CN206125430U

CN206125430U - Unmanned aerial vehicle

Info

Publication number: CN206125430U
Application number: CN201621164877.5U
Authority: CN
Inventors: 张会军
Original assignee: Shenzhen Yifei Fonda Technology Co Ltd
Current assignee: Shenzhen Huaxun ark System Technology Co Ltd
Priority date: 2016-10-25
Filing date: 2016-10-25
Publication date: 2017-04-26
Anticipated expiration: 2026-10-25

Abstract

The utility model provides a stationary vane unmanned aerial vehicle which includes the fuselage, sets up electrical propulsion mechanism, the setting of fuselage head are in the wing and the setting of fuselage both sides are in the horizontal tail of afterbody, before taking off, electrical propulsion mechanism can for unmanned aerial vehicle provides the pulling force that is more than or equal to 5.4kg, the wing is high lift coefficient wing section, the horizontal tail is the flying tail. Unmanned aerial vehicle need not to provide extra initial velocity when the transmission, and zero run -up hand throwing mode transmission can be accomplished, and the limited environment use in multiple region can be adapted to, like service environment such as island reef, mountain region, roof, naval vessels.

Description

Unmanned plane

Technical field

The utility model is related to a kind of unmanned plane, more particularly to a kind of hand throwing type fixed-wing unmanned plane.

Background technology

Miniaturization, Highgrade integration with electric load, small-sized electric unmanned plane is particularly the electronic nothing that hand throws transmitting Man-machine quick development, has application at military, civilian aspect.Traditional hand throws electronic unmanned plane and there is problems with urgently It is to be solved：

Because there is the flying speed of a minimum in fixed-wing unmanned plane（That is stalling speed）, so sending out being thrown using hand Release speed is thrown to the hand 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.

Utility model content

In view of this, embodiment of the present utility model provides a kind of unmanned plane of mode of taking off using zero run-up.

A kind of fixed-wing unmanned plane, it 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 put down for entirely dynamic Tail.

Preferably, the mechanism that is electric-only propulsion includes motor and screw, and the motor is arranged on the fuselage Head, the screw is arranged on the motor.

Preferably, the screw is separate type screw, and the screw 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 is 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 under extremely low speed speed by flying tail so that unmanned plane transmitting when need not There is provided extra initial velocity, you can complete zero run-up hand throwing mode and launch, and be adapted to various region constrained environments to make With such as islands and reefs, mountain region, roof, naval vessel use environment.

Description of the drawings

Technical scheme in order to be illustrated more clearly that embodiment of the present utility model, below will be to institute in embodiment description The accompanying drawing that needs are used is briefly described.

Fig. 1 is the unmanned plane stereogram of the utility model embodiment.

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

It is new to this practicality below in conjunction with accompanying drawing to make the purpose of this utility model, technical scheme and advantage clearer The unmanned plane of type embodiment is further described.

Refer to Fig. 1, the unmanned plane of the utility model embodiment include fuselage 10, be electric-only propulsion mechanism 20, wing 30, Vertical fin 40, 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 two of fuselage 10 Side, vertical fin 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 nobody Machine 100 also includes other functions component, such as rudder, hatchcover, hereafter not detailed to these other functions modules to save space Thin description.

Fuselage 10 is formed with load cabin, and it is located at the interlude of fuselage 10, is the load for adapting to multi-form, and load cabin is Up and down penetrating opening, according to different load different equipment installed parts can be arranged.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.

Mechanism 20 is electric-only propulsion including motor 21 and screw 23, is drawn for providing 0.35-6.8kg for unmanned plane 100 Power, motor 21 is arranged on the head of fuselage 10, and screw 23 is arranged on motor 21.In the utility model embodiment, Screw 23 adopts separate type screw, screw 23 to include blade and propeller hub, and blade is connected by bolt with propeller hub, and blade can Fold.Before unmanned plane 100 takes off on the ground, the rotating speed of screw 23 reaches more than 11000RPM, and its thrust for providing exists More than 5.4kg, the duration is shorter, generally less than 30 seconds；In cruise, the rotating speed of screw 23 can then maintain 4500 ~ Between 6000RPM, 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 is 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 to 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), can as needed be configured to aileron configuration 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 the middle wing 31 has low-angle established angle, and the left outside wing 33 and starboard outboard 35 have There is low-angle negative twist to turn, while having the larger upper counterangle, outer wing in descent is reduced while stability is increased and wipes ground The possibility of damage.The middle wing 31 defines a plane with designated mounting angle with the contact portion of fuselage 10, 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, optimum is 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 embodiment, above-mentioned parameter also can within the specific limits be adjusted according to actual conditions.

Vertical fin 40 is dismounted with the afterbody of fuselage 10 by plug connector 41 without instrument.Vertical fin 40 is also formed with installing space 401, Horizontal tail manipulates steering wheel（It is not shown）With rudder control steering wheel（It is 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, the rear of fuselage 10 is provided with horizontal tail rotating shaft fixing end 102.Set without any electronics in horizontal tail 50 It is standby, to prevent from being damaged when landing is decomposed.

Buffers packet 60 includes the first buffers packet 61, the second buffers packet 63, the 3rd buffers packet 65, and it 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 throw mode and launch using zero run-up hand, be produced by the electricpropulsion installation 20 positioned at the position of head 10 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 hand 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 hand throws unmanned plane is as follows：Both hands holding fuselage 10, head 10 raises up slightly, and wing 30 is protected Water holding is put down, and starts motor 23, is adjusted to a suitable rotating speed, and unmanned plane is sent, and unmanned plane can be in the time of 1s It is interior, accelerate to 10m/s（Stalling speed）More than, complete zero run-up hand throw it is winged.

Herein, term " including ", "comprising" or its any other variant are intended to including for nonexcludability, remove Comprising those listed key elements, but also other key elements being not expressly set out can be included.

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.

Preferred embodiment of the present utility model is the foregoing is only, it is all in this practicality not to limit the utility model Within new spirit and principle, any modification, equivalent substitution and improvements made etc. should be included in guarantor of the present utility model Within the scope of shield.

Claims

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 The pulling force for being more than or equal to 5.4kg can be provided for the unmanned plane, the wing is high coefficient of lift combined aerofoil profile, and 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 is including motor and spiral shell Rotation oar, the motor is arranged on the head of the fuselage, and the screw is arranged on the motor.

3. fixed-wing unmanned plane as claimed in claim 2, it is characterised in that：The screw is separate type screw, described Screw includes blade and propeller hub, and the blade is connected by bolt with the propeller hub, 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 is 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 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 elastic tape is arranged with 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.