CN216301454U - Unmanned aerial vehicle with descending shock-absorbing function - Google Patents
Unmanned aerial vehicle with descending shock-absorbing function Download PDFInfo
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- CN216301454U CN216301454U CN202122915977.4U CN202122915977U CN216301454U CN 216301454 U CN216301454 U CN 216301454U CN 202122915977 U CN202122915977 U CN 202122915977U CN 216301454 U CN216301454 U CN 216301454U
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Abstract
The utility model discloses an unmanned aerial vehicle with landing and shock absorption functions, which comprises a body, wherein supporting legs are symmetrically arranged at the bottom of the body, an upper transverse plate, a lower transverse plate and a shock absorption system are arranged at the bottom of each supporting leg, vertical rods are symmetrically and fixedly connected to the lower surfaces of two ends of the upper transverse plate, vertical cylinders are fixedly connected to the upper surfaces of two ends of the lower transverse plate, springs are arranged in the vertical cylinders, the vertical rods are connected with the vertical cylinders in an inserting mode through the springs, the vertical rods stretch out and draw back in the vertical cylinders, and the shock absorption system is composed of at least one of the following devices: a primary damping device is arranged between the upper transverse plate and the lower transverse plate; and a secondary damping device at the bottom of the lower transverse plate. Through one-level damping device and the second grade damping device who possesses the material characteristics of economizing through the air pocket protection, absorb the reaction force when unmanned aerial vehicle opens and stops, protect each component on unmanned aerial vehicle.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle with landing shock absorption function.
Background
When unmanned aerial vehicle's descending carries out the shock attenuation, form the shock mitigation system of supporting legs for spring or support or spring and support cooperation among the prior art, the shock attenuation design of this kind of unmanned aerial vehicle supporting legs is mostly fixed assembly, has the problem that uses for a long time and be difficult for changing, and the shock mitigation system of spring or support is comparatively heavy, is unfavorable for unmanned aerial vehicle load flight, consequently stops for a long time and can't carry out good shock attenuation to unmanned aerial vehicle, and the shock attenuation effect is poor.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide an unmanned aerial vehicle with landing and shock absorption functions, which is characterized in that at least two stages of shock absorption devices are arranged on supporting legs, so that the reaction force of a ground to the unmanned aerial vehicle is buffered when the unmanned aerial vehicle lands and takes off, and the reaction force when the unmanned aerial vehicle is started and stopped is absorbed through a primary shock absorption device and a secondary shock absorption device which has the material-saving characteristic and is protected through air pockets, so that all elements on the unmanned aerial vehicle are protected.
In order to solve the technical problem, the utility model adopts the following scheme:
the utility model provides an unmanned aerial vehicle with descending shock-absorbing function, includes the fuselage to and fuselage bottom symmetry is provided with the supporting legs, the bottom of supporting legs is provided with diaphragm, lower diaphragm and shock mitigation system, the equal symmetrical rigid coupling of lower surface at last diaphragm both ends has the montant, the equal rigid coupling of upper surface at diaphragm both ends has a vertical section of thick bamboo down, be provided with the spring in the vertical section of thick bamboo, the montant passes through the spring links to each other with vertical section of thick bamboo grafting, shock mitigation system comprises at least one in the following device:
a primary damping device is arranged between the upper transverse plate and the lower transverse plate;
the embedded second grade damping device in diaphragm bottom down.
Further, the secondary damping device includes: the cylinder support element is hollow and cylindrical, the cylinder support element is an embedded hole in the lower transverse plate or a protruding portion located on the lower surface of the lower transverse plate, the other end of the cylinder support element is open, the top of the elastic stud is located in the cylinder support element, and a limiting cap is arranged at the bottom of the elastic stud.
Furthermore, the first-level damping device is a plurality of damping balls fixedly connected between the upper transverse plate and the lower transverse plate.
Furthermore, the first-level damping device is a plurality of damping springs fixedly connected between the upper transverse plate and the lower transverse plate.
Further, a sealed air pocket exists between the top of the elastic stud and the inner top wall of the cylindrical support element.
Furthermore, the elastic stud is in a hollow cylindrical shape with an opening at one end, a sealing ring is arranged on the outer surface of the opening of the elastic stud, and the sealing ring is extruded on the inner periphery of the cylindrical support element to form sealing fit.
Furthermore, a limiting ring matched with the elastic stud is arranged in the cylindrical support element.
Further, a rubber pad is arranged between the elastic stud and the limiting cap.
Furthermore, a plurality of silica gel protrusions are arranged at the bottom of the limiting cap.
The utility model has the following beneficial effects:
1. one-level damping device is mechanical shock attenuation or chemical material shock attenuation or gaseous shock attenuation, absorbs unmanned aerial vehicle's reaction force through mechanical spring's deformation, or absorbs reaction force through elastic material's such as chemical material silica gel deformation, or absorbs reaction force through the deformation of the shock attenuation ball that is full of inert gas.
2. Second grade damping device is the air shock attenuation, the inside cavity of cylindrical support component forms first space, the inside cavity of elasticity double-screw bolt forms the second space, inserts under pressure in the first space when the elasticity double-screw bolt, first space and second space intercommunication form the air pocket, and then form the damping of buffering air, the damping of buffering air cooperates with the rubber pad of elasticity double-screw bolt, absorbs the reaction force of applying on unmanned aerial vehicle.
3. The secondary damping device is of a structure with the lower transverse plate embedded inside, and the cylindrical supporting element and the elastic stud are both of hollow structures, so that materials are saved, and damping is performed through air pockets.
Drawings
Fig. 1 is a schematic perspective view of an unmanned aerial vehicle with landing shock absorption function according to the present invention;
FIG. 2 is a schematic structural view of a primary damping device of a damping ball in accordance with embodiment 1;
FIG. 3 is a schematic structural view of a primary spring shock-absorbing device in embodiment 1;
FIG. 4 is a schematic structural view of a secondary vibration damper in accordance with embodiment 2;
FIG. 5 is a schematic sectional view showing a cylindrical support member according to example 2;
FIG. 6 is a schematic view showing the structure of a shock absorbing system according to embodiment 4;
the reference numerals are explained below: 1-machine body, 2-supporting legs, 3-upper transverse plate, 4-lower transverse plate, 5-vertical rod, 6-vertical cylinder, 7-damping ball, 8-damping spring, 9-cylindrical supporting element, 10-elastic stud, 11-limiting cap, 12-rubber pad, 13-sealing ring and 14-limiting ring.
Detailed Description
The present invention will be described in further detail with reference to examples and drawings, but the present invention is not limited to these examples.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "longitudinal", "lateral", "horizontal", "inner", "outer", "front", "rear", "top", "bottom", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or the orientations or positional relationships that are conventionally placed when the products of the present invention are used, and are used only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element that is referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "open," "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example 1
The utility model provides an unmanned aerial vehicle with descending shock-absorbing function, includes fuselage 1 to and 1 bottom symmetry of fuselage is provided with supporting legs 2, the bottom of supporting legs 2 is provided with diaphragm 3, lower diaphragm 4 and shock mitigation system, the equal symmetrical rigid coupling of lower surface at 3 both ends of last diaphragm has montant 5, the equal rigid coupling of upper surface at 4 both ends of diaphragm has a vertical section of thick bamboo 6 down, be provided with the spring in the vertical section of thick bamboo 6, montant 5 passes through the spring links to each other with 6 pegs graft of vertical section of thick bamboo, shock mitigation system is: the first-level damping device is arranged between the upper transverse plate 3 and the lower transverse plate 4. The primary damping device adopts spring deformation or damping ball 7 deformation to absorb reaction force.
The primary damping device is a plurality of damping balls 7 fixedly connected between the upper transverse plate 3 and the lower transverse plate 4; or a plurality of damping springs 8 fixedly connected between the upper transverse plate 3 and the lower transverse plate 4.
When the unmanned aerial vehicle main part descends, at first the lower diaphragm 4 of supporting legs 2 will with ground contact to receive the impact force of pushing down, lower diaphragm 4 will do all can conduct to one-level damping device, absorb reaction force through one-level damping device's deformation, get montant 5 and vertical section of thick bamboo 6 through the activity between the diaphragm 4 about this moment and carry out relative motion, further absorb the impact force.
Example 2
The utility model provides an unmanned aerial vehicle with descending shock-absorbing function, includes fuselage 1 to and 1 bottom symmetry of fuselage is provided with supporting legs 2, the bottom of supporting legs 2 is provided with diaphragm 3, lower diaphragm 4 and shock mitigation system, the equal symmetrical rigid coupling of lower surface at 3 both ends of last diaphragm has montant 5, the equal rigid coupling of upper surface at 4 both ends of diaphragm has a vertical section of thick bamboo 6 down, be provided with the spring in the vertical section of thick bamboo 6, montant 5 passes through the spring links to each other with 6 pegs graft of vertical section of thick bamboo, shock mitigation system is: and the lower surface of the lower transverse plate 4 is fixedly connected with a second-stage damping device. The secondary damping device absorbs the reaction force through air damping.
Specifically, the secondary damping device includes: a plurality of cylinder support element 9, elastic stud 10, cylinder support element 9 is hollow cylindricly, cylinder support element 9 is the embedded hole in the diaphragm down, and the other end opening, elastic stud 10 top is located cylinder support element 9, elastic stud 10 bottom is equipped with spacing cap 11.
Specifically, when not compressed, the distance S between the stop cap 11 and the cylindrical support element 9 is smaller than the distance L between the top of the elastic stud 10 and the inner top wall of the cylindrical support element 9. When the secondary damping device is stressed, the distance is limited, so that when the elastic stud 10 is pressed and inserted into the cylindrical support element 9, the top of the elastic stud 10 is still spaced from the inner wall of the cylindrical support element 9 by a certain distance under the condition of non-contact through the limiting effect of the limiting cap 11, and the existence of air pockets and the damping effect are guaranteed.
Specifically, the elastic stud 10 is a hollow cylinder with an opening at one end, and a sealing ring is arranged on the outer surface of the opening of the elastic stud 10.
Specifically, a limiting ring 14 matched with the elastic stud 10 is arranged in the cylindrical support element 9. For preventing the elastic stud 10 from falling out of the cylindrical support element 9.
Specifically, a rubber pad 12 is arranged between the elastic stud 10 and the limit cap 11.
Specifically, the bottom of the limiting cap 11 is provided with a plurality of silica gel protrusions.
The cylindrical support element 9 is also of suitable dimensions so that the elastic stud 10 fits inside it.
The rubber pads 12 on the elastomeric stud base gradually absorb locally the forces exerted on the drone as required.
Specifically, the elastic stud is made of elastic materials such as rubber.
When the unmanned aerial vehicle main part descends, at first the lower diaphragm 4 of supporting legs 2 will with ground contact to receive the impact force of pushing down, conduct to second grade damping device at present the impact force, form air damping through second grade damping device, carry out energy absorption to reaction force. The inside cavity of cylindrical support element 9 forms first space, the inside cavity of elasticity double-screw bolt 10 forms the second space, inserts under pressure in the first space when elasticity double-screw bolt 10, the first space forms the air pocket with the second space intercommunication, and then forms the damping of buffering air, the damping of buffering air cooperates with rubber pad 12 of elasticity double-screw bolt 10, absorbs the reaction force of applying on unmanned aerial vehicle.
Example 3
The utility model provides an unmanned aerial vehicle with descending shock-absorbing function, includes fuselage 1 to and 1 bottom symmetry of fuselage is provided with supporting legs 2, the bottom of supporting legs 2 is provided with diaphragm 3, lower diaphragm 4 and shock mitigation system, the equal symmetrical rigid coupling of lower surface at 3 both ends of last diaphragm has montant 5, the equal rigid coupling of upper surface at 4 both ends of diaphragm has a vertical section of thick bamboo 6 down, be provided with the spring in the vertical section of thick bamboo 6, montant 5 passes through the spring links to each other with 6 pegs graft of vertical section of thick bamboo, and montant 5 is flexible in the inside of vertical section of thick bamboo 6, shock mitigation system is:
a primary damping device is arranged between the upper transverse plate 3 and the lower transverse plate 4;
and a secondary damping device at the bottom of the lower transverse plate 4.
The primary damping device and the secondary damping device are respectively the same as those of the embodiment 1 and the embodiment 2.
When the unmanned aerial vehicle main part descends, at first the lower diaphragm 4 of supporting legs 2 will with ground contact to receive the impact force of pushing down, impact force at first conducts to second grade damping device down, forms air damping through second grade damping device, carries out energy absorption to reaction force. The inside cavity of cylindrical support element 9 forms first space, the inside cavity of elasticity double-screw bolt 10 forms the second space, inserts under pressure in the first space when elasticity double-screw bolt 10, the first space forms the air pocket with the second space intercommunication, and then forms the damping of buffering air, the damping of buffering air cooperates with rubber pad 12 of elasticity double-screw bolt 10, absorbs the reaction force of applying on unmanned aerial vehicle. Secondly, the counter-impact force is transmitted to the primary damping device, the deformation of the primary damping device absorbs the counter-impact force, and at the moment, the vertical rod 5 and the vertical cylinder 6 move relatively between the upper transverse plate 4 and the lower transverse plate 4 through movement, so that the impact force is further absorbed. Through the absorption of duplex damping device to the counter-impact force, realize opening the buffering shock attenuation that stops to unmanned aerial vehicle, improve absorbing efficiency, the shock attenuation effect is showing and is improving.
This kind of secondary buffer still carries out shock attenuation protection to unmanned aerial vehicle when economizeing material, and the air pocket that forms through the space of cylindrical support element 9 and inside elastic stud 10 is right unmanned aerial vehicle carries out shock attenuation protection.
The foregoing is only a preferred embodiment of the present invention, and the present invention is not limited thereto in any way, and any simple modification, equivalent replacement and improvement made to the above embodiment within the spirit and principle of the present invention still fall within the protection scope of the present invention.
Claims (8)
1. The utility model provides an unmanned aerial vehicle with descending shock-absorbing function, includes fuselage (1) to and fuselage (1) bottom symmetry is provided with supporting legs (2), its characterized in that: the bottom of supporting legs (2) is provided with diaphragm (3), lower diaphragm (4) and shock mitigation system, the equal symmetry rigid coupling of lower surface at last diaphragm (3) both ends has montant (5), the equal rigid coupling of upper surface at diaphragm (4) both ends has a vertical section of thick bamboo (6) down, be provided with the spring in vertical section of thick bamboo (6), montant (5) are passed through the spring links to each other with vertical section of thick bamboo (6) are pegged graft, shock mitigation system comprises at least one in the device below:
a primary damping device is arranged between the upper transverse plate (3) and the lower transverse plate (4);
a secondary damping device at the bottom of the lower transverse plate (4),
the second-stage damping device comprises: a plurality of cylinder support element (9), elastic stud (10), cylinder support element (9) are hollow cylindricly, cylinder support element (9) do the embedded hole in diaphragm (4) down or be located the protruding portion of diaphragm (4) lower surface down, other end opening, elastic stud (10) top is located cylinder support element (9), elastic stud (10) bottom is equipped with stop cap (11).
2. An unmanned aerial vehicle with landing shock-absorbing function according to claim 1, characterized in that: the first-level damping device is a plurality of damping balls (7) fixedly connected between the upper transverse plate (3) and the lower transverse plate (4).
3. An unmanned aerial vehicle with landing shock-absorbing function according to claim 1, characterized in that: the first-level damping device is a plurality of damping springs (8) fixedly connected between the upper transverse plate (3) and the lower transverse plate (4).
4. An unmanned aerial vehicle with landing shock-absorbing function according to claim 1, characterized in that: and a sealed air cavity is formed between the top of the elastic stud (10) and the inner top wall of the cylindrical support element (9).
5. An unmanned aerial vehicle with landing shock-absorbing function according to claim 4, characterized in that: the elastic stud (10) is in a hollow cylindrical shape with an opening at one end, a sealing ring (13) is arranged on the outer surface of the opening of the elastic stud (10), and the sealing ring (13) is extruded on the inner periphery of the cylindrical supporting element (9) to form sealing fit.
6. An unmanned aerial vehicle with landing shock-absorbing function according to claim 5, characterized in that: and a limiting ring (14) matched with the elastic stud (10) is arranged in the cylindrical supporting element (9).
7. An unmanned aerial vehicle with landing shock-absorbing function according to claim 1, characterized in that: a rubber pad (12) is arranged between the elastic stud (10) and the limiting cap (11).
8. An unmanned aerial vehicle with landing shock-absorbing function according to claim 1, characterized in that: the bottom of the limiting cap (11) is provided with a plurality of silica gel bulges.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122915977.4U CN216301454U (en) | 2021-11-25 | 2021-11-25 | Unmanned aerial vehicle with descending shock-absorbing function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122915977.4U CN216301454U (en) | 2021-11-25 | 2021-11-25 | Unmanned aerial vehicle with descending shock-absorbing function |
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| Publication Number | Publication Date |
|---|---|
| CN216301454U true CN216301454U (en) | 2022-04-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122915977.4U Active CN216301454U (en) | 2021-11-25 | 2021-11-25 | Unmanned aerial vehicle with descending shock-absorbing function |
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| CN (1) | CN216301454U (en) |
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2021
- 2021-11-25 CN CN202122915977.4U patent/CN216301454U/en active Active
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