CN207875971U - A kind of unmanned plane - Google Patents
A kind of unmanned plane Download PDFInfo
- Publication number
- CN207875971U CN207875971U CN201820258653.3U CN201820258653U CN207875971U CN 207875971 U CN207875971 U CN 207875971U CN 201820258653 U CN201820258653 U CN 201820258653U CN 207875971 U CN207875971 U CN 207875971U
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- wing
- frame
- fuselage
- tail
- hoisting frame
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- 230000001737 promoting effect Effects 0.000 claims description 7
- 238000005452 bending Methods 0.000 claims description 3
- 230000000630 rising effect Effects 0.000 description 8
- 230000001133 acceleration Effects 0.000 description 3
- 238000005303 weighing Methods 0.000 description 3
- 230000000295 complement effect Effects 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000007514 turning Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Abstract
The utility model discloses a kind of unmanned planes, including fuselage, the pusher side wing and tail, it is provided with head on the left of the fuselage, and advance rotor is installed on the outside of head, fixed organic upper frame among the top of the fuselage, and balance plate is installed on the outside of machine upper frame, the first hoisting frame is provided on the left of the balance plate, and the second hoisting frame is installed on the right side of balance plate, it is both provided with promotion helical mount above first hoisting frame and the second hoisting frame, and it is promoted and is fixed with the promotion wing on the outside of helical mount, it is both provided with crane below first hoisting frame and the second hoisting frame, it is provided with top wing above the pusher side wing, and the pusher side wing is located at the outside of fuselage, balance empennage is installed on the right side of the tail, and tail is located at the right side of truss.The unmanned plane during flying is stablized, and the air-flow flow-disturbing that can be fought under high altitude environment influences, and machine rise range is larger, and the secondary power-assisted that can carry out flying height is promoted.
Description
Technical field
The utility model is related to air vehicle technique field, specially a kind of unmanned plane.
Background technology
Referred to as " unmanned plane ", english abbreviation is " UAV " to UAV, using radio robot and is provided for oneself
The not manned aircraft that presetting apparatus manipulates, or autonomous operation fully or is intermittently carried out by car-mounted computer, nobody
Machine is widely used in military and civil field, usually executes more severe or fairly simple aerial mission.Modern
Unmanned plane is light-weight since type is small in flight, is easy to be influenced by high-altitude flow-disturbing, and when flying, upper Altitude is poor, such as
High wind, thunderstorm weather, when having to execute aerial mission, such flying condition is very unfavorable for unmanned plane,
Can even unmanned plane be caused surprisingly to crash, caused any property loss, unmanned plane can be by the more of air-flow after rising to certain altitude
Recast is used, and the machine rise of unmanned plane is restricted, for this purpose, it is proposed that a kind of flight stability and machine rise range is larger
Unmanned plane.
Invention content
The purpose of this utility model is to provide a kind of unmanned planes, to solve the nothing in modern times mentioned above in the background art
It is man-machine in flight, it is light-weight since type is small, be easy influenced by high-altitude flow-disturbing, unmanned plane is after rising to certain altitude
Can be by the multiple action of air-flow, the problem of machine rise of unmanned plane is restricted.
To achieve the above object, the utility model provides the following technical solutions：A kind of unmanned plane, including fuselage, the pusher side wing
And tail, head is provided on the left of the fuselage, and advance rotor is installed on the outside of head, among the top of the fuselage
Fixed organic upper frame, and balance plate is installed on the outside of machine upper frame, the first hoisting frame is provided on the left of the balance plate, and flat
The second hoisting frame is installed on the right side of weighing apparatus plate, promotion spiral is both provided with above first hoisting frame and the second hoisting frame
Frame, and promoted and be fixed with the promotion wing on the outside of helical mount, it is both provided with liter below first hoisting frame and the second hoisting frame
Frame is dropped, and English truss is installed on the outside of crane, top wing is provided with above the pusher side wing, and the pusher side wing is located at machine
The outside of body is equipped with lower wing below the pusher side wing, and between the pusher side wing and top wing, between the pusher side wing and lower wing
It is both provided with adjusting bracket, the lower right of the fuselage is fixed with truss, and power-assisted swing frame is equipped with below truss, described to help
It is fixed with power-assisted rotor on the outside of power swing frame, balance empennage is installed, and tail is located at the right side of truss on the right side of the tail,
Auxiliary tail power swing frame is installed below the tail, and is fixed with auxiliary tail rotor, institute on the outside of auxiliary tail power swing frame
It states and shutdown holder is installed below fuselage.
Preferably, between the balance plate about there are two the horizontal cross center line symmetrical settings of fuselage, and balance plate
Whole is in arcuation bending structure.
Preferably, the wing that promoted is symmetrically distributed in the outside for promoting helical mount in " ten " word, and between each promotion wing
Equal length.
Preferably, the machine upper frame by crane and English truss respectively with the first hoisting frame and the second Lifting Scheme at
Liftable structure, and the position height of the second hoisting frame is higher than the position height of the first hoisting frame.
Preferably, the horizontal center line between the top wing and lower wing about the pusher side wing is symmetrical, and top wing is outer
Arc size is equal between surface and the outer surface of lower wing.
Preferably, the tail is arranged with 30 ° of angles of inclination obliquely on the right side of fuselage, and auxiliary tail power swing frame
Between about tail horizontal center line it is symmetrical.
Compared with prior art, the utility model has the beneficial effects that：The unmanned plane during flying is stablized, and high idle loop can be fought
Air-flow flow-disturbing under border influences, and machine rise range is larger, and the secondary power-assisted that can carry out flying height is promoted, and balance plate is to fuselage
Outside expansion, the top half of fuselage play the role of one be similar to balance wing, make fuselage in flight, Neng Gouzeng
Contact area between fuselage and upper air current by force, makes fuselage held stationary as much as possible, and " ten " word for promoting the wing is symmetrical arranged,
Stability fundamental is provided to the promotion power for promoting helical mount, in flight, according to actual needs, machine liter is carried out or unmanned plane is flown
The holding of scanning frequency degree, makes unmanned plane steadily rise, while it is flat to ensure that the flight path of unmanned plane keeps stablizing as much as possible
Weighing apparatus, convenient for controlling, crane and the first hoisting frame of English truss co- controlling and the second hoisting frame rise and fall, by being carried to first
The adjusting for rising frame and the second hoisting frame position height, makes the first hoisting frame and the second hoisting frame carry out promotion operation to unmanned plane
When, flight adjustment can be carried out with a suitable distance of disembarking, by disembarking distance to the first hoisting frame and the second hoisting frame
Adjusting, enhance unmanned plane second lift when fight high-altitude inverted draft ability, make unmanned plane during rising by
Upper air current in minimum degree influences, and ensures that machine liter acts equalization stable, top wing and auxiliary of the lower wing as unmanned plane
Wing can respectively be carried out the adjusting of opposite pusher side wing position by adjusting bracket, increase the wind area of the pusher side wing, to unmanned plane
Speed limit is carried out, while the angle of inclination of top wing pusher side wing surface opposite with lower wing can also be adjusted by adjusting bracket
Section, the surface for increasing the pusher side wing tilt radian, and to reduce flight resistance, being obliquely installed for tail is whole in order to reduce unmanned plane
The flight resistance of body carries out complementary tail portion to unmanned plane by auxiliary tail power swing frame and auxiliary tail rotor and pushes, is nothing
The actions such as man-machine acceleration, turning provide power.
Description of the drawings
FIG. 1 is a schematic structural view of the utility model；
Fig. 2 is the utility model positive structure schematic；
Fig. 3 is the utility model bottom substance schematic diagram.
In figure：1, fuselage, 2, head, 3, advance rotor, 4, machine upper frame, 5, balance plate, the 6, first hoisting frame, 7, second carries
Rise frame, 8, promote helical mount, 9, promote the wing, 10, crane, 11, English truss, 12, the pusher side wing, 13, top wing, 14, lower machine
The wing, 15, adjusting bracket, 16, truss, 17, power-assisted swing frame, 18, power-assisted rotor, 19, tail, 20, balance empennage, 21, auxiliary tail it is dynamic
Power swing frame, 22, auxiliary tail rotor, 23, shut down holder.
Specific implementation mode
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
The every other embodiment obtained, shall fall within the protection scope of the present invention.
- 3 are please referred to Fig.1, the utility model provides a kind of technical solution：A kind of unmanned plane, including fuselage 1, the pusher side wing 12
With tail 19, the left side of fuselage 1 is provided with head 2, and the outside of head 2 is equipped with advance rotor 3, among the top of fuselage 1
Fixed organic upper frame 4, and the outside of machine upper frame 4 is equipped with balance plate 5, the horizontal cross center between balance plate 5 about fuselage 1
There are two line is symmetrical arranged, and it is in arcuation bending structure that balance plate 5 is whole, and balance plate 5 is unfolded to the outside of fuselage 1, in fuselage 1
Top half play the role of one be similar to balance wing, make fuselage 1 in flight, fuselage 1 and high air can be enhanced
Contact area between stream makes the held stationary as much as possible of fuselage 1, the left side of balance plate 5 be provided with the first hoisting frame 6, and flat
The right side of weighing apparatus plate 5 is equipped with the second hoisting frame 7, and the top of the first hoisting frame 6 and the second hoisting frame 7 is both provided with promotion helical mount
8, and the outside for promoting helical mount 8 is fixed with and promotes the wing 9, promotes the wing 9 and is symmetrically distributed in the outer of promotion helical mount 8 in " ten " word
Side, and equal length between each promotion wing 9, " ten " word for promoting the wing 9 is symmetrical arranged, to the promotion power for promoting helical mount 8
Stability fundamental is provided, in flight, according to actual needs, machine liter or the holding to unmanned plane during flying speed is carried out, makes unmanned plane
It is steady to rise, while can ensure that the flight path of unmanned plane preserves the stable equilibrium as much as possible, convenient for controlling, the first hoisting frame
6 and second the lower section of hoisting frame 7 be both provided with crane 10, and the outside of crane 10 is equipped with English truss 11, machine upper frame 4
Liftable structure is constituted with the first hoisting frame 6 and the second hoisting frame 7 respectively by crane 10 and English truss 11, and second carries
The position height for rising frame 7 is higher than the position height of the first hoisting frame 6, and crane 10 and 11 co- controlling first of English truss are promoted
Rising and falling for frame 6 and the second hoisting frame 7, by the adjusting to 7 position height of the first hoisting frame 6 and the second hoisting frame, makes first to carry
Frame 6 and the second hoisting frame 7 are risen when carrying out promotion operation to unmanned plane, flight tune can be carried out with a suitable distance of disembarking
It is whole, by the adjusting for distance of disembarking to the first hoisting frame 6 and the second hoisting frame 7, high-altitude is fought when enhancing unmanned plane second lift
The ability of inverted draft makes unmanned plane be influenced by the upper air current in minimum degree during rising, and it is dynamic to ensure that machine rises
Make equalization stable, the top of the pusher side wing 12 is provided with top wing 13, and the pusher side wing 12 is located at the outside of fuselage 1, the pusher side wing 12
Lower section is equipped with lower wing 14, and is both provided with tune between the pusher side wing 12 and top wing 13, between the pusher side wing 12 and lower wing 14
Frame 15 is saved, the horizontal center line between top wing 13 and lower wing 14 about the pusher side wing 12 is symmetrical, and the outer surface of top wing 13
Arc size is equal between the outer surface of lower wing 14, and top wing 13 and auxiliary wing of the lower wing 14 as unmanned plane lead to
The adjusting of opposite 12 position of the pusher side wing can respectively be carried out by overregulating frame 15, increase the wind area of the pusher side wing 12, to unmanned plane
Speed limit is carried out, while can also be by adjusting bracket 15 to the angle of inclination of top wing 13 and opposite 12 surface of the pusher side wing of lower wing 14
It is adjusted, the surface for increasing the pusher side wing 12 tilts radian, and to reduce flight resistance, the lower right of fuselage 1 is fixed with purlin
Frame 16, and the lower section of truss 16 is equipped with power-assisted swing frame 17, the outside of power-assisted swing frame 17 is fixed with power-assisted rotor 18, tail 19
Right side is equipped with balance empennage 20, and tail 19 is located at the right side of truss 16, and the lower section of tail 19 is equipped with the rotation of auxiliary tail power
Frame 21, and the outside of auxiliary tail power swing frame 21 is fixed with auxiliary tail rotor 22, tail 19 is set with 30 ° of angles of inclination obliquely
It sets on the right side of fuselage 1, and the horizontal center line between auxiliary tail power swing frame 21 about tail 19 is symmetrical, the inclination of tail 19
Setting is in order to reduce the flight resistance of unmanned plane entirety, by auxiliary tail power swing frame 21 and auxiliary tail rotor 22 to unmanned plane
It carries out complementary tail portion to push, provides power for actions such as acceleration, the turnings of unmanned plane, the lower section of fuselage 1 is equipped with shutdown
Holder 23.
Operation principle：This kind of unmanned plane power-assisted swing frame 17 first is acted, power-assisted rotor 18 rotates therewith, unmanned plane
It begins to ramp up, the promotion helical mount 8 on the first hoisting frame 6 and the second hoisting frame 7 rotates, and promotes the wing 9 and rotates therewith, utilizes rotation direction
Action, makes unmanned plane rise on higher position, promotes the rotary speed of helical mount 8 and can carry out big minor adjustment appropriate, with
Achieve the purpose that second lift drone flying height, and promote stable equilibrium, advance rotor 3 acts, and unmanned plane can be in height
Empty real shows forward motion, to complete aerial mission, 11 the first hoisting frame of co- controlling 6 and second of crane 10 and English truss
Hoisting frame 7 rises and falls, and by the adjusting to 7 position height of the first hoisting frame 6 and the second hoisting frame, makes the first hoisting frame 6 and
Two hoisting frames 7 can carry out flight adjustment, by right when carrying out promotion operation to unmanned plane with a suitable distance of disembarking
First hoisting frame 6 and the second hoisting frame 7 are disembarked the adjusting of distance, confrontation high-altitude inverted draft when enhancing unmanned plane second lift
Ability makes unmanned plane be influenced by the upper air current in minimum degree during rising, ensures that machine liter acts equalization stable,
Balance plate 5 is constantly in open configuration, generates the effect of a balance wing in the top half of fuselage 1, fuselage 1 is made to fly
When, the contact area between fuselage 1 and upper air current can be enhanced, so that the held stationary as much as possible of fuselage 1 is flown, under tail 19
The auxiliary tail power swing frame 21 and auxiliary tail rotor 22 being just arranged mainly help out to the flight of unmanned plane, such as when nobody
When machine is accelerated or turned to, it can carry out flight using the same acceleration of two auxiliary tail power swing frames 21 and add
Speed can carry out dogled using the different rotating speeds of two auxiliary tail power swing frames 21, can be to top wing 13 using adjusting bracket 15
Or lower wing 14 is adjusted with respect to the position on 12 surface of the pusher side wing and placed angle, by top wing 13 or lower wing 14
The adjusting set can correspondingly change the wind area of the pusher side wing 12, to unmanned plane carry out speed limit, by top wing 13 or under
The adjusting of 14 placed angle of wing, the surface that can increase the pusher side wing 12 tilts radian, like this complete to reduce flight resistance
At the use process of entire unmanned plane.
While there has been shown and described that the embodiments of the present invention, for the ordinary skill in the art,
It is appreciated that can these embodiments be carried out with a variety of variations in the case where not departing from the principles of the present invention and spirit, repaiied
Change, replace and modification, the scope of the utility model are defined by the appended claims and the equivalents thereof.
Claims (6)
1. a kind of unmanned plane, including fuselage（1）, the pusher side wing（12）And tail（19）, it is characterised in that：The fuselage（1）A left side
Side is provided with head（2）, and head（2）Outside advance rotor is installed（3）, the fuselage（1）Top among be fixed with
Machine upper frame（4）, and machine upper frame（4）Outside balance plate is installed（5）, the balance plate（5）Left side be provided with the first promotion
Frame（6）, and balance plate（5）Right side the second hoisting frame is installed（7）, first hoisting frame（6）With the second hoisting frame（7）'s
Top is both provided with promotion helical mount（8）, and promote helical mount（8）Outside be fixed with the promotion wing（9）, first hoisting frame
（6）With the second hoisting frame（7）Lower section be both provided with crane（10）, and crane（10）Outside English truss is installed
（11）, the pusher side wing（12）Top be provided with top wing（13）, and the pusher side wing（12）Positioned at fuselage（1）Outside, it is described
The pusher side wing（12）Lower section lower wing is installed（14）, and the pusher side wing（12）With top wing（13）Between, the pusher side wing（12）With under
Wing（14）Between be both provided with adjusting bracket（15）, the fuselage（1）Lower right be fixed with truss（16）, and truss（16）
Lower section power-assisted swing frame is installed（17）, the power-assisted swing frame（17）Outside be fixed with power-assisted rotor（18）, the tail
（19）Right side balance empennage is installed（20）, and tail（19）Positioned at truss（16）Right side, the tail（19）Lower section
Auxiliary tail power swing frame is installed（21）, and auxiliary tail power swing frame（21）Outside be fixed with auxiliary tail rotor（22）, described
Fuselage（1）Lower section shutdown holder is installed（23）.
2. a kind of unmanned plane according to claim 1, it is characterised in that：The balance plate（5）Between about fuselage（1）'s
There are two horizontal cross center line symmetrical settings, and balance plate（5）Whole is in arcuation bending structure.
3. a kind of unmanned plane according to claim 1, it is characterised in that：The promotion wing（9）It is symmetrical in " ten " word
Promoting helical mount（8）Outside, and each promotion wing（9）Between equal length.
4. a kind of unmanned plane according to claim 1, it is characterised in that：The machine upper frame（4）Pass through crane（10）With
English truss（11）Respectively with the first hoisting frame（6）With the second hoisting frame（7）Constitute liftable structure, and the second hoisting frame（7）
Position height be higher than the first hoisting frame（6）Position height.
5. a kind of unmanned plane according to claim 1, it is characterised in that：The top wing（13）With lower wing（14）Between
About the pusher side wing（12）Horizontal center line it is symmetrical, and top wing（13）Outer surface and lower wing（14）Outer surface between circle
Arc is equal sized.
6. a kind of unmanned plane according to claim 1, it is characterised in that：The tail（19）With 30 ° of inclinations obliquely
Angle is arranged in fuselage（1）Right side, and auxiliary tail power swing frame（21）Between about tail（19）Horizontal center line it is symmetrical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820258653.3U CN207875971U (en) | 2018-02-14 | 2018-02-14 | A kind of unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820258653.3U CN207875971U (en) | 2018-02-14 | 2018-02-14 | A kind of unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207875971U true CN207875971U (en) | 2018-09-18 |
Family
ID=63499181
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820258653.3U Expired - Fee Related CN207875971U (en) | 2018-02-14 | 2018-02-14 | A kind of unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207875971U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114412229A (en) * | 2022-01-12 | 2022-04-29 | 厦门安科科技有限公司 | Control method and control device of high-altitude-based building dismantling machine |
-
2018
- 2018-02-14 CN CN201820258653.3U patent/CN207875971U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114412229A (en) * | 2022-01-12 | 2022-04-29 | 厦门安科科技有限公司 | Control method and control device of high-altitude-based building dismantling machine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180918 |