CN210822736U - Unmanned aerial vehicle undercarriage with damping in rotation direction - Google Patents
Unmanned aerial vehicle undercarriage with damping in rotation direction Download PDFInfo
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- CN210822736U CN210822736U CN201921334765.3U CN201921334765U CN210822736U CN 210822736 U CN210822736 U CN 210822736U CN 201921334765 U CN201921334765 U CN 201921334765U CN 210822736 U CN210822736 U CN 210822736U
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- rotating shaft
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Abstract
An unmanned aerial vehicle undercarriage with damping in a rotation direction comprises a steering engine mounting box supported on a damping device through a rotating shaft, wherein a steering engine is arranged in the steering engine mounting box, the output end of the steering engine is connected with the rotating shaft through a connecting rod mechanism, the damping device can be driven to change the direction through the rotating shaft, and the bottom of the damping device is connected with an airplane wheel through a support frame; damping device includes first hinge and the second hinge of upper and lower interval and articulated together, and interval space arrangement between first hinge and the second hinge has a plurality of arc stretch cords, and the circular arc direction of arc stretch cord is the pressurized direction, and the arc stretch cord passes through the top board and fixes respectively on the surface of first hinge and second hinge with lower clamp plate, and the pin joint of first hinge and second hinge sets up the hinge joint, and trompil and erection pin axle are connected on the hinge joint. The utility model provides an unmanned aerial vehicle the problem of the bounce of jolting from top to bottom to can prevent to turn to the gear damage in the steering wheel, the windward resistance is little simultaneously, can obtain more during voyages and universities.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle undercarriage, concretely relates to rotation direction has damped unmanned aerial vehicle undercarriage.
Background
With the rapid development of industrial technology, the application of the unmanned aerial vehicle is more and more extensive, and the unmanned aerial vehicle occupies an important position in various fields, and a lot of new demands are generated on accessories of the unmanned aerial vehicle. At present, the undercarriage mechanism of small and medium-sized fixed wing unmanned aerial vehicle is various in form, but the structural principle is different greatly, and the undercarriage mechanism is composed of a wheel and a spring shock absorber (or a gas spring) and a fixing structure. Unmanned aerial vehicle is taking off and when descending, because the condition on runway road surface, the gesture of aircraft then is different, can make unmanned aerial vehicle vibrations. The damping of the landing gear is particularly important at this point. Common undercarriage can transmit damping device (spring damper, air spring) with the impact force that the wheel received, through damping device, the impact force becomes gentle then reaches the fuselage, and unmanned aerial vehicle's vibrations will reduce, and this makes unmanned aerial vehicle take off and land will be very gentle, and the security is higher.
Because the drive form of medium and small-sized unmanned aerial vehicle is motor drive, and the battery is as the energy, so can consider losing weight and drag reduction on whole optimization, but spring and gas spring are bigger in the vertical direction size, so the air resistance of whole undercarriage is bigger. I and spring receive to strike the back convert kinetic energy into elastic potential energy, then release fast again, can make unmanned aerial vehicle play certain displacement volume, because the release time is short, can make unmanned aerial vehicle jolt when descending on the runway. When the wheels rotate in the direction, as no damping exists in the rotating square, larger impulsive force is directly applied to the steering gear, and the steering gear is damaged.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to the problem among the above-mentioned prior art, a rotation direction has damped unmanned aerial vehicle undercarriage is provided, has light in weight, the little advantage of size to can prevent to turn to the gear damage in the steering wheel.
In order to realize the purpose, the utility model discloses a technical scheme be:
the steering engine mounting box is supported on the damping device through a rotating shaft, a steering engine is arranged in the steering engine mounting box, the output end of the steering engine is connected with the rotating shaft through a connecting rod mechanism, the damping device can be driven to change the direction through the rotating shaft, and the bottom of the damping device is connected with an airplane wheel through a support frame; damping device include interval and articulated first hinge and the second hinge together from top to bottom, the interval space arrangement between first hinge and the second hinge has a plurality of arc stretch cords, and the circular arc direction of arc stretch cord is the pressurized direction, and the arc stretch cord passes through the top board and fixes respectively on the surface of first hinge and second hinge with lower clamp plate, the pin joint of first hinge and second hinge sets up the hinge joint, and trompil and erection pin axle are connected on the hinge joint.
Preferably, the output end of the steering engine is arranged upwards, rocker arms are arranged at the output end of the steering engine and the end part of the rotating shaft, the two rocker arms are connected through a connecting rod mechanism, and the connecting rod mechanism comprises a pull rod and ball heads arranged at two ends of the pull rod.
Preferably, the rotating shaft penetrates out from the bottom surface to the top surface of the steering engine mounting box, and a bearing is arranged at the joint of the steering engine mounting box and the rotating shaft.
Preferably, the cross section of the arc-shaped elastic rope is circular, the arc-shaped elastic rope can rotate along a mounting groove formed by the hinge and the pressing plate, a hole in the hinge joint is a U-shaped hole, and the pin shaft can swing in the allowance space in the U-shaped hole.
Preferably, the arc-shaped elastic ropes are all processed by steel wire ropes.
Preferably, the hinge joint is processed at the end part of the second hinge, the end part of the first hinge is L-shaped, and the end part of the first hinge extends downwards into the hinge joint through the connecting part and is connected together through the pin shaft.
Preferably, the support frame adopts a plate, is arranged outside the end surfaces of the two sides of the wheel and is connected with the center of the wheel.
Preferably, the steering engine mounting box is provided with a plurality of through holes corresponding to the positions of the steering engine arrangement.
Compared with the prior art, the utility model discloses following beneficial effect has: during operation is by steering wheel drive pivot, and damping device's first hinge is connected in the pivot, with power transmission to the arc stretch cord on, through the damping effect of a plurality of arc stretch cords with power again reach damping device's second hinge, the second hinge passes through the support frame and connects the wheel, then drive unmanned aerial vehicle's wheel turns to. In the vertical direction, the wheel of unmanned aerial vehicle when descending receives the impact load on perpendicular ground, transmits the stretch cord through the wheel, and after the stretch cord carries out the shock attenuation, the first hinge that reaches damping device again finally reaches unmanned aerial vehicle's organism for unmanned aerial vehicle descending vibrations are little, and is more gentle, avoids the steering wheel gear to damage. The utility model discloses a simple mechanism obtains required shock attenuation effect, and structure light in weight to the structure is small, so makes unmanned aerial vehicle's windward resistance just less, can obtain more time-of-flight.
Further, the utility model discloses a wire rope has solved the problem of unmanned aerial vehicle bounce from top to bottom as shock attenuation buffer, and the cross-section of arc stretch cord is circular, and the arc stretch cord can be followed the mounting groove rotation that hinge and clamp plate formed, and the hole on the hinge joint is U type hole, and the surplus space swing that the round pin axle can be in U type hole has realized turning to the shock attenuation on perpendicular absorbing basis. The first hinge and the second hinge are cylindrical hinges, and the problem that the wheel is inclined due to large unilateral deformation of the damping device is solved.
Drawings
Fig. 1 is a perspective view of the overall structure of the present invention;
FIG. 2 is a front view of the overall structure of the present invention;
FIG. 3 is a cross-sectional view of the overall structure of the present invention;
FIG. 4 is a schematic view of a U-shaped hole structure of the hinge joint of the present invention;
in the drawings: 1-a steering engine mounting box; 2-a rotating shaft; 3-a first hinge; 4-a second hinge; 5, an upper pressing plate; 6, pressing a lower plate; 7-rotating shaft rocker arm; 8-a bearing sleeve; 9-hinge joint; 10-a pin shaft; 11-a steering engine rocker arm; 12-a pull rod; 13-a steering engine; 14-arc elastic cord; 15-a support frame; 16-a ball head; 17-a bearing; 18-hole.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
Unmanned aerial vehicle undercarriage in the past adopts spring damper or air spring as damper, and is bigger at the size of vertical direction, and the air resistance that causes whole undercarriage is also bigger, and the spring receives to convert kinetic energy into elastic potential energy after assaulting, then releases fast again, and release time is shorter, can make unmanned aerial vehicle produce when descending on the runway jolt. Meanwhile, when the wheels of the unmanned aerial vehicle rotate, the steering engine which drives the steering wheel to turn is easy to cause gear damage because the rotating direction is not damped.
Referring to fig. 1-3, the utility model discloses an unmanned aerial vehicle undercarriage, including steering wheel mounting box 1, damping device and the support frame 15 of connecting the wheel, steering wheel mounting box 1 sets up steering wheel 13 in the middle of steering wheel mounting box 1 on damping device through 2 supports of pivot, and steering wheel 13's output passes through link mechanism and links to each other with pivot 2, can drive damping device redirecting through pivot 2.
The output end of the steering engine 13 is arranged upwards, rocker arms are arranged at the output end of the steering engine 13 and the end part of the rotating shaft 2, the two rocker arms are connected through a connecting rod mechanism, and the connecting rod mechanism comprises a pull rod 12 and ball heads 16 arranged at two ends of the pull rod 12. The rotating shaft 2 penetrates out from the bottom surface to the top surface of the steering engine mounting box 1, and a bearing 17 is arranged at the joint of the steering engine mounting box 1 and the rotating shaft 2 through a bearing sleeve 8.
Damping device includes first hinge 3 and second hinge 4 that upper and lower interval and articulated together, and the tip of first hinge 3 is the L type, and the interval space arrangement between first hinge 3 and the second hinge 4 has a plurality of arc elastic ropes 14, and arc elastic rope 14 all adopts wire rope processing to form. The arc direction of arc stretch cord 14 is the pressurized direction, arc stretch cord 14 passes through top board 5 and holding down plate 6 to be fixed respectively on first hinge 3 and second hinge 4's surface, the pin joint of first hinge 3 and second hinge 4 sets up hinged joint 9, hinged joint 9 processing is at the tip of second hinge 4, trompil and erection pin axle 10 are connected on hinged joint 9, the tip of first hinge 3 stretches into hinged joint 9 through connecting portion downwards to link together through round pin axle 10.
Referring to fig. 4, the cross section of the arc elastic rope 14 is circular, the arc elastic rope 14 can rotate along a mounting groove formed by the hinge and the pressing plate, the hole on the hinge joint 9 is a U-shaped hole, and the pin shaft 10 can swing in the allowance space in the U-shaped hole.
The support frame 15 for mounting the wheel is a plate, is arranged outside the end surfaces of the two sides of the wheel and is connected with the center of the wheel. A plurality of through holes are formed in the positions, corresponding to the steering engines 13, of the steering engine mounting box 1, heat dissipation is carried out through the through holes, and parts are convenient to disassemble and assemble.
The utility model discloses a theory of operation and technological effect do:
turning direction:
the undercarriage is characterized in that a rotating shaft 2 is driven by a steering engine 13, the rotating shaft 2 is connected with a first hinge 3 of a composite hinge, force is transmitted to a steel wire rope, the force is transmitted to a second hinge 4 connected with the airplane wheel assembly under the damping action of the steel wire rope, and then the airplane wheel is driven to steer.
Vertical direction:
unmanned aerial vehicle wheel receives perpendicular ground's impact load when descending, passes to wire rope through the wheel, and after the wire rope shock attenuation, the first hinge 3 of compound hinge is arrived again, finally reaches unmanned aerial vehicle's organism for unmanned aerial vehicle descending vibrations are little, and are mild.
The utility model discloses a wire rope has solved the problem of the unmanned aerial vehicle bounce of jolting from top to bottom as shock attenuation buffer. And a steel wire rope is used as a damping buffer device, so that steering damping is realized. The cylindrical hinge is adopted, so that the problem that the wheel is inclined due to large unilateral deformation of the steel wire rope shock absorber is solved. The required shock absorption effect is obtained through a simple mechanism, and the structure weight is lighter.
The utility model discloses an undercarriage structure is small, so unmanned aerial vehicle's windward resistance is just less, can obtain more time-of-flight.
Claims (6)
1. The utility model provides a direction of rotation has damped unmanned aerial vehicle undercarriage which characterized in that: the steering engine damping device comprises a steering engine mounting box (1) supported on a damping device through a rotating shaft (2), wherein a steering engine (13) is arranged in the steering engine mounting box (1), the output end of the steering engine (13) is connected with the rotating shaft (2) through a connecting rod mechanism, the damping device can be driven to change the direction through the rotating shaft (2), and the bottom of the damping device is connected with an airplane wheel through a supporting frame (15); the damping device comprises a first hinge (3) and a second hinge (4) which are vertically spaced and hinged together, a plurality of arc-shaped elastic ropes (14) are arranged in a spacing space between the first hinge (3) and the second hinge (4), the arc-shaped elastic ropes (14) are in a compression direction, the arc-shaped elastic ropes (14) are respectively fixed on the surfaces of the first hinge (3) and the second hinge (4) through an upper pressing plate (5) and a lower pressing plate (6), hinge joints (9) are arranged at the hinged points of the first hinge (3) and the second hinge (4), and holes (18) are formed in the hinge joints (9) and pin shafts (10) are mounted for connection; the output end of the steering engine (13) is arranged upwards, rocker arms are arranged at the output end of the steering engine (13) and the end part of the rotating shaft (2), the two rocker arms are connected through a connecting rod mechanism, and the connecting rod mechanism comprises a pull rod (12) and ball heads (16) arranged at the two ends of the pull rod (12); the cross section of the arc-shaped elastic rope (14) is circular, the arc-shaped elastic rope (14) can rotate along a mounting groove formed by the hinge and the pressing plate, a hole (18) in the hinge joint (9) is a U-shaped hole, and the pin shaft (10) can swing in the allowance space in the U-shaped hole.
2. An unmanned landing gear with damping in the direction of rotation according to claim 1, wherein: the rotating shaft (2) penetrates out from the bottom surface to the top surface of the steering engine mounting box (1), and a bearing (17) is arranged at the joint of the steering engine mounting box (1) and the rotating shaft (2).
3. An unmanned landing gear with damping in the direction of rotation according to claim 1, wherein: the arc-shaped elastic ropes (14) are all formed by processing steel wire ropes.
4. An unmanned landing gear with damping in the direction of rotation according to claim 1, wherein: the hinge joint (9) is processed at the end part of the second hinge (4), the end part of the first hinge (3) is L-shaped, and the end part of the first hinge (3) downwards extends into the hinge joint (9) through the connecting part and is connected together through the pin shaft (10).
5. An unmanned landing gear with damping in the direction of rotation according to claim 1, wherein: the support frame (15) adopts a plate, is arranged outside the end surfaces of the two sides of the airplane wheel and is connected with the center of the airplane wheel.
6. An unmanned landing gear with damping in the direction of rotation according to claim 1, wherein: the steering engine mounting box (1) is provided with a plurality of through holes corresponding to the positions where the steering engines (13) are arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921334765.3U CN210822736U (en) | 2019-08-16 | 2019-08-16 | Unmanned aerial vehicle undercarriage with damping in rotation direction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921334765.3U CN210822736U (en) | 2019-08-16 | 2019-08-16 | Unmanned aerial vehicle undercarriage with damping in rotation direction |
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| CN210822736U true CN210822736U (en) | 2020-06-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921334765.3U Active CN210822736U (en) | 2019-08-16 | 2019-08-16 | Unmanned aerial vehicle undercarriage with damping in rotation direction |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111824365A (en) * | 2020-07-15 | 2020-10-27 | 中船重工（海南）飞船发展有限公司 | Ground effect wing ship landing wheel device |
-
2019
- 2019-08-16 CN CN201921334765.3U patent/CN210822736U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111824365A (en) * | 2020-07-15 | 2020-10-27 | 中船重工（海南）飞船发展有限公司 | Ground effect wing ship landing wheel device |
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