CN208498792U - A kind of rotor wing unmanned aerial vehicle quickly approached - Google Patents
A kind of rotor wing unmanned aerial vehicle quickly approached Download PDFInfo
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- CN208498792U CN208498792U CN201821103525.8U CN201821103525U CN208498792U CN 208498792 U CN208498792 U CN 208498792U CN 201821103525 U CN201821103525 U CN 201821103525U CN 208498792 U CN208498792 U CN 208498792U
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- bevel gear
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- 238000013459 approach Methods 0.000 claims abstract description 10
- 230000013011 mating Effects 0.000 claims abstract description 4
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 22
- 239000006185 dispersion Substances 0.000 claims description 16
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 12
- 239000007789 gas Substances 0.000 claims description 11
- 239000007788 liquid Substances 0.000 claims description 6
- 229910052757 nitrogen Inorganic materials 0.000 claims description 6
- 230000005389 magnetism Effects 0.000 claims description 5
- 230000003447 ipsilateral effect Effects 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 230000006378 damage Effects 0.000 description 4
- 230000001133 acceleration Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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Abstract
The utility model discloses the rotor wing unmanned aerial vehicles that one kind quickly approaches, including fuselage main body, emit shell and emitter, coaxial double-oar leaf device is equipped at the top of the fuselage main body, the coaxial double-oar leaf device includes inner shaft, the bottom of the inner shaft is equipped with bevel gear one, upper rotating disk is equipped at the top position of the inner shaft, set is equipped with outer shaft at the medium position of the inner shaft, the fuselage main body lower part is equipped with task apparatus, the transmitting shell and the fuselage main body for folding blade match, the transmitting shell includes two pieces etc. big of cambered surface shell, it is in mating connection between the cambered surface shell, the emission cavity that shell matches is equipped with and emitted in the emitter, the device of ejection launch shell is equipped in the emitter.The utility model overcomes prior art disadvantage, structurally reasonable, is laid out using coaxial anti-paddle, has foldable blade, carries out hovering or flight operation after can quickly approaching target area.
Description
Technical field
The utility model relates to air vehicle technique field, in particular to a kind of rotor wing unmanned aerial vehicles quickly approached.
Background technique
Currently, unmanned air vehicle technique is quickly grown, many traditional industries start the application for slowly introducing unmanned plane, promote row
The intelligentized updating of industry.
Unmanned plane in the market is usually based on rotor wing unmanned aerial vehicle and fixed-wing unmanned plane.Rotor wing unmanned aerial vehicle can be in the sky
Hovering, works, but have the shortcomings that endurance is short, flying speed is slow in designated place overhead；Fixed-wing unmanned plane during flying speed
Fastly, the task in a wide range of can be completed the short time, but can not be hovered, and have higher requirement to landing site, be not easy to
Rapid deployment quickly uses.
In actual use, unmanned plane high speed is such as needed to approach operation of hovering behind workspace, then needs a kind of novel nobody
Machine is to meet this special application scenarios.
Utility model content
The technical problems to be solved in the utility model is to overcome prior art disadvantage, provides a kind of rotor quickly approached
Unmanned plane, it is structurally reasonable, it is laid out using coaxial anti-paddle, there is foldable blade, hanged after can quickly approaching target area
Stop or flight operation.
In order to solve the above technical problems, technical solution provided by the utility model are as follows: the rotor that quickly approaches of one kind nobody
Machine, including fuselage main body, transmitting shell and emitter, the fuselage main body top is equipped with coaxial double-oar leaf device, described total
Axis double blades device includes inner shaft, and the bottom of the inner shaft is equipped with bevel gear one, is equipped with upper rotation at the top position of the inner shaft
Turntable, set is equipped with outer shaft at the medium position of the inner shaft, and the outer shaft bottom is equipped with bevel gear two, two He of bevel gear
Bevel gear one is symmetrical arranged, and is arranged at the center of the inner shaft perforation bevel gear two, the bevel gear two and bevel gear one are all provided with
It is placed in fuselage main body, is equipped in the fuselage main body and simultaneously and the drive bevel gear that matches of bevel gear two, bevel gear one,
The output shaft end of decelerating motor is connected at the center of the drive bevel gear, and controller is equipped in the fuselage main body, it is described to subtract
Speed motor is electrically connected controller, and the upper outside of the outer shaft is equipped with lower rotating disc, in the upper rotating disk and lower rotating disc
It is circumferentially symmetrically arranged with a pair of of blade, the blade is hinged on rotating disk and lower rotating disc edge, and the blade is close to hinge
Position lower hinge is connect equipped with connecting rod, in the inner shaft and outer shaft and blade is ipsilateral is equipped with blade draw off gear, the connection
The other end articulated blade draw off gear of bar, the folding and unfolding of the blade draw off gear driving connecting rod control blade, the fuselage
Lower body part is equipped with task apparatus, and the transmitting shell and the fuselage main body for folding blade match, and the transmitting shell includes
Two pieces etc. big of cambered surface shell, in mating connection between the cambered surface shell, the transmitting shell is closed at one end, other end buckle
Connection disperses pedestal, is equipped with and emits the emission cavity that shell matches in the emitter, be equipped in the emitter
The device of ejection launch shell.
As an improvement, the blade tips are equipped with stepped interface, the upper rotating disk and lower rotating disc end be equipped with
The stepped interface that blade tips match, the ladder type interface is equipped with elastic buffer film, when preventing blade hinged open, damage
Bad components.
As an improvement, the blade draw off gear includes the sliding slot being arranged in inner shaft and outer shaft, it is equipped in the sliding slot
Magnetic saddle, one end of the magnetism saddle bar that is articulated and connected are connected between the top and sliding slot top of the magnetism saddle
Spring, the sliding slot bottom are equipped with electromagnet, and the electromagnet is electrically connected controller, by the absorption of magnet switching electricity with
It decontrols, completes the contraction and expansion to blade.
As an improvement, the task apparatus includes camera, the camera is electrically connected controller, can control camera shooting
Head completes shooting task.
As an improvement, be equipped with inflation packet in the dispersion pedestal, equipped with liquid nitrogen container in inflation packet, on the liquid nitrogen container
Equipped with electromagnetic gas valve, the electromagnetic gas valve is electrically connected controller, is equipped with and keeps off close to transmitting shell side in the dispersion pedestal
Plate, the transmitting shell and dispersion pedestal junction are circumferentially uniformly provided with Elastic buckle, and the dispersion pedestal is equipped with and bullet
Property the deck that matches of buckle, transmitting shell snaps connection dispersion pedestal, so that secured in emission process, inflation packet fills rapidly
Gas struts baffle and completes separation.
The utility model compared with prior art the advantages of be: coaxial twin screw is different from conventional single-blade disk and goes straight up to
Machine, the torque that blade rotation generates can be because rotating backward and cancelling out each other for upper and lower paddle disk, do not need additionally to configure tail
Paddle to balance the torsional moment, meanwhile, the power loss that engine exports tail-rotor can also be saved.In addition, because upper and lower two sets
Paddle disk provides lift simultaneously, therefore rotor disk area required under same lift is much smaller than the area of single-blade disk, aircraft overall dimensions
It is more compact, save space；Fuselage include unmanned plane body basic structure, inside be equipped with engine, flight control system and
The conventional equipments such as communication device；The task system is installed on the fuselage, can specifically be completed required by unmanned plane
The equipment of task definition.
Folded unmanned plane can bear higher overload to obtaining biggish initial velocity, can be with simple fast hand
Section makes unmanned plane quickly approach target area；The form of rotor wing unmanned aerial vehicle after expansion ensure that unmanned plane possesses in target area
The task ability of overhead hovering operation；Coaxial double-oar layout can make unmanned plane obtain more compact shape and more stable rotor
Balance simplifies control member and the control of unmanned plane.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the utility model patent.
Fig. 2 is the structural schematic diagram of coaxial double-oar leaf device in the utility model patent.
Fig. 3 is the structural schematic diagram of blade draw off gear in the utility model patent.
Fig. 4 is the structural schematic diagram emitted at shell in the utility model patent.
Fig. 5 is the schematic diagram of the utility model patent operational process.
Fig. 6 is the structural schematic diagram of blade hinged place in the utility model patent.
It is as shown in the figure: 1, fuselage main body, 2, coaxial double-oar leaf device, 3, inner shaft, 4, bevel gear one, 5, upper rotating disk, 6,
Outer shaft, 7, bevel gear two, 8, drive bevel gear, 9, lower rotating disc, 10, blade, 11, connecting rod, 12, blade draw off gear, 13,
Emit shell, 14, task apparatus, 15, cambered surface shell, 16, emitter, 17, elastic buffer film, 18, sliding slot, 19, magnetic cunning
Part, 20, spring, 21, electromagnet, 22, dispersion pedestal, 23, inflation packet, 24, electromagnetic gas valve, 25, baffle, 26, Elastic buckle,
27, deck.
Specific embodiment
The following describes the utility model in further detail with reference to the accompanying drawings.
In conjunction with attached drawing 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5, Fig. 6.
The utility model in the specific implementation, a kind of rotor wing unmanned aerial vehicle quickly approached, including fuselage main body 1, transmitting shell
Body 13 and emitter 16, coaxial double-oar leaf device 2 is equipped at the top of the fuselage main body 1, and the coaxial double-oar leaf device 2 includes
Inner shaft 3, the bottom of the inner shaft 3 are equipped with bevel gear 1, and upper rotating disk 5 is equipped at the top position of the inner shaft 3, described interior
Set is equipped with outer shaft 6 at the medium position of axis 3, and 6 bottom of outer shaft is equipped with bevel gear 27, the bevel gear 27 and bevel gear
One 4 are symmetrical arranged, and the inner shaft 3, which penetrates through at the center of bevel gear 27, to be arranged, and the bevel gear 27 and bevel gear 1 are respectively provided with
In in fuselage main body 1, it is equipped in the fuselage main body 1 and simultaneously and the active conical tooth that matches of bevel gear 27, bevel gear 1
8 are taken turns, the output shaft end of decelerating motor is connected at the center of the drive bevel gear 8, is equipped with controller in the fuselage main body 1,
The decelerating motor is electrically connected controller, and the upper outside of the outer shaft 6 is equipped with lower rotating disc 9, and the upper rotating disk 5 is under
A pair of of blade 10 is circumferentially symmetrically respectively equipped in rotating disk 9, the blade 10 is hinged on 9 side of rotating disk 5 and lower rotating disc
At edge, the blade 10 is equipped with connecting rod 11 close to articulated position lower hinge, and in the inner shaft 3 and outer shaft 6 and blade 10 is same
Side is equipped with blade draw off gear 12, the other end articulated blade draw off gear 12 of the connecting rod 11, the blade draw off gear
12 driving connecting rods 11 control the folding and unfolding of blade 10, and 1 lower part of fuselage main body is equipped with task apparatus 14, the transmitting shell 13
It is matched with the fuselage main body 1 for folding blade 10, the transmitting shell 13 includes two pieces etc. big of cambered surface shell 15, the cambered surface
In mating connection between shell 15, the transmitting shell 13 is closed at one end, and the other end snaps connection dispersion pedestal 22, the transmitting
The emission cavity that shell 13 matches is equipped with and emitted in device 16, is equipped with ejection launch shell 13 in the emitter 16
Device.
10 end of blade is equipped with stepped interface, and the upper rotating disk 5 and 9 end of lower rotating disc are equipped with and blade 10
The stepped interface of matching ends, the ladder type interface are equipped with elastic buffer film 17, and the blade draw off gear 12 includes
Sliding slot 18 in inner shaft 3 and outer shaft 6 is set, magnetic saddle 19 is equipped in the sliding slot 18, the magnetism saddle 19 hingedly connects
One end of extension bar 11 is connected with spring 20,18 bottom of sliding slot between the top and the top of sliding slot 18 of the magnetism saddle 19
Equipped with electromagnet 21, the electromagnet 21 is electrically connected controller.
The task apparatus 14 includes camera, and the camera is electrically connected controller, sets in the dispersion pedestal 22
There is inflation packet 23, is equipped with liquid nitrogen container in the inflation packet 23, the liquid nitrogen container is equipped with electromagnetic gas valve 24, the electromagnetic gas valve 24
It is electrically connected controller, close transmitting 13 side of shell is equipped with baffle 25,13 He of transmitting shell in the dispersion pedestal 22
Dispersion 22 junction of pedestal is circumferentially uniformly provided with Elastic buckle 26, and the dispersion pedestal 22 is equipped with and Elastic buckle 26 matches
The deck 27 of conjunction.
Working principle of the utility model is: the coaxial twin-propeller blade is foldable, can also be unfolded in the sky, blade
Expansion can be used and be not limited to using modes such as steering engine turning gear wheel disc or spring restoring forces, the present embodiment is using electromagnet suction
Subsidiary formula formula.In the unmanned plane initial velocity for giving blade folded state, lesser front face area can reduce the damage of initial velocity
It loses, makes unmanned plane can be with fast approaching target area.Rotor blade is unfolded in unmanned plane close to after target area, at this time the biography of rotor
It is dynamic to be disconnected with engine or engine is only needed to provide a small amount of output.
Unmanned plane collocation plays shape shell and uses, and shell can protect unmanned plane knot in initial acceleration and high-speed flight stage
Structure reduces its loss or destruction for contacting and generating with emitter or high-speed flow, in addition smooth case surface and bullet shape
Shelling machine can greatly reduce aerodynamic drag when high-speed flight, reduce initial acceleration energy consumption, improve high-speed flight efficiency.Shell
Body is made of the above cambered surface shell of two panels, and cambered surface shell is mutually tightened connection and forms hollow bullet shape shell.It can be used and unlimited
In releasing the modes such as bolt limitation destruction using steering engine, the shell place of being fastenedly connected can be opened in the sky, the present embodiment, which uses, to be filled
Gas bag inflation compression baffle makes shell be detached from the mode of buckle, to make to separate between shell, is detached from unmanned plane.
The offer of unmanned plane initial velocity may be from launching other different modes, and the equipment for giving unmanned plane initial velocity is also unlimited
In fixed or mobile form.
An engine built in unmanned aerial vehicle body can drive upper and lower two sets of rotors to rotate backward, provide power.Below fuselage
A gondola task apparatus is carried, it is distant that the collected video of mission area is back to ground by control system and data link
Control end.
Upper and lower two sets of propeller blades are staggered folding by unmanned plane using preceding, are encapsulated in a bullet shape material shell
It is interior, in the gun barrel of whole piece of body filling above-ground launcher.For example, high pressure gas holder is connected in the gun barrel of above-ground launcher, it can
Abrupt release high pressure gas provides transmitting thrust for body and unmanned plane.
Above-ground launcher adjusts launch angle and the direction of the launch, and the body for carrying unmanned plane is projected, unmanned plane high speed
Approach the A point in task object region；When close near A point, shell is detached from unmanned plane, subsequent unmanned plane blade expansion, unmanned plane
Whole front face area increases, and suffered resistance increases, and unmanned plane reduces speed now and obtains a part of lift with propeller spin；Nothing
Man-machine to be decelerated to hovering flight state, the gondola task apparatus below fuselage is started to work, and the video pictures of mission area are adopted
Collect and passes ground remote control end back；After the change of location of target area, unmanned plane flies to next mesh according to the instruction at ground remote control end
Mark region.
The utility model and embodiments thereof are described above, this description is no restricted, shown in attached drawing
Be also one of the embodiments of the present invention, actual structure is not limited to this.All in all if this field
Those of ordinary skill is enlightened by it, without deviating from the purpose of the present invention, not inventively design with
The similar frame mode of the technical solution and embodiment, all should belong to the protection range of the utility model.
Claims (5)
1. the rotor wing unmanned aerial vehicle that one kind quickly approaches, including fuselage main body (1), transmitting shell (13) and emitter (16),
It is characterized in that: being equipped with coaxial double-oar leaf device (2) at the top of the fuselage main body (1), the coaxial double-oar leaf device (2) includes interior
Axis (3), the bottom of the inner shaft (3) are equipped with bevel gear one (4), are equipped with upper rotating disk at the top position of the inner shaft (3)
(5), it covers and is equipped with outer shaft (6) at the medium position of the inner shaft (3), outer shaft (6) bottom is equipped with bevel gear two (7), institute
It states bevel gear two (7) and bevel gear one (4) is symmetrical arranged, be arranged at the center of inner shaft (3) perforation bevel gear two (7), institute
State bevel gear two (7) and bevel gear one (4) be all set in fuselage main body (1), be equipped in the fuselage main body (1) and simultaneously and
The drive bevel gear (8) that bevel gear two (7), bevel gear one (4) match connects at the center of the drive bevel gear (8) and subtracts
The output shaft end of speed motor, the fuselage main body (1) is interior to be equipped with controller, and the decelerating motor is electrically connected controller, described
The upper outside of outer shaft (6) is equipped with lower rotating disc (9), circumferentially symmetrical on the upper rotating disk (5) and lower rotating disc (9) to distinguish
Equipped with a pair of of blade (10), the blade (10) is hinged on rotating disk (5) and lower rotating disc (9) edge, the blade
(10) connecting rod (11) are equipped with close to articulated position lower hinge, on the inner shaft (3) and outer shaft (6) with blade (10) are ipsilateral sets
Have blade draw off gear (12), the other end articulated blade draw off gear (12) of the connecting rod (11), the blade folding and unfolding dress
The folding and unfolding of (12) driving connecting rod (11) control blade (10) is set, fuselage main body (1) lower part is equipped with task apparatus (14), institute
The fuselage main body (1) for stating transmitting shell (13) and folding blade (10) matches, and the transmitting shell (13) is big including two pieces etc.
Cambered surface shell (15), in mating connection between the cambered surface shell (15), the transmitting shell (13) is closed at one end, the other end
Dispersion pedestal (22) is snapped connection, is equipped with and emits the emission cavity that shell (13) matches, institute in the emitter (16)
State the device that ejection launch shell (13) are equipped in emitter (16).
2. the rotor wing unmanned aerial vehicle that one kind according to claim 1 quickly approaches, it is characterised in that: blade (10) end
Equipped with stepped interface, the upper rotating disk (5) and lower rotating disc (9) end are equipped with the ladder with blade (10) matching ends
Type interface, the ladder type interface are equipped with elastic buffer film (17).
3. the rotor wing unmanned aerial vehicle that one kind according to claim 1 quickly approaches, it is characterised in that: the blade draw off gear
(12) include the sliding slot (18) being arranged in inner shaft (3) and outer shaft (6), magnetic saddle (19), institute are equipped in the sliding slot (18)
One end of magnetic saddle (19) bar that is articulated and connected (11) is stated, is connected between the top and sliding slot (18) top of the magnetism saddle (19)
It is connected to spring (20), sliding slot (18) bottom is equipped with electromagnet (21), and the electromagnet (21) is electrically connected controller.
4. the rotor wing unmanned aerial vehicle that one kind according to claim 1 quickly approaches, it is characterised in that: the task apparatus (14)
Including camera, the camera is electrically connected controller.
5. the rotor wing unmanned aerial vehicle that one kind according to claim 1 quickly approaches, it is characterised in that: the dispersion pedestal (22)
It is interior to be equipped with inflation packet (23), liquid nitrogen container is equipped in the inflation packet (23), the liquid nitrogen container is equipped with electromagnetic gas valve (24), described
Electromagnetic gas valve (24) is electrically connected controller, and close transmitting shell (13) side is equipped with baffle in the dispersion pedestal (22)
(25), the transmitting shell (13) and dispersion pedestal (22) junction are circumferentially uniformly provided with Elastic buckle (26), the dispersion
The deck (27) that pedestal (22) is equipped with and Elastic buckle (26) match.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821103525.8U CN208498792U (en) | 2018-07-12 | 2018-07-12 | A kind of rotor wing unmanned aerial vehicle quickly approached |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821103525.8U CN208498792U (en) | 2018-07-12 | 2018-07-12 | A kind of rotor wing unmanned aerial vehicle quickly approached |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208498792U true CN208498792U (en) | 2019-02-15 |
Family
ID=65284232
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821103525.8U Active CN208498792U (en) | 2018-07-12 | 2018-07-12 | A kind of rotor wing unmanned aerial vehicle quickly approached |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208498792U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791859A (en) * | 2018-07-12 | 2018-11-13 | 西安君晖航空科技有限公司 | A kind of rotor wing unmanned aerial vehicle quickly approached |
-
2018
- 2018-07-12 CN CN201821103525.8U patent/CN208498792U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791859A (en) * | 2018-07-12 | 2018-11-13 | 西安君晖航空科技有限公司 | A kind of rotor wing unmanned aerial vehicle quickly approached |
| CN108791859B (en) * | 2018-07-12 | 2024-02-06 | 西安君晖航空科技有限公司 | Rotor unmanned aerial vehicle who supports closely fast |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: A rapidly approaching rotor drone Effective date of registration: 20231020 Granted publication date: 20190215 Pledgee: Pudong Development Bank of Shanghai Limited by Share Ltd. Xi'an branch Pledgor: XI'AN JUNHUI AVIATION TECHNOLOGY CO.,LTD. Registration number: Y2023980062077 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right |