CN106516113A - Unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle Download PDFInfo
- Publication number
- CN106516113A CN106516113A CN201610940405.2A CN201610940405A CN106516113A CN 106516113 A CN106516113 A CN 106516113A CN 201610940405 A CN201610940405 A CN 201610940405A CN 106516113 A CN106516113 A CN 106516113A
- Authority
- CN
- China
- Prior art keywords
- wing
- unmanned plane
- fixed
- fuselage
- left outside
- 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.)
- Pending
Links
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/28—Collapsible or foldable blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
-
- 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
- B64U50/19—Propulsion using electrically powered motors
Abstract
A fixed-wing unmanned aerial vehicle comprises a fuselage, an electric propulsion mechanism arranged at the head of the fuselage, wings arranged on the two sides of the fuselage and a horizontal tail arranged at the tail of the fuselage. Before the unmanned aerial vehicle takes off, the electric propulsion mechanism can provide larger than or equal to 5.4 kg tension for the unmanned aerial vehicle. The wings are airfoils high in lift coefficient. The horizontal tail is a stabilator. During launching of the unmanned aerial vehicle, zero-run-up hand throwing launching can be completed without providing the additional initial velocity, and the fixed-wing unmanned aerial vehicle can adapt to various area-limited environments, such as island reefs, mountain, roofs, ships and other usage environments.
Description
Technical field
A kind of a kind of the present invention relates to unmanned plane, more particularly to hand throwing type fixed-wing unmanned plane.
Background technology
With miniaturization, the Highgrade integration of electric load, small-sized electric unmanned plane is particularly the electronic nothing that handss throw transmitting
Man-machine quick development, has application at military, civilian aspect.Traditional handss are thrown electronic unmanned plane and there is problems with urgently
It is to be solved：
As fixed-wing unmanned plane has a minimum flight speed (i.e. stalling speed), so sending out being thrown using handss
Release speed is thrown to the handss of launching crew when penetrating and proposes higher requirement, need the run-up speed to launching crew, sell fast
Degree, attitude of selling carry out special training, and need certain open area, it is impossible to adapt to finite region transmitting application.
The content of the invention
In view of this, embodiments of the present invention provide a kind of unmanned plane of mode of taking off using zero run-up.
A kind of fixed-wing unmanned plane, which includes fuselage, is arranged on being electric-only propulsion mechanism, being arranged on institute for the fuselage head
The wing for stating fuselage both sides and the horizontal tail for being arranged on the afterbody, before take-off, the mechanism that is electric-only propulsion can be institute
State unmanned plane and the pulling force for being more than or equal to 5.4kg is provided, the wing is high coefficient of lift combined aerofoil profile, and the horizontal tail is entirely dynamic putting down
Tail.
Preferably, the mechanism that is electric-only propulsion includes motor and propeller, and the motor is arranged on the fuselage
Head, the propeller are arranged on the motor.
Preferably, the propeller is separate type propeller, and the propeller includes blade and propeller hub, and the blade passes through
Bolt is connected with the propeller hub, and the blade can be folded.
Preferably, the wing includes the middle wing, the left outside wing and starboard outboard, and the middle wing is arranged on the neighbour of the fuselage
The nearly top for being electric-only propulsion mechanism, the left outside wing are arranged on the left side of the middle wing, and the starboard outboard is arranged on institute
The right side of the middle wing is stated, the assembling of the middle wing, the left outside wing and starboard outboard is adopted and assembled without instrument fast assembling-disassembling mode.
Preferably, the relative side of the left outside wing and the middle wing is provided with two intubations, and covers in every intubation
Elastic tape is provided with, the middle wing accordingly offers jack, and the intubation inserts the jack, so as to be coupled with one
Rise.
Preferably, the scope of the upper counterangle degree of the left outside wing and the starboard outboard is 4.8 ° to 7.2 °.
Preferably, the scope of the established angle of the middle wing is+1.6 ° to+2.4 °.
Preferably, the scope of the torsion angle of the left outside wing and the starboard outboard is -2.4 ° to -3.6 °.
Preferably, the scope of the aspect ratio of the wing is 9.25 to 13.87.
Preferably, the left outside wing and the starboard outboard are each equipped with aileron rudder face.
Enough pulling force are produced by electricpropulsion installation, the wing of high coefficient of lift combined can be produced necessarily in relatively low speed
Lift, provide enough operating torques by flying tail under extremely low speed speed so that unmanned plane transmitting when need not
There is provided extra initial velocity, you can complete zero run-up handss throwing mode and launch, and be adapted to various region constrained environments to make
With the such as use environment such as islands and reefs, mountain region, roof, naval vessel.
Description of the drawings
For the technical scheme being illustrated more clearly that in embodiments of the invention, below will be to wanting needed for embodiment description
The accompanying drawing for using is briefly described.
Fig. 1 is the unmanned plane axonometric chart of embodiment of the present invention.
Fig. 2 is the wing exploded view of unmanned plane shown in Fig. 1.
Fig. 3 is the aileron rudder face structural representation of unmanned plane shown in Fig. 1.
Fig. 4 is the vertical fin structural representation of unmanned plane shown in Fig. 1.
Fig. 5 is the afterbody schematic diagram of unmanned plane shown in Fig. 1.
Specific embodiment
For making the object, technical solutions and advantages of the present invention clearer, below in conjunction with accompanying drawing to embodiment party of the present invention
The unmanned plane of formula is further described.
Fig. 1 is referred to, the unmanned plane of embodiment of the present invention includes fuselage 10, is electric-only propulsion mechanism 20, wing 30, vertical fin
40th, horizontal tail 50 and buffers packet 60.20 heads for being arranged on fuselage 10 are electric-only propulsion, wing 30 is arranged on the both sides of fuselage 10, are hung down
Tail 40 and horizontal tail 50 are arranged on the afterbody of fuselage 10, and buffers packet 60 is arranged on the bottom of fuselage 10.It is appreciated that unmanned plane 100
Also include other functions component, such as rudder, hatchcover etc., for saving space, are not hereafter retouched to these other functions modules in detail
State.
Fuselage 10 is formed with load cabin, and which is located at the interlude of fuselage 10, is the load for adapting to multi-form, and load cabin is
Penetrating opening, can arrange different equipment installed parts according to different load up and down.Load cabin is designed without hatchcover, and top is by machine
The middle wing of the wing is completely covered, and forms enclosed water-proof structure, as shown in Figure 1.
Being electric-only propulsion mechanism 20 includes motor 21 and propeller 23, draws for providing 0.35-6.8kg for unmanned plane 100
Power, motor 21 are arranged on the head of fuselage 10, and propeller 23 is arranged on motor 21.In embodiment of the present invention, spiral
Oar 23 adopts separate type propeller, propeller 23 to include blade and propeller hub, and blade is connected with propeller hub by bolt, and blade can be rolled over
It is folded.Before unmanned plane 100 is taken off on the ground, the rotating speed of propeller 23 reaches more than 11000RPM, and the thrust which provides is in 5.4kg
More than, the persistent period is shorter, generally less than 30 seconds；In cruise, the rotating speed of propeller 23 can then maintain 4500～6000RPM
Between, there is provided thrust be 0.35～0.7kg.
Wing 30 includes the middle wing 31, the left outside wing 33 and starboard outboard 35, and the middle wing 31 is arranged on the neighbouring electronic of fuselage 10
The top of propulsive mechanism 20, the left outside wing 33 are arranged on the left side of the middle wing 31, and starboard outboard 35 is arranged on the right side of the middle wing 31.In
Between the wing 31, the left outside wing 33 and starboard outboard 35 assembling using assembling without instrument fast assembling-disassembling mode.Specifically, the left outside wing 33 with
The relative side of the middle wing 31 is provided with two intubations 331, and every intubation 331 and is arranged with elastic tape 333,31 pairs, the middle wing
Offer jack 310 with answering, the insertion jack 310 of intubation 331 can be with the overall structure of load so as to be constituted one.It is right outer
The wing 35 constitutes one with the middle wing 31 also by similar structures can be with the overall structure of load.
After the middle wing 31, the left outside wing 33 and starboard outboard 35 form a whole, by four extensions in front and back on the middle wing 31
Point is connected on the upside of fuselage 10.The left outside wing 33 and starboard outboard 35 are each equipped with aileron rudder face 351, and (the aileron rudder face of the left outside wing 33 is not
Mark), aileron configuration can be configured to as needed and without aileron configuration, and its aileron rudder face can using same mold into
Type.The left outside wing 33 and starboard outboard 35 have larger upper counterangle degree, to lift the stability of lower-speed state.Wing 30 uses high-lift
Coefficient aerofoil profile combines high aspect ratio plane figure, and there is the middle wing 31 low-angle established angle, the left outside wing 33 and starboard outboard 35 to have
There is low-angle negative twist to turn, while having the larger upper counterangle, outer wing wipes ground in reducing descent while stability is increased
The probability of damage.The middle wing 31 defines a plane with designated mounting angle with 10 contact portion of fuselage, with fuselage 10
Docking belongs to complete plane connection, rather than surface intersection, reduces frock required precision.Specifically, in the present embodiment, machine
The scope of the aspect ratio of the wing 30 substantially 9.25～13.87, optimum is 11.56；The upper counterangle degree of the left outside wing 33 and starboard outboard 35
Substantially 4.8 ° to 7.2 ° of scope, optimum is 6 °；Substantially+1.6 ° to+2.4 ° of the scope of the established angle of the middle wing 31, it is optimum
For 2 °；Substantially -2.4 ° to -3.6 ° of the scope of the torsion angle of the left outside wing 33 and starboard outboard 3, optimum is -3 °.It is appreciated that
In other embodiments, above-mentioned parameter also can be adjusted according to practical situation within the specific limits.
Afterbody of the vertical fin 40 by plug connector 41 with fuselage 10 is dismounted without instrument.Vertical fin 40 is also formed with installing space 401,
Horizontal tail manipulates steering wheel (not shown) and rudder control steering wheel (not shown) peace is mounted in installing space 401.
Horizontal tail 50 is flying tail, is connected with the rear of fuselage 10 by horizontal tail Rocker arm 51, and horizontal tail Rocker arm 51 is made simultaneously
For the rotation support end of horizontal tail 50,10 rear of fuselage is provided with horizontal tail rotating shaft fixing end 102.Set without any electronics in horizontal tail 50
It is standby, to prevent from damaging when landing is decomposed.
Buffers packet 60 includes the first buffers packet 61, the second buffers packet 63, the 3rd buffers packet 65, and which is separately positioned on fuselage 10
The bottom surface of head, middle part and afterbody, as shown in Figure 1.First buffers packet 61, the second buffers packet 63, the 3rd buffers packet 65 are by PU
Foam is made.
Unmanned plane 100 can be thrown mode using zero run-up handss and launch, and be produced by the electricpropulsion installation 20 positioned at 10 position of head
The enough pulling force of life, the wing 30 of high coefficient of lift combined can produce certain lift in relatively low speed, be existed by flying tail 50
Enough operating torques are provided under extremely low speed speed so that unmanned plane 100 need not provide extra initial speed in transmitting
Degree, you can complete zero run-up handss throwing mode and launch, and be adapted to various region constrained environments to use, such as islands and reefs, mountain region, building
The use environments such as top, naval vessel.
The take-off process that zero run-up handss throw unmanned plane is as follows：Both hands holding fuselage 10, head 10 is raised up slightly, and wing 30 is protected
Water holding is put down, and actuating motor 23 adjusts to a suitable rotating speed, unmanned plane is sent, and unmanned plane can be in the time of 1s
It is interior, accelerate to more than 10m/s (stalling speed), complete zero run-up handss throw it is winged.
Herein, term " including ", "comprising" or its any other variant are intended to including for nonexcludability, remove
Comprising those listed key element, but also can be comprising other key elements being not expressly set out.
Herein, the involved noun of locality such as forward and backward, upper and lower is to be located in figure with parts in accompanying drawing and zero
Part position each other is intended merely to the clear and convenient of expression technology scheme come what is defined.It should be appreciated that the noun of locality
Use should not limit the scope that the application is claimed.
In the case where not conflicting, the feature in embodiment herein-above set forth and embodiment can be combined with each other.
The foregoing is only presently preferred embodiments of the present invention, not to limit the present invention, all spirit in the present invention and
Within principle, any modification, equivalent substitution and improvements made etc. should be included within the scope of the present invention.
Claims (10)
1. a kind of fixed-wing unmanned plane, it include fuselage, be arranged on the fuselage head be electric-only propulsion mechanism, be arranged on it is described
The wing of fuselage both sides and it is arranged on the horizontal tail of the afterbody, it is characterised in that：Before take-off, it is described to be electric-only propulsion mechanism
Pulling force more than or equal to 5.4kg can be provided for the unmanned plane, the wing is high coefficient of lift combined aerofoil profile, the horizontal tail is
Flying tail.
2. fixed-wing unmanned plane as claimed in claim 1, it is characterised in that：The mechanism that is electric-only propulsion includes motor and spiral shell
Rotation oar, the motor are arranged on the head of the fuselage, and the propeller is arranged on the motor.
3. fixed-wing unmanned plane as claimed in claim 2, it is characterised in that：The propeller is separate type propeller, described
Propeller includes blade and propeller hub, and the blade is connected with the propeller hub by bolt, and the blade can be folded.
4. fixed-wing unmanned plane as claimed in claim 1, it is characterised in that：The wing includes the middle wing, the left outside wing and the right side
Outer wing, the middle wing are arranged on the neighbouring described top for being electric-only propulsion mechanism of the fuselage, and the left outside wing is arranged on institute
The left side of the middle wing is stated, the starboard outboard is arranged on the right side of the middle wing, the group of the middle wing, the left outside wing and starboard outboard
Dress is adopted and is assembled without instrument fast assembling-disassembling mode.
5. fixed-wing unmanned plane as claimed in claim 4, it is characterised in that：The relative side of the left outside wing and the middle wing
Face is provided with two intubations, and is arranged with elastic tape in every intubation, and the middle wing accordingly offers jack, the intubation
The jack is inserted, so as to be coupled with together.
6. fixed-wing unmanned plane as claimed in claim 4, it is characterised in that：The upper counterangle of the left outside wing and the starboard outboard
The scope of degree is 4.8 ° to 7.2 °.
7. fixed-wing unmanned plane as claimed in claim 4, it is characterised in that：The scope of the established angle of the middle wing for+
1.6 ° to+2.4 °.
8. fixed-wing unmanned plane as claimed in claim 4, it is characterised in that：The torsion angle of the left outside wing and the starboard outboard
Scope be -2.4 ° to -3.6 °.
9. fixed-wing unmanned plane as claimed in claim 4, it is characterised in that：The scope of the aspect ratio of the wing be 9.25 to
13.87。
10. fixed-wing unmanned plane as claimed in claim 4, it is characterised in that：The left outside wing and the starboard outboard are configured
There is aileron rudder face.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610940405.2A CN106516113A (en) | 2016-10-25 | 2016-10-25 | Unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610940405.2A CN106516113A (en) | 2016-10-25 | 2016-10-25 | Unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106516113A true CN106516113A (en) | 2017-03-22 |
Family
ID=58293439
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610940405.2A Pending CN106516113A (en) | 2016-10-25 | 2016-10-25 | Unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106516113A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108803640A (en) * | 2018-05-31 | 2018-11-13 | 深圳市易飞方达科技有限公司 | Unmanned plane and the method for realizing aerial dispensing unmanned plane |
| CN108839570A (en) * | 2018-06-17 | 2018-11-20 | 北京蓝色动力科技有限公司 | Using solar panel and lithium battery group as the small-sized solar unmanned plane of power source |
| CN112644686A (en) * | 2020-12-25 | 2021-04-13 | 中国航天空气动力技术研究院 | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
| CN114089777A (en) * | 2021-11-22 | 2022-02-25 | 广州市华科尔科技股份有限公司 | Control method and device for throwing unmanned aerial vehicle |
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| CN202115704U (en) * | 2011-05-14 | 2012-01-18 | 珠海银通航空器材有限公司 | Electric aircraft |
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| CN103600843A (en) * | 2013-11-05 | 2014-02-26 | 新誉集团有限公司 | Hand-launched take-off unmanned aerial vehicle |
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| CN105667790A (en) * | 2016-01-15 | 2016-06-15 | 中国人民解放军国防科学技术大学 | General layout of unmanned aerial vehicle capable of taking off with catapult assisted and being recovered by bumping net |
| CN205707297U (en) * | 2016-04-19 | 2016-11-23 | 牛睿 | Fixed-wing unmanned plane |
| CN206125430U (en) * | 2016-10-25 | 2017-04-26 | 深圳市易飞方达科技有限公司 | Unmanned aerial vehicle |
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| CN202115704U (en) * | 2011-05-14 | 2012-01-18 | 珠海银通航空器材有限公司 | Electric aircraft |
| US20130320103A1 (en) * | 2012-06-04 | 2013-12-05 | Zamir Margalit | Foreign object damage protection device and system for aircraft |
| CN103600843A (en) * | 2013-11-05 | 2014-02-26 | 新誉集团有限公司 | Hand-launched take-off unmanned aerial vehicle |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108803640A (en) * | 2018-05-31 | 2018-11-13 | 深圳市易飞方达科技有限公司 | Unmanned plane and the method for realizing aerial dispensing unmanned plane |
| CN108839570A (en) * | 2018-06-17 | 2018-11-20 | 北京蓝色动力科技有限公司 | Using solar panel and lithium battery group as the small-sized solar unmanned plane of power source |
| CN112644686A (en) * | 2020-12-25 | 2021-04-13 | 中国航天空气动力技术研究院 | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
| CN114089777A (en) * | 2021-11-22 | 2022-02-25 | 广州市华科尔科技股份有限公司 | Control method and device for throwing unmanned aerial vehicle |
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Application publication date: 20170322 |
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