CN214190089U - Unmanned aerial vehicle undercarriage - Google Patents
Unmanned aerial vehicle undercarriage Download PDFInfo
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- CN214190089U CN214190089U CN202120089876.3U CN202120089876U CN214190089U CN 214190089 U CN214190089 U CN 214190089U CN 202120089876 U CN202120089876 U CN 202120089876U CN 214190089 U CN214190089 U CN 214190089U
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Abstract
The utility model provides an unmanned aerial vehicle undercarriage belongs to unmanned air vehicle technical field. It has solved current unmanned aerial vehicle undercarriage can not use under the prerequisite of guaranteeing aerodynamic performance stable, the lightweight problem of structure. The unmanned aerial vehicle undercarriage comprises a skid, a connecting assembly and a cabin door, wherein a support arm is hinged to the skid, the connecting assembly comprises a first connecting rod, a second connecting rod, a third connecting rod and a fourth connecting rod, one end of the first connecting rod is hinged to the skid, the other end of the first connecting rod is hinged to the middle of the second connecting rod, one end of the second connecting rod is hinged to the support arm, the other end of the second connecting rod is hinged to one end of the third connecting rod, the other end of the third connecting rod is hinged to a machine body, an executing element is hinged to the middle of the third connecting rod, one end of the fourth connecting rod is hinged to the cabin door, and the other end of the fourth connecting rod is hinged to the middle of the second connecting rod. This unmanned aerial vehicle undercarriage can be under the prerequisite of guaranteeing unmanned aerial vehicle aerodynamics, and it is that the unmanned aerial vehicle undercarriage uses more stably, and the structure is lightweight more.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle, a unmanned aerial vehicle undercarriage is related to.
Background
In recent years, The application of The unmanned aerial vehicle technology is more and more extensive, for example, city management, agriculture, geology, meteorology, Electric power, rescue and relief work, video shooting, etc., and The unmanned aerial vehicle has The advantages of low cost and high efficiency, and with The continuous development of The technology, The research footfall of The unmanned aerial vehicle is faster and faster in recent years, and The purpose is to develop a medium-large unmanned aerial vehicle capable of carrying people and goods and transporting, which is called as The Electric VTOL.
The Electric VTOL is a novel aircraft, which adopts a vertical take-off and landing scheme for shortening The take-off distance of The aircraft and reducing The environment required for take-off, and in order to increase The flight time and The flight distance, The aircraft can convert a rotor into a propulsion device in The flight process, so as to ensure The increase of The flight distance.
Wheeled undercarriage generally comprises bumper shock absorber, the pillar, wheel and brake equipment, its structure is complicated, buffering effect is good, but weight is heavier, great influence unmanned aerial vehicle's time of endurance, and ordinary skid formula undercarriage is all integral, and generally all be bow-shaped beam type, the support with ground contact is outwards extended downwards, its topography adaptability is high, not only can take off and land on the runway that the environment is good, also can take off and land on meadow, snow, sandy beach, gobi etc. rugged unevenness, the ground of wet smooth and soft, but general skid formula undercarriage can not pack up at aircraft flight in-process, very big influence the aerodynamic performance of aircraft at flight in-process.
Disclosure of Invention
The utility model aims at having the above-mentioned problem to current technique, provided an unmanned aerial vehicle undercarriage, the utility model aims to solve the technical problem that: make the unmanned aerial vehicle undercarriage use more stably under the prerequisite of guaranteeing aerodynamic performance, and the structure is lightweight more.
The purpose of the utility model can be realized by the following technical proposal: the utility model provides an unmanned aerial vehicle undercarriage, includes skid and hatch door, its characterized in that, swing joint has coupling assembling on the skid, coupling assembling and hatch door swing joint, just install the execute component that can drive skid and hatch door and receive and release on the coupling assembling.
The unmanned aerial vehicle landing gear comprises a skid, the bottom of the skid can be abutted against the ground, a connecting assembly is movably connected onto the skid, an executing element is movably connected onto the connecting assembly, when the unmanned aerial vehicle lands, the executive component can push the connecting component, and the connecting component drives the skid to enable the skid to be in a laying-down state, so that the skid can be abutted against the ground, when the unmanned aerial vehicle is parked, the executive component can apply force to the connecting component, so that the connecting component can prop against the skid, the skid can be ensured to be in a putting down state all the time, the unmanned aerial vehicle is ensured to be more stable in a parking state, when the unmanned aerial vehicle takes off, in order to ensure that the unmanned aerial vehicle has better pneumatic performance, the actuating element can drive the connecting component to move, and make coupling assembling drive the skid and pack up, and drive the hatch door through executive component and coupling assembling and close, guarantee the level and smooth of unmanned aerial vehicle outer wall, reduce the resistance at the flight process.
In foretell unmanned aerial vehicle undercarriage, swing joint has the support arm on the skid, coupling assembling and support arm swing joint.
Install the support arm on the skid, the one end of support arm articulates on the unmanned aerial vehicle fuselage, the other end and skid swing joint, and coupling assembling and the also swing joint of support arm, when the skid of this unmanned aerial vehicle undercarriage is put down, because only articulated relation between skid and the support arm, it is unbalanced when skid offsets with ground very likely, lead to skid and ground to support and lean on unstably, can't guarantee unmanned aerial vehicle landing, stability when parking, through installing the support arm on the skid, and carry out swing joint through coupling assembling and support arm, when the skid puts down, make coupling assembling enough drive the skid motion and also can drive the support arm motion, and move the support arm after the certain degree and can carry out spacingly to earlier stage position, guarantee that the skid can be spacing when moving furthest, guarantee that the skid lies in ground and offset when more stable.
In foretell unmanned aerial vehicle undercarriage, coupling assembling includes connecting rod one and connecting rod two, connecting rod one end is articulated with two middle parts of connecting rod, and the other end is articulated mutually with the skid, two one ends of connecting rod are articulated mutually with the support arm.
The connecting assembly comprises a first connecting rod and a second connecting rod, one end of the first connecting rod is hinged to the skid, the other end of the first connecting rod is hinged to the middle of the second connecting rod, one end of the second connecting rod is hinged to the support arm, and therefore when the landing gear is put down, two ends of the first connecting rod rotate around the hinged point to a certain angle and then are in a limited state, and the landing gear of the unmanned aerial vehicle is guaranteed to be used more stably.
In foretell unmanned aerial vehicle undercarriage, coupling assembling still includes connecting rod three and connecting rod four, three one end of connecting rod and connecting rod two are not articulated mutually with support arm articulated one end, three middle parts of connecting rod are articulated mutually with the executive component, four one end of connecting rod are articulated mutually with the hatch door, and the other end is articulated mutually with two middle parts of connecting rod.
The connecting assembly also comprises a connecting rod III and a connecting rod IV, one end of the connecting rod III is hinged with one end of the connecting rod II which is not hinged with the support arm, the other end of the connecting rod III is hinged on the body of the unmanned aerial vehicle, and the middle part of the connecting rod I is hinged with the executing element, when the connecting assembly works, the executing element drives one end of the connecting rod III which is hinged with the connecting rod to swing upwards or downwards, so that the connecting rod II drives the support arm to swing inwards or outwards, and the support arm drives the skid to move in the swinging process, the connecting rod I which is used for connecting the support arm and the skid can drive the skid to adjust, so that the included angle between the skid and the ground in the laid-down state is larger, the manufactured stability is ensured, in the folded state, the skid is ensured to be further folded upwards, the skid is ensured not to be exposed outside the body, one end of the connecting rod IV is hinged with the cabin door, the other end of the connecting rod II is hinged, in the moving process of the connecting rod II, the second connecting rod can also drive the fourth connecting rod to move, so that the fourth connecting rod drives the cabin door to move, when the skid is put down, the cabin door is ensured to be opened, the skid and the support arm can be put down, the skid is folded to enable the cabin door to be closed and matched with the outer surface of the unmanned aerial vehicle, the outer surface of the unmanned aerial vehicle is planar, and the pneumatic performance of the unmanned aerial vehicle is ensured to be better when the unmanned aerial vehicle flies.
In the landing gear of the unmanned aerial vehicle, the cabin door is integrally formed with a plurality of hinged protruding heads for fixing the cabin door.
The cabin door is also integrally formed with a plurality of hinged raised heads, and the cabin door can be hinged with the cabin body through the hinged raised heads, so that the subsequent cabin door can be timely disassembled and maintained when deformed.
In the landing gear of the unmanned aerial vehicle, the actuating element is a hydraulic actuator cylinder.
The simple structure of hydraulic actuator, and the pressure of during operation output also can reach great pressure, can guarantee that this unmanned aerial vehicle undercarriage lasts output pressure in the use always, guarantees that this unmanned aerial vehicle undercarriage uses more stably.
In the landing gear of the unmanned aerial vehicle, the support arm and the skid are made of composite materials.
The support arm all adopts combined material to make with the skid, compares in the alloy material among the prior art, adopts combined material more light, guarantees that this unmanned aerial vehicle undercarriage is lighter more.
Compared with the prior art, this unmanned aerial vehicle undercarriage has following advantage:
one, swing joint has coupling assembling on this skid in the unmanned aerial vehicle undercarriage, installs the execute component on the coupling assembling, and the execute component drives coupling assembling and rotates to make coupling assembling make the skid pack up or put down according to unmanned aerial vehicle's operating condition, guarantee that unmanned aerial vehicle resistance is littleer at flight in-process, and pneumatic performance is better.
The connecting assembly comprises a first connecting rod, a second connecting rod and a third connecting rod, one end of the first connecting rod is hinged to the skid, the other end of the first connecting rod is hinged to the middle of the second connecting rod, one end of the second connecting rod is hinged to the support arm, the other end of the second connecting rod is hinged to the third connecting rod, an executing element is hinged to the middle of the third connecting rod, the third connecting rod is driven by the executing element to rotate, the second connecting rod drives the second connecting rod, the second connecting rod drives the support arm to move with the first connecting rod, the first connecting rod drives the skid to be folded or unfolded in the moving process, the first connecting rod drives the skid to be folded and unfolded in the rotating process, and the first connecting rod, the second connecting rod and the support arm are matched to ensure that the skid is limited when being folded and unfolded to a certain degree, and the unmanned aerial vehicle is guaranteed to be more stable when being descended and parked.
Third, coupling assembling still includes connecting rod four, and four one ends of connecting rod are articulated with the hatch door, and the other end is articulated with connecting rod two, and executive component can drive four messenger's hatchdoors of connecting rod in time to open or be closed through connecting rod two when flexible, and guarantees that the unmanned aerial vehicle fuselage is more level and smooth after the closure, and pneumatic performance is better.
And fourthly, a plurality of hinged raised heads are integrally formed on the cabin door, and the cabin door can be hinged with the fuselage through the hinged raised heads, so that the cabin door can be timely detached and maintained when deformed.
Drawings
Fig. 1 is a schematic structural diagram of the landing gear of the unmanned aerial vehicle when being retracted.
Fig. 2 is a schematic structural view of the landing gear of the unmanned aerial vehicle when the landing gear is down.
Fig. 3 is a schematic diagram of the structure of the connecting assembly and the actuator of the landing gear of the unmanned aerial vehicle.
In the figure, 1, a skid; 1a, a connecting component; 1a1, connecting rod one; 1a2 and a second connecting rod; 1a3 and a third connecting rod; 1a4, link four; 1b, an actuator; 1c, a support arm; 2. a cabin door; 2a, hinging the raised head.
Detailed Description
The following are specific embodiments of the present invention and the accompanying drawings are used to further describe the technical solution of the present invention, but the present invention is not limited to these embodiments.
As shown in fig. 1-3, the landing gear of the unmanned aerial vehicle comprises a skid 1 and a support arm 1c made of composite materials, wherein the skid 1 can be made of carbon fiber epoxy resin matrix composite materials, glass fiber epoxy resin matrix composite materials and other composite materials, and has the advantages of light weight and high hardness, the bottom of the skid 1 can be abutted against the ground, the skid 1 comprises two first vertical rods, the top of each first vertical rod is provided with a first hinge part, the support arm 1c is provided with two second vertical rods, the bottom end of each second vertical rod is provided with a second hinge part, the support arm 1c is hinged with the skid 1 through the first hinge part and the second hinge part, the skid 1 can rotate around the hinge point when in use, the top end of each second vertical rod is provided with a third hinge part, the support arm 1c can be hinged with the body of the unmanned aerial vehicle through the third hinge part, and the skid 1 and the support arm 1c can be folded through multiple hinge parts to ensure smaller volume, is easier to store in the machine body.
As shown in fig. 1-3, the landing gear of the drone further includes a connecting assembly 1a and a door 2, the connecting assembly 1a is specifically composed of a first connecting rod 1a1, a second connecting rod 1a2, a third connecting rod 1a3 and a fourth connecting rod 1a4, the first connecting rod 1a1, the second connecting rod 1a2, the third connecting rod 1a3 and the fourth connecting rod 1a4 are all in a flat plate shape, the skid 1 further includes a first cross rod, the first cross rod is integrally formed on the outer side wall of the middle portion of the first hinge plate, one end of the first connecting rod 1a1 is hinged to the first hinge plate, the other end extends to the middle portion of the second connecting rod 1a2 and is hinged to the outer wall of the middle portion of the second connecting rod 1a2, the support arm 1c further includes a second cross rod, the second cross rod is integrally formed on the outer side wall of the middle portion of the second cross rod, one hinge plate 2 is hinged to the two hinge plates, the other end is hinged to one end of the third connecting rod 1a3, the other end of the third connecting rod 1a3 extends to the inside of the drone body and is hinged to the drone body, a hinged plate III is integrally formed on the inner side wall of the cabin door 2, one end of a connecting rod IV 1a4 is hinged with the hinged plate IV, the other end of the connecting rod IV extends to the position close to the middle part of a connecting rod II 1a2 and is hinged with the middle part of a connecting rod II 1a2, an executing element 1b is installed at the middle part of a connecting rod III 1a3, the executing element 1b is specifically a hydraulic actuating cylinder or an air actuating cylinder, the number of the executing elements 1b is at least one, one end of the executing element 1b is hinged with the middle part of the connecting rod III 1a3, the other end of the executing element extends to the unmanned aerial vehicle body and is hinged with the unmanned aerial vehicle body, when the unmanned aerial vehicle landing gear is put down, the executing element 1b extends to push the connecting rod III 1a3 to swing downwards, the connecting rod III 1a3 drives the connecting rod II 1a2 to move, and the connecting rod II 1a2 can drive the support arm 1c to rotate outwards and drive the connecting rod I1 a1 to move, the connecting rod I1 a1 is made to drive the skid 1 to move, the connecting rod II 1a2 is made to drive the support arm 1c to move in the moving process, the skid 1 hinged with the support arm 1c rotates outwards along with the support arm 1c to enable the skid to be in a put-down state, the connecting rod I1 a1 is made to drive the skid 1 to rotate to a certain angle around the hinged position of the skid 1 and the support arm 1c and then is limited, the skid 1 can be kept still under the condition of pressure continuously output by the execution element 1b, the unmanned aerial vehicle landing gear is guaranteed to be more stable when the unmanned aerial vehicle lands and parks, in addition, normal direction, lateral direction and course load born by the unmanned aerial vehicle landing gear can be effectively transmitted to the landing gear through transmission of all the connecting rods, and the load born by the unmanned aerial vehicle landing gear is reduced.
As shown in fig. 1-3, when the landing gear is retracted, the actuator 1b contracts and drives one end of the connecting rod three 1a3 hinged to the connecting rod two 1a2 to lift upwards, the connecting rod two 1a2 drives the support arm 1c to retract inwards, and simultaneously drives the connecting rod one 1a1 to move, so that the end of the connecting rod one 1a1 drives the sled 1 to rotate, the connecting rod two 1a2 drives the support arm 1c to rotate and retract into the fuselage, the connecting rod one 1a1 drives the sled 1 to rotate, so that the sled 1 is also fully retracted into the fuselage, in addition, the connecting rod two 1a2 also drives the connecting rod four 1a4 to move, so that the connecting rod four 1a4 drives the hatch 2 plate to cover, thereby ensuring that the outer surface of the fuselage of the unmanned aerial vehicle is smoother, better in air mobility during flight, and in addition, each connecting rod can be replaced by a hollow tube and a joint.
Still integrated into one piece has two articulated plush copper 2a on the inside wall face of hatch door 2, and hatch door 2 can rely on articulated plush copper 2a to articulate with the unmanned aerial vehicle fuselage, guarantees that hatch door 2 can dismantle the maintenance if appear when warping in subsequent use.
When the actuator 1b contracts, the first pushing link 1a1, the second pushing link 1a2, the third pushing link 1a3, the fourth pushing link 1a4, the support arm 1c and the skid 1 move, so that the whole landing gear gradually retracts, when the actuator 1b extends, the first pushing link 1a1, the second pushing link 1a2, the third pushing link 1a3, the fourth pushing link 1a4, the support arm 1c and the skid 1 move, the landing gear gradually lowers, and finally reaches a designated position, and the unmanned aerial vehicle can be ensured to land normally.
The specific embodiments described herein are merely illustrative of the spirit of the invention. Various modifications, additions and substitutions for the specific embodiments described herein may be made by those skilled in the art without departing from the spirit of the invention or exceeding the scope of the invention as defined in the accompanying claims.
Although the terms connecting assembly 1a, link one 1a1, link two 1a2, link three 1a3, link four 1a4, arm 1c, door 2, hinge projection 2a, etc., are used more herein, the possibility of using other terms is not excluded. These terms are used merely to more conveniently describe and explain the nature of the present invention; they are to be construed in a manner that is inconsistent with the spirit of the invention.
Claims (7)
1. The utility model provides an unmanned aerial vehicle undercarriage, includes skid (1) and hatch door (2), its characterized in that, swing joint has coupling assembling (1a) on skid (1), coupling assembling (1a) and hatch door (2) swing joint, just install on coupling assembling (1a) and can drive skid (1) and hatch door (2) and carry out execute component (1b) that receive and releases.
2. The undercarriage for unmanned aerial vehicles according to claim 1, wherein the skid (1) is movably connected with a support arm (1c), and the connecting assembly (1a) is movably connected with the support arm (1 c).
3. The drone landing gear of claim 2, wherein the connection assembly (1a) comprises a first link (1a1) and a second link (1a2), the first link (1a1) being hinged at one end to the middle of the second link (1a2) and at the other end to the skid (1), and the second link (1a2) being hinged at one end to the arm (1 c).
4. The drone landing gear according to claim 3, wherein the connection assembly (1a) further comprises a third link (1a3) and a fourth link (1a4), the third link (1a3) being hinged at one end to the second link (1a2) at the end not hinged to the arm (1c), the third link (1a3) being hinged at its middle to the actuator (1b), and the fourth link (1a4) being hinged at one end to the door (2) and at the other end to the second link (1a2) at its middle.
5. The unmanned landing gear according to claim 1 or 4, wherein the door (2) has integrally formed thereon several articulated noses (2a) for fixing the door (2).
6. An unmanned aircraft landing gear according to claim 1 or 4, wherein the actuator (1b) is a hydraulic ram.
7. The unmanned landing gear of any of claims 2 to 4, wherein the arm (1c) and the skid (1) are formed of a composite material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120089876.3U CN214190089U (en) | 2021-01-13 | 2021-01-13 | Unmanned aerial vehicle undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120089876.3U CN214190089U (en) | 2021-01-13 | 2021-01-13 | Unmanned aerial vehicle undercarriage |
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| Publication Number | Publication Date |
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| CN214190089U true CN214190089U (en) | 2021-09-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120089876.3U Active CN214190089U (en) | 2021-01-13 | 2021-01-13 | Unmanned aerial vehicle undercarriage |
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| CN (1) | CN214190089U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114408165A (en) * | 2022-03-30 | 2022-04-29 | 沃飞长空科技(成都)有限公司 | Link mechanism and contain this link mechanism's undercarriage, aircraft |
| CN116101482A (en) * | 2023-04-17 | 2023-05-12 | 成都沃飞天驭科技有限公司 | Aircraft test platform, landing gear thereof and design method of landing gear |
-
2021
- 2021-01-13 CN CN202120089876.3U patent/CN214190089U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114408165A (en) * | 2022-03-30 | 2022-04-29 | 沃飞长空科技(成都)有限公司 | Link mechanism and contain this link mechanism's undercarriage, aircraft |
| CN114408165B (en) * | 2022-03-30 | 2022-06-14 | 沃飞长空科技(成都)有限公司 | Link mechanism and undercarriage and aircraft comprising same |
| CN116101482A (en) * | 2023-04-17 | 2023-05-12 | 成都沃飞天驭科技有限公司 | Aircraft test platform, landing gear thereof and design method of landing gear |
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