CN108189999A - A kind of split type unmanned plane - Google Patents
A kind of split type unmanned plane Download PDFInfo
- Publication number
- CN108189999A CN108189999A CN201711452398.2A CN201711452398A CN108189999A CN 108189999 A CN108189999 A CN 108189999A CN 201711452398 A CN201711452398 A CN 201711452398A CN 108189999 A CN108189999 A CN 108189999A
- Authority
- CN
- China
- Prior art keywords
- plugboard
- wing
- fuselage
- wedge block
- unmanned plane
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Forklifts And Lifting Vehicles (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of split type unmanned plane, including head, fuselage, the first plugboard, the second plugboard, main wing mechanism, empennage mechanism and power plant；One in first plugboard and the second plugboard is mounted on head, and another to be mounted on fuselage, head is connected with fuselage by the first plugboard and the second plugboard；The edge of first plugboard is provided with the first wing plate for connection, and the first wedge block and the second wedge block are provided on the first wing plate；The edge of second plugboard is provided with the second wing plate for connection, and third wedge block and wedge block group are provided on the second wing plate, and main wing mechanism, empennage mechanism and power plant are mounted on fuselage.Unmanned aerial vehicle design is split structure by the present invention, passes through the first plugboard and the grafting each other of the second plugboard between head and fuselage so that same fuselage can carry different heads to adapt to different tasks.
Description
Technical field
The present invention relates to aircraft devices field more particularly to a kind of split type unmanned planes.
Background technology
Unmanned plane refers to unpiloted not manned aircraft, is generally controlled and flown by airborne program or ground remote control facility
Machine.It is small and do not fear the characteristics of danger so that unmanned plane suffers from very extensive purposes, example in dual-use field
Such as take photo by plane, plant protection, disaster relief, exploration and anti-terrorism field.Different application fields has different working environments, in order to suitable
Complicated working environment is answered, the unmanned plane of the prior art has developed diversified radiation pattern, such as racetrack transmitting, fire
The transmitting of arrow assisted, the transmitting of orbit shot formula, machine tool air-launched and cartridge type transmitting etc..Wherein, cartridge type transmitting is mainly used in
Unmanned plane after folding is stored in inner barrel by folding wings unmanned plane, launching tube, lights the firer in launching tube before transmission
Product utilize compressed gas source boosting unmanned plane, unmanned plane is made to obtain suitable initial velocity and finally take off.
The advantages of folding unmanned plane of cartridge type transmitting, is that radiation pattern is flexible, and launching tube is small, can be carried with individual soldier,
Launch site is hardly influenced by landform.It is however, small in order to cope with complicated task or combat duty, a transmitting
Group generally requires many different folding unmanned planes of configuration, not convenient enough.
Invention content
The technical problem to be solved in the present invention is to provide a kind of split type unmanned planes so that a fuselage can efficiently be taken
With different heads to adapt to different work requirements.
In order to solve the above technical problems, the technical solution adopted by the present invention is：A kind of split type unmanned plane, including head,
Fuselage, the first plugboard, the second plugboard, main wing mechanism, empennage mechanism and power plant；
One in first plugboard and the second plugboard is mounted on head, another to be mounted on fuselage, head and machine
Body is connected by the first plugboard and the second plugboard；
The edge of first plugboard is provided with the first wing plate for connection, generally each in the left and right edges of the first plugboard
One piece of first wing plate is set, the first wedge block and the second wedge block are provided on the first wing plate；
The edge of second plugboard is provided with the second wing plate for connection, generally each in the left and right edges of the second plugboard
One piece of second wing plate is set, is provided with third wedge block and wedge block group on the second wing plate, the wedge block group include two pieces that
This opposite wedge block so that the intermediate of wedge block group forms a V-shaped slot；
When the first plugboard and the second plugboard connect, the first wedge block and third wedge block are caught on each other, the second wedge
Shape block is inserted into the centre of wedge block group；
Main wing mechanism, empennage mechanism and power plant are mounted on fuselage, wherein main wing mechanism and empennage mechanism be can
The wing structure of folding.
Further, pressing plate, one end connection head of pressing plate are provided on fuselage.
Specifically, the main wing mechanism includes the first main wing, the second main wing, shaft, torsional spring and rocking arm；It first main wing and shakes
Arm is fixedly connected with shaft, and shaft is hinged on fuselage；Second main wing is hinged in shaft, the first wing and the second wing it
Between between be separated with polytetrafluoroethylene gasket；The hinged end of second main wing is provided with circular groove, and torsional spring is mounted in circular groove, is turned round
First end of spring is fixed in the circular hole of rocking arm, and the second end is fixed in circular groove；The end of pressing plate is buckled in shaft
Upper end.
Specifically, the empennage mechanism includes sleeve, guide rod, wing bar and empennage ontology；Sleeve is installed on the machine of unmanned plane
Body, the surface of sleeve are provided with helicla flute, and guide rod is mounted in sleeve, axis pin is provided on guide rod, axis pin is plugged on helicla flute
It is interior；When axially reciprocating of the guide rod along sleeve, axis pin drive leader rotation under the action of helicla flute；Guide rod and sleeve
Between be provided with spring；The end of wing bar and guide rod is hinged, and empennage ontology is mounted on wing bar.
Advantageous effect：Unmanned aerial vehicle design is split structure by the present invention, passes through the first plugboard between head and fuselage
With the grafting each other of the second plugboard so that same fuselage can carry different heads to adapt to different tasks；Together
When, the connected structure between head and fuselage of the present invention is simple, grafting simple operation, in production plant or use site
Head replacement can be rapidly completed, and replacement operation is without technical professional.
Description of the drawings
Fig. 1 is the stereogram of 1 unmanned plane of embodiment.
Fig. 2 is the part drawing (connection status) of 1 unmanned plane head of embodiment and fuselage.
Fig. 3 is the part drawing (disassembled form) of 1 unmanned plane head of embodiment and fuselage.
Fig. 4 is the vertical view of 1 unmanned plane head of embodiment and fuselage.
Fig. 5 is the A-A sectional views of Fig. 4.
Fig. 6 is the vertical view of the main wing mechanism of 1 unmanned plane of embodiment.
Fig. 7 is the B-B sectional views of Fig. 6.
Fig. 8 is the partial perspective view of the main wing mechanism of 1 unmanned plane of embodiment.
Fig. 9 is the stereogram (unfolded state) of 1 unmanned airplane empennage mechanism of embodiment.
Figure 10 is the stereogram (folded state) of 1 unmanned airplane empennage mechanism of embodiment.
Figure 11 is the sectional view of 1 unmanned airplane empennage mechanism of embodiment.
Wherein：1st, head；2nd, fuselage；3rd, the first plugboard；3-1, the first wing plate；3-2, the first wedge block；3-3, second
Wedge block；4th, the second plugboard；4-1, the second wing plate；4-2, third wedge block；4-3, wedge block group；5th, pressing plate；6th, main wing machine
Structure；6-1, the first main wing；6-2, the second main wing；6-3, shaft；6-4, torsional spring；6-5, rocking arm；6-6, washer；7th, empennage mechanism；
7-1, sleeve；7-1-1, helicla flute；7-2, guide rod；7-3, wing bar, 7-4, empennage ontology；7-5, axis pin；7-6, spring；8th, power
Device.
Specific embodiment
The present invention is described in further detail With reference to embodiment.
Embodiment 1
As shown in Figures 1 to 5, the split type unmanned plane of the present embodiment, including head 1, fuselage 2, the first plugboard 3,
Two plugboards 4, pressing plate 5, main wing mechanism 6, empennage mechanism 7 and power plant 8；
As shown in figure 3, the first plugboard 3 is mounted on head 1, the second plugboard 4 is mounted on fuselage 2；First grafting
The left and right edges of plate 3, which are provided on the first wing plate 3-1, the first wing plate 3-1 for connection, is provided with the first wedge block 3-2 and
Two wedge block 3-3；The left and right edges of second plugboard 4 are provided on the second wing plate 4-1, the second wing plate 4-1 for connection and set
It is equipped with third wedge block 4-2 and wedge block group 4-3, the wedge block group 4-3 includes two pieces of wedge blocks relative to each other so that wedge
The intermediate of shape block group 4-3 forms a V-shaped slot；
As shown in figure 5, when the first plugboard 3 and the second plugboard 4 connect, the first wedge block 3-2 and third wedge block
4-2 is caught on each other, and the second wedge block 3-3 is inserted into the centre of wedge block group 4-3；
As shown in Fig. 2, being provided with pressing plate 5 on fuselage 2, one end of pressing plate 5 is fixedly connected with the housing of head 1 by screw；
Specifically, as shown in Figure 6 to 8, main wing mechanism 6 includes the first main wing 6-1, the second main wing 6-2, shaft 6-3, turns round
Spring 6-4 and rocking arm 6-5；First main wing 6-1 and rocking arm 6-5 are fixedly connected with shaft 6-3, and shaft 6-3 is hinged on fuselage 2；
Second main wing 6-2 is hinged on shaft 6-3, and the second main wing 6-2 is stacked on the first main wing 6-1, the masters of the second main wing 6-2 and first
Polytetrafluoroethylene gasket 6-6 is separated between wing 6-1；The hinged end of second main wing 6-2 is provided with circular groove, torsional spring 6-4 peaces
In circular groove, the first end of torsional spring 6-4 is fixed in the circular hole of rocking arm 6-5 (specifically as shown in figure 8, for convenience
Observation, Fig. 8 separate the first end from circular hole), the second end is fixed in circular groove；When folding main wing, the
One main wing 6-1 and the second main wing 6-2 passes through shaft 6-3 and circular groove spinning torsional spring 6-4 accumulation of energys respectively；
The empennage mechanism 7 includes sleeve 7-1, guide rod 7-2, wing bar 7-3 and empennage ontology 7-4；Sleeve 7-1 is installed on nothing
Man-machine fuselage 2, as shown in Figure 9 and Figure 10, the surface of sleeve 7-1 are provided with helicla flute 7-1-1, as shown in figure 11, guide rod 7-2
In sleeve 7-1, axis pin 7-5 is provided on guide rod 7-2, axis pin 7-5 is plugged in helicla flute 7-1-1, guide rod 7-2 with
Spring 7-6 is provided between sleeve 7-1；When axially reciprocatings of the guide rod 7-2 along sleeve 7-1, axis pin 7-5 is in helicla flute
Drive leader 7-2 rotations under the action of 7-1-1；As shown in figure 11, when folding fin, guide rod 7-2 moves downward compressed spring
7-6 accumulation of energys；
Power plant 8 is mounted on 2 tail portion of fuselage.
The unmanned plane of the present embodiment is a kind of folding unmanned plane for cartridge type transmitting, and all wings of unmanned plane are by folding
The entire unmanned plane approximate cylinder shape of poststack, the unmanned plane after folding, which is filled in launching tube, to be emitted；Unmanned plane after lift-off
Under the action of torsional spring 6-4, the first main wing 6-1 and the second main wing 6-2 Automatic-expandings；Under the action of spring 7-6, empennage ontology
7-4 Automatic-expandings；At the same time 8 synchronous averaging of power plant realizes that unmanned plane launches.All wings are installed in fuselage
On 2, fuselage 2 live can be dismounted with head 1, and different communication devices, guidance device, search are provided in different heads 1
Device, combat gear or deliverance apparatus etc. significantly increase the flexibility of unmanned plane, to cope with the work of various complexity
Task.
Although embodiments of the present invention are illustrated in specification, these embodiments are intended only as prompting,
It should not limit protection scope of the present invention.It is equal that various omission, substitution, and alteration are carried out without departing from the spirit and scope of the present invention
It should include within the scope of the present invention.
Claims (4)
1. a kind of split type unmanned plane, it is characterised in that：Including head, fuselage, the first plugboard, the second plugboard, main wing machine
Structure, empennage mechanism and power plant；
One in first plugboard and the second plugboard is mounted on head, and another to be mounted on fuselage, head and fuselage lead to
Cross the first plugboard and the connection of the second plugboard；
The edge of first plugboard is provided with the first wing plate for connection, and the first wedge block and second are provided on the first wing plate
Wedge block；
The edge of second plugboard is provided with the second wing plate for connection, and third wedge block and wedge shape are provided on the second wing plate
Block group, the wedge block group include two pieces of wedge blocks relative to each other；
When the first plugboard and the second plugboard connect, the first wedge block and third wedge block are caught on each other, the second wedge block
It is inserted into the centre of wedge block group；
Main wing mechanism, empennage mechanism and power plant are mounted on fuselage.
2. split type unmanned plane according to claim 1, it is characterised in that：Pressing plate, one end of pressing plate are provided on fuselage
Connect head.
3. split type unmanned plane according to claim 2, it is characterised in that：The main wing mechanism includes the first main wing, the
Two main wings, shaft, torsional spring and rocking arm；First main wing and rocking arm are fixedly connected with shaft, and shaft is hinged on fuselage；Second master
The wing is hinged in shaft, between the first wing and the second wing between be separated with polytetrafluoroethylene gasket；The hinged end of second main wing is set
Circular groove is equipped with, torsional spring is mounted in circular groove, and the first end of torsional spring is fixed in the circular hole of rocking arm, and the second end is consolidated
It is scheduled in circular groove；
The end of pressing plate is buckled in the upper end of shaft.
4. split type unmanned plane according to claim 3, it is characterised in that：The empennage mechanism includes sleeve, guide rod, the wing
Bar and empennage ontology；
Sleeve is installed on the fuselage of unmanned plane, and the surface of sleeve is provided with helicla flute, and guide rod is mounted in sleeve, is set on guide rod
There is axis pin, axis pin is plugged in helicla flute；When axially reciprocating of the guide rod along sleeve, axis pin is under the action of helicla flute
Drive leader rotation；
Spring is provided between guide rod and sleeve；
The end of wing bar and guide rod is hinged, and empennage ontology is mounted on wing bar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711452398.2A CN108189999B (en) | 2017-12-28 | 2017-12-28 | Split type unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711452398.2A CN108189999B (en) | 2017-12-28 | 2017-12-28 | Split type unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108189999A true CN108189999A (en) | 2018-06-22 |
| CN108189999B CN108189999B (en) | 2022-04-26 |
Family
ID=62584842
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711452398.2A Active CN108189999B (en) | 2017-12-28 | 2017-12-28 | Split type unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108189999B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606609A (en) * | 2018-12-29 | 2019-04-12 | 成都纵横大鹏无人机科技有限公司 | A kind of unmanned plane |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4667899A (en) * | 1984-11-28 | 1987-05-26 | General Dynamics, Pomona Division | Double swing wing self-erecting missile wing structure |
| US4957455A (en) * | 1988-04-19 | 1990-09-18 | Sumitomo Wiring Systems, Limited | Socket for wedge-base lamp |
| US20030178527A1 (en) * | 2002-03-19 | 2003-09-25 | Eisentraut Rudolph Adolph | Missile having deployment mechanism for stowable fins |
| KR101303062B1 (en) * | 2013-02-01 | 2013-09-03 | 주식회사 오주산업 | Apparatus for connecting of plastic pipe |
| CN103722537A (en) * | 2013-12-17 | 2014-04-16 | 宁波汉浦工具有限公司 | Multi-nose electric tool |
| CN204197267U (en) * | 2014-10-29 | 2015-03-11 | 北京中科遥数信息技术有限公司 | A kind of fixed-wing unmanned plane body two sectional type rapid dismounting apparatus |
| CN105129069A (en) * | 2015-08-04 | 2015-12-09 | 江西洪都航空工业集团有限责任公司 | Wedge block cabin connecting device |
| CN105174084A (en) * | 2015-06-10 | 2015-12-23 | 南京工业大学 | Inner tower body and outer tower body automatic locking and unlocking apparatus of rapid installation folding tower crane |
| CN205150218U (en) * | 2015-11-18 | 2016-04-13 | 陕西中科博亿电子科技有限公司 | A wing folding mechanism for managing penetrate unmanned aerial vehicle |
| CN106586482A (en) * | 2016-12-02 | 2017-04-26 | 广州三五汽车部件有限公司 | Automatic transposition device |
| CN206231611U (en) * | 2016-12-06 | 2017-06-09 | 广东泰一高新技术发展有限公司 | Off-loadable unmanned aerial vehicle body structure |
| CN206327562U (en) * | 2016-12-27 | 2017-07-14 | 陕西中科博亿电子科技有限公司 | One kind folds the distributed rotary expansion mechanism of unmanned plane wing |
| CN206645035U (en) * | 2017-04-06 | 2017-11-17 | 观典防务技术股份有限公司 | The attachment means of split type unmanned plane body and load cabin |
-
2017
- 2017-12-28 CN CN201711452398.2A patent/CN108189999B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4667899A (en) * | 1984-11-28 | 1987-05-26 | General Dynamics, Pomona Division | Double swing wing self-erecting missile wing structure |
| US4957455A (en) * | 1988-04-19 | 1990-09-18 | Sumitomo Wiring Systems, Limited | Socket for wedge-base lamp |
| US20030178527A1 (en) * | 2002-03-19 | 2003-09-25 | Eisentraut Rudolph Adolph | Missile having deployment mechanism for stowable fins |
| KR101303062B1 (en) * | 2013-02-01 | 2013-09-03 | 주식회사 오주산업 | Apparatus for connecting of plastic pipe |
| CN103722537A (en) * | 2013-12-17 | 2014-04-16 | 宁波汉浦工具有限公司 | Multi-nose electric tool |
| CN204197267U (en) * | 2014-10-29 | 2015-03-11 | 北京中科遥数信息技术有限公司 | A kind of fixed-wing unmanned plane body two sectional type rapid dismounting apparatus |
| CN105174084A (en) * | 2015-06-10 | 2015-12-23 | 南京工业大学 | Inner tower body and outer tower body automatic locking and unlocking apparatus of rapid installation folding tower crane |
| CN105129069A (en) * | 2015-08-04 | 2015-12-09 | 江西洪都航空工业集团有限责任公司 | Wedge block cabin connecting device |
| CN205150218U (en) * | 2015-11-18 | 2016-04-13 | 陕西中科博亿电子科技有限公司 | A wing folding mechanism for managing penetrate unmanned aerial vehicle |
| CN106586482A (en) * | 2016-12-02 | 2017-04-26 | 广州三五汽车部件有限公司 | Automatic transposition device |
| CN206231611U (en) * | 2016-12-06 | 2017-06-09 | 广东泰一高新技术发展有限公司 | Off-loadable unmanned aerial vehicle body structure |
| CN206327562U (en) * | 2016-12-27 | 2017-07-14 | 陕西中科博亿电子科技有限公司 | One kind folds the distributed rotary expansion mechanism of unmanned plane wing |
| CN206645035U (en) * | 2017-04-06 | 2017-11-17 | 观典防务技术股份有限公司 | The attachment means of split type unmanned plane body and load cabin |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606609A (en) * | 2018-12-29 | 2019-04-12 | 成都纵横大鹏无人机科技有限公司 | A kind of unmanned plane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108189999B (en) | 2022-04-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108128460A (en) | A kind of spiral expansion unmanned plane | |
| Zufferey et al. | How ornithopters can perch autonomously on a branch | |
| CN204916161U (en) | No rotorcraft multiaxis aircraft | |
| CN108189999A (en) | A kind of split type unmanned plane | |
| US9815554B2 (en) | Unmanned aerial vehicle | |
| CN207050575U (en) | Unmanned plane carry catches net rifle in the air | |
| CN108190003A (en) | A kind of unmanned plane with buffer gear | |
| CN108177783A (en) | A kind of training type unmanned plane | |
| CN101249891A (en) | Rifle grenade type cartridge unmanned aircraft | |
| CN204871613U (en) | Unmanned aerial vehicle throws down and launches formula parachute -opening device | |
| CN209192222U (en) | A kind of convertible unmanned plane of flight attitude | |
| CN204788036U (en) | Unmanned aerial vehicle darts transmitter | |
| CN209192221U (en) | A kind of modularized multipurpose unmanned plane | |
| CN108928469A (en) | A kind of modularized combination type multi-rotor unmanned aerial vehicle | |
| CN109515732B (en) | Combined aircraft based on barrel type launching | |
| CN203666970U (en) | Driving connecting structure for aileron of unmanned aerial vehicle | |
| CN108146613A (en) | A kind of unmanned plane with retaining mechanism | |
| CN206900643U (en) | A kind of agricultural spraying unmanned plane | |
| CN108146611A (en) | A kind of portable agricultural formula unmanned plane and its application method | |
| CN109264018A (en) | A kind of compact storage and transportation unmanned plane fast assembling disassembling structure layout | |
| CN210852910U (en) | Electronic folding flight oar of unmanned aerial vehicle | |
| CN211630857U (en) | Unmanned aerial vehicle mows | |
| CN207311833U (en) | A kind of unmanned plane horn and unmanned plane | |
| CN216035136U (en) | Unmanned aerial vehicle powder spraying device | |
| McCarthy | Flight hardware development for a space-based robotic assembly and servicing testbed |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |