CN109018318B - Lightweight unmanned aerial vehicle shock attenuation landing gear - Google Patents
Lightweight unmanned aerial vehicle shock attenuation landing gear Download PDFInfo
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- CN109018318B CN109018318B CN201811178948.0A CN201811178948A CN109018318B CN 109018318 B CN109018318 B CN 109018318B CN 201811178948 A CN201811178948 A CN 201811178948A CN 109018318 B CN109018318 B CN 109018318B
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- 230000035939 shock Effects 0.000 title claims abstract description 21
- 238000013016 damping Methods 0.000 claims abstract description 97
- 230000003139 buffering effect Effects 0.000 claims abstract description 36
- 239000002184 metal Substances 0.000 claims description 6
- 239000011148 porous material Substances 0.000 claims description 6
- 238000010521 absorption reaction Methods 0.000 claims description 4
- 238000005096 rolling process Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 7
- 230000002411 adverse Effects 0.000 abstract description 3
- 230000001174 ascending effect Effects 0.000 abstract description 2
- 238000006073 displacement reaction Methods 0.000 abstract description 2
- 238000001125 extrusion Methods 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 1
- 235000017491 Bambusa tulda Nutrition 0.000 description 1
- 241001330002 Bambuseae Species 0.000 description 1
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 1
- 239000011425 bamboo Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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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
- B64C25/62—Spring shock-absorbers; Springs
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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
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
- Seats For Vehicles (AREA)
Abstract
The invention discloses a light-weight unmanned aerial vehicle damping landing gear, which can greatly improve the damping effect when an unmanned aerial vehicle is landed, ensure the landing stability of the unmanned aerial vehicle and improve the adverse effect of landing on parts of the unmanned aerial vehicle; the horizontal buffering damper in bottom can be at horizontal displacement to realize front and back direction and the ascending shock attenuation of vertical side, like this, not only can realize vertical shock attenuation, can realize horizontal shock attenuation moreover, effectively realize unmanned aerial vehicle's protection, reduce the impact property when its organism receives to rise and fall, simultaneously, guarantee the reliability of inner circuit structure, reduce the fault rate.
Description
Technical Field
The invention relates to a light unmanned aerial vehicle damping landing gear, and belongs to the technical field of unmanned aerial vehicle equipment.
Background
At present, although the continuous development of unmanned aerial vehicle technique, unmanned aerial vehicle's application is also more and more, to unmanned aerial vehicle, because lightweight unmanned aerial vehicle consumes energy fewly, rise and fall the convenience, its application is the most extensive. To lightweight unmanned aerial vehicle, because the structure of its support body is lighter, consequently, its rigidity also can receive certain influence, and to unmanned aerial vehicle, influence its life-span and structural stability and rise and fall exactly unmanned aerial vehicle's the lift of the most important factor, it is when rising and falling, the organism can receive very big power and vibration, this kind of impact force and vibration can lead to the loose and inside electronic control of unmanned aerial vehicle support body to appear becoming flexible, influence unmanned aerial vehicle's life, this is especially obvious in lightweight unmanned aerial vehicle.
Aiming at the problems, the invention provides the light-weight unmanned aerial vehicle damping landing gear, so that the damping effect of the unmanned aerial vehicle is improved, and the influence of landing on the unmanned aerial vehicle is reduced.
Disclosure of Invention
In order to achieve the purpose, the invention provides the following technical scheme: the damping landing gear of the light unmanned aerial vehicle comprises mounting lugs, an inverted L-shaped seat, a hinged ball seat, a vertical landing damping assembly, a bottom transverse damping assembly and a landing seat, wherein the mounting lugs are fixedly arranged at the bottom of a main body frame of the light unmanned aerial vehicle, one end of an upper horizontal section of the inverted L-shaped seat is hinged to the mounting lugs, the other end of the upper horizontal section of the inverted L-shaped seat is hinged to the bottom of the main body frame of the light unmanned aerial vehicle through the hinged ball seat, the lower end of a lower vertical section of the inverted L-shaped seat is fixedly connected with the vertical landing damping assembly, the lower end of the vertical landing damping assembly is connected with the bottom transverse damping assembly, the lower end of the transverse damping assembly is connected with the landing seat, the vertical landing damping assembly comprises a damping cylinder seat, a primary spring damping assembly and a secondary air pressure damping assembly, the primary spring damping assembly is arranged in the damping cylinder seat, and the secondary air pressure damping assembly connected with the primary spring assembly is arranged at the lower end of the damping cylinder seat; the bottom transverse buffering and damping component is arranged at the bottom of the secondary air pressure damping component; the primary spring damping assembly and the secondary air pressure damping assembly can reset in the vertical direction so as to realize vertical damping; the bottom transverse buffering and damping assembly can be displaced in the horizontal transverse direction so as to realize damping in the front-back direction and the vertical direction; the lower end surface of the seat-taking and-taking seat which is contacted with the ground is of a convex cambered surface structure.
Further, as preferred, one-level spring shock attenuation subassembly includes interior fixed plate, damping spring group, interior sliding seat and interior slip ring, wherein, the shock attenuation barrel holder is hollow structure, be provided with interior sliding tray in the well cavity of shock attenuation barrel holder, the setting that interior slip ring can be slided from top to bottom is in the interior sliding tray, interior sliding seat is fixed in on the interior slip ring, upper portion in the shock attenuation barrel holder is fixed and is provided with and lays the level along its radial cross-section and extend interior fixed plate, interior sliding seat with parallel arrangement between the interior fixed plate, just interior fixed plate with be provided with the damping spring group of range between the interior sliding seat.
Further, as preferred, second grade atmospheric pressure damper assembly includes atmospheric pressure pole seat, piston, pneumatic cylinder and outer sliding block, wherein, the bottom level of damper cylinder seat is fixed to be provided with to its radial inboard extension outer sliding block, be provided with along its axial extension's vertical outer spout on the outer circumference of pneumatic cylinder, outer sliding block with outer spout cooperation slides, be provided with upper end open-ended atmospheric pressure pore in the pneumatic cylinder, the lower extreme of atmospheric pressure pole seat is provided with the piston, the piston with construct to establish to sealed gliding cylinder structure between the atmospheric pressure pore of pneumatic cylinder, the top fixed connection of atmospheric pressure pole seat in on the interior sliding seat, through the piston is down, the extrusion gaseous medium in the atmospheric pressure pore of pneumatic cylinder realizes atmospheric pressure shock attenuation.
Further, preferably, the air pressure duct is filled with air with a certain pressure, the air pressure cylinder is provided with a pressure control hole communicated with the air pressure duct, the pressure control hole is provided with a valve, and the internal air pressure damping strength is controlled by filling the air pressure control hole with air.
Further, as preferred, the horizontal buffering shock-absorbing component in bottom includes preceding buffering articulated wheel seat, back buffering articulated wheel seat, articulated pillar, preceding slider, back slider and elasticity centering subassembly, wherein, preceding buffering articulated wheel seat, back buffering articulated wheel seat are laid respectively second grade atmospheric pressure section of thick bamboo lower extreme front side and rear side of atmospheric pressure shock-absorbing component, all connect the articulated pillar that is provided with the slope on preceding buffering articulated wheel seat, the back buffering articulated wheel seat, just the articulated pillar can realize inclination's regulation along with the rotation of preceding buffering articulated wheel seat, back buffering articulated wheel seat, the lower extreme of articulated pillar articulates respectively and is provided with preceding slider and back slider, the up end that rises to take a seat is provided with the horizontally horizontal groove, preceding slider and back slider slidable set up in the horizontal groove, just be provided with between each other of preceding slider, back slider and horizontal groove centering subassembly, two still be provided with the auxiliary spring between the articulated pillar.
Further, as a preferred option, the centering assembly includes a first spring, a second spring, a third spring and a guide pillar, wherein the guide pillar is horizontally disposed in the horizontal groove, the front slider and the rear slider are horizontally slidably sleeved on the guide pillar, the first spring, the second spring and the third spring are all sleeved on the guide pillar, the first spring is abutted against the front end of the horizontal groove and the front slider, the second spring is abutted against the rear end of the horizontal groove and the rear slider, the third spring is abutted against the front slider and the rear slider, and the first spring and the second spring are completely the same cylindrical spring.
Preferably, a front extending shoulder extending upwards is arranged on the end face, close to the rear slider, of the front slider, a rear extending shoulder extending upwards is arranged on the end face, close to the front slider, of the rear slider, and a spring four is arranged between the front extending shoulder and the rear extending shoulder.
Further, as preferred, preceding buffering articulated wheel seat, back buffering articulated wheel seat structure are the same, all include cylinder fixing base, guide roller group, interior round rail, rotation uide bushing seat and arc guide block, wherein, be provided with the blind hole on the cylinder fixing base, the cylinder fixing base is fixed to be set up the pneumatic cylinder lower extreme, the blind hole outside of cylinder fixing base is provided with the circular shape annular spout coaxial with the blind hole, annular spout with the coaxial setting of blind hole, be provided with the interior round rail coaxial with the blind hole on the bottom wall of the blind hole of cylinder fixing base, the outside of interior round rail is provided with the guide roller group that the circumference was arranged, be provided with on the interior round rail can along interior round rail slides and around the central axis pivoted rotation uide bushing seat of cylinder fixing base, the outer terminal surface of rotation uide bushing seat with guide roller group direction is supported and is leaned on the rolling cooperation, still be provided with on the rotation uide bushing seat the arc guide block, the arc guide block is in the gliding setting of annular spout, the upper end of articulated pillar is connected on the rotation uide bushing seat.
Further, as preferred, be provided with the opening that is fan-shaped structure on the cylinder fixing base, articulated pillar stretches into the opening with the rotation uide bushing seat is connected, it includes upper end sheet metal spare and lower extreme elastic rubber pad to get up to take a seat, upper end sheet metal spare is the flat structure, the lower terminal surface of lower extreme elastic rubber pad is convex cambered surface structure.
Preferably, the inner circumferential wall of the rotary guide sleeve seat is provided with meshing teeth, the bottom wall of the blind hole is further provided with a plurality of rotatable gears, the gears are meshed with the meshing teeth, and a torsion spring is further arranged between the gears and the bottom wall of the blind hole, so that when the rotary guide sleeve seat rotates, the rotary guide sleeve seat is subjected to the torsion spring force of the gears to achieve damping and resetting.
Compared with the prior art, the invention has the beneficial effects that:
the lightweight damping landing gear of the unmanned aerial vehicle can greatly improve the damping effect when the unmanned aerial vehicle is landed, ensure the landing stability and improve the adverse effect of landing on parts of the unmanned aerial vehicle; the horizontal buffering damper assembly in bottom can be at horizontal displacement to realize the ascending shock attenuation of front and back direction and vertical side, like this, not only can realize vertical shock attenuation, can realize horizontal shock attenuation moreover, effectively realize the protection to unmanned aerial vehicle, reduce the impact property when its organism receives rising and falling, simultaneously, guarantee the reliability of internal circuit structure, reduce the fault rate.
Drawings
Fig. 1 is a schematic view of the overall mounting structure of the shock-absorbing landing gear of the lightweight unmanned aerial vehicle of the present invention;
FIG. 2 is an enlarged schematic view of the shock absorbing landing gear of the lightweight unmanned aerial vehicle of the present invention;
FIG. 3 is a schematic structural view of a centering assembly portion of the lightweight landing gear for unmanned aerial vehicles of the present invention;
fig. 4 is a schematic structural view of a front buffer articulated wheel seat or a rear buffer articulated wheel seat of the lightweight unmanned aerial vehicle shock absorption landing gear.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-4, the present invention provides a technical solution: the damping landing device of the light unmanned aerial vehicle comprises mounting lugs 2, an inverted L-shaped seat 4, a hinged ball seat 5, a vertical landing damping component 7, a bottom transverse damping component 8 and a landing seat 9, wherein the mounting lugs 2 are fixedly arranged at the bottom of a main body frame 1 of the light unmanned aerial vehicle, one end of an upper horizontal section of the inverted L-shaped seat 4 is hinged to the mounting lugs 2, the other end of an upper horizontal section of the inverted L-shaped seat 4 is hinged to the bottom of the main body frame 1 of the light unmanned aerial vehicle through the hinged ball seat 5, the lower end of a lower vertical section of the inverted L-shaped seat 4 is fixedly connected with the vertical landing damping component 7, the lower end of the vertical landing damping component 7 is connected with the bottom transverse damping component 8, the lower end of the transverse damping component 8 is connected with the landing component 9, the landing damping component 7 comprises a damping cylinder seat 6, a primary spring damping component and a secondary air pressure damping component, the primary spring damping component is arranged in the damping cylinder seat 6, and the lower end of the damping cylinder seat is connected with the secondary air pressure component; the bottom transverse buffering and damping component 8 is arranged at the bottom of the secondary air pressure damping component; the primary spring damping assembly and the secondary air pressure damping assembly can reset in the vertical direction so as to realize vertical damping; the bottom transverse buffer and shock absorption assembly 8 can be displaced in the horizontal transverse direction so as to realize shock absorption in the front-back direction and the vertical direction; the lower end surface of the take-up and seating seat 9 contacting with the ground is of a convex cambered surface structure.
In this embodiment, one-level spring shock attenuation subassembly includes interior fixed plate 11, damping spring group 12, interior sliding seat 16 and interior slip ring 13, wherein, damping cylinder seat 6 is hollow structure, the well intracavity of damping cylinder seat is provided with interior slip groove 10, the gliding setting from top to bottom of interior slip ring 13 is in interior slip groove 10, interior sliding seat 16 is fixed in on the interior slip ring 13, upper portion in the damping cylinder seat 6 is fixed to be provided with and lays the level along its radial cross-section and extend interior fixed plate 11, interior sliding seat 16 with parallel arrangement between the interior fixed plate 11, just interior fixed plate 11 with be provided with the damping spring group 12 of range between the interior sliding seat 16.
The secondary air pressure damping assembly comprises an air pressure rod seat 15, a piston 17, an air pressure cylinder 18 and an outer sliding block 14, wherein the bottom of the damping cylinder seat 6 is horizontally and fixedly provided with the outer sliding block 14 extending towards the radial inner side of the damping cylinder seat, the outer circumference of the air pressure cylinder 18 is provided with a vertical outer sliding groove 19 extending along the axial direction of the air pressure cylinder, the outer sliding block 14 is matched with the outer sliding groove 19 to slide, an air pressure hole 24 with an upper end opened is formed in the air pressure cylinder 18, the lower end of the air pressure rod seat 15 is provided with the piston 17, the piston and the air pressure hole of the air pressure cylinder are arranged in a sealed sliding cylinder structure, the top of the air pressure rod seat 15 is fixedly connected onto the inner sliding seat, and air pressure damping is realized by the aid of a gas medium in the air pressure hole of the air pressure cylinder through downward extrusion of the piston.
As a preferred embodiment, the air pressure duct is filled with air at a certain pressure, the air pressure cylinder is provided with a pressure control hole 28 communicated with the air pressure duct, the pressure control hole is provided with a valve, and the internal air pressure damping strength is controlled by filling the air into the pressure control hole.
In this embodiment, the horizontal buffering damper assembly in bottom includes that preceding buffering hinge wheel seat 25, back buffering hinge wheel seat 20, hinge pillar 21, preceding slider 23, back slider 22 and elasticity centering subassembly, wherein, preceding buffering hinge wheel seat 25, back buffering hinge wheel seat 20 lay respectively two grade atmospheric pressure damper assembly's pneumatic cylinder lower extreme front side and rear side, all connect the hinge pillar 21 that is provided with the slope on preceding buffering hinge wheel seat 25, the back buffering hinge wheel seat 20, just hinge pillar 21 can realize inclination's regulation along with the rotation of preceding buffering hinge wheel seat, back buffering hinge wheel seat, the lower extreme of hinge pillar 21 articulates respectively and is provided with preceding slider 23 and back slider 22, the up end that plays to take a seat is provided with the horizontally horizontal groove, preceding slider and back slider slidable set up in the horizontal groove, just preceding slider, back slider and horizontal groove be provided with each other centering subassembly, two still be provided with auxiliary spring between the hinge pillar.
As a preferred embodiment, the centering assembly includes a first spring, a second spring 28, a third spring and a guide post 29, wherein the guide post is horizontally disposed in the horizontal groove, the front slider 23 and the rear slider 21 are horizontally slidably disposed on the guide post 29, the first spring, the second spring and the third spring are all disposed on the guide post, the first spring is disposed between the front end of the horizontal groove and the front slider in an abutting manner, the second spring 28 is disposed between the rear end of the horizontal groove and the rear slider in an abutting manner, the third spring is disposed between the front slider and the rear slider in an abutting manner, and the first spring and the second spring are completely identical cylindrical springs.
As a preferred embodiment, a front extension shoulder extending upward is disposed on an end surface of the front slider close to the rear slider, a rear extension shoulder extending upward is disposed on an end surface of the rear slider close to the front slider, and a spring four 30 is disposed between the front extension shoulder and the rear extension shoulder.
As a better embodiment, the front buffer hinge wheel seat and the rear buffer hinge wheel seat have the same structure, and each of the front buffer hinge wheel seat and the rear buffer hinge wheel seat includes a cylindrical fixing seat 31, a guide roller set 37, an inner circular guide rail 34, a rotary guide sleeve seat 38 and an arc-shaped guide block 39, wherein the cylindrical fixing seat is provided with a blind hole 33, the cylindrical fixing seat is fixedly disposed at the lower end of the air cylinder, a circular annular sliding groove 32 coaxial with the blind hole 33 is disposed outside the blind hole of the cylindrical fixing seat 31, the annular sliding groove is disposed coaxially with the blind hole 33, the inner circular guide rail 34 coaxial with the blind hole is disposed on the bottom wall of the blind hole of the cylindrical fixing seat 31, the guide roller set 37 circumferentially disposed outside the inner circular guide rail 34, the rotary guide sleeve seat 38 capable of sliding along the inner circular guide rail and rotating around the central axis of the cylindrical fixing seat is disposed on the inner circular guide rail 34, the outer end surface of the rotary guide sleeve seat 38 is in rolling fit with the guide roller set 37, the arc-shaped guide block 39 is disposed on the annular sliding groove 32, and the upper end of the rotary hinge support post 21 is connected to the rotary guide sleeve seat 38.
As a better embodiment, an opening in a fan-shaped structure is provided on the cylindrical fixing seat, the hinge support extends into the opening to connect with the rotary guide sleeve seat, the seat lifting and seating device includes an upper metal plate 26 and a lower elastic rubber pad 27, the upper metal plate is in a flat plate structure, and the lower end surface of the lower elastic rubber pad is in a convex arc structure.
The inner circumferential wall of the rotary guide sleeve seat is provided with meshing teeth, the bottom wall of the blind hole is further provided with a plurality of rotatable gears 35, the gears are meshed with the meshing teeth, and a torsion spring 36 is further arranged between the gears and the bottom wall of the blind hole, so that when the rotary guide sleeve seat rotates, the rotary guide sleeve seat is subjected to the torsion spring force of the gears to achieve damping and resetting.
The damping device of the light unmanned aerial vehicle landing foot stand can greatly improve the damping effect when the unmanned aerial vehicle is landed, ensure the landing stability of the unmanned aerial vehicle and improve the adverse effect of landing on the unmanned aerial vehicle parts; although the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and variations may be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (4)
1. The damping landing gear of the light unmanned aerial vehicle is characterized by comprising mounting lugs, an inverted L-shaped seat, a hinged ball seat, a vertical landing damping assembly, a bottom transverse damping assembly and a lifting seat, wherein the mounting lugs are fixedly arranged at the bottom of a main body frame of the light unmanned aerial vehicle, one end of an upper horizontal section of the inverted L-shaped seat is hinged to the mounting lugs, the other end of an upper horizontal section of the inverted L-shaped seat is hinged to the bottom of the main body frame of the light unmanned aerial vehicle through the hinged ball seat, the lower end of a lower vertical section of the inverted L-shaped seat is fixedly connected with the vertical landing damping assembly, the lower end of the vertical landing damping assembly is connected with the bottom transverse damping assembly, the lower end of the transverse damping assembly is connected with the lifting seat, the vertical landing damping assembly comprises a damping cylinder seat, a primary spring damping assembly and a secondary air pressure damping assembly, and the primary spring damping assembly is connected with the primary spring assembly; the bottom transverse buffering and damping component is arranged at the bottom of the secondary air pressure damping component; the primary spring damping assembly and the secondary air pressure damping assembly can reset in the vertical direction so as to realize vertical damping; the bottom transverse buffering and damping assembly can be displaced in the horizontal transverse direction so as to realize damping in the front-back direction and the vertical direction; the lower end surface of the take-up and take-up seat, which is in contact with the ground, is of a convex cambered surface structure;
the bottom transverse buffering and damping assembly comprises a front buffering hinged wheel seat, a rear buffering hinged wheel seat, hinged pillars, a front slider, a rear slider and an elastic centering assembly, wherein the front buffering hinged wheel seat and the rear buffering hinged wheel seat are respectively arranged on the front side and the rear side of the lower end of a pneumatic cylinder of the secondary pneumatic damping assembly, the front buffering hinged wheel seat and the rear buffering hinged wheel seat are respectively connected with inclined hinged pillars, the hinged pillars can realize the adjustment of the inclination angle along with the rotation of the front buffering hinged wheel seat and the rear buffering hinged wheel seat, the lower end of each hinged pillar is respectively hinged with the front slider and the rear slider, the upper end surface of the lifting seat is provided with a horizontal groove, the front slider and the rear slider are slidably arranged in the horizontal groove, the centering assembly is arranged among the front slider, the rear slider and the horizontal groove, and an auxiliary spring is arranged between the two hinged pillars; the centering assembly comprises a first spring, a second spring, a third spring and a guide pillar, wherein the guide pillar is horizontally arranged in the horizontal groove, the front sliding block and the rear sliding block are sleeved on the guide pillar in a horizontally sliding manner, the first spring, the second spring and the third spring are all sleeved on the guide pillar, the first spring is abutted against and arranged between the front end of the horizontal groove and the front sliding block, the second spring is abutted against and arranged between the rear end of the horizontal groove and the rear sliding block, the third spring is abutted against and arranged between the front sliding block and the rear sliding block, and the first spring and the second spring are completely identical columnar springs;
the front buffer hinged wheel seat and the rear buffer hinged wheel seat are identical in structure and respectively comprise a cylindrical fixed seat, a guide roller group, an inner circle guide rail, a rotary guide sleeve seat and an arc-shaped guide block, wherein a blind hole is formed in the cylindrical fixed seat, the cylindrical fixed seat is fixedly arranged at the lower end of the air cylinder, a circular annular chute coaxial with the blind hole is formed in the outer side of the blind hole of the cylindrical fixed seat, the annular chute is coaxial with the blind hole, the inner circle guide rail coaxial with the blind hole is arranged on the bottom wall of the blind hole of the cylindrical fixed seat, the guide roller group arranged in a circumferential mode is arranged on the outer side of the inner circle guide rail, the inner circle guide rail is provided with the rotary guide sleeve seat which can slide along the inner circle guide rail and rotate around the central axis of the cylindrical fixed seat, the outer end face of the rotary guide sleeve seat is in guide abutting rolling fit with the guide roller group, the rotary guide sleeve seat is further provided with the arc-shaped guide block, the arc-shaped guide block slides in the annular chute, and the upper end of the hinged support column is connected to the rotary guide sleeve seat;
the inner circumferential wall of the rotating guide sleeve seat is provided with meshing teeth, the bottom wall of the blind hole is also provided with a plurality of rotatable gears, the gears are meshed with the meshing teeth, and a torsion spring is arranged between the gears and the bottom wall of the blind hole, so that when the rotating guide sleeve seat rotates, the damping and resetting are realized under the force of the torsion spring of the gears;
the primary spring damping assembly comprises an inner fixed plate, a damping spring group, an inner sliding seat and an inner sliding ring, wherein the damping cylinder seat is of a hollow structure, an inner sliding groove is formed in a hollow cavity of the damping cylinder seat, the inner sliding ring is arranged in the inner sliding groove in a vertically sliding manner, the inner sliding seat is fixed on the inner sliding ring, the inner fixed plate horizontally extending along the radial cross section of the inner sliding seat is fixedly arranged at the upper part in the damping cylinder seat, the inner sliding seat and the inner fixed plate are arranged in parallel, and the damping spring group is arranged between the inner fixed plate and the inner sliding seat;
the cylindrical fixing seat is provided with an opening in a sector structure, and the hinged strut extends into the opening to be connected with the rotary guide sleeve seat;
the secondary air pressure damping assembly comprises an air pressure rod seat, a piston, an air pressure cylinder and an outer sliding block, wherein the outer sliding block extending towards the radial inner side of the air pressure cylinder is horizontally and fixedly arranged at the bottom of the damping cylinder seat, a vertical outer sliding groove extending along the axial direction of the air pressure cylinder is arranged on the outer circumference of the air pressure cylinder, the outer sliding block and the outer sliding groove are matched and slide, an air pressure pore passage with an opening at the upper end is formed in the air pressure cylinder, the piston is arranged at the lower end of the air pressure rod seat, a sealed sliding air cylinder structure is formed between the piston and the air pressure pore passage of the air pressure cylinder, the top of the air pressure rod seat is fixedly connected to the inner sliding seat, and the piston descends to extrude a gas medium in the air pressure pore passage of the air pressure cylinder to realize air pressure damping;
the landing seat comprises an upper metal plate and a lower elastic rubber pad.
2. The lightweight unmanned aerial vehicle shock attenuation landing gear of claim 1, characterized in that: the pneumatic tube is filled with gas with certain pressure, the pneumatic tube is provided with a pressure control hole communicated with the pneumatic hole, the pressure control hole is provided with a valve, and the internal pneumatic damping strength is controlled by filling the gas into the pressure control hole.
3. The lightweight unmanned aerial vehicle shock absorption landing gear of claim 1, wherein: the front sliding block is close to the end face of the rear sliding block, a front extending shoulder extending upwards is arranged on the end face of the rear sliding block, the rear sliding block is close to the end face of the front sliding block, a rear extending shoulder extending upwards is arranged on the end face of the front sliding block, and a spring IV is arranged between the front extending shoulder and the rear extending shoulder.
4. The light unmanned aerial vehicle shock attenuation landing gear of claim 1, its characterized in that: the upper end metal plate is of a flat plate structure, and the lower end face of the lower end elastic rubber pad is of a convex arc surface structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811178948.0A CN109018318B (en) | 2018-10-10 | 2018-10-10 | Lightweight unmanned aerial vehicle shock attenuation landing gear |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811178948.0A CN109018318B (en) | 2018-10-10 | 2018-10-10 | Lightweight unmanned aerial vehicle shock attenuation landing gear |
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| CN109018318A CN109018318A (en) | 2018-12-18 |
| CN109018318B true CN109018318B (en) | 2023-03-28 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110979686A (en) * | 2019-10-31 | 2020-04-10 | 王国瑞 | Intelligent plant protection unmanned aerial vehicle and use method thereof |
| CN110775257B (en) * | 2019-11-04 | 2021-03-02 | 桂林航天工业学院 | Lightweight unmanned aerial vehicle foot rest winding and unwinding devices |
| CN111619794B (en) * | 2020-06-02 | 2021-08-10 | 许昌学院 | Unmanned aerial vehicle buffering fender bracket that rises and falls |
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Application publication date: 20181218 Assignee: GUILIN FLIGHT TECHNOLOGY CO. Assignor: GUILIN University OF AEROSPACE TECHNOLOGY Contract record no.: X2023980043464 Denomination of invention: Lightweight unmanned aerial vehicle shock absorption landing device Granted publication date: 20230328 License type: Common License Record date: 20231016 |
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