CN106143911A - A kind of individual soldier carries, can cartridge type storage and the collapsible unmanned plane launched - Google Patents
A kind of individual soldier carries, can cartridge type storage and the collapsible unmanned plane launched Download PDFInfo
- Publication number
- CN106143911A CN106143911A CN201610550233.8A CN201610550233A CN106143911A CN 106143911 A CN106143911 A CN 106143911A CN 201610550233 A CN201610550233 A CN 201610550233A CN 106143911 A CN106143911 A CN 106143911A
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- China
- Prior art keywords
- fuselage
- folding shaft
- grid
- tail
- wing
- Prior art date
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- 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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U80/00—Transport or storage specially adapted for UAVs
- B64U80/70—Transport or storage specially adapted for UAVs in containers
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Transportation (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of individual soldier carry, can cartridge type storage and launch collapsible unmanned plane, including fuselage, host wing, grid empennage mechanism, vertical tail and power assembly, power assembly is provided with camera, it is provided with at the tail of fuselage, the host wing at the upper and lower two ends of fuselage is connected by main wing folding shaft, main wing folding shaft is located at the 30% ~ 40% of the spanwise length of host wing, and vertical tail is connected with fuselage by vertical tail folding shaft；Power assembly includes fluted disc propeller hub, drives motor and motor gear, motor gear coordinates with fluted disc propeller hub internal messing, and motor gear is connected with the output of driving motor, fluted disc propeller hub is provided with at least two and fixes seat, and each fixing seat is all connected with screw by screw folding shaft.Beneficial effects of the present invention: have a smooth flight, reliability is high, reduces wing load and improves cruising time, opens resistance little, it is simple to individual soldier carries, and whole layout is self-stabilization layout.
Description
Technical field
The present invention relates to a kind of unmanned plane, it particularly relates to a kind of individual soldier carries, can cartridge type storage and rolling over of launching
Folded unmanned plane.
Background technology
" switchblade " MAV is developed by US Airways Envirolution, INC. of California, USA.It can be by individual soldier
Use low expense ejector to launch, then rely on battery power flight, carry monitoring apparatus, mobile surface targets can be implemented
Tracing and monitoring, is also equipped with a bomblet in body.Why this small-sized attack unmanned plane can insert in launching tube
Carry, be because that it have employed before and after two to can be with the wing of folding and expanding and locking as switchblade.
" switchblade " unmanned plane is only about 45 centimetres, can load infantry's knapsack.U.S. army is thought, uses " switchblade " energy notable
Weaken enemy firepower, such as attack sniper, machine gun and mortar etc., and also the subsidiary injury of " switchblade " is few, and especially suitable
In urban operation.
But the layout of switchblade unmanned plane has two problems.One is that two pairs of wings have two independent rotating shafts, altogether
Four wings, reduce reliability when wing launches.Two is owing to two pairs of wing areas of front and back are close, the control moment of generation
Balancing each other mutually, therefore pitching is poor from stability, the concussion that pitch attitude controls easily occurs.
For the problem in correlation technique, effective solution is not yet proposed at present.
Content of the invention
It is an object of the invention to provide a kind of individual soldier carry, can cartridge type storage and launch collapsible unmanned plane, to overcome
Currently available technology above shortcomings.
For realizing above-mentioned technical purpose, the technical scheme is that and be achieved in that:
A kind of individual soldier carries, can cartridge type storage and the collapsible unmanned plane launched, including fuselage, be provided with at the head of described fuselage
Power assembly, described power assembly is provided with camera away from one end of fuselage, and the tail left and right sides of described fuselage is equipped with can
The grid empennage mechanism folding towards the heading of described fuselage, on described fuselage, the two ends up and down at body nodal point are equal
Being provided with host wing, the described host wing at the upper and lower two ends of described fuselage is connected by main wing folding shaft, and described main wing folding shaft
Penetrating described fuselage, described main wing folding shaft is located at the 30% ~ 40% of the spanwise length of host wing, and outside host wing is longer,
Inner side host wing is shorter, near grid tail at grid empennage mechanism and on the right side of described fuselage tail on the left of described fuselage tail
Being equipped with vertical tail at wing mechanism, described vertical tail is connected with described fuselage by vertical tail folding shaft；Described dynamic
Power assembly includes fluted disc propeller hub, drives motor and motor gear, and described fluted disc propeller hub is connected with the head of fuselage, described motor
Gear coordinates with fluted disc propeller hub internal messing, and described motor gear is connected with the output of described driving motor, described fluted disc
The excircle of propeller hub is provided with at least two and fixes seat, and each fixing seat is all connected with by screw folding shaft can be towards institute
State the screw that the tail direction of fuselage folds.
Further, described grid empennage mechanism includes the grid empennage mounting seat being fixedly installed on fuselage tail side,
Described grid empennage mounting seat is all connected with can be folded towards the heading of described fuselage by grid empennage folding shaft
Grid empennage.
Further, the quantity of described fixing seat is two, and the angle between two fixing seats is 180 °.
Further, described vertical tail can be rotated towards described body joint by vertical tail folding shaft, and angle of rotation
Degree is between 0 ° to 180 °.
Further, described fluted disc propeller hub is hollow-core construction.
Beneficial effects of the present invention: the present invention uses the aerodynamic arrangement of static-stability, preposition screw, and flight is relatively more steady,
Host wing is opened backward around a main wing folding shaft, improves reliability, and host wing is divided into left and right two around main wing folding shaft
Part, adds wing area, reduces wing load and improves cruising time, connects simultaneously because the main wing folding shaft of host wing compares
The center of gravity of nearly host wing, therefore host wing is less to the asymmetrical stress of main wing folding shaft, opens resistance also less, after folding,
Unmanned plane can put into the container of a long cartridge type, it is simple to individual soldier carries, and whole layout is self-stabilization layout.
Brief description
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to institute in embodiment
The accompanying drawing using is needed to be briefly described, it should be apparent that, the accompanying drawing in describing below is only some enforcements of the present invention
Example, for those of ordinary skill in the art, on the premise of not paying creative work, can also obtain according to these accompanying drawings
Obtain other accompanying drawing.
The individual soldier that Fig. 1 is described according to embodiments of the present invention carries, can cartridge type storage and the collapsible unmanned plane launched
Structural representation；
The individual soldier that Fig. 2 is described according to embodiments of the present invention carries, can the folding of cartridge type storage and the collapsible unmanned plane launched
State diagram；
The individual soldier that Fig. 3 is described according to embodiments of the present invention carries, can the local of cartridge type storage and the collapsible unmanned plane launched
Structural representation；
Fig. 4 is the structural representation of power assembly described according to embodiments of the present invention.
In figure:
1st, fuselage；2nd, host wing；3rd, grid empennage；4th, camera；5th, grid empennage mechanism；6th, main wing folding shaft；7th, vertical end
The wing；8th, vertical tail folding shaft；9th, fluted disc propeller hub；10th, motor is driven；11st, motor gear；12nd, seat is fixed；13rd, screw folding
Folded axle；14th, screw；15th, grid empennage mounting seat；16th, grid empennage folding shaft.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Describe, it is clear that described embodiment is only a part of embodiment of the present invention, rather than whole embodiments wholely.Based on
Embodiment in the present invention, all other embodiment that those of ordinary skill in the art are obtained, broadly fall into present invention protection
Scope.
As shown in Figures 1 to 4, a kind of individual soldier according to embodiments of the invention carries, cartridge type can store and launch
Collapsible unmanned plane, including fuselage 1, at the head of described fuselage 1, be provided with power assembly, described power assembly is away from fuselage 1
One end be provided with camera 4, the tail left and right sides of described fuselage 1 be equipped with can towards described fuselage 1 heading fold
Grid empennage mechanism 5, described fuselage 1 is equipped with host wing 2, on described fuselage 1 near the two ends up and down of fuselage 1 center of gravity
The described host wing 2 at lower two ends is connected by main wing folding shaft 6, and described main wing folding shaft 6 penetrates described fuselage 1, described
Main wing folding shaft 6 is located at the 30% ~ 40% of the spanwise length of host wing 2, and outside host wing 2 is longer, and inner side host wing 2 is relatively
Short, on the left of described fuselage 1 tail at grid empennage mechanism 5 and on the right side of described fuselage 1 tail at grid empennage mechanism 5
Being equipped with vertical tail 7, described vertical tail 7 is connected with described fuselage 1 by vertical tail folding shaft 8；Described power is total
Becoming to include that the 9th, fluted disc propeller hub drives motor 10 and motor gear 11, described fluted disc propeller hub 9 is connected with the head of fuselage 1, described
Motor gear 11 coordinates with fluted disc propeller hub 9 internal messing, and described motor gear 11 is connected with the output of described driving motor 10
Connecing, the excircle of described fluted disc propeller hub 9 is provided with at least two and fixes seat 12, and each fixing seat 12 is all folded by screw
Axle 13 is connected with the screw 14 that can fold towards the tail direction of described fuselage 1.
Described grid empennage mechanism 5 includes the grid empennage mounting seat 15 being fixedly installed on fuselage 1 tail side, described lattice
Grid empennage mounting seat 15 is all connected with by grid empennage folding shaft 16 can be towards the heading folding of described fuselage 1
Grid empennage 3.
The quantity of described fixing seat 12 is two, and the angle between two fixing seats 12 is 180 °.
Described vertical tail 7 can be rotated towards described fuselage 1 head by vertical tail folding shaft 8, and rotational angle is 0 °
Between 180 °.
Described fluted disc propeller hub 9 is hollow-core construction, thus convenient installation camera 4.
Understand the technique scheme of the present invention for convenience, below by way of above-mentioned to the present invention in specifically used mode
Technical scheme is described in detail.
When specifically used, described screw 14 and described driving motor the 10th, described fluted disc propeller hub the 9th, described motor gear
11st, described screw folding shaft 13 constitutes power assembly, and described motor gear 11 and described driving motor 10 connect, by described
The inside engaged gear of fluted disc propeller hub 9 drives described fluted disc propeller hub 9 to rotate, and drives described screw 14 to produce pulling force, described fluted disc
Propeller hub 9 is hollow-core construction, and described camera 4 and other cables can pass through from head, and described screw 14 is with described fluted disc propeller hub 9
For axle, can fold to tail, the described host wing 2 at described fuselage two ends about 1 is by described main wing folding shaft 6 and described fuselage
1 connects, and is attached to described fuselage 1 upper and lower after folding, and described vertical tail 7 can be rolled over to head around described vertical tail folding shaft 8
Folding and being attached to described fuselage 1 both sides, described grid empennage 3 is folded in described fuselage 1 both sides by described grid empennage folding shaft 16,
After folding, unmanned plane can put into the container of a long cartridge type, it is simple to individual soldier carries.
The described host wing 2 of described fuselage 1 upper and lower shares a described main wing folding shaft 6, and described main wing folding shaft 6 sets
At the 30% ~ 40% of the spanwise length of described host wing 2, and outside described host wing 2 is longer, and inner side described host wing 2 is shorter,
Therefore described host wing 2 is less to the asymmetrical stress of described main wing folding shaft 6, opens resistance also less.
In sum, the technique scheme by means of the present invention, the present invention uses the aerodynamic arrangement of static-stability, preposition spiral shell
Rotation oar 14, flight is relatively more steady, and host wing 2 is opened backward around a main wing folding shaft 6, improves reliability, and host wing 2 encloses
It is divided into left and right two parts around main wing folding shaft 6, adds wing area, reduce wing load and improve cruising time, simultaneously because
The center of gravity of the main wing folding shaft 6 of host wing 2 relatively host wing 2, the therefore asymmetric pressure to main wing folding shaft 6 for the host wing 2
Power is less, opens resistance also less, and after folding, unmanned plane can put into the container of a long cartridge type, it is simple to individual soldier carries, whole
Individual layout is self-stabilization layout.
The foregoing is only presently preferred embodiments of the present invention, not in order to limit the present invention, all essences in the present invention
Within god and principle, any modification, equivalent substitution and improvement etc. made, should be included within the scope of the present invention.
Claims (5)
1. individual soldier carry, can cartridge type storage and the collapsible unmanned plane launched, including fuselage (1), it is characterised in that described
Being provided with power assembly at the head of fuselage (1), described power assembly is provided with camera (4), described machine away from one end of fuselage (1)
The tail left and right sides of body (1) is equipped with the grid empennage mechanism (5) that can fold, institute towards the heading of described fuselage (1)
State the upper two ends up and down near fuselage (1) center of gravity of fuselage (1) and be equipped with host wing (2), the institute at the upper and lower two ends of described fuselage (1)
State host wing (2) to be connected by main wing folding shaft (6), and described main wing folding shaft (6) penetrates described fuselage (1), described master
Wingfold axle (6) is located at the 30% ~ 40% of the spanwise length of host wing (2), and outside host wing (2) is longer, inner side host wing
(2) shorter, near grid on the right side of grid empennage mechanism (5) place and described fuselage (1) tail on the left of described fuselage (1) tail
Empennage mechanism (5) place is equipped with vertical tail (7), and described vertical tail (7) is by vertical tail folding shaft (8) and described fuselage
(1) it is connected；Described power assembly includes fluted disc propeller hub (9), drives motor (10) and motor gear (11), described fluted disc propeller hub
(9) being connected with the head of fuselage (1), described motor gear (11) coordinates with fluted disc propeller hub (9) internal messing, and described motor tooth
Wheel (11) is connected with the output of described driving motor (10), and the excircle of described fluted disc propeller hub (9) is provided with at least two
Fixing seat (12), each fixing seat (12) is all connected with by screw folding shaft (13) can be towards the machine of described fuselage (1)
The screw (14) that tail direction folds.
2. a kind of individual soldier according to claim 1 carry, can cartridge type storage and launch collapsible unmanned plane, its feature exists
In described grid empennage mechanism (5) includes grid empennage mounting seat (15) being fixedly installed on fuselage (1) tail side, described
Grid empennage mounting seat (15) is all connected with by grid empennage folding shaft (16) can be towards the head side of described fuselage (1)
To the grid empennage (3) folding.
3. a kind of individual soldier according to claim 1 carry, can cartridge type storage and launch collapsible unmanned plane, its feature exists
In the quantity of described fixing seat (12) is two, and the angle between two fixing seats (12) is 180 °.
4. a kind of individual soldier according to claim 1 carry, can cartridge type storage and launch collapsible unmanned plane, its feature exists
In described vertical tail (7) can be rotated towards described fuselage (1) head by vertical tail folding shaft (8), and rotational angle is 0 °
Between 180 °.
5. a kind of individual soldier according to claim 1 carry, can cartridge type storage and launch collapsible unmanned plane, its feature exists
In described fluted disc propeller hub (9) is hollow-core construction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610550233.8A CN106143911B (en) | 2016-07-13 | 2016-07-13 | A kind of foldable unmanned plane that individual soldier carries, can cartridge type storage and emit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610550233.8A CN106143911B (en) | 2016-07-13 | 2016-07-13 | A kind of foldable unmanned plane that individual soldier carries, can cartridge type storage and emit |
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| Publication Number | Publication Date |
|---|---|
| CN106143911A true CN106143911A (en) | 2016-11-23 |
| CN106143911B CN106143911B (en) | 2018-08-10 |
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| CN201610550233.8A Active CN106143911B (en) | 2016-07-13 | 2016-07-13 | A kind of foldable unmanned plane that individual soldier carries, can cartridge type storage and emit |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516147A (en) * | 2016-12-01 | 2017-03-22 | 南京航空航天大学 | Mobile launch type autogyro and control method thereof |
| CN106828878A (en) * | 2017-03-29 | 2017-06-13 | 深圳市轻准科技有限公司 | Examine and beat one unmanned plane |
| CN106986002A (en) * | 2017-03-29 | 2017-07-28 | 北京华信智航科技有限公司 | A kind of folding wings unmanned plane of cartridge type storage |
| CN108177783A (en) * | 2017-12-28 | 2018-06-19 | 陕西中科博亿电子科技有限公司 | A kind of training type unmanned plane |
| CN109436296A (en) * | 2018-12-26 | 2019-03-08 | 西北工业大学 | Tubular launching folding wing unmanned aerial vehicle and its launching method |
| CN110567326A (en) * | 2019-07-30 | 2019-12-13 | 中国人民解放军陆军工程大学 | Integrated flying patrol bomb of aircraft |
| CN110834715A (en) * | 2019-10-21 | 2020-02-25 | 中国运载火箭技术研究院 | Missile-borne unmanned aerial vehicle's folding wing |
| CN110979741A (en) * | 2019-11-25 | 2020-04-10 | 北京宇航系统工程研究所 | A zigzag stepped variable section grid rudder structure based on drop zone control |
| CN111099011A (en) * | 2018-10-25 | 2020-05-05 | 酷黑科技（北京）有限公司 | Aircraft |
| KR102202014B1 (en) * | 2020-09-07 | 2021-01-12 | 국방과학연구소 | Projectile with folding wings and control method thereof |
| CN113291457A (en) * | 2021-05-19 | 2021-08-24 | 中航西安飞机工业集团股份有限公司 | Aircraft nose fairing structure and aircraft attitude control method |
| CN114291247A (en) * | 2022-01-20 | 2022-04-08 | 北京航空航天大学 | Foldable full-motion film wing micro unmanned aerial vehicle system |
| CN115320824A (en) * | 2022-06-28 | 2022-11-11 | 西安羚控电子科技有限公司 | Unfolding method |
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| CN205931256U (en) * | 2016-07-13 | 2017-02-08 | 西藏长源动力科技有限公司 | But individual soldier carries collapsible unmanned aerial vehicle of cylinder storage and transmission |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106516147A (en) * | 2016-12-01 | 2017-03-22 | 南京航空航天大学 | Mobile launch type autogyro and control method thereof |
| CN106828878A (en) * | 2017-03-29 | 2017-06-13 | 深圳市轻准科技有限公司 | Examine and beat one unmanned plane |
| CN106986002A (en) * | 2017-03-29 | 2017-07-28 | 北京华信智航科技有限公司 | A kind of folding wings unmanned plane of cartridge type storage |
| CN108177783A (en) * | 2017-12-28 | 2018-06-19 | 陕西中科博亿电子科技有限公司 | A kind of training type unmanned plane |
| CN111099011A (en) * | 2018-10-25 | 2020-05-05 | 酷黑科技（北京）有限公司 | Aircraft |
| CN109436296A (en) * | 2018-12-26 | 2019-03-08 | 西北工业大学 | Tubular launching folding wing unmanned aerial vehicle and its launching method |
| CN109436296B (en) * | 2018-12-26 | 2024-02-13 | 西北工业大学 | Barrel-type launching folding wing unmanned aerial vehicle and launching method thereof |
| CN110567326A (en) * | 2019-07-30 | 2019-12-13 | 中国人民解放军陆军工程大学 | Integrated flying patrol bomb of aircraft |
| CN110834715A (en) * | 2019-10-21 | 2020-02-25 | 中国运载火箭技术研究院 | Missile-borne unmanned aerial vehicle's folding wing |
| CN110979741A (en) * | 2019-11-25 | 2020-04-10 | 北京宇航系统工程研究所 | A zigzag stepped variable section grid rudder structure based on drop zone control |
| CN110979741B (en) * | 2019-11-25 | 2021-02-09 | 北京宇航系统工程研究所 | Sawtooth step type variable profile grid rudder structure based on falling area control |
| KR102202014B1 (en) * | 2020-09-07 | 2021-01-12 | 국방과학연구소 | Projectile with folding wings and control method thereof |
| CN113291457A (en) * | 2021-05-19 | 2021-08-24 | 中航西安飞机工业集团股份有限公司 | Aircraft nose fairing structure and aircraft attitude control method |
| CN113291457B (en) * | 2021-05-19 | 2023-09-05 | 中航西安飞机工业集团股份有限公司 | Aircraft nose fairing structure and aircraft attitude control method |
| CN114291247A (en) * | 2022-01-20 | 2022-04-08 | 北京航空航天大学 | Foldable full-motion film wing micro unmanned aerial vehicle system |
| CN115320824A (en) * | 2022-06-28 | 2022-11-11 | 西安羚控电子科技有限公司 | Unfolding method |
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| CN106143911B (en) | 2018-08-10 |
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