CN214729628U - Shock attenuation undercarriage and many rotor unmanned aerial vehicle - Google Patents
Shock attenuation undercarriage and many rotor unmanned aerial vehicle Download PDFInfo
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- CN214729628U CN214729628U CN202120016652.XU CN202120016652U CN214729628U CN 214729628 U CN214729628 U CN 214729628U CN 202120016652 U CN202120016652 U CN 202120016652U CN 214729628 U CN214729628 U CN 214729628U
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- landing gear
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Abstract
The utility model discloses a shock attenuation undercarriage and many rotor unmanned aerial vehicle belongs to the unmanned aerial vehicle field. The shock absorption undercarriage comprises an upper frame and a lower frame; an upper sliding sleeve is arranged on the upper frame, a lower sliding sleeve is arranged on the lower frame, and the upper sliding sleeve and the lower sliding sleeve are mutually sleeved and can axially move relatively; the compression spring is arranged inside the upper sliding sleeve or the lower sliding sleeve and connected between the upper rack and the lower rack. Many rotor unmanned aerial vehicle includes fuselage, horn, motor and paddle to and connect the shock attenuation undercarriage on fuselage or horn. The utility model discloses the structure is retrencied, reasonable in design, and the impact force that ground gave when can effectively cushion the descending effectively protects airborne equipment's safety.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle field, in particular to shock attenuation undercarriage and many rotor unmanned aerial vehicle.
Background
Unmanned aerial vehicle is called for short for unmanned aerial vehicle, be the unmanned aerial vehicle who utilizes radio remote control equipment and self-contained program control device to control, unmanned aerial vehicle is unmanned aerial vehicle's the general name in fact, classify according to the flight platform configuration, unmanned aerial vehicle can divide into fixed wing unmanned aerial vehicle, rotor unmanned aerial vehicle, unmanned airship, umbrella wing unmanned aerial vehicle, flapping wing unmanned aerial vehicle etc. compare with manned aircraft, it has small, the cost is low, high durability and convenient use, low to operational environment requirement, advantages such as battlefield viability is stronger.
A multi-rotor unmanned aerial vehicle is a special unmanned helicopter with three or more rotor shafts. It is rotated by a motor on each shaft, driving the rotor, thereby generating lift. The collective pitch of the rotors is fixed and not variable as in a typical helicopter. Through changing the relative speed between the different rotors, the size of unipolar propulsive force can be changed to the orbit of control aircraft. The method has the characteristics of strong controllability, capability of vertical take-off and landing and hovering, and is mainly suitable for task types with low altitude, low speed and vertical take-off and landing and hovering requirements.
The landing gear is the important component of unmanned aerial vehicle, is used for supporting aircraft gravity when parking on the ground, slides, takes off and lands and the roll off, bears the device of corresponding load, and unmanned aerial vehicle is when descending, and the landing gear is first to descend, and it can consume and absorb the impact energy of aircraft when landing.
Wherein many rotor unmanned aerial vehicle need take off perpendicularly and descend, especially descending the process because dead weight and airspeed are great, the undercarriage can form the impact action with ground, but the big shock attenuation effect of unmanned aerial vehicle undercarriage on the present market is not good, can't effectively alleviate the collision impact force of unmanned aerial vehicle and ground, it is unstable when leading to unmanned aerial vehicle to descend, receive great impact easily, and the inside comparatively accurate instrument that need be equipped with of unmanned aerial vehicle usually, equipment, stronger impact will be to the accuracy that reduces instrument equipment, the structural performance of each part of unmanned aerial vehicle consequently receives the influence.
SUMMERY OF THE UTILITY MODEL
Be applied to unmanned aerial vehicle's the not good problem of undercarriage shock attenuation effect to prior art existence, the utility model aims to provide a shock attenuation undercarriage and many rotor unmanned aerial vehicle.
In order to achieve the above purpose, the technical scheme of the utility model is that:
on one hand, the utility model provides a damping undercarriage, which comprises an upper frame and a lower frame; an upper sliding sleeve is arranged on the upper rack, a lower sliding sleeve is arranged on the lower rack, and the upper sliding sleeve and the lower sliding sleeve are mutually sleeved and enable the upper rack and the lower rack to move axially and relatively; the compression spring is configured inside the upper sliding sleeve or the lower sliding sleeve and is connected between the upper rack and the lower rack; still include the elastic cushion block, the elastic cushion block can dismantle the connection in the bottom of lower frame.
Preferably, the upper sliding sleeve and the lower sliding sleeve are tubular structures with one closed ends and the other open ends, the open end of the upper sliding sleeve is opposite to the open end of the lower sliding sleeve, and the upper sliding sleeve is sleeved inside the lower sliding sleeve.
Further, still include the center pin, the center pin can be dismantled to fix go up on the inner wall of the closed one end of sliding sleeve, still fixed mounting has the spring board on the center pin, compression spring cover is established on the circumference outer wall of center pin, just compression spring's upper end butt is in spring board upper and lower end is fixed on the inner wall of the closed one end of lower sliding sleeve.
Preferably, the central shaft is in threaded connection with the upper sliding sleeve.
Preferably, the elastic cushion block is connected with the lower frame through a screw.
Preferably, the elastic cushion block is a rubber pad.
On the other hand, the utility model provides a many rotor unmanned aerial vehicle, include the fuselage, install a plurality of horn on the fuselage, install at every motor on the horn and install at every paddle on the motor still includes at least one foretell shock attenuation undercarriage.
Preferably, each horn is mounted with at least one shock absorbing landing gear.
Preferably, the shock-absorbing undercarriage is provided with a plurality of shock-absorbing undercarriage bodies, and the shock-absorbing undercarriage bodies are all fixedly mounted on the machine body.
By adopting the technical scheme, the upper frame and the lower frame can move relatively along the axial direction of the shaft sleeve due to the arrangement of the upper sliding sleeve and the lower sliding sleeve, and have telescopic property; and owing to connect the setting of the pressure cover spring between last frame and the lower frame, make on the one hand and constitute inseparable connection relation between last frame and the lower frame, on the other hand makes the lower frame be close to and even keep away from the in-process of last frame and all receive elasticity and the tensile restriction that compression spring provided, thereby weaken the relative motion trend of frame of going up of lower frame, thereby alleviate the impact, reach the absorbing effect, the unmanned aerial vehicle of rotor who contains this shock attenuation undercarriage then can reduce the impact force that it received when descending, thereby protect airborne equipment, and the service life is prolonged.
Drawings
FIG. 1 is a schematic structural view of a shock absorbing landing gear of the present invention;
fig. 2 is the utility model discloses well many rotor unmanned aerial vehicle's schematic structure diagram.
In the figure, 1-elastic cushion block, 2-screw, 3-lower frame, 4-lower sliding sleeve, 5-compression spring, 6-upper sliding sleeve, 7-central shaft, 8-motor, 9-blade, 10-machine body, 11-machine arm, 12-upper frame and 13-spring plate.
Detailed Description
The following describes the present invention with reference to the accompanying drawings. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. In addition, the technical features related to the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
It should be noted that, in the description of the present invention, the terms "upper", "lower", "left", "right", "front", "back", etc. indicate the orientation or position relationship of the structure of the present invention based on the drawings, and are only for the convenience of describing the present invention, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
In the technical scheme, the terms "first" and "second" are only used for referring to the same or similar structures or corresponding structures with similar functions, and are not used for ranking the importance of the structures, or comparing the sizes or other meanings.
In addition, unless expressly stated or limited otherwise, the terms "mounted" and "connected" are to be construed broadly, e.g., the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; the two structures can be directly connected or indirectly connected through an intermediate medium, and the two structures can be communicated with each other. To those skilled in the art, the specific meanings of the above terms in the present invention can be understood in relation to the present scheme in specific terms according to the general idea of the present invention.
Example one
A shock absorbing landing gear, as shown in figure 1, comprises an upper chassis 12 and a lower chassis 3.
Wherein, the upper frame 12 is fixedly provided with an upper sliding sleeve 6, for example, the upper end of the upper sliding sleeve 6 is fixed at the bottom of the upper frame 12 by welding. Correspondingly, a lower sliding sleeve 4 is fixedly arranged on the lower rack 3, and the lower end of the lower sliding sleeve 4 is fixed at the top of the lower rack 3 in a welding mode. Meanwhile, the upper sliding sleeve 6 and the lower sliding sleeve 4 are sleeved with each other, and the upper frame 12 (the upper sliding sleeve 6) and the lower frame 3 (the lower sliding sleeve 4) can move relatively along the respective axial directions; for example, in the present embodiment, the upper sliding sleeve 6 is inserted inside the lower sliding sleeve 4, and the two are in clearance fit, so that the two can perform an unimpeded axial movement, and it can be understood that the implementation of the present scheme is not affected by the insertion of the lower sliding sleeve 4 inside the upper sliding sleeve 6.
The upper sliding sleeve 6 and the lower sliding sleeve 4 are connected into a whole, the compression spring 5 is arranged in the assembly, the compression spring 5 is connected between the upper frame 12 and the lower frame 3, and for example, the upper end and the lower end of the compression spring 5 are respectively welded on the upper frame 12 and the lower frame 3. The arrangement is such that the upper frame 12 can be connected with the lower frame 3 by the compression spring 5 and can move axially relative to each other under the limit of the upper sliding sleeve 6 and the lower sliding sleeve 4.
Therefore, in the process of using the upper frame 12 connected to the body of the unmanned aerial vehicle or other equipment, when the bottom of the lower frame 3 is subjected to impact force given by the ground, the lower frame 3 moves along the axial direction of the sliding sleeve and is close to the upper frame 12, the compression spring 5 is correspondingly compressed at the moment to generate elastic force, the elastic force effectively counteracts the impact force, the movement of the lower frame 3 is rapidly reduced, and then the impact force on the body of the unmanned aerial vehicle connected with the upper frame 12 or other equipment is reduced, so that the safety of parts carried on the body of the unmanned aerial vehicle or other equipment is effectively protected.
In this embodiment, the upper sliding sleeve 6 and the lower sliding sleeve 4 are both configured to be tubular structures with one closed end and the other open end, and the open end of the upper sliding sleeve 6 is opposite to the open end of the lower sliding sleeve 4; meanwhile, the central shaft 7 is further included, the central shaft 7 is coaxially arranged inside the upper sliding sleeve 6, the upper end of the central shaft 7 is detachably and fixedly connected to the inner wall of the closed end of the upper sliding sleeve 6 through threads, a spring plate 13 is further fixedly installed on the central shaft 7, and the spring plate 13 is screwed on external threads arranged on the circumferential outer wall of the central shaft 7 through threaded holes; the compression spring 7 is sleeved on the circumferential outer wall of the central shaft 7, and the upper end of the compression spring 7 abuts against the lower end face of the spring plate 13, and the lower end is fixed on the inner wall of the closed end of the lower sliding sleeve 4 in a welding manner.
In addition, in order to prevent the compression spring 5 from being excessively pulled and twisted, in one embodiment, a limit block is disposed on the circumferential outer wall of the upper sliding sleeve 6, and an axial sliding groove adapted to the limit block is disposed on the circumferential outer wall of the lower sliding sleeve 4, so that the limit block can only slide in the axial sliding groove, and thus the relative movement between the upper frame 12 and the lower frame 3 is limited within a certain range, and only the relative movement along the axial direction of the sliding sleeve can be performed. Meanwhile, in this embodiment, both ends of the compression spring 5 only need to abut against between the upper frame 12 and the lower frame 3, or abut against the inner walls of the spring plate 13 and the closed end of the lower sliding sleeve 4.
In this embodiment, the shock absorption undercarriage comprises a cushion block 1, the cushion block 1 is detachably connected to the bottom of the lower frame 3 through a screw 2 or a pin, for example, the cushion block 1 is configured as a rubber pad, so as to enhance the shock absorption effect on the impact force.
Example two
A multi-rotor unmanned aerial vehicle comprises a body 10, a plurality of arms 11 mounted on the body, a motor 8 mounted on each arm 11, and blades 9 mounted on each motor 8, and further comprises at least one shock-absorbing landing gear disclosed in the above embodiments, as shown in FIG. 2. Among them, the motor 8 is preferably a brushless motor.
In this embodiment, the number of the shock-absorbing landing gear is multiple, and at least one (for example, one) shock-absorbing landing gear is mounted on the bottom surface of each horn 11, and specifically, the top of the upper frame 12 is fixedly connected to the horn 11, for example, welded or bolted.
Alternatively, in one embodiment, the shock absorbing landing gear has a plurality of locations uniformly and fixedly mounted around the bottom surface of the fuselage 10. And it is understood that the number of the shock-absorbing landing gear may be only one, and it is only necessary to increase the size of the cross section of the shock-absorbing landing gear and arrange the shock-absorbing landing gear at the center of the bottom surface of the fuselage 10.
The utility model discloses a when many rotor unmanned aerial vehicle landed, when speed is very fast, the fuselage is when heavier, the shock attenuation undercarriage is bigger with the impact force on ground, produce the vibration easily and cause destruction to unmanned aerial vehicle, the energy that shock attenuation undercarriage and ground collision produced this moment is transmitted compression spring 5 through last frame 12 and undercarriage 3, after compression spring 5 compresses, will strike energy absorption, produce the reaction force simultaneously, the impact force that receives when slowing down many rotor unmanned aerial vehicle landing, and the impact force when the elastic cushion block 1 of shock attenuation undercarriage bottom further slows down many rotor unmanned aerial vehicle landing, ensure that unmanned aerial vehicle can steadily descend, dual shock attenuation design can ensure that many rotor unmanned aerial vehicle's decline process is more stable, unmanned aerial vehicle each side structural performance is not influenced.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. It will be apparent to those skilled in the art that various changes, modifications, substitutions and alterations can be made in the embodiments without departing from the principles and spirit of the invention, and the scope of the invention is to be accorded the full scope of the claims.
Claims (9)
1. A shock absorbing landing gear, characterized by: comprises an upper frame and a lower frame; an upper sliding sleeve is arranged on the upper rack, a lower sliding sleeve is arranged on the lower rack, and the upper sliding sleeve and the lower sliding sleeve are mutually sleeved and enable the upper rack and the lower rack to move axially and relatively; the compression spring is configured inside the upper sliding sleeve or the lower sliding sleeve and is connected between the upper rack and the lower rack; still include the elastic cushion block, the elastic cushion block can dismantle the connection in the bottom of lower frame.
2. The shock absorbing landing gear of claim 1, wherein: the upper sliding sleeve and the lower sliding sleeve are tubular structures with one closed ends and the other open ends, the open end of the upper sliding sleeve is opposite to the open end of the lower sliding sleeve, and the upper sliding sleeve is sleeved inside the lower sliding sleeve.
3. The shock absorbing landing gear of claim 2, wherein: the sliding sleeve is characterized by further comprising a central shaft, the central shaft can be detachably fixed to the inner wall of the closed end of the upper sliding sleeve, a spring plate is fixedly mounted on the central shaft, the compression spring sleeve is arranged on the circumferential outer wall of the central shaft, and the upper end and the lower end of the compression spring are fixed to the inner wall of the closed end of the lower sliding sleeve.
4. A shock absorbing landing gear according to claim 3, wherein: the central shaft is in threaded connection with the upper sliding sleeve.
5. The shock absorbing landing gear of claim 1, wherein: the elastic cushion block is connected with the lower rack through a screw.
6. The shock absorbing landing gear of claim 1, wherein: the elastic cushion block is a rubber pad.
7. The utility model provides a many rotor unmanned aerial vehicle, includes the fuselage, installs a plurality of horn on the fuselage, install every motor on the horn and install every paddle on the motor, its characterized in that: further comprising at least one shock absorbing landing gear according to any of claims 1 to 6.
8. A multi-rotor drone according to claim 7, wherein: each horn is provided with at least one damping undercarriage.
9. A multi-rotor drone according to claim 7, wherein: the shock attenuation undercarriage has a plurality ofly and all fixed mounting in on the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120016652.XU CN214729628U (en) | 2021-01-05 | 2021-01-05 | Shock attenuation undercarriage and many rotor unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120016652.XU CN214729628U (en) | 2021-01-05 | 2021-01-05 | Shock attenuation undercarriage and many rotor unmanned aerial vehicle |
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| CN214729628U true CN214729628U (en) | 2021-11-16 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112607007A (en) * | 2021-01-05 | 2021-04-06 | 复旦大学 | Shock attenuation undercarriage and many rotor unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112607007A (en) * | 2021-01-05 | 2021-04-06 | 复旦大学 | Shock attenuation undercarriage and many rotor unmanned aerial vehicle |
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