CN206826927U - Mixed layout unmanned plane - Google Patents
Mixed layout unmanned plane Download PDFInfo
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- CN206826927U CN206826927U CN201720654117.0U CN201720654117U CN206826927U CN 206826927 U CN206826927 U CN 206826927U CN 201720654117 U CN201720654117 U CN 201720654117U CN 206826927 U CN206826927 U CN 206826927U
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- unmanned plane
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- mixed layout
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Abstract
It the utility model is related to unmanned air vehicle technique field, a kind of more particularly to mixed layout unmanned plane, including fuselage, the fixed-wings of fuselage both sides is fixed on, the empennage of afterbody and the propulsion electric machine installed in fuselage afterbody is installed on, blade is installed on the output shaft of the propulsion electric machine；The middle part of the fuselage is provided with bar shaped mounting hole, and four rotor closing-folding mechanisms are provided with the bar shaped mounting hole.Using original creation can wireless one-key fold more rotor horns, allow unmanned plane landing as rotor craft, when unmanned plane will enter quick cruising phase, four horns are recovered to the side of fuselage two by remote control, unmanned plane is set to be flown in a manner of fixed wing aircraft, relatively fairshaped fuselage more conforms to aerodynamic demands than more rotors, can there are higher speed and smaller windage, lift mixed layout unmanned plane entirety flight stability.
Description
Technical field
It the utility model is related to unmanned air vehicle technique field, more particularly to a kind of mixed layout unmanned plane.
Background technology
Whether rotor class aircraft turns according to rotor, can be divided into：Helicopter and autogyro (referred to as rotor
Machine).Helicopter can realize VTOL and low latitude hovering, and have superior mobility, achievable hovering, vertical flight,
Inverted flight and side are winged etc..But there is complicated, vibration and noise is higher, speed limit is relatively low in helicopter.Gyroplane and helicopter
To compare, gyroplane is simple in construction, and bare weight is than low, low cost, and pneumatic efficiency is higher, compared with fixed wing aircraft, gyroplane
It can be landed with short takeoff, and the performance that flies at low speed is good, is not easy stall.In recent years, the unique advantage of gyroplane and its business
Gradually it is taken seriously with military application potential, again as the focus of aviation field concern.
But there is problems with gyroplane：Although gyroplane can be realized richochet or ultra-short takeoff, pass through by prewhirling
Rotor, which efficiently slows down, realizes that short distance lands, but gyroplane is without the same high-speed flight of image of Buddha fixed wing aircraft, while does not also have
Standby VTOL ability and hovering ability.
A kind of multi-modal multipurpose flight of combined type is disclosed in Application No. 201410852017.X patent document
Device, based on blade tip gas jet technique, three kinds of fixed-wing, helicopter, gyroplane aerodynamic arrangements are merged, it is proposed that based on blade tip
The mixed layout rotor craft of jet.During landing, rotor is turned by blade tip jet engine, realized in a manner of helicopter
VTOL.During low-speed operations, mainly pulling force is provided by autorotating rotor, during high-speed flight, by adjusting oar disk inclination angle and rotor
Always away from reducing rotor rotating speed, unload rotor, using the bigger wing-borne major part lift of lift-drag ratio, improve the liter of complete machine
Ratio is hindered, improves flying speed.The shortcomings that said structure is：Although when realizing rapid flight using fixed-wing, due to rotor and
The presence of helicopter is unable to reach quick flight, is restricted each other, can not play the characteristics of respective maximum completely.
Utility model content
The purpose of this utility model is to overcome the shortcomings of above-mentioned technology, and provides a kind of mixed layout unmanned plane, solid
When determining wing flight, rotor does not interfere with flight stability and flying speed.
The utility model to achieve the above object, using following technical scheme：
A kind of mixed layout unmanned plane, it is characterised in that：Including fuselage, the fixed-wings of fuselage both sides is fixed on, is installed on
The empennage of afterbody and the propulsion electric machine installed in fuselage afterbody, blade is installed on the output shaft of the propulsion electric machine；
The middle part of the fuselage is provided with bar shaped mounting hole, and four rotor closing-folding mechanisms, four rotor are provided with the bar shaped mounting hole
Closing-folding mechanism includes installing plate, four rotor horns, four brushless electric machines, leading screw, pull bar and motor, the installing plate
It is fixed in the bar shaped mounting hole, four brushless electric machines are separately mounted to the outer end of four rotor horns, each
Blade is installed, the inner of four rotor horns is arranged on the installation by hinge respectively on the output shaft of brushless electric machine
On plate, the both ends of the leading screw are arranged on the installing plate by bearing block, and the motor drives the leading screw to rotate,
Two thread bush are threaded with leading screw, the both ends of each thread bush have been respectively articulated with a pull bar, the pull bar
Outer end and the inner of the rotor horn are hinged, and the outer end of four rotor horns is installed from the bar shaped in the deployed state
The both sides in hole are stretched out.
Preferably, the inner of four rotor horns is respectively fixed with engaging lug, the engaging lug and the pull bar
Outer end is hinged.
Preferably, the empennage is connected by two connecting rods with the fixed-wing.
Preferably, the fuselage is fixedly arranged at the front end with erecting bed.
Preferably, the bottom of the fuselage is provided with sliding wheel.
Preferably, camera cradle head is installed in the bottom of the fuselage.
Preferably, the internal thread of described two thread bush is in opposite direction.
The beneficial effects of the utility model are:Using original creation can more rotor horns for folding of a key, make unmanned plane can be with
The landing as rotor craft, when unmanned plane will enter fixed-wing quick cruising phase, remote control is by four rotor horns
The side of fuselage two is recovered to, unmanned plane is flown in a manner of fixed wing aircraft, relatively fairshaped fuselage is than more rotors
Aerodynamic demands are more conformed to, can there is higher speed and smaller resistance.
Traditional fixed wing aircraft and modern multi-rotor aerocraft each advantage, novel changable shape fixed-wing and four are merged
Rotor mixed layout unmanned plane can realize the VTOL of rotor craft, and the function of hovering again can be as fixed-wing
Aircraft equally quickly cruises, and reaches energy-efficient, the purpose of a tractor serves several purposes.
Brief description of the drawings
Fig. 1 is stereogram of the present utility model；
Fig. 2 is the structural representation of four rotor closing-folding mechanisms in the utility model；
Fig. 3 is the stereogram in another direction of the utility model；
Fig. 4 positions control flow chart of the present utility model.
Embodiment
Below in conjunction with the accompanying drawings and preferred embodiment describes specific embodiment of the present utility model in detail.Such as Fig. 1 and Fig. 2 institutes
Show, a kind of mixed layout unmanned plane, including fuselage 1, the fixed-wing 2 for being fixed on fuselage both sides, be installed on the empennage 3 of afterbody
And the propulsion electric machine 4 installed in fuselage afterbody, blade is installed on the output shaft of the propulsion electric machine；The middle part of the fuselage
Provided with bar shaped mounting hole 5, four rotor closing-folding mechanisms 6 are installed in the bar shaped mounting hole, four rotors are received in the case of folding
Folding mechanism will reduce flight resistance in four rotor foldings to bar shaped mounting hole, in the case of needing to be vertically moved up or down, four rotor foldings
Mechanism deploying, four rotors stretch out out of bar shaped mounting hole, and four rotors are divided into two groups of both sides for being each positioned at fuselage two-by-two, reach flat
The purpose of weighing apparatus.
In the utility model, it is brushless that the four rotors closing-folding mechanism includes the rotor horn 62, four of installing plate 61, four
Motor 63, leading screw 64, pull bar 65 and motor (do not regard in figure, coaxially can be connected with leading screw, can also pass through decelerator
It is connected with leading screw), the installing plate is fixed in the bar shaped mounting hole, and four brushless electric machines are separately mounted to described four
The outer end of root rotor horn, blade is installed (as existing mounting means, thus in figure on the output shaft of each brushless electric machine
Do not regard), the inner of four rotor horns is arranged on the installing plate by hinge 66 respectively, and four rotor horns can
Rotated centered on hinge, the both ends of the leading screw are arranged on the installing plate by bearing block 67, and the motor drives
The dynamic leading screw rotates, and in the utility model, two thread bush internal threads on leading screw are in opposite direction, can so ensure two
Group rotor inwardly or simultaneously outwards deploys simultaneously, and two thread bush 68, the both ends point of each thread bush are threaded with leading screw
A pull bar is not hinged with, and the outer end of the pull bar and the inner of the rotor horn are hinged, four rotor horns
Outer end stretched out in the deployed state from the both sides of the bar shaped mounting hole.When motor drives leading screw to rotate, screw set
Moved left and right on leading screw, so as to drive one end of pull bar to follow movement, and the other end of pull bar due to four rotor horns
The inner is be hinged, four rotor horns can be driven to be swung centered on hinge, so as to realize the folding of four rotor horns.
In the utility model, the inners of four rotor horns is respectively fixed with engaging lug 69, the engaging lug with
The outer end of the pull bar is hinged.
The empennage is connected by two connecting rods 7 with the fixed-wing.
In order to which according to equipment such as following illumination or shootings, erecting bed 8 is fixedly arranged at the front end with the fuselage.
In the utility model, the bottom of the fuselage is provided with sliding wheel 9.
As shown in figure 3, camera cradle head 10 is installed in the bottom of the fuselage.
As shown in figure 4, the course of work is as follows：
Step 1: will be with four rotor modes during VTOL, motor driving leading screw rotates, four rotor horns it is outer
End expansion, four brushless electric machines stretch out from the both sides of bar shaped mounting hole, drive blade to produce by the dynamic brushless electric machine of electric transfer drive and rise
Power, hovered after going up to the air to certain altitude；
Step 2: when steadily advancing, propulsion electric machine starts lifting pace, by fixed-wing wing generating unit decilitre
Power, current gas pressure is detected by barometer BMP085 in real time and is converted into height, four brushless electric machines for coordinating four rotors are reduced
Rotating speed makes total life be equal to gravity to keep stable state to reach height-lock control effect gradually to lack lift；
Step 3: when the lift that fixed-wing wing provides is enough to make flight stability, four rotor wings progressively slow down and stopped
Only, it is delayed after 5s, the work of four rotor closing-folding mechanisms, the air drag being subject to when packing up four rotors to reduce flight；
Step 4: under fixed-wing cruise mode, aircraft will keep balance appearance by the fixed-wing at fixed-wing wing both ends
State, empennage adjustment flying height, to stablize high-speed flight posture；
Step 5: worked close to destination, the rotor mode of fixed-wing pattern switching four, four rotor closing-folding mechanisms by four rotors
Four horn expansion, start four rotors, four brushless electric machines, while the phased out rotation of propulsion electric machine deceleration, switch to four rotors
Pattern, vertical landing can be carried out.
The utility model is carried out in Machine Design by the research to fixed-wing and multi-rotor aerocraft using new idea
Transformation, and be based on Arduino Mega2560 controllers, using high-performance brushless electric machine, electricity tune, big thrust loading propeller and
Arduino nano single-chip microcomputers and digital transmission module have manufactured and designed the mixed layout unmanned plane that the more rotors of a fixed-wing combine, collection
Into 7MGPS modules, BMP085 barometers, the three-axis gyroscope three axis accelerometers of MPU 6000, the three axle magnetometers of HMC 5843
Aircraft is set to be accurately positioned destination flight Deng sensor, it is fixed high from steady flight.
Using original creation can a key fold horn, allow unmanned plane landing as rotor craft, in unmanned plane
Four horns are recovered to the side of fuselage two by remote control when entering quick cruising phase, allow unmanned plane with fixed wing aircraft
Mode fly, relatively fairshaped fuselage more conforms to aerodynamic demands than more rotors, can there is higher speed
Smaller resistance.
Traditional fixed wing aircraft and modern multi-rotor aerocraft each advantage, novel changable shape fixed-wing and four are merged
Rotor mixed layout unmanned plane can realize the VTOL of rotor craft, and the function of hovering again can be as fixed-wing
Aircraft equally quickly cruises, and reaches the purpose for saving finite energy resource.
The utility model has the characteristics that：(1) the hybrid aerodynamic arrangement that is combined using rotor/fixed-wing, it is necessary to
The Synthetical Optimization of aerodynamic arrangement is carried out according to overall performance demand；(2) VTOL, STOL can be realized, is hovered
And low-speed operations；(3) high speed cruise flight can be realized；(4) there are a variety of model of flight, aircraft uses during different mode
Different aerodynamic configuration, lift/thrust presentation mode and control modes.
Unmanned mixed layout gyroplane is the knot of the fusion development of mixed layout rotor craft technology and unmanned air vehicle technique
Fruit, the growth requirement of unmanned plane multiple task ability is on the one hand come from, on the other hand also compensate for mixed layout rotor has man-machine behaviour
The problem of control is difficult, pilot training's difficulty is larger.Unmanned mixed layout gyroplane represents following unmanned air vehicle technique development
One important trend, i.e., cause unmanned plane by using the mixed layout form of innovation while there is the vertical of helicopter to rise
The high-performance cruise ability of drop, hovering ability and fixed wing aircraft, to improve its combination property and task compatibility, meet not
Same mission requirements.
Described above is only preferred embodiment of the present utility model, it is noted that for the common skill of the art
For art personnel, on the premise of the utility model principle is not departed from, some improvements and modifications can also be made, these improve and
Retouching also should be regarded as the scope of protection of the utility model.
Claims (7)
- A kind of 1. mixed layout unmanned plane, it is characterised in that：Including fuselage, the fixed-wings of fuselage both sides is fixed on, is installed on machine The empennage of body afterbody and the propulsion electric machine installed in fuselage afterbody, blade is installed on the output shaft of the propulsion electric machine；Institute The middle part for stating fuselage is provided with bar shaped mounting hole, and four rotor closing-folding mechanisms are provided with the bar shaped mounting hole, and four rotor is received Folding mechanism includes installing plate, four rotor horns, four brushless electric machines, leading screw, pull bar and motor, the installing plate and consolidated It is scheduled in the bar shaped mounting hole, four brushless electric machines are separately mounted to the outer end of four rotor horns, Mei Gewu Blade is installed, the inner of four rotor horns is arranged on the installing plate by hinge respectively on the output shaft of brush motor On, the both ends of the leading screw are arranged on the installing plate by bearing block, and the motor drives the leading screw to rotate, silk Be threaded with two thread bush on thick stick, the both ends of each thread bush have been respectively articulated with a pull bar, the pull bar it is outer The inner with the rotor horn is held to be hinged, the outer end of four rotor horns is in the deployed state from the bar shaped mounting hole Both sides stretch out.
- 2. mixed layout unmanned plane according to claim 1, it is characterised in that：The inner difference of four rotor horns Engaging lug is fixed with, the outer end of the engaging lug and the pull bar is hinged.
- 3. mixed layout unmanned plane according to claim 1, it is characterised in that：The empennage passes through two connecting rods and institute State fixed-wing connection.
- 4. mixed layout unmanned plane according to claim 1, it is characterised in that：The fuselage is fixedly arranged at the front end with installation Platform.
- 5. mixed layout unmanned plane according to claim 1, it is characterised in that：The bottom of the fuselage, which is provided with, slides Wheel.
- 6. mixed layout unmanned plane according to claim 1, it is characterised in that：Shooting is installed in the bottom of the fuselage Head.
- 7. mixed layout unmanned plane according to claim 1, it is characterised in that：The internal thread direction of described two thread bush Conversely.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720654117.0U CN206826927U (en) | 2017-06-07 | 2017-06-07 | Mixed layout unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720654117.0U CN206826927U (en) | 2017-06-07 | 2017-06-07 | Mixed layout unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206826927U true CN206826927U (en) | 2018-01-02 |
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ID=60773202
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720654117.0U Expired - Fee Related CN206826927U (en) | 2017-06-07 | 2017-06-07 | Mixed layout unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206826927U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111152921A (en) * | 2020-01-08 | 2020-05-15 | 北京建筑大学 | Control system of unmanned aerial vehicle capable of taking off and landing vertically |
| CN111361727A (en) * | 2020-03-31 | 2020-07-03 | 厦门恰再注包装有限公司 | A delivery unmanned aerial vehicle for rural equidistance area |
| CN113895623A (en) * | 2021-10-27 | 2022-01-07 | 桂林电子科技大学 | Unmanned aerial vehicle is patrolled and examined in monitoring |
| CN115520384A (en) * | 2022-11-28 | 2022-12-27 | 成都睿铂科技有限责任公司 | Vertical take-off and landing fixed wing unmanned aerial vehicle |
-
2017
- 2017-06-07 CN CN201720654117.0U patent/CN206826927U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111152921A (en) * | 2020-01-08 | 2020-05-15 | 北京建筑大学 | Control system of unmanned aerial vehicle capable of taking off and landing vertically |
| CN111361727A (en) * | 2020-03-31 | 2020-07-03 | 厦门恰再注包装有限公司 | A delivery unmanned aerial vehicle for rural equidistance area |
| CN113895623A (en) * | 2021-10-27 | 2022-01-07 | 桂林电子科技大学 | Unmanned aerial vehicle is patrolled and examined in monitoring |
| CN115520384A (en) * | 2022-11-28 | 2022-12-27 | 成都睿铂科技有限责任公司 | Vertical take-off and landing fixed wing unmanned aerial vehicle |
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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 |
Granted publication date: 20180102 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |