CN215752989U - Aircraft undercarriage - Google Patents
Aircraft undercarriage Download PDFInfo
- Publication number
- CN215752989U CN215752989U CN202122471257.3U CN202122471257U CN215752989U CN 215752989 U CN215752989 U CN 215752989U CN 202122471257 U CN202122471257 U CN 202122471257U CN 215752989 U CN215752989 U CN 215752989U
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- aircraft
- landing gear
- push rod
- electric push
- leg
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- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 238000013016 damping Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000035945 sensitivity Effects 0.000 description 2
- 230000000087 stabilizing effect Effects 0.000 description 2
- 230000002337 anti-port Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000012876 topography Methods 0.000 description 1
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Abstract
The utility model relates to an aircraft landing gear in the technical field of aircraft, which comprises a plurality of supporting legs, wherein the plurality of supporting legs are uniformly distributed at the bottom of a body of the aircraft along the circumferential direction, the bottom of the body is provided with a plurality of through grooves which correspond to the supporting legs one by one, one end, close to the body, of each supporting leg is connected with a hinged shaft, two ends of each hinged shaft are rotatably connected with two side walls of the outer end of the corresponding through groove, the other end of each supporting leg is connected with a roller through a connecting rod, a first electric push rod is hinged in each through groove, and the other end of each electric push rod is hinged with the outer wall of the bottom of the corresponding supporting leg. The landing leg device has the advantages of simple and reasonable structure and simplicity and convenience in operation, the landing legs can be retracted into the through grooves of the machine body, the size is reduced, the carrying and the transportation are convenient, the angle between the unfolded landing legs and the bottom surface of the machine body can be flexibly changed, the height of the bottom surface of the machine body from the ground can be adjusted, the bottom surface of the machine body is not contacted with the ground after the landing legs are landed, and the damage is avoided.
Description
Technical Field
The utility model relates to the technical field of aircrafts, in particular to an aircraft landing gear.
Background
With the rapid development of aircrafts, the aircraft landing gear is widely applied to the fields of civil use, scientific research and the like, the process of lifting off the ground of the aircrafts has a landing or recovery stage, and the aircraft landing gear is a device for supporting the gravity of the aircrafts and bearing corresponding loads when the aircrafts are parked, slide, take off, land and run on the ground. All adopt the mode installation of fix with screw between present majority's aircraft and the undercarriage, the assembly process is more loaded down with trivial details, and dismantles inconveniently, and general undercarriage all is fixed strutting, when carrying and transporting the aircraft, because the bulky of undercarriage and aircraft is great, the case of needs is great relatively, causes the inconvenience of carrying and transporting. But the existing folding landing gear simply splices the folding structure of the landing gear, can not reliably realize the quick expansion and retraction of the landing gear, and has poor damping effect.
SUMMERY OF THE UTILITY MODEL
Aiming at the defects in the prior art, the utility model provides an aircraft landing gear which comprises a plurality of supporting legs, wherein the supporting legs are uniformly distributed at the bottom of the aircraft body of the aircraft along the circumferential direction, a plurality of through grooves which are in one-to-one correspondence with the supporting legs are formed in the bottom of the aircraft body, one ends, close to the aircraft body, of the supporting legs are connected with hinged shafts, two ends of each hinged shaft are rotatably connected with two side walls of the outer end of the corresponding through groove, the other ends of the supporting legs are connected with rollers through connecting rods, a first electric push rod is hinged in each through groove, and the other end of each electric push rod is hinged with the outer wall of the bottom of the corresponding supporting leg.
Preferably, the connecting end of the connecting rod and the roller is provided with an elastic buffer layer, and the connecting rod is further sleeved with a buffer spring. The damping device can buffer the stress of the aircraft body through the damping spring when the aircraft lands on the ground, and avoids the roller from generating large impulsive force on the aircraft body.
Preferably, one end of the first electric push rod is connected with the through groove through a first universal joint bearing, the other end of the first electric push rod is connected with the supporting leg through a second universal joint bearing, and the arrangement of the first universal joint bearing improves the sensitivity of the first electric push rod in the stretching process.
Preferably, be equipped with on the bottom outer wall of landing leg with an electric putter assorted holding tank, this department sets up and can be when an electric putter shrink, and the landing leg rotates around the articulated shaft and withdraws when leading to the groove, and electric putter holds in the holding tank, has reduced the volume.
Preferably, the number of the supporting legs is not less than three. Ensuring the balance of the fuselage.
Preferably, the roller is a universal wheel.
Preferably, the bottom of the machine body is circular, the length of the supporting leg is not more than the radius of the bottom of the machine body, and the length of the through groove is not less than that of the supporting leg, so that the supporting leg can be effectively folded in the through groove.
Preferably, a vertical telescopic rod is fixedly connected in the through groove, and one end of the first electric push rod is hinged with the vertical telescopic rod. The arrangement of the supporting legs can enable the vertical telescopic rod to be properly extended and form a triangle with the electric push rod I and the supporting legs when the electric push rod I extends, and the electric push rod is matched with the supporting legs to play a better supporting and stabilizing role.
Preferably, the vertical telescopic rod is an electric push rod II.
The utility model also includes other components which enable the normal use of an aircraft landing gear, such as a control component of a power push rod I, a control component of an aircraft and the like, which are conventional in the art. In addition, the devices or components which are not limited in the utility model all adopt the conventional technical means in the field, and the electric push rod I, the universal joint II, the universal wheel and the like are all conventional equipment in the field.
The working principle of the utility model is that when the aircraft is transported, the electric push rod I contracts to enable each supporting leg to rotate around the hinge shaft, the supporting legs are stored in the through grooves, the total volume of the aircraft is reduced, the aircraft is convenient to carry and transport, when the aircraft lands, the electric push rod I extends to enable each supporting leg to rotate around the hinge shaft in the reverse direction, the supporting legs are opened to support the aircraft, meanwhile, the extension length of the electric push rod I can be adjusted according to the landform of a landing place, the angle between the unfolded supporting legs and the bottom surface of the aircraft body is flexibly changed, the height of the bottom surface of the aircraft body from the ground is adjustable, and therefore, the bottom surface of the aircraft body is not in contact with the ground after landing of the supporting legs, and damage is avoided.
The utility model has the advantages of simple and reasonable structure and simple and convenient operation, the support legs can be put into the through grooves of the machine body when being carried and transported through the mutual matching of the electric push rod I and the support legs, the volume is reduced, the carrying and the transportation are convenient, in addition, when the support legs are opened, the extension length of the electric push rod I can be adjusted, the angle between the unfolded support legs and the bottom surface of the machine body is flexibly changed, the height of the bottom surface of the machine body from the ground can be adjusted, so that the bottom surface of the machine body is not contacted with the ground after the support legs are landed, and the damage is avoided.
Drawings
The utility model is further illustrated with reference to the following figures and examples.
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a top view of FIG. 1;
FIG. 3 is a bottom view of FIG. 1;
fig. 4 is a state view of the leg of fig. 3 folded into the channel.
In the figure: 1. the novel electric push rod type telescopic shaft comprises a machine body, 2 connecting rods, 3 supporting legs, 4 rolling wheels, 5 buffer springs, 6 universal joint bearings, 7 vertical telescopic rods, 8 accommodating grooves, 9 electric push rods, 10 universal joint bearings, 11 through grooves, 12 and a hinge shaft.
Detailed Description
The present invention will be described more clearly with reference to the accompanying drawings, which are included to illustrate and not to limit the present invention. All other embodiments, which can be obtained by those skilled in the art without any inventive step based on the embodiments of the present invention, should be included in the scope of the present invention.
Examples
As shown in fig. 1-4, the utility model provides an aircraft landing gear, which comprises a plurality of supporting legs 3, wherein the supporting legs 3 are uniformly distributed at the bottom of a body 1 of the aircraft along the circumferential direction, the bottom of the body 1 is provided with a plurality of through grooves 11 corresponding to the supporting legs 3 one by one, one end, close to the body 1, of each supporting leg 3 is connected with a hinge shaft 12, two ends of each hinge shaft 12 are rotatably connected with two side walls of the outer end of the corresponding through groove 11, the other end of each supporting leg 3 is connected with a roller 4 through a connecting rod 2, a first electric push rod 9 is hinged in each through groove 11, and the other end of each first electric push rod 9 is hinged with the outer wall of the bottom of the corresponding supporting leg 3.
The connecting rod 2 is equipped with the elastic buffer layer with the link of gyro wheel 4, still overlaps on the connecting rod 2 to be equipped with buffer spring 5. This setting can be when the aircraft falls to the ground, cushions fuselage 1 atress through buffer spring 5, avoids gyro wheel 4 to produce great impulsive force to fuselage 1.
One end of the first electric push rod 9 is connected with the through groove 11 through the first universal joint bearing 10, the other end of the first electric push rod 9 is connected with the supporting leg 3 through the second universal joint bearing 6, and the arrangement of the universal joint bearing improves the sensitivity of the first electric push rod 9 in the stretching process.
Be equipped with on the bottom outer wall of landing leg 3 with a 9 assorted holding tanks 8 of electric putter, this department sets up and can be when a 9 contractions of electric putter, and when landing leg 3 rotated around articulated shaft 12 and withdrawed logical groove 11, a 9 holds in holding tanks 8 of electric putter, has reduced the volume.
The number of the supporting legs 3 is not less than three. Ensuring the balance of the fuselage 1.
The rollers 4 are universal wheels.
The bottom of the machine body 1 is circular, the length of the supporting leg 3 is not more than the radius of the bottom of the machine body 1, the length of the through groove 11 is not less than the length of the supporting leg 3, and the supporting leg 3 can be effectively folded in the through groove 11.
The vertical telescopic rod 7 is fixedly connected in the through groove 11, and one end of the first electric push rod 9 is hinged to the vertical telescopic rod 7. The arrangement of the supporting leg can ensure that when the electric push rod I9 extends, the vertical telescopic rod 7 properly extends, and forms a triangle with the electric push rod I9 and the supporting leg 3, and the electric push rod I9 is matched to play a better supporting and stabilizing role for the supporting leg 3.
The vertical telescopic rod 7 is an electric push rod II.
The during operation, when transporting the aircraft, electric putter 9 contracts, make each landing leg 3 rotate around articulated shaft 12, landing leg 3 is accomodate and is gone into logical inslot 11, the total volume of aircraft has been reduced, be convenient for carry and transportation of aircraft, when the aircraft descends, electric putter 9 extension makes each landing leg 3 around articulated shaft 12 antiport, landing leg 3 is opened and is supported the aircraft, simultaneously according to the topography of landing department, the extension length of adjustable electric putter 9, change in a flexible way angle between 3 expandes backs of each landing leg and the bottom surface of fuselage 1, the bottom surface that makes fuselage 1 apart from the height-adjustable on ground, so that after landing leg 3, the bottom surface of fuselage 1 does not contact with ground, avoid the damage.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the illustrated embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. An aircraft landing gear comprising a plurality of legs, wherein: a plurality of landing legs are evenly distributed along circumference in the bottom of the fuselage of aircraft, the fuselage bottom is equipped with a plurality of logical grooves with the landing leg one-to-one, and the one end that the landing leg is close to the fuselage is connected with the articulated shaft, the both ends of articulated shaft rotate with two lateral walls of corresponding logical groove's outer end to be connected, and the other end of landing leg is connected with the gyro wheel through the connecting rod, it has electric putter one to lead to the inslot hinge connection, electric putter one's the other end is connected with the outer wall hinge of corresponding landing leg bottom.
2. An aircraft landing gear according to claim 1, wherein: the connecting rod is equipped with the elastic buffer layer with the link of gyro wheel, still overlaps on the connecting rod to be equipped with buffer spring.
3. An aircraft landing gear according to claim 1, wherein: one end of the first electric push rod is connected with the through groove through a first universal joint bearing, and the other end of the first electric push rod is connected with the supporting leg through a second universal joint bearing.
4. An aircraft landing gear according to claim 1, wherein: and the outer wall of the bottom of the supporting leg is provided with a containing groove matched with the electric push rod.
5. An aircraft landing gear according to claim 1, wherein: the number of the supporting legs is not less than three.
6. An aircraft landing gear according to claim 1, wherein: the rollers are universal wheels.
7. An aircraft landing gear according to claim 1, wherein: the bottom of the machine body is circular, the length of the supporting leg is not more than the radius of the bottom of the machine body, and the length of the through groove is not less than the length of the supporting leg.
8. An aircraft landing gear according to claim 1, wherein: the interior fixedly connected with vertical telescopic link of logical inslot, electric putter one end is connected with vertical telescopic link hinge.
9. An aircraft landing gear according to claim 8, wherein: the vertical telescopic rod is an electric push rod II.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122471257.3U CN215752989U (en) | 2021-10-13 | 2021-10-13 | Aircraft undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122471257.3U CN215752989U (en) | 2021-10-13 | 2021-10-13 | Aircraft undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215752989U true CN215752989U (en) | 2022-02-08 |
Family
ID=80095662
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122471257.3U Active CN215752989U (en) | 2021-10-13 | 2021-10-13 | Aircraft undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215752989U (en) |
-
2021
- 2021-10-13 CN CN202122471257.3U patent/CN215752989U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 454950 building 4, intelligent hardware industrial port, intersection of Zhengbei Avenue and Qinhuai Avenue, Wuzhi County, Jiaozuo City, Henan Province Patentee after: Henan Arlo Aviation Industry Co.,Ltd. Country or region after: China Address before: 454950 building 4, intelligent hardware industrial port, intersection of Zhengbei Avenue and Qinhuai Avenue, Wuzhi County, Jiaozuo City, Henan Province Patentee before: Henan Alok Industrial Co.,Ltd. Country or region before: China |
|
| CP03 | Change of name, title or address |