CN205574292U - Rotor unmanned aerial vehicle protection device - Google Patents
Rotor unmanned aerial vehicle protection device Download PDFInfo
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- CN205574292U CN205574292U CN201620217918.6U CN201620217918U CN205574292U CN 205574292 U CN205574292 U CN 205574292U CN 201620217918 U CN201620217918 U CN 201620217918U CN 205574292 U CN205574292 U CN 205574292U
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- long tube
- pipe
- shaped part
- aerial vehicle
- unmanned aerial
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Abstract
The utility model discloses a rotor unmanned aerial vehicle protection device, including long tube, nozzle stub, side pipe, ring pipe, coupling, three way connection and undercarriage connecting piece, long tube and nozzle stub are connected through the coupling that is fixed in long tube, nozzle stub both ends, wherein pass through bolted connection between the coupling, the undercarriage connecting piece is fixed in on the ring of long tube, nozzle stub constitution, be connected through three way connection respectively between long tube and side pipe, side pipe and the ring pipe, accompany one deck thin rubber pad between long tube and three way connection, ring pipe and the three way connection respectively. The utility model discloses weight is lighter, and simple structure is handsome in appearance, and the installation of being convenient for is in case when the unmanned aerial vehicle of low -latitude flying operation was out of order the air crash, the device can play the cushioning effect, effectively guarantees the safety of unmanned aerial vehicle and airborne equipment.
Description
Technical field
The present invention relates to rotor wing unmanned aerial vehicle, particularly to a kind of rotor wing unmanned aerial vehicle protection device.
Background technology
Along with the development of unmanned air vehicle technique, the rotor wing unmanned aerial vehicle application in fields such as agricultural spray, electric stringing, transportation is more and more universal.The deficiency of the aspects such as machinery and control often makes unmanned plane break down in flight course and causes air crash, and the usually not unexpected protection device of current unmanned plane.Ensure the safety of rotor wing unmanned aerial vehicle accordingly, it would be desirable to adopt an effective measure, reduce aviation accident loss to greatest extent.
Summary of the invention
Present invention is primarily targeted at and a kind of rotor wing unmanned aerial vehicle protection device is provided, lighter in weight, simple in construction, handsome in appearance, it is simple to install.Being out of order air crash once the unmanned plane of low altitude flight operation, this device can play cushioning effect, and the safety of unmanned plane and airborne equipment is effectively ensured, and can effectively solve the problem in background technology.
For achieving the above object, the technical scheme that the present invention takes is:
A kind of rotor wing unmanned aerial vehicle protection device; including long tube, short tube, side pipe, ring pipe, pipe joint, three way cock and undercarriage connector; described long tube and short tube by being fixed on long tube, the pipe joint at short tube two ends connects into circular ring structure, undercarriage connector is fixed on circular ring structure；It is bolted between described pipe joint, it is connected by three way cock respectively between described long tube with side pipe, side pipe and ring pipe, described three way cock is bolted, and accompanies one layer of thin rubber pad between described long tube and three way cock, ring pipe and three way cock respectively；
Described undercarriage connector includes U-shaped part, lower U-shaped part, T shape part, perforation bolt and nut of clip, wherein said upper U-shaped part is positioned at above lower U-shaped part, and described upper U-shaped part and lower U-shaped part are connected by T-piece and perforation nut, described upper U-shaped part is bolted with undercarriage respectively with long tube, lower U-shaped part.
Further, the end of thread of T-piece also sets up a through hole, this through hole and the apertures align on perforation nut, and plays locking effect through a split pin.
Further, the number of described side pipe is multiple, and on the circular ring structure that described side pipe is distributed in long tube symmetrically and evenly, short tube connects into.
Further, the length of described long tube, short tube, side pipe and ring pipe, radian and spacing can change accordingly according to specifically used demand.
Further, between described side pipe and three way cock, with bolts between upper U-shaped part and long tube and between lower U-shaped part and undercarriage or interference connects or welding or the bonding or connected mode of riveting.
Further, described long tube, short tube, side pipe and ring pipe use tubular structure or filament or strip structure, the material of the tubular structure of described long tube, short tube, side pipe and ring pipe or filament or strip structure uses titanium alloy or steel alloy or plastics or carbon fibre material, and described three way cock, pipe joint and undercarriage connector use 7075 aluminum alloy materials or steel alloy or plastic material.
Compared with prior art, there is advantages that
1, present configuration uses titanium alloy or steel alloy or plastics or carbon fibre material and 7075 aluminum alloy materials so that whole installation weight is light, and intensity is high.
2, the annulus of device lower end is to realize by the way of long tube and short tube connection, it is simple to the handling of this device, and is not affected by fuselage.
3, the introducing of three way cock makes side pipe position adjustment, center of gravity trim become simple.
4, the introducing of rubber blanket makes side pipe tightr with the connection of long tube and ring pipe.
5, the mode that undercarriage connector uses upper and lower U-shaped part to connect is fixed, it is possible to fixes adjacent two and manages at any angle.
6, protection device use multiple loop configuration splicing mode, can effectively buffer unmanned plane with rolling or rotation status born time impact force.
7, protection device uses half cage structure, can wrap unmanned aerial vehicle body wing, protection unmanned aerial vehicle body, wing and airborne equipment.
8, this apparatus structure is reasonable, and highly versatile is common to single rotor of the band undercarriage of various uses and many rotor wing unmanned aerial vehicles.
9, the splicing demountable structure of long tube and short tube so that protection device can be conveniently mounted on unmanned plane undercarriage.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the polycrystalline substance enlarged diagram of the present invention；
Fig. 3 is undercarriage connecting-piece structure schematic diagram；
Fig. 4 is the structural representation of three way cock；
Fig. 5 is the structural representation after single rotor wing unmanned aerial vehicle protection device for installing；
Fig. 6 is the structural representation after four rotor wing unmanned aerial vehicle protection device for installing；
In figure: 1, long tube；2, short tube；3, side pipe；4, ring pipe；5, pipe joint；6, three way cock；7, undercarriage connector；7.1, upper U-shaped part；7.2, lower U-shaped part；7.3, T shape part；7.4, perforation nut；7.5, split pin.
Detailed description of the invention
For the technological means making the present invention realize, creation characteristic, reach purpose and be easy to understand with effect, below in conjunction with detailed description of the invention, the present invention is expanded on further.
nullAs shown in figures 1 to 6，A kind of rotor wing unmanned aerial vehicle protection device，A kind of rotor wing unmanned aerial vehicle protection device，It is by long tube 1、Short tube 2、Side pipe 3、Ring pipe 4、Pipe joint 5、Three way cock 6 and undercarriage connector 7 form，Described long tube 1 and short tube 2 are by being fixed on long tube 1、The pipe joint 5 at short tube 2 two ends connects，Wherein it is bolted between pipe joint 5，Described undercarriage connector 7 is fixed on long tube 1、On the annulus of short tube 2 composition，Described long tube 1 and side pipe 3、It is connected by three way cock 6 respectively between side pipe 3 with ring pipe 4，Before and after adjusting protection device during installation, position makes protection device center of gravity on the vertical line at unmanned plane center of gravity place，Described three way cock 6 is bolted，Also with plasma weldering or argon arc welding, interface tube position can be welded，Or make the mode of two fixture splicings，Or make the mode of hinge.Described long tube 1 and three way cock 6, one layer of thin rubber pad is accompanied respectively between ring pipe 4 and three way cock 6, play antiskid, shock-absorbing effect, described undercarriage connector includes U-shaped part 7.1, lower U-shaped part 7.2, T shape part 7.3, perforation nut 7.4 and split pin 7.5, wherein, described upper U-shaped part 7.1 is positioned at above lower U-shaped part 7.2, and connected by T-piece 7.3 and perforation nut 7.4, there is screw thread described T-piece 7.3 one end, and it is connected with perforation nut 7.4, described upper U-shaped part 7.1 and long tube 1, lower U-shaped part 7.2 is bolted respectively with undercarriage or welds or bonding or riveting mode connects, these connected modes make protection device can be fixedly secured on unmanned plane undercarriage.
Wherein, the end of thread of described T-piece 7.3 has a through hole, and when screwing perforation nut 7.4, this through hole can be with the apertures align on perforation nut 7.4, it is simple to split pin 7.5 passes.
Wherein, the number of wherein said side pipe 3 is multiple, and described side pipe 3 is distributed symmetrically and evenly, and side pipe (3) quantity can change other number into according to specifically used demand, such as 3,4,5,7,8 etc..
Wherein, described long tube 1, short tube 2, side pipe 3 and the length of ring pipe 4, radian and spacing can change accordingly according to specifically used demand, and length equidimension needs the size assortment according to unmanned plane, and the radian of side pipe can be greater or lesser.
Wherein, the bolt connecting mode between described pipe joint 5, between side pipe 3 and three way cock 6, between upper U-shaped part 7.1 and long tube 1, between lower U-shaped part 7.2 and undercarriage uses interference to connect or welds or the bonding or connected mode of riveting.
Wherein, described long tube 1, short tube 2, side pipe 3, ring pipe 4 and three way cock 6 all use titanium pipe, and described pipe joint 5 and undercarriage connector 7 all use 7075 aluminum alloy materials.Material can replace with the other materials such as steel, plastics according to specifically used occasion and demand herein, the solid construction such as the most replaceable one-tenth of tubular construction is thread, lamellar.If unmanned plane take-off weight is the use that 5 kilograms to 100 kilograms structure and materials can be recommended according to aforementioned invention；If the small-sized model plane level unmanned plane that unmanned plane is take-off weight less than 5 kilograms, then tubular construction is changed to memory wire or plastic strip or carbon-fibre strips, and connector material can use plastics；If unmanned plane is more than 100 kilograms large-scale unmanned planes of take-off weight, the optional spring steel of tubular construction material, optional No. 45 steel of connector material.
Wherein, described rotor wing unmanned aerial vehicle protection device can also install connecting rod and other mechanism making device more consolidate additional.As installed inclined tube additional on side pipe 3 and long tube 1, increase protection device axial stability.Or on side pipe 3 with unmanned aerial vehicle body, add connecting rod, increase protection device laterally, vertical stability.
As shown in Figure 5, Figure 6, protection device be mountable to single rotor, four rotors and other take up on many rotor wing unmanned aerial vehicles of frame.
First assemble protection device, then install on aircraft.During installation, turn on a bolt between long tube 1 and short tube 2, short tube is turn 90 degrees outside protection device.Now below protection device, annulus just has an opening, by this opening towards unmanned plane head, pushes unmanned plane to, to position shown in Fig. 5, Fig. 6, then short tube 2 other end is fixed back long tube 1.
The operation principle of the present invention is:
The present invention is first assembled on unmanned plane before unmanned plane takes off, and can take off after carrying out center of gravity leveling unmanned plane.Protection device protects unmanned aerial vehicle body and load equipment thereof from all quarter so that the impact force received when unmanned plane lands focuses in undercarriage and protection device.When unmanned plane vertically lands with the posture ajusted, undercarriage undertake the impact force with ground.When unmanned plane lands with the posture of rollover, protection device is first contacted to earth, and props up unmanned plane.When having the rotational kinetic energy of any direction when unmanned plane lands, the annular side pipe of protection device can allow unmanned plane can buffer rotational kinetic energy along rolling one end, own rotation direction distance after landing.When unmanned plane stands upside down and lands, owing to ring pipe 4 is higher than rotor, therefore protection device can erect unmanned plane, alleviates the shock of unmanned plane and ground to greatest extent, protects carried equipment.
The ultimate principle of the present invention and principal character and advantages of the present invention have more than been shown and described.Skilled person will appreciate that of the industry; the present invention is not restricted to the described embodiments; the principle that the present invention is simply described described in above-described embodiment and description; without departing from the spirit and scope of the present invention; the present invention also has various changes and modifications, and these changes and improvements both fall within scope of the claimed invention.Claimed scope is defined by appending claims and equivalent thereof.
Claims (6)
1. a rotor wing unmanned aerial vehicle protection device; it is characterized in that: include long tube (1), short tube (2), side pipe (3), ring pipe (4), pipe joint (5), three way cock (6) and undercarriage connector (7); described long tube (1) and short tube (2) by being fixed on long tube (1), the pipe joint (5) at short tube (2) two ends connect into circular ring structure, undercarriage connector (7) is fixed on circular ring structure；Described pipe joint is bolted between (5), it is connected by three way cock (6) respectively between described long tube (1) with side pipe (3), side pipe (3) and ring pipe (4), described three way cock (6) is bolted, and accompanies one layer of thin rubber pad respectively between described long tube (1) and three way cock (6), ring pipe (4) and three way cock (6)；
Described undercarriage connector (7) includes U-shaped part (7.1), lower U-shaped part (7.2), T shape part (7.3), perforation nut (7.4) and split pin (7.5), wherein said upper U-shaped part (7.1) is positioned at lower U-shaped part (7.2) top, and described upper U-shaped part (7.1) and lower U-shaped part (7.2) are by T-piece (7.3) and perforation nut (7.4) connection, described upper U-shaped part (7.1) is bolted with undercarriage respectively with long tube (1), lower U-shaped part (7.2).
Rotor wing unmanned aerial vehicle protection device the most according to claim 1; it is characterized in that: the end of thread of described T-piece (7.3) also sets up a through hole; this through hole and the apertures align in perforation nut (7.4), and play locking effect through a split pin (7.5).
Rotor wing unmanned aerial vehicle protection device the most according to claim 1, it is characterised in that: the number of described side pipe (3) is multiple, and on the circular ring structure that described side pipe (3) is distributed in long tube (1) symmetrically and evenly, short tube (2) connects into.
Rotor wing unmanned aerial vehicle protection device the most according to claim 1, it is characterised in that: length, radian and the spacing of described long tube (1), short tube (2), side pipe (3) and ring pipe (4) can change accordingly according to specifically used demand.
Rotor wing unmanned aerial vehicle protection device the most according to claim 1, it is characterised in that: with bolts or interference connects or welding or the bonding or connected mode of riveting between described side pipe (3) with three way cock (6), between upper U-shaped part (7.1) and long tube (1) and between lower U-shaped part (7.2) and undercarriage.
Rotor wing unmanned aerial vehicle protection device the most according to claim 1; it is characterized in that: described long tube (1), short tube (2), side pipe (3) and ring pipe (4) use tubular structure or filament or strip structure; the material of described long tube (1), short tube (2), side pipe (3) and the tubular structure of ring pipe (4) or filament or strip structure uses titanium alloy or steel alloy or plastics or carbon fibre material, and described three way cock (6), pipe joint (5) and undercarriage connector (7) use 7075 aluminum alloy materials or steel alloy or plastic material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620217918.6U CN205574292U (en) | 2016-03-21 | 2016-03-21 | Rotor unmanned aerial vehicle protection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620217918.6U CN205574292U (en) | 2016-03-21 | 2016-03-21 | Rotor unmanned aerial vehicle protection device |
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| CN205574292U true CN205574292U (en) | 2016-09-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201620217918.6U Active CN205574292U (en) | 2016-03-21 | 2016-03-21 | Rotor unmanned aerial vehicle protection device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105836147A (en) * | 2016-03-21 | 2016-08-10 | 飞智控（天津）科技有限公司 | Rotor wing unmanned aerial vehicle protection device |
-
2016
- 2016-03-21 CN CN201620217918.6U patent/CN205574292U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105836147A (en) * | 2016-03-21 | 2016-08-10 | 飞智控（天津）科技有限公司 | Rotor wing unmanned aerial vehicle protection device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Rotor wing unmanned aerial vehicle protection device Effective date of registration: 20190102 Granted publication date: 20160914 Pledgee: Credit Guarantee Center of small and medium enterprises in Tianjin Pledgor: EFY (TIANJIN) TECHNOLOGY CO., LTD. Registration number: 2018120000046 |
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| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20200318 Granted publication date: 20160914 Pledgee: Credit Guarantee Center of small and medium enterprises in Tianjin Pledgor: EFY INTELLIGENT CONTROL (TIANJIN) TECH Co.,Ltd. Registration number: 2018120000046 |
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| PC01 | Cancellation of the registration of the contract for pledge of patent right |