CN206664932U - A kind of VTOL fixed-wing unmanned plane - Google Patents
A kind of VTOL fixed-wing unmanned plane Download PDFInfo
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- CN206664932U CN206664932U CN201720441529.6U CN201720441529U CN206664932U CN 206664932 U CN206664932 U CN 206664932U CN 201720441529 U CN201720441529 U CN 201720441529U CN 206664932 U CN206664932 U CN 206664932U
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- wing
- fuselage
- engine
- propeller
- unmanned plane
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Abstract
The utility model discloses a kind of VTOL fixed-wing unmanned plane, including fuselage, wing, engine, propeller and flight control units；The wing is fixedly mounted on the both sides of fuselage, and the bottom of wing controls steering wheel to be rotatably connected to aileron by aileron；Nose shell is installed with the top of the fuselage, and the bottom of nose shell inner chamber is installed with engine；The power output shaft of the engine is fixedly connected by gear-box with the bottom of propeller rotational axle；Upper and positioned at nose shell the external stability installation propeller of the propeller rotational axle；Fuel tank is installed with the top of the fuselage inner chamber, and flight control units are provided with behind fuel tank；The utility model VTOL fixed-wing unmanned plane, it is applied widely, it is cost-effective, simplify aircraft landing process；Cost is low, can recycle；Special airport without wide flat；Full autonomous flight, it is not necessary to skilled winged hand manipulation, training and popularization more convenient quickly.
Description
Technical field
Unmanned air vehicle technique field is the utility model is related to, specially a kind of VTOL fixed-wing unmanned plane.
Background technology
Depopulated helicopter can not limited with VTOL by place, but cruising time and speed are always short slab, fixed
Wing unmanned plane cruising time is long, speed is fast, but takeoff runway or ejector are needed when taking off, and also needs to during landing very big
How space or runway, balance is found between, be once a problem urgently to be resolved hurrily.Since eighties of last century,
Start constantly to explore with regard to someone, it is intended to find a kind of composite wing that the high speed of a ship or plane and long endurance can be both ensured with VTOL and can without
It is man-machine.
Utility model content
The purpose of this utility model is to provide a kind of VTOL fixed-wing unmanned plane, allows fixed-wing unmanned plane can
VTOL is not limited by place, can carry out long endurance high-efficiency homework again, and specific practice is by traditional fixed wing aircraft
Takeoff be changed to taking off vertically for rocket launching formula, be changed to horizontal flight after flying to certain altitude, will first fly during landing
The vertical pull-up hovering of machine in the air, then slowly declines, and posture and landing position when declining using aileron control aircraft, makes aircraft
Grease it in.
To achieve the above object, the utility model provides following technical scheme：A kind of VTOL fixed-wing unmanned plane, bag
Include fuselage, wing, engine, propeller and flight control units；The wing is fixedly mounted on the both sides of fuselage, and wing
Bottom controls steering wheel to be rotatably connected to aileron by aileron；Nose shell is installed with the top of the fuselage, and in nose shell
The bottom of chamber is installed with engine；The bottom that the power output shaft of the engine passes through gear-box and propeller rotational axle
It is fixedly connected；Upper and positioned at nose shell the external stability installation propeller of the propeller rotational axle；The fuselage inner chamber
Top is installed with fuel tank, and flight control units are provided with behind fuel tank；The top of the flight control units is set
There is umbrella cabin；The bottom of the flight control units is provided with mission payload cabin；The front of the fuselage be provided with can folding and unfolding rise and fall
Frame, and the back side of fuselage is provided with vertical tail, and control steering wheel to be rotatably connected to rudder by rudder on vertical tail.
As a kind of optimal technical scheme of the present utility model, the flight control units include gyro, accelerometer, gas
Height sensor, airspeed sensor, GPS location instrument and controller are pressed, and controller is high with gyro, accelerometer, air pressure respectively
Sensor, airspeed sensor, GPS location instrument, engine, aileron control steering wheel and rudder control flaps machine is spent to be electrically connected with.
As a kind of optimal technical scheme of the present utility model, the engine and the bottom junctions of nose shell inner chamber are set
It is equipped with engine shock absorber.
As a kind of optimal technical scheme of the present utility model, the propeller is provided with two groups, and is uniformly fixedly mounted
On propeller rotational axle.
As a kind of optimal technical scheme of the present utility model, the both ends of the bottom of the wing are provided with undercarriage.
Beneficial effect
Compared with prior art, the beneficial effects of the utility model are：The utility model VTOL fixed-wing unmanned plane,
Solve the problems, such as the runway of fixed wing aircraft takeoff and anding, change the flying method of fixed wing aircraft takeoff completely, change
With taking off vertically as rocket launching, deflected after reaching certain altitude along the path taken off vertically to side, with parabola
Track revert to level flight state, first aircraft vertical pull-up hovering in the air, then is slowly declined during landing, is controlled and flown using aileron
Posture and landing position when machine declines, make aircraft grease it in；Using coaxial double-oar separate unit engine as power, solve
The problem of endurance of electronic unmanned plane is short, operating efficiency can be greatly improved, reduce operating cost, applied widely, cost performance
Height, simplify aircraft landing process；Cost is low, can recycle；Special airport without wide flat；Full autonomous flight,
Winged hand that need not be skilled manipulates, training and popularization more convenient quickly；It is practical, use easy to spread.
Brief description of the drawings
Fig. 1 is front view of the present utility model；
Fig. 2 is side view of the present utility model；
In figure：1- fuselages；2- wings；3- engines；4- gear-boxes；5- propellers；6- engine shock absorbers；7- aileron controls
Steering wheel processed；8- ailerons；9- undercarriages；10- fuel tanks；11- umbrellas cabin；12- flight control units；13- mission payloads cabin；14- can be received
Blow the gear down；15- rudders control steering wheel；16- vertical tails；17- rudders；18- nose shells；19- propeller rotational axles.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the embodiment of the utility model is carried out
Clearly and completely describing, it is clear that described embodiment is only the utility model part of the embodiment, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not under the premise of creative work is made
The every other embodiment obtained, belong to the scope of the utility model protection.
Refer to a kind of Fig. 1-2 embodiments provided by the utility model：A kind of VTOL fixed-wing unmanned plane, including machine
Body 1, wing 2, engine 3, propeller 5 and flight control units 12；The wing 2 is fixedly mounted on the both sides of fuselage 1, and machine
The bottom of the wing 2 controls steering wheel 7 to be rotatably connected to aileron 8 by aileron；The top of the fuselage 1 is installed with nose shell 18,
And the bottom of the inner chamber of nose shell 18 is installed with engine 3；The power output shaft of the engine 3 passes through gear-box 4 and spiral shell
The bottom of rotation oar rotary shaft 19 is fixedly connected；Upper and positioned at nose shell 18 the external stability of the propeller rotational axle 19 is installed
Propeller 5；Fuel tank 10 is installed with the top of the inner chamber of fuselage 1, and flight control units 12 are provided with behind fuel tank；
The top of the flight control units 12 is provided with umbrella cabin 11；The bottom of the flight control units 12 is provided with mission payload cabin
13；The front of the fuselage 1 is provided with retractable landing gear 14, and the back side of fuselage 1 is provided with vertical tail 16, and vertical end
Steering wheel 15 is controlled to be rotatably connected to rudder 17 by rudder on the wing 16；The flight control units 12 include gyro, accelerated
Spend meter, pressure-altitude sensor, airspeed sensor, GPS location instrument and controller, and controller respectively with gyro, accelerometer,
Pressure-altitude sensor, airspeed sensor, GPS location instrument, engine 3, aileron control steering wheel 7 and the electricity of rudder control steering wheel 15
Property connection；The engine 3 and the bottom junctions of the inner chamber of nose shell 18 are provided with engine shock absorber 7；The propeller 6 is set
Two groups are equipped with, and is uniformly fixedly mounted on propeller rotational axle 19；The both ends of the bottom of the wing 2 are provided with undercarriage 9.
Design feature：
Power unit provides power using an engine 3, and by the gear-box 4 of a particular design, power output becomes
Reversely rotated for concentric double-shaft, form coaxial anti-slurry dynamical system, asked to overcome propeller 5 to rotate caused reaction torque
Topic, makes 1 stress complete equipilibrium of fuselage, is easy to the control of flying aircraft posture, the lower end of engine 3 passes through engine shock absorber
6 are connected with fuselage 1.
The layout of wing 2 uses integrated design, and without single empennage, structure is more compact, and fuselage both sides are provided with vertical
Fin 16, the lower end of wing 2 are designed with two ailerons 8, for controlling flight attitude, including pitching and rolling, the both ends of wing 2
It is designed with undercarriage 9, it is simultaneous that the back lower end of fuselage 1 is designed with fixed vertical fin（And undercarriage）, tail vane is designed with vertical fin, is used for
The course of aircraft is controlled, belly lower end is designed with retractable landing gear 14, and the indoor design of fuselage 1 has fuel tank 10, flight control
Unit 12, data radio station, umbrella storehouse and mission payload cabin 13 processed, mission payload cabin 13 can carry different according to different mission requirements
Mission payload, such as aviation measuring camera, photoelectric nacelle, multispectral camera, EO-1 hyperion camera, oblique photograph camera etc..
It should be noted that herein, such as first and second or the like relational terms are used merely to a reality
Body or operation make a distinction with another entity or operation, and not necessarily require or imply and deposited between these entities or operation
In any this actual relation or order.Moreover, term " comprising ", "comprising" or its any other variant are intended to
Nonexcludability includes, so that process, method, article or equipment including a series of elements not only will including those
Element, but also the other element including being not expressly set out, or it is this process, method, article or equipment also to include
Intrinsic key element.In the absence of more restrictions.By sentence " including one ... the key element limited, it is not excluded that
Other identical element in the process including the key element, method, article or equipment also be present ".
While there has been shown and described that embodiment of the present utility model, for the ordinary skill in the art,
It is appreciated that these embodiments can be carried out with a variety of changes in the case where not departing from principle of the present utility model and spirit, repaiied
Change, replace and modification, the scope of the utility model are defined by the appended claims and the equivalents thereof.
Claims (5)
1. a kind of VTOL fixed-wing unmanned plane, including fuselage（1）, wing（2）, engine（3）, propeller（5）And flight
Control unit（12）；It is characterized in that：The wing（2）It is fixedly mounted on fuselage（1）Both sides, and wing（2）Bottom lead to
Cross aileron control steering wheel（7）It is rotatably connected to aileron（8）；The fuselage（1）Top be installed with nose shell（18）, and machine
Head-shield（18）The bottom of inner chamber is installed with engine（3）；The engine（3）Power output shaft pass through gear-box（4）
With propeller rotational axle（19）Bottom be fixedly connected；The propeller rotational axle（19）It is upper and be located at nose shell（18）It is outer
Propeller is fixedly mounted in portion（5）；The fuselage（1）Fuel tank is installed with the top of inner chamber（10）, and fuel tank（10）Behind
It is provided with flight control units（12）；The flight control units（12）Top be provided with umbrella cabin（11）；The flight control
Unit（12）Bottom be provided with mission payload cabin（13）；The fuselage（1）Front be provided with retractable landing gear（14）, and
Fuselage（1）The back side vertical tail is installed（16）, and vertical tail（16）It is upper that steering wheel is controlled by rudder（15）The company of rotation
It is connected to rudder（17）.
A kind of 2. VTOL fixed-wing unmanned plane according to claim 1, it is characterised in that：The flight control units
（12）Including gyro, accelerometer, pressure-altitude sensor, airspeed sensor, GPS location instrument and controller, and controller divides
Not with gyro, accelerometer, pressure-altitude sensor, airspeed sensor, GPS location instrument, engine（3）, aileron control steering wheel
（7）Steering wheel is controlled with rudder（15）It is electrically connected with.
A kind of 3. VTOL fixed-wing unmanned plane according to claim 1, it is characterised in that：The engine（3）With
Nose shell（18）The bottom junctions of inner chamber are provided with engine shock absorber（6）.
A kind of 4. VTOL fixed-wing unmanned plane according to claim 1, it is characterised in that：The propeller（5）If
Two groups are equipped with, and is uniformly fixedly mounted on propeller rotational axle（19）On.
A kind of 5. VTOL fixed-wing unmanned plane according to claim 1, it is characterised in that：The wing（2）Bottom
The both ends in portion are provided with undercarriage（9）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720441529.6U CN206664932U (en) | 2017-04-25 | 2017-04-25 | A kind of VTOL fixed-wing unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720441529.6U CN206664932U (en) | 2017-04-25 | 2017-04-25 | A kind of VTOL fixed-wing unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206664932U true CN206664932U (en) | 2017-11-24 |
Family
ID=60370433
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720441529.6U Expired - Fee Related CN206664932U (en) | 2017-04-25 | 2017-04-25 | A kind of VTOL fixed-wing unmanned plane |
Country Status (1)
| Country | Link |
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| CN (1) | CN206664932U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107097949A (en) * | 2017-04-25 | 2017-08-29 | 河南三和航空工业有限公司 | A kind of VTOL fixed-wing unmanned plane |
| CN108545182A (en) * | 2018-03-09 | 2018-09-18 | 中国科学院长春光学精密机械与物理研究所 | A kind of VTOL fixed-wing unmanned plane |
| CN108819633A (en) * | 2018-05-30 | 2018-11-16 | 北京艾达方武器装备技术研究所 | The convertible aircraft carrier of AI Intelligent vertical landing sea, land and air, airborne carrier and general toter |
| CN110466754A (en) * | 2019-09-09 | 2019-11-19 | 西安交通大学 | A kind of tailstock formula tilting rotor vertical take-off and landing drone |
-
2017
- 2017-04-25 CN CN201720441529.6U patent/CN206664932U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107097949A (en) * | 2017-04-25 | 2017-08-29 | 河南三和航空工业有限公司 | A kind of VTOL fixed-wing unmanned plane |
| CN108545182A (en) * | 2018-03-09 | 2018-09-18 | 中国科学院长春光学精密机械与物理研究所 | A kind of VTOL fixed-wing unmanned plane |
| CN108819633A (en) * | 2018-05-30 | 2018-11-16 | 北京艾达方武器装备技术研究所 | The convertible aircraft carrier of AI Intelligent vertical landing sea, land and air, airborne carrier and general toter |
| CN110466754A (en) * | 2019-09-09 | 2019-11-19 | 西安交通大学 | A kind of tailstock formula tilting rotor vertical take-off and landing drone |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171124 Termination date: 20210425 |
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| CF01 | Termination of patent right due to non-payment of annual fee |