connecting rod passes through the outer wall of the main support outer cylinder 1, so that smooth power transmission is realized.
In order to further ensure the operational reliability of the device, the cam 19 is provided with a guide groove 20, the transmission mechanism 5 is provided with a guide block 21 matched with the guide groove 20, the guide block 21 is slidably arranged in the guide groove 20, and when the cam 19 rotates, the guide block 21 slides along the guide groove 20 so as to pull the transmission mechanism 5 to move.
Furthermore, the invention also provides an aircraft, which comprises the telescopic aircraft landing gear, so that the ground clearance of the aircraft is improved, and the flight performance of the aircraft is ensured.
In the working process of the telescopic aircraft landing gear, the actuator 13 drives the telescopic rod 4 to be slowly retracted from a lowered state (shown in figure 1), and simultaneously drives the first connecting rod 14 to rotate relative to the main strut outer cylinder 1, so as to drive the second connecting rod 15 to push down, the second connecting rod 15 drives the third connecting rod 16 to move upwards through the first rocker arm 17, and the third connecting rod 16 drives the second rocker arm 18 to rotate, so as to drive the cam 19 in the buffer 200 to rotate. The cam 19 drives the transmission mechanism 5 to lift the transmission piston 7 through the guide groove 20, so that the telescopic rod 4 is retracted into the buffer 200, as shown in fig. 6; similarly, when the device is put down, the cam 19 in the buffer 200 will generate opposite rotation angles, and under the action of the air cavity pressure of the piston cavity of the buffer 200, the transmission piston 7 descends, and the telescopic rod 4 pops up.
During the landing process of the aircraft, when the aircraft lands, the telescopic rod 4 is firstly loaded, and when the telescopic rod 4 is fully retracted into the main support piston rod 2, the connecting rocker arm 3 is contacted with the main support piston rod 2, so that the telescopic rod 4 is not loaded more, and the telescopic rod 4 is prevented from deforming and damaging; when the aircraft takes off, the aircraft gradually rises, the lifting force gradually increases, and when the lifting force increases to a certain value, the telescopic rod 4 pops up to prevent the tail from wiping the ground.
Compared with the landing gear in the prior art, the telescopic aircraft landing gear can automatically extend when the device is put down and can be ejected out in the process of taking off the aircraft so as to prevent the tail of the aircraft from wiping the ground; when the device is retracted, the device can retract automatically to meet the requirement of the storage space; meanwhile, the telescopic rod 4 can also serve as primary buffering, and the buffer 200 still plays a main role in buffering after the connecting rocker arm 3 contacts with the main strut piston rod 2 in the landing stage.
The principles and embodiments of the present invention have been described in detail with reference to specific examples, which are provided to facilitate understanding of the method and core ideas of the present invention; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.

Claims (9)

1. A retractable aircraft landing gear, comprising:
a drive assembly;
the buffer comprises a main support outer cylinder and a main support piston rod, wherein the main support piston rod is connected with the main support outer cylinder through a sliding pair, and the main support outer cylinder is also in transmission connection with the driving assembly;
the machine wheel assembly comprises a connecting rocker arm and a telescopic rod, the connecting rocker arm can be connected with a machine wheel, one end of the telescopic rod extends out of a main support piston rod and is hinged to the connecting rocker arm, the other end of the telescopic rod is connected with a driving assembly in a transmission mode through a transmission mechanism, the transmission mechanism is arranged in a buffer, the connecting rocker arm is rotatably connected with the main support outer cylinder through a torque arm, and the driving assembly can drive the telescopic rod to move through the transmission mechanism so that the connecting rocker arm rotates relative to the buffer.
2. The retractable aircraft landing gear of claim 1, wherein: the machine wheel assembly further comprises a transmission cylinder arranged in the main support piston rod, the transmission cylinder comprises a transmission sleeve and a transmission piston, the transmission sleeve is connected with the transmission piston through a sliding pair, one end of the transmission piston is hinged to the telescopic rod, the other end of the transmission piston stretches into the transmission sleeve and is connected with the transmission mechanism, and a piston cavity of the transmission cylinder is communicated with a piston cavity of the buffer.
3. The retractable aircraft landing gear of claim 2, wherein: the transmission mechanism comprises an upper connecting rod, a middle sleeve and a lower connecting rod which are sequentially connected, wherein the upper connecting rod and the lower connecting rod are both slidably connected with the middle sleeve, one end of the upper connecting rod, which is far away from the middle sleeve, is connected with the driving assembly, and one end of the lower connecting rod, which is far away from the middle sleeve, is connected with the transmission piston.
4. The retractable aircraft landing gear of claim 1, wherein: the torque arm comprises an upper torque arm and a lower torque arm, one end of the upper torque arm is hinged with the main support outer cylinder, the other end of the upper torque arm is hinged with the lower torque arm, and one end of the lower torque arm, which is far away from the upper torque arm, is hinged with the connecting rocker arm.
5. The retractable aircraft landing gear of claim 1, wherein: when the telescopic aircraft landing gear is in a retracted state, the wheel assembly is in a retracted state, and the connecting rocker arm abuts against the main strut piston rod.
6. A retractable aircraft landing gear according to any of claims 1 to 5, wherein: the driving assembly comprises an actuator and a first connecting rod, the length of the actuator can be adjusted, the movable end of the actuator is hinged with the main support outer cylinder, the fixed end of the actuator is hinged with the first connecting rod, and the first connecting rod is also hinged with the main support outer cylinder.
7. The retractable aircraft landing gear of claim 6, wherein: the driving assembly further comprises a second connecting rod, a third connecting rod, a first rocker arm and a second rocker arm, one end of the second connecting rod is hinged to the first connecting rod, the other end of the second connecting rod is hinged to one end of the first rocker arm, the hinged surface of the second connecting rod and the first rocker arm is spherical, the other end of the first rocker arm is hinged to one end of the third connecting rod, the other end of the third connecting rod is hinged to one end of the second rocker arm, and the other end of the second rocker arm is connected with the transmission mechanism.
8. The retractable aircraft landing gear of claim 7, wherein: the second rocker arm is connected with a cam, the cam is positioned in the main support outer cylinder, the transmission mechanism is rotationally connected with the cam, and the second rocker arm can drive the cam to rotate, so that the cam drives the telescopic rod to move by using the transmission mechanism.
9. The retractable aircraft landing gear of claim 8, wherein: the cam is provided with a guide groove, the transmission mechanism is provided with a guide block matched with the guide groove, and the guide block is slidably arranged in the guide groove.
CN202310828178.4A 2023-07-06 2023-07-06 Telescopic aircraft landing gear Pending CN116729624A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310828178.4A CN116729624A (en) 2023-07-06 2023-07-06 Telescopic aircraft landing gear

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310828178.4A CN116729624A (en) 2023-07-06 2023-07-06 Telescopic aircraft landing gear

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