CN210416967U - Landing gear with damping function for aircraft - Google Patents
Landing gear with damping function for aircraft Download PDFInfo
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- CN210416967U CN210416967U CN201921409269.XU CN201921409269U CN210416967U CN 210416967 U CN210416967 U CN 210416967U CN 201921409269 U CN201921409269 U CN 201921409269U CN 210416967 U CN210416967 U CN 210416967U
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- outer sleeve
- sleeve
- base
- landing gear
- hinged
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Abstract
The utility model discloses a landing gear with shock-absorbing function for aircraft, which comprises a base, an outer sleeve, an inner sleeve, a support rod, a roller, a connecting rod and a driving component, wherein the outer sleeve is hinged with the base through the connecting rod, the upper end of the inner sleeve is embedded into the outer sleeve, the lower end of the inner sleeve is hinged with the roller through the support rod, the driving component is hinged on the base, the driving component is positioned at one side of the outer sleeve and is in transmission connection with the outer sleeve, in the landing gear with shock-absorbing function for aircraft, when the roller contacts the ground, the roller can transmit acting force to the inner sleeve through the support rod, at the moment, the inner sleeve can move towards the inner part of the outer sleeve under the buffer action between a rubber ring and a buffer groove, when moving to the top end of the outer sleeve, the rubber ball can buffer for the second, the structure is simple, a good buffering effect can be achieved, and the landing safety of the airplane is improved.
Description
Technical Field
The utility model relates to a shock attenuation technical field, concretely relates to a landing gear that has shock-absorbing function for aircraft.
Background
In current aircraft undercarriage, the aircraft is when descending, all can add hydraulic buffer gear in the undercarriage, effectively cushions when coming to the aircraft landing, but because the effort that buffer gear gives the undercarriage at the brake that touches ground is huge, and then causes buffer gear to damage easily, in addition because the mechanism of undercarriage is complicated, in case the trouble is just difficult to maintain, will change even, has just increased cost of maintenance this moment.
SUMMERY OF THE UTILITY MODEL
The utility model provides an overcome foretell not enough, provide a landing gear who is used for having shock-absorbing function of aircraft.
The utility model discloses a following technical scheme realizes above-mentioned purpose:
a landing gear with a shock absorption function for an aircraft comprises a base, an outer sleeve, an inner sleeve, a supporting rod, a roller, a connecting rod and a driving assembly, wherein the outer sleeve is hinged with the base through the connecting rod, the upper end of the inner sleeve is embedded into the outer sleeve, the lower end of the inner sleeve is hinged with the roller through the supporting rod, the driving assembly is hinged on the base, and the driving assembly is positioned on one side of the outer sleeve and is in transmission connection with the outer sleeve;
the periphery cover that interior sleeve pipe is located one section of outer tube is equipped with a plurality of rubber bands, and the inner wall of outer tube is equipped with a plurality of dashpots, and during the rubber band can be embedded into the dashpot, be equipped with a plurality of rubber balls that set gradually between the inner wall of interior sheathed tube tip and outer tube.
In the landing gear with the shock absorption function for the airplane, the base is arranged at the bottom of the airplane, the conventional shock absorption mechanism is arranged between the base and the base of the airplane, when the airplane lands, the outer sleeve is driven to be in a vertical state by the driving assembly, when the roller contacts the ground, the primary shock absorption can be carried out through the landing gear, then the shock absorption mechanism carries out the secondary shock absorption, the impact force on the shock absorption mechanism is reduced, the shock absorption mechanism is protected, after the roller contacts the ground, the roller can transmit the acting force to the inner sleeve through the supporting rod, at the moment, the inner sleeve can move towards the inside of the outer sleeve under the buffer action between the rubber ring and the buffer groove, when the rubber ball moves to the top end of the outer sleeve, the rubber ball can carry out the secondary buffer, the position between the inner sleeve and the outer sleeve can also be reset, the landing gear is simple in structure, the safety of the aircraft landing is improved.
Preferably, the driving assembly comprises a cylinder, the end of the cylinder is hinged to the base, a piston rod of the cylinder is hinged to one side of the outer sleeve, the cylinder can pull or push the outer sleeve through the piston rod, and when the cylinder is located on the left side of the outer sleeve, the cylinder contracts to pull out the outer sleeve, so that the outer sleeve is vertical; when the cylinder is positioned on the right side of the outer sleeve, the cylinder stretches out to push the outer sleeve, so that the outer sleeve is vertical.
Preferably, the number of the connecting rods is two, the two connecting rods are respectively positioned at two sides of the outer sleeve, and when the outer sleeve rotates, the outer sleeve can be balanced through the two connecting rods, so that the landing reliability is improved.
Preferably, the base is fixed at the bottom of the airplane, the lower end face of the base is provided with a containing groove, and the air cylinder can control the outer sleeve to be contained in the containing groove through the piston rod.
Preferably, the number of the rubber bands is three, and the number of the buffer grooves is three.
Preferably, both ends of the inner sleeve are sealed, and one end of the outer sleeve connected with the inner sleeve is open.
The utility model has the advantages that: this a landing gear that is used for having shock-absorbing function of aircraft, when the gyro wheel contacted ground, the gyro wheel will transmit the effort for interior sleeve pipe through the bracing piece, interior sleeve pipe will be under the cushioning effect between rubber circle and buffer slot this moment, toward the inside removal of outer tube, when removing to the outer tube top, the rubber ball will carry out the buffering of second time, and can also make the position reset between interior sleeve pipe and the outer tube, this simple structure, and can play fine buffering effect, the security that the aircraft descends has been improved.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
fig. 1 is a schematic structural diagram of the present invention;
fig. 2 is a schematic structural view of the outer sleeve and the inner sleeve according to the present invention.
In the figure: 1. the device comprises a base, 2 parts of an outer sleeve, 3 parts of a connecting rod, 4 parts of an inner sleeve, 5 parts of a supporting rod, 6 parts of a roller, 7 parts of an air cylinder, 8 parts of a piston rod, 9 parts of a rubber ring and 10 parts of a rubber ball.
Detailed Description
The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic drawings and illustrate the basic structure of the present invention only in a schematic manner, and thus show only the components related to the present invention.
As shown in fig. 1 and 2, a landing gear with a shock absorption function for an aircraft comprises a base 1, an outer sleeve 2, an inner sleeve 4, a support rod 5, a roller 6, a connecting rod 3 and a driving assembly, wherein the outer sleeve 2 is hinged with the base 1 through the connecting rod 3, the upper end of the inner sleeve 4 is embedded into the outer sleeve 2, the lower end of the inner sleeve 4 is hinged with the roller 6 through the support rod 5, the driving assembly is hinged on the base 1, and the driving assembly is positioned at one side of the outer sleeve 2 and is in transmission connection with the outer sleeve 2;
the periphery cover that interior sleeve pipe 4 is located one section of outer tube 2 is equipped with a plurality of rubber bands, and the inner wall of outer tube 2 is equipped with a plurality of dashpots, and during the rubber band can be embedded into the dashpot, be equipped with a plurality of rubber balls 10 that set gradually between the tip of interior sleeve pipe 4 and the inner wall of outer tube 2.
In this example: the driving assembly comprises a cylinder 7, the end part of the cylinder 7 is hinged on the base 1, a piston rod 8 of the cylinder 7 is hinged with one side of the outer sleeve 2, the cylinder 7 can pull or push the outer sleeve 2 through the piston rod 8, when the cylinder 7 is positioned at the left side of the outer sleeve 2, the cylinder 7 contracts, namely the outer sleeve 2 is pulled out, so that the outer sleeve 2 is vertical; when the cylinder 7 is located at the right side of the outer sleeve 2, the cylinder 7 is extended to push the outer sleeve 2, so that the outer sleeve 2 is vertical.
In this example: the number of the connecting rods 3 is two, the two connecting rods 3 are respectively positioned on two sides of the outer sleeve 2, and when the outer sleeve 2 rotates, the outer sleeve 2 can be balanced through the two connecting rods 3, so that the landing reliability is improved.
In this example: the base 1 is fixed in the bottom of aircraft, and the lower terminal surface of base 1 has seted up and has accomodate the groove, and the cylinder 7 can control outer tube 2 to accomodate in the groove through piston rod 8.
In this example: the number of the rubber rings is three, and the number of the buffer grooves is three.
In this example: the two ends of the inner sleeve 4 are sealed, and one end of the outer sleeve 2 connected with the inner sleeve 4 is open.
In light of the above, the present invention is not limited to the above embodiments, and various changes and modifications can be made by the worker without departing from the scope of the present invention. The technical scope of the present invention is not limited to the content of the specification, and must be determined according to the scope of the claims.
Claims (6)
1. A landing gear with shock absorbing capabilities for an aircraft, characterized by: the device comprises a base, an outer sleeve, an inner sleeve, a supporting rod, a roller, a connecting rod and a driving assembly, wherein the outer sleeve is hinged with the base through the connecting rod, the upper end of the inner sleeve is embedded into the outer sleeve, the lower end of the inner sleeve is hinged with the roller through the supporting rod, the driving assembly is hinged on the base, and the driving assembly is positioned on one side of the outer sleeve and is in transmission connection with the outer sleeve;
the periphery cover that interior sleeve pipe is located one section of outer tube is equipped with a plurality of rubber bands, and the inner wall of outer tube is equipped with a plurality of dashpots, and during the rubber band can be embedded into the dashpot, be equipped with a plurality of rubber balls that set gradually between the inner wall of interior sheathed tube tip and outer tube.
2. A landing gear with shock absorbing function for an aircraft according to claim 1, wherein: the driving assembly comprises an air cylinder, the end part of the air cylinder is hinged to the base, and a piston rod of the air cylinder is hinged to one side of the outer sleeve.
3. A landing gear with shock absorbing function for an aircraft according to claim 1, wherein: the number of connecting rods is two, and two connecting rods are located the both sides of outer tube respectively.
4. A landing gear with shock absorbing function for an aircraft according to claim 1, wherein: the base is fixed in the bottom of aircraft, and the lower terminal surface of base has seted up and has accomodate the groove, and the cylinder can control the outer tube and accomodate in accomodating the groove through the piston rod.
5. A landing gear with shock absorbing function for an aircraft according to claim 1, wherein: the number of the rubber rings is three, and the number of the buffer grooves is three.
6. A landing gear with shock absorbing function for an aircraft according to claim 1, wherein: the two ends of the inner sleeve are sealed, and one end of the outer sleeve connected with the inner sleeve is open.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921409269.XU CN210416967U (en) | 2019-08-27 | 2019-08-27 | Landing gear with damping function for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921409269.XU CN210416967U (en) | 2019-08-27 | 2019-08-27 | Landing gear with damping function for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210416967U true CN210416967U (en) | 2020-04-28 |
Family
ID=70365416
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921409269.XU Active CN210416967U (en) | 2019-08-27 | 2019-08-27 | Landing gear with damping function for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210416967U (en) |
-
2019
- 2019-08-27 CN CN201921409269.XU patent/CN210416967U/en active Active
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