CN108001672A - Power system and control system disconnect-type aircraft - Google Patents
Power system and control system disconnect-type aircraft Download PDFInfo
- Publication number
- CN108001672A CN108001672A CN201711164728.8A CN201711164728A CN108001672A CN 108001672 A CN108001672 A CN 108001672A CN 201711164728 A CN201711164728 A CN 201711164728A CN 108001672 A CN108001672 A CN 108001672A
- Authority
- CN
- China
- Prior art keywords
- control panel
- oil
- propeller
- unmanned plane
- pesticide
- 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
- 239000000575 pesticide Substances 0.000 claims abstract description 33
- 230000005540 biological transmission Effects 0.000 claims abstract description 20
- 238000002347 injection Methods 0.000 claims abstract description 15
- 239000007924 injection Substances 0.000 claims abstract description 15
- 238000005183 dynamical system Methods 0.000 claims description 22
- 239000000446 fuel Substances 0.000 claims description 15
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 6
- 239000003814 drug Substances 0.000 claims description 4
- 229940079593 drug Drugs 0.000 claims description 2
- 239000007921 spray Substances 0.000 claims description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims 3
- 238000000034 method Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 238000005507 spraying Methods 0.000 description 3
- 230000004888 barrier function Effects 0.000 description 2
- 244000025254 Cannabis sativa Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000037396 body weight Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 239000003337 fertilizer Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/16—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting
- B64D1/18—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting by spraying, e.g. insecticides
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Life Sciences & Earth Sciences (AREA)
- Pest Control & Pesticides (AREA)
- Remote Sensing (AREA)
- Catching Or Destruction (AREA)
Abstract
The invention relates to an aircraft with a power system and a control system separated from each other, which comprises a base frame, a horizontal cross beam, an oil power system, an oil power transmission mechanism, propellers, a Y-direction control panel, an X-direction control panel, a pesticide box, a pesticide conveying conduit and a pesticide injection pipeline, wherein the base frame supports the horizontal cross beam, and the propellers are arranged on the horizontal cross beam; the oil power system comprises an oil storage tank and an oil-driven engine, and the oil-driven engine drives the propeller to rotate through the oil power transmission mechanism; the Y-direction control panel and the X-direction control panel are arranged below the propeller. According to the invention, the power system is separated from the control system for adjusting the flight attitude of the unmanned aerial vehicle, the oil power system is adopted for supplying energy, the large load and long endurance of the unmanned aerial vehicle are realized, the working efficiency of the agricultural unmanned aerial vehicle is improved, the X-direction control panel and the Y-direction control panel are arranged to realize the adjustment of the flight state of the unmanned aerial vehicle, and the cost and the failure rate of the unmanned aerial vehicle are reduced by a simple structure.
Description
Technical field
The present invention relates to aircraft field, more particularly to a kind of dynamical system and control system separate type aircraft.
Background technology
With the development of unmanned air vehicle technique, it is also answered in the sprinkling of the medicine and liquid chemical fertilizer of crops
With.During pesticide spraying, national standard has particular provisions for the spray concentration of unit tree and grass coverage, and this requires nothing
The man-machine flying speed when spraying medicine cannot be too fast, and in extensive sprinkling, unmanned plane will possess heavy－duty and long continuation of the journey energy
Power.
Recorded according to the prior art, the unmanned plane applied to pesticide spraying is mostly multi-rotor unmanned aerial vehicle, but works as and use electric power
When driving agricultural multi-rotor unmanned aerial vehicle, its payload and cruising ability wretched insufficiency, when using oily power drive, generally
To use variable-pitch propeller adjustment unmanned plane during flying state, but variable-pitch propeller complicated, of high cost, high failure rate.
The content of the invention
In order to solve the above technical problems, the present invention provides a kind of dynamical system and control system separate type aircraft, utilize
The device of the invention, it will thus provide the dynamical system of power is with controlling the control system of unmanned plane during flying state to be separated, with letter
Single structure realizes the heavy－duty of agricultural unmanned plane and long continuation of the journey, reduces unmanned plane cost and failure rate.
Technical solution is used by the present invention solves above-mentioned technical problem：
A kind of dynamical system and control system separate type aircraft, including：Pedestal, horizontal gird, oily dynamical system, oil are dynamic
Force transmission mechanism, propeller, Y-direction control panel, X are to control panel, pesticide box, pesticide delivery conduit and pesticide playpipe
Road；The pedestal supports the horizontal gird, and the propeller is installed on the horizontal gird；The oil dynamical system includes
Fuel reserve tank and the dynamic engine of oil, the dynamic engine of oil drive the propeller to rotate by the oily power transmitting mechanism；Institute
Y-direction control panel is stated to be installed on below the propeller to control panel with the X.
In a preferred embodiment, the horizontal gird is Y-direction horizontal gird, several described propellers are in institute
State and be uniformly distributed on Y-direction horizontal gird in yi word pattern, and the midpoint of the relatively described Y-direction horizontal gird of several described propellers is left
It is right symmetrical.
In a preferred embodiment, Y-direction horizontal rotating shaft, the Y-direction are provided with below the Y-direction horizontal gird
Level turns to include just half section of shaft and the minus half section of shaft being mutually rotatablely connected；Just half section of shaft turns with described minus half section
Axis is respectively fixedly connected with one piece of Y-direction control panel；Just half section of axis from minus half section of shaft by different servo drivings, and then
Drive the forward and reverse rotation of Y-direction control panel each connected.
In a preferred embodiment, the Y-direction horizontal gird, Y-direction horizontal rotating shaft, the centre of Y-direction control panel
Position is both provided with folding fastener.
In a preferred embodiment, the oily power drive mechanism includes shaft, driving wheel, driven wheel and transmission
Band, the dynamic engine of oil drive the driving wheel by the shaft, are rotated and then the drive driven wheel, the driving wheel
Be respectively arranged with rotary middle spindle with the center of the driven wheel, the rotary middle spindle with the closest propeller
The transmission belt is socketed between heart shaft；The Y into the left and right sides of horizontal gird, the adjacent propeller of homonymy
The transmission belt is socketed between central rotating shaft.
In a preferred embodiment, the dynamic engine of the oil is set below the oily power drive mechanism, it is described
X is set to fuel reserve tank bottom plate, the X along midpoint to being symmetrically set with oil storage on fuel reserve tank bottom plate below the dynamic engine of oil
Case.
In a preferred embodiment, the X is provided with two pieces in collinear to fuel reserve tank bottom plate lower section
The X is to control panel.
In a preferred embodiment, the pesticide box is arranged on the Y-direction horizontal gird centre position, the agriculture
Medicine injection pipe is arranged on below unmanned plane, and the pesticide conveyance conduit is set along unmanned plane surrounding, connect the pesticide box with
The pesticide injection pipe, the pesticide injection pipe lower section are provided with injection perforate.
In a preferred embodiment, it is cavity body structure below the Y-direction horizontal gird, it is the driving wheel, driven
Wheel and the transmission belt are built in the cavity body structure.
In a preferred embodiment, when unmanned plane hovers vertically, the Y-direction control panel rotates in same direction around Y-axis
Realize rotary balance of the complete machine around Y-axis, the Y realizes the rotary balance of complete machine about the z axis, the X to the incorgruous rotation of control panel
The rotary balance for realizing complete machine around X-axis is rotate in same direction around X-axis to control panel；Unmanned plane along X-direction move when, the Y-direction
Control panel significantly rotates in same direction with the Y-direction horizontal rotating shaft around Y axis；Unmanned plane along Y direction move when, the X is to control
Panel significantly rotates in same direction around X-axis；Unmanned plane is in VTOL, by the throttle tune for increasing or reducing the dynamic engine of the oil
Save revolution speed of propeller.
The beneficial effects of the invention are as follows：
The present invention is by the way that dynamical system is separated with adjusting the control structure of unmanned plane during flying posture, using oily dynamical system
Energy supply, realizes the heavy－duty of unmanned plane and long continuation of the journey, improves the work efficiency for agriculture unmanned plane of knowing clearly, while set X to control
Panel processed realizes the adjustment of unmanned plane during flying state with Y-direction control panel, and cost and the event of unmanned plane are reduced with simple structure
Barrier rate.
Brief description of the drawings
The present invention will be further described with reference to the accompanying drawings and examples.
Fig. 1 is the composition structure diagram of one embodiment of the invention；
Fig. 2 is the composition structure diagram of another angle of Fig. 1 embodiments of the present invention；
Fig. 3 is the schematic diagram of one embodiment of oily power drive mechanism of the invention.
Embodiment
Carried out clearly below with reference to the technique effect of the design of embodiment and attached drawing to the present invention, concrete structure and generation
Chu, complete description, to be completely understood by the purpose of the present invention, scheme and effect.It should be noted that in situation about not conflicting
Under, the feature in embodiment and embodiment in the application can be mutually combined.
It should be noted that unless otherwise specified, when a certain feature is referred to as " fixing ", " connection " in another feature,
It can directly fix, be connected in another feature, can also indirectly fix, be connected in another feature.In addition, this
The descriptions such as the upper and lower, left and right used in invention are only to be closed relative to the mutual alignment of each part of the present invention in attached drawing
For system.
In addition, unless otherwise defined, the technology of all of technologies and scientific terms used here by the article and the art
The normally understood implication of personnel is identical.Term used in the description is intended merely to description specific embodiment herein, without
It is to limit the present invention.Term as used herein " and/or " include the arbitrary of one or more relevant Listed Items
Combination.
Fig. 1 is the composition structure diagram of one embodiment of the invention, with reference to Fig. 1, the dynamical system and control system point
Include from formula aircraft：
Pedestal 1, Y-direction horizontal gird 2, fuel reserve tank 3, the dynamic engine 4 of oil, oily power drive mechanism 5, propeller 6, Y-direction control
Panel 7 processed, X is to control panel 8, and pesticide box 9, pesticide conveyance conduit 10, pesticide injection pipe 11, Y-direction horizontal rotating shaft 12, rolls over
Folded 13, the X that detains is to fuel reserve tank bottom plate 14, annular duct 15, cavity body structure 16 and controller 17.
X-axis, Y-axis and Z-direction mentioned in the present invention are as shown in fig. 1.
In the present invention, as shown in Figure 1,1 support level crossbeam of pedestal, propeller 6 are installed on horizontal gird；Oil is dynamic
Force system includes fuel reserve tank 3 and the dynamic engine 4 of oil, and the dynamic engine 4 of oil drives propeller 6 to revolve by oily power drive mechanism 5
Turn, the VTOL of unmanned plane is realized by the rotation of propeller 6；Y-direction control panel 7 and X is installed on spiral shell to control panel 8
The lower section of paddle 6 is revolved, Y-direction control panel 7 and X is rotated to control panel 8 under the driving effect of steering engine (not shown), and then
Adjust the flight attitude of unmanned plane.
The present invention is by the way that dynamical system is separated with adjusting the control system of unmanned plane during flying posture, using oily dynamical system
Energy supply, realizes the heavy－duty of unmanned plane and long continuation of the journey, improves the work efficiency for agriculture unmanned plane of knowing clearly, while set X to control
Panel processed and Y-direction control panel, realize the adjustment of unmanned plane during flying state, and cost and the event of unmanned plane are reduced with simple structure
Barrier rate.
In the present embodiment, it is preferable that as shown in Figure 1, horizontal gird is Y-direction horizontal gird 2, several propellers 6 are in Y-direction
It is uniformly distributed on horizontal gird 2 in yi word pattern, and several propellers 6 are symmetrical with respect to the midpoint of Y-direction horizontal gird 2.It is excellent
Selection of land, is provided with even number propeller 6 (propeller quantity is greater than or equal to 2n, and n takes positive integer), the list of Y-direction horizontal gird 2
Side is provided with n propeller, and Y to the propeller 6 set on horizontal gird with respect to the symmetrical distribution in midpoint.Select herein
One specific direction sets a horizontal gird to disclosure satisfy that the sprinkling demand of agricultural unmanned plane, and simplifies structure, mitigates
Unmanned plane body weight；Certain distribution to horizontal gird herein is not specifically limited with quantity, as long as can guarantee that unmanned plane machine
The basic stability of equilibrium of body.Several propellers 6 word order and relative level crossbeam on Y-direction horizontal gird 2
The 2 symmetrical distribution in midpoint, can ensure that fuselage balances to the full extent.In the present embodiment, propeller 6 is provided with 4, edge
The midpoint of Y-direction horizontal gird 2 is symmetrically respectively distributed with two.
It is preferred that being provided with annular duct 15 in the top of each propeller 6, annular duct 15 can be spiral
The lift of bigger is lifted in the rotation process of paddle 6 for unmanned plane.
In the present embodiment, it is preferable that the lower section of Y-direction horizontal gird 2 is provided with Y-direction horizontal rotating shaft 12, and Y-direction horizontal rotating shaft 12 wraps
The just half section of shaft 121 and minus half section of shaft 122, just half section of shaft 121 for including rotation connection are fixedly connected with one piece of Y-direction chain of command
Plate 7, minus half section of shaft 122 are fixedly connected with another piece of Y-direction control panel 7；Just half section of shaft 121 is distinguished with minus half section of shaft 122
By different servo drivings, and then drive 7 rotating of Y-direction control panel each connected.
The rotating manner of Y-direction control panel 7 is not specifically limited herein, as long as Y-direction control panel 7 can be made to be adjusted by rotating
The state of flight of whole unmanned plane, it is simple in structure herein by the way of shaft is driven control panel 7 to rotate by servo driving.
Herein, it is preferable that just half section of shaft 121, minus half section of shaft 122 are each integrally formed with one piece of Y-direction control panel 7,
The globality lifting of structure.
In the present embodiment, it is preferable that Y-direction horizontal gird 2, Y-direction horizontal rotating shaft 12, the middle part of Y-direction control panel 7
Folding fastener is both provided with, makes unmanned plane is foldable in transportational process to pack up, accumulating is more convenient, opens again when in use solid
It is fixed.
In the present embodiment, as shown in Figure 3, it is preferable that oily power drive mechanism 5 includes shaft 501, driving wheel 502, driven
Wheel 503 and transmission belt 504, the dynamic engine 4 of oil rotate, and drive driving wheel 502 to rotate by shaft 501, driving wheel 502 with it is driven
The engagement of wheel 503, driven wheel 503 rotate；Driving wheel 502 and the center of driven wheel 503 are respectively arranged with rotary middle spindle 505, turn
Transmission belt 504 is socketed between dynamic central shaft 505 and the central rotating shaft 601 of closest propeller 6；A left side for Y-direction horizontal gird 2
In right both sides, transmission belt 504 is socketed between the central rotating shaft 601 of homonymy adjoining spiral paddle 6.
The structure of oily power transmission arrangment 5 is not specifically limited with mode herein, the modes such as chain drive can also be passed through
It is driven.
In the present embodiment, it is preferable that the oily lower section of power drive mechanism 5 sets the dynamic engine 4 of oil, the dynamic lower section of engine 4 of oil
X is set to fuel reserve tank bottom plate 14, X along midpoint to being symmetrically set with fuel reserve tank 3 on fuel reserve tank bottom plate 14.It can so make oil dynamic
Engine 4 and 501 direct-drive of shaft in oily power drive mechanism 5.Fuel reserve tank 3, which is symmetrical arranged, to be conducive to ensure unmanned plane
The balance of fuselage.
In the present embodiment, it is preferable that X is provided with two pieces to the lower section of fuel reserve tank bottom plate 14 and is in collinear X to control
Panel 8, control panel 8 can be rotated by the driving of motor (not shown) around X-axis, and then adjust the state of flight of unmanned plane.
In the present embodiment, Y-direction control panel 7 and X is respectively positioned on the underface of propeller 6 to control panel 8, and propeller 6 produces
Raw air-flow makes the control panel of unmanned plane in regulation and control unhinderedly directly through Y-direction control panel 7 and X to control panel 8
It is more efficient also more flexible.
In the present embodiment, it is preferable that pesticide box 9 is arranged on the centre position of Y-direction horizontal gird 2, pesticide injection pipe 11
It is arranged on below unmanned plane, pesticide conveyance conduit 12 is set along unmanned plane surrounding, connection pesticide box 9 and pesticide injection pipe 11；
The lower section of pesticide injection pipe 11 is provided with injection perforate.Pesticide injection pipe 11 is arranged on below unmanned plane, pesticide can be made to exist
Under the collective effect for the downdraught that dead weight and propeller 6 produce, directly it is sprayed onto on crops；12 edge of pesticide conveyance conduit
Unmanned plane surrounding is set, rather than between interspersed propeller 6 and control panel, can be to avoid the interference to air-flow.
In the present embodiment, it is preferable that the lower section of Y-direction horizontal gird 2 is cavity body structure 16, driving wheel 502, driven wheel 503
And transmission belt 504 is built in cavity body structure 16.Cavity body structure 16 is to internal driving wheel 502, driven wheel 503 and transmission
Band 504 plays a protective role, and prevents above-mentioned transmission parts from working for a long time in the weather to expose to the sun and rain, and corrosion and damage occurs.
In the present embodiment, the state of flight of unmanned plane is as follows：
During taking off vertically, the dynamic engine 4 of oil starts unmanned plane, increases the throttle of the dynamic engine 4 of oil, the dynamic hair of oil
Motivation 4 drives propeller 6 to rotate by oily power drive mechanism 5, when the lift that propeller 6 produces, which is more than unmanned plane, conducts oneself with dignity,
Unmanned plane takes off vertically；When unmanned plane wants vertical landing, by reducing the throttle of the dynamic engine 4 of oil, the rotating speed of propeller 6
Slack-off, the lift of generation reduces, when lift is gradually less than dead weight, the gradual vertical landing of unmanned plane；Y-direction horizontal gird 2 is in
The symmetrical propeller 6 of point rotates backward, to offset the turning moment of unmanned plane complete machine.
When the lift that propeller 6 produces, which is equal to unmanned plane, conducts oneself with dignity, unmanned plane hovering, Y-direction control panel 7 is around Y-axis at this time
Rotate synchronously, realize rotary balance of the complete machine around Y-axis, Y-direction control panel 7 realizes the rotation of complete machine about the z axis around the incorgruous rotation of Y-axis
Balance, X rotate in same direction to control panel 8, realize rotary balance of the complete machine around X-axis；Whole balance and stability process passes through controller
17 are adjusted, it is preferable that controller 17 is located at unmanned plane position of centre of gravity.
Unmanned plane along X-axis positive direction move when, Y-direction control panel 7 significantly rotates in same direction with Y-direction horizontal rotating shaft 12 around Y-axis,
Rotation direction is rotates counterclockwise in terms of Y-axis positive direction, and unmanned plane is integrally subject to from the torsion clockwise in terms of Y-axis positive direction at this time
Square, unmanned plane produce inclination, and the lift that propeller 6 produces can produce a component in X-axis positive direction, drive unmanned plane along X-axis
Forward direction is mobile；Unmanned plane moves similarly along X-axis negative direction.
Unmanned plane along Y-axis positive direction move when, X significantly rotates in same direction to control panel 8 around X-axis；Rotation direction is from X-axis
Positive direction, which is seen, to be rotated counterclockwise, and unmanned plane is integrally subject to from the clockwise torque in terms of X-axis positive direction at this time, and unmanned plane, which produces, to incline
Tiltedly, the lift that propeller 6 produces can produce a component in Y-axis positive direction, drive unmanned plane to be moved along Y-axis forward direction；Unmanned plane
Moved similarly along Y-axis negative direction.
Above is the preferable of the present invention is implemented to be illustrated, but the invention is not limited to the implementation
Example, those skilled in the art can also make a variety of equivalent variations on the premise of without prejudice to spirit of the invention or replace
Change, these equivalent deformations or replacement are all contained in the application claim limited range.
Claims (10)
1. a kind of dynamical system and control system separate type aircraft, it is characterised in that including：Pedestal, horizontal gird, oily power
System, oily power drive mechanism, propeller, Y-direction control panel, X are to control panel, pesticide box, pesticide delivery conduit and agriculture
Medicine injection pipe；The pedestal supports the horizontal gird, and the propeller is installed on the horizontal gird；The oil power
System includes fuel reserve tank and the dynamic engine of oil, and the dynamic engine of oil drives the propeller by the oily power transmitting mechanism
Rotation；The Y-direction control panel is installed on below the propeller with the X to control panel.
2. dynamical system according to claim 1 and control system separate type aircraft, it is characterised in that：It is described horizontal horizontal
Beam is Y-direction horizontal gird, several described propellers are uniformly distributed on the Y-direction horizontal gird in yi word pattern, and several
The midpoint of the relatively described Y-direction horizontal gird of the propeller is symmetrical.
3. dynamical system according to claim 2 and control system separate type aircraft, it is characterised in that：The Y-direction water
Flat below the crossbeam is provided with Y-direction horizontal rotating shaft, and the Y-direction is horizontal to be turned to include the just half section of shaft and negative half being mutually rotatablely connected
Section shaft；Just half section of shaft is respectively fixedly connected with one piece of Y-direction control panel with minus half section of shaft；Just half section of axis
From minus half section of shaft by different servo drivings, and then drive the forward and reverse rotation of Y-direction control panel each connected.
4. dynamical system according to claim 3 and control system separate type aircraft, it is characterised in that：The Y-direction water
Flat crossbeam, Y-direction horizontal rotating shaft, the middle part of Y-direction control panel are both provided with folding fastener.
5. dynamical system according to claim 4 and control system separate type aircraft, it is characterised in that：The oil power
Transmission mechanism includes shaft, driving wheel, driven wheel and transmission belt, and the dynamic engine of oil drives the active by the shaft
Take turns and then drive the driven wheel to rotate, the center of the driving wheel and the driven wheel is respectively arranged with rotary middle spindle, institute
State and be socketed with the transmission belt between the central rotating shaft of rotary middle spindle and the closest propeller；The Y-direction is horizontal horizontal
In the left and right sides of beam, the transmission belt is socketed between the central rotating shaft of the adjacent propeller of homonymy.
6. dynamical system according to claim 5 and control system separate type aircraft, it is characterised in that：The oil power
The oil dynamic engine is set below transmission mechanism, X is set below the dynamic engine of oil to fuel reserve tank bottom plate, the X is to storage
On oil tank bottom plate fuel reserve tank is symmetrically set with along midpoint.
7. dynamical system according to claim 6 and control system separate type aircraft, it is characterised in that：The X is to storage
Two pieces are provided with below oil tank bottom plate and is in the collinear X to control panel.
8. the dynamical system and control system separate type aircraft, its feature according to any one of claim 2 to 7 exist
In：The pesticide box is arranged on the Y-direction horizontal gird centre position, and the pesticide injection pipe is arranged on below unmanned plane,
The pesticide conveyance conduit is set along unmanned plane surrounding, connects the pesticide box and the pesticide injection pipe, the pesticide spray
Penetrate below pipeline and be provided with injection perforate.
9. dynamical system according to claim 1 and control system separate type aircraft, it is characterised in that：The Y-direction water
Flat below the crossbeam is cavity body structure, and the driving wheel, driven wheel and the transmission belt are built in the cavity body structure.
10. according to claim 1 to 7, the dynamical system any one of claim 9 is flown with control system separate type
Device, it is characterised in that：When unmanned plane hovers vertically, the Y-direction control panel rotates in same direction around Y-axis realizes that complete machine turns around Y-axis
The rotary balance of complete machine about the z axis is realized in dynamic balancing, the incorgruous rotation of Y-direction control panel, and the X is same around X-axis to control panel
Rotary balance of the complete machine around X-axis is realized to rotation；Unmanned plane along X-direction move when, the Y-direction control panel is with the Y-direction
Horizontal rotating shaft significantly rotates in same direction around Y-axis；Unmanned plane along Y direction move when, the X is significantly in the same direction around X-axis to control panel
Rotate；Unmanned plane is in VTOL, by the throttle adjustment revolution speed of propeller for increasing or reducing the dynamic engine of the oil.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711164728.8A CN108001672A (en) | 2017-11-21 | 2017-11-21 | Power system and control system disconnect-type aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711164728.8A CN108001672A (en) | 2017-11-21 | 2017-11-21 | Power system and control system disconnect-type aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108001672A true CN108001672A (en) | 2018-05-08 |
Family
ID=62053007
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711164728.8A Pending CN108001672A (en) | 2017-11-21 | 2017-11-21 | Power system and control system disconnect-type aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108001672A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109305351A (en) * | 2018-11-20 | 2019-02-05 | 南京森林警察学院 | A kind of autonomous extendible extension width rotor wing unmanned aerial vehicle |
| CN109383759A (en) * | 2018-11-05 | 2019-02-26 | 南方科技大学 | Aircraft based on flight attitude is adjusted to control plane |
| CN113212745A (en) * | 2021-04-26 | 2021-08-06 | 南方科技大学 | Rotor unmanned aerial vehicle and endurance prolonging method thereof |
| CN115806072A (en) * | 2022-12-21 | 2023-03-17 | 南方科技大学 | Vector control-based rotor aircraft and control method thereof |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101366310B1 (en) * | 2012-09-03 | 2014-02-21 | 한국항공대학교산학협력단 | Multi-copter |
| CN205076044U (en) * | 2015-10-27 | 2016-03-09 | 中航维拓（北京）科技有限责任公司 | Oil moves four rotor unmanned aerial vehicle power - transmission system of displacement |
| CN105775120A (en) * | 2016-04-15 | 2016-07-20 | 广州市派飞科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN106114852A (en) * | 2016-06-29 | 2016-11-16 | 饶大林 | A kind of cross-arranging type dual-culvert vertical take-off and landing Spacecraft Attitude Control |
| CN205738083U (en) * | 2016-05-10 | 2016-11-30 | 程靖 | The dynamic many rotor power drive system of a kind of oil |
| CN106927023A (en) * | 2017-03-27 | 2017-07-07 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of agricultural plant protection controls culvert type unmanned plane with rudder face |
| CN107042883A (en) * | 2017-03-27 | 2017-08-15 | 上海珞鹏航空科技有限公司成都研发分公司 | Double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding can generate electricity with loading |
| CN207683776U (en) * | 2017-11-21 | 2018-08-03 | 南方科技大学 | Power system and control system disconnect-type aircraft |
-
2017
- 2017-11-21 CN CN201711164728.8A patent/CN108001672A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101366310B1 (en) * | 2012-09-03 | 2014-02-21 | 한국항공대학교산학협력단 | Multi-copter |
| CN205076044U (en) * | 2015-10-27 | 2016-03-09 | 中航维拓（北京）科技有限责任公司 | Oil moves four rotor unmanned aerial vehicle power - transmission system of displacement |
| CN105775120A (en) * | 2016-04-15 | 2016-07-20 | 广州市派飞科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN205738083U (en) * | 2016-05-10 | 2016-11-30 | 程靖 | The dynamic many rotor power drive system of a kind of oil |
| CN106114852A (en) * | 2016-06-29 | 2016-11-16 | 饶大林 | A kind of cross-arranging type dual-culvert vertical take-off and landing Spacecraft Attitude Control |
| CN106927023A (en) * | 2017-03-27 | 2017-07-07 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of agricultural plant protection controls culvert type unmanned plane with rudder face |
| CN107042883A (en) * | 2017-03-27 | 2017-08-15 | 上海珞鹏航空科技有限公司成都研发分公司 | Double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding can generate electricity with loading |
| CN207683776U (en) * | 2017-11-21 | 2018-08-03 | 南方科技大学 | Power system and control system disconnect-type aircraft |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109383759A (en) * | 2018-11-05 | 2019-02-26 | 南方科技大学 | Aircraft based on flight attitude is adjusted to control plane |
| CN109383759B (en) * | 2018-11-05 | 2023-08-22 | 南方科技大学 | Aircraft capable of adjusting flight attitude based on control surface |
| CN109305351A (en) * | 2018-11-20 | 2019-02-05 | 南京森林警察学院 | A kind of autonomous extendible extension width rotor wing unmanned aerial vehicle |
| CN109305351B (en) * | 2018-11-20 | 2023-09-22 | 南京森林警察学院 | Independent retractable type hanging rotor unmanned aerial vehicle |
| CN113212745A (en) * | 2021-04-26 | 2021-08-06 | 南方科技大学 | Rotor unmanned aerial vehicle and endurance prolonging method thereof |
| CN115806072A (en) * | 2022-12-21 | 2023-03-17 | 南方科技大学 | Vector control-based rotor aircraft and control method thereof |
| CN115806072B (en) * | 2022-12-21 | 2024-01-26 | 南方科技大学 | Vector control-based rotorcraft and control method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108001672A (en) | Power system and control system disconnect-type aircraft | |
| CN105539833B (en) | Fixed-wing Multi-axis aircraft | |
| CN110316370B (en) | Layout and control method of distributed power tilting wing aircraft | |
| CN103538714A (en) | Vertical take-off and landing model aircraft unmanned aerial vehicle | |
| CN107914870B (en) | Rotor robot for logistics distribution | |
| CN107225925B (en) | A kind of rolling wing VTOL is dwelt aircraft more | |
| CN207683776U (en) | Power system and control system disconnect-type aircraft | |
| CN206141823U (en) | Many rotors plant protection unmanned aerial vehicle | |
| CN107416198A (en) | Aircraft and its flying method | |
| CN107140208A (en) | STOL top load multiaxis fans wing unmanned plane | |
| CN114715392B (en) | Variant flying wing type tilting rotor unmanned aerial vehicle | |
| CN109383759B (en) | Aircraft capable of adjusting flight attitude based on control surface | |
| CN214824154U (en) | Linear multi-rotor-wing plant protection aircraft structure | |
| CN112623224B (en) | Linear type many rotors plant protection aircraft structure | |
| CN211196613U (en) | Deformable aircraft | |
| CN104044733B (en) | Six rotor duct aircraft | |
| CN206367581U (en) | New many rotor multi-purpose unmanned aerial vehicles | |
| CN206384131U (en) | A kind of composite wing unmanned plane | |
| CN108674644A (en) | A kind of multi-rotor aerocraft with slave | |
| CN110065629B (en) | Multifunctional tilting duct unmanned aerial vehicle | |
| CN207482180U (en) | Aircraft | |
| CN105667774A (en) | Multi-rotor aircraft | |
| CN216969996U (en) | Multi-rotor unmanned aerial vehicle | |
| CN212797307U (en) | Multi-shaft tilting fixed-wing unmanned aerial vehicle | |
| CN217348209U (en) | Aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180508 |