CN106741896A - A kind of quadrotor - Google Patents
A kind of quadrotor Download PDFInfo
- Publication number
- CN106741896A CN106741896A CN201611252846.XA CN201611252846A CN106741896A CN 106741896 A CN106741896 A CN 106741896A CN 201611252846 A CN201611252846 A CN 201611252846A CN 106741896 A CN106741896 A CN 106741896A
- Authority
- CN
- China
- Prior art keywords
- motor
- flank
- fuselage
- quadrotor
- erecting bed
- 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
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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
- 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
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/20—UAVs specially adapted for particular uses or applications for use as communications relays, e.g. high-altitude platforms
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of quadrotor.The surface installation base plate of the fuselage of the quadrotor；Substrate is connected by head rod with the first motor erecting bed, and substrate is connected by the second connecting rod with the second motor erecting bed, and substrate is connected by the 3rd connecting rod with the 3rd motor erecting bed；Sustainer is oil machine, installed in the surface of substrate；Main oar is arranged on the surface of sustainer；First motor is arranged on the surface of the first motor erecting bed；First flank is arranged on the surface of the first motor；Second motor is arranged on the surface of the second motor erecting bed；Second flank is arranged on the surface of the second motor；3rd motor is arranged on the 3rd motor erecting bed；Empennage is arranged on afterbody, and empennage is arranged on the 3rd motor.The present invention not only causes that quadrotor control gets up more flexible and convenient, and hovering when realizing boat long, and the maximum operating time is three hours.
Description
Technical field
The present invention relates to space technology field, more particularly to a kind of quadrotor.
Background technology
At present, aircraft mainly has three kinds of fixed-wing, single rotor and multi-rotor aerocraft, and Fixed Wing AirVehicle volume is big,
Taking off needs runway, and course line needs blank pipe department to ratify, therefore place is restricted, and is not suitable for quick in some narrow and small places
Walk；Single rotary-wing flight direction and lifting are completed all by a rotor, and security is poor；Multi-rotor aerocraft volume
It is small, Anywhere can landing, hovering and VTOL can be realized, and have a safety feature, detectd in covering target, information
Examine, military and civilian's task dispatching multiple fields such as battlefield surveillance, power-line patrolling and petroleum pipeline played an important role.
Dominant position is accounted in multi-rotor aerocraft is quadrotor, in the prior art the four of quadrotor
Propeller size is identical and in sustained height plane, each propeller one engine of correspondence, and motor is used engine more, but
Same size, identical elevation plane and engine are set using four propellers of motor, quadrotor is not only caused
Hovering during boat long can not be realized, and control gets up underaction conveniently.
The content of the invention
It is an object of the invention to provide a kind of quadrotor, the quadrotor can realize hovering during boat long
And control gets up flexible.
To achieve the above object, the invention provides following scheme：
A kind of quadrotor, including：Fuselage, main oar, the first flank, the second flank, empennage, sustainer, substrate,
Head rod, the second connecting rod, the 3rd connecting rod, the first motor, the first motor erecting bed, the second motor, the second motor peace
Dress platform, the 3rd motor, the 3rd motor erecting bed；
The surface of the fuselage is installed by the substrate；The substrate passes through the head rod and first motor
Erecting bed is connected, and the substrate is connected by second connecting rod with the second motor erecting bed, and the substrate passes through institute
The 3rd connecting rod is stated to be connected with the 3rd motor erecting bed；The sustainer is arranged on the surface of the substrate, described
Sustainer is oil machine, for driving main oar；The main oar is arranged on the surface of the sustainer, for controlling four rotors
Aircraft speed in vertical direction and displacement；First motor is arranged on the surface of the first motor erecting bed,
For driving first flank；First flank is arranged on the surface of first motor；Second motor is installed
In the surface of the second motor erecting bed, for driving second flank；Second flank is arranged on described second
The surface of motor；First flank and second flank are symmetricly set on the both sides of the fuselage, described for adjusting
The roll attitude of quadrotor；3rd motor is arranged on the 3rd motor erecting bed, for driving the tail
The wing；The empennage is arranged on the afterbody of fuselage, and the empennage is arranged on the 3rd motor, flies for adjusting four rotor
The course attitude of row device.
Optionally, the bottom of the sustainer is connected with sustainer mounting bracket, the sustainer and the main hair
Damping device is provided between motivation mounting bracket.
Optionally, the sustainer is the engine of 3W-275XiB2TS models.
Optionally, the main oar, first flank, second flank and the empennage are three-bladed propeller；Institute
The rotating diameter of main oar is stated for 0.864m, the rotating diameter of first flank, second flank and the empennage is
0.376m。
Optionally, the Plane of rotation of first flank and second flank less than the main oar Plane of rotation and with
The Plane of rotation of the main oar is parallel；The Plane of rotation of the empennage is vertical with the Plane of rotation of the main oar.
Optionally, the fuselage volume is 26L, and the fuselage carries fuel tank, Aerial Electronic Equipment and task system, the fuel tank
Including preceding fuel tank and rear fuel tank, the leading portion and back segment of the fuselage, the Aerial Electronic Equipment and task system position are respectively placed in
In the stage casing of the fuselage, the Aerial Electronic Equipment is located at the bottom of the middle fuselage, and the task system is located at the fuselage
Separated with dividing plate in the middle of the top in stage casing, the Aerial Electronic Equipment and the task system.
Optionally, the fuel tank uses the first hatch door, first hatch door to be located at close described first side of the fuselage
The side of the wing.
Optionally, the Aerial Electronic Equipment and the task system share the second hatch door, and second hatch door is located at the machine
The side of the close described empennage of body.
Optionally, first motor, second motor and the 3rd motor are equipped with independent current source.
Optionally, the quadrotor also includes：Undercarriage and undercarriage base plate；The undercarriage is arranged on described
On undercarriage base plate, the undercarriage uses tricycle layout, and the undercarriage uses dome-like roof, in the undercarriage
Section is connected with reinforcing steel wire；The undercarriage base plate is arranged on immediately below the fuselage.
Compared with prior art, the beneficial effects of the invention are as follows：
The present invention proposes a kind of quadrotor, and wherein sustainer uses 3W-275XiB2TS, the other three hair
Motivation uses motor, and the oil machine itself that sustainer is used first is lighter so that bare weight is relatively reduced, secondly according to sustainer
The diameter of the main oar chosen is smaller so that overall structure appearance and size is smaller, and bare weight is also relatively reduced, therefore, it is possible to realize length
Time hovering work, the maximum operating time is three hours, when accident occurs, for example, meets with earthquake, mud-rock flow etc. certainly
During right disaster, the quadrotor can be responded rapidly to as communication base station, it is ensured that the people get in touch with disaster area, it is ensured that each
Item disaster relief information can be passed in real time, and the quadrotor sets main oar, two flanks and an empennage, flank
Plane of rotation with the Plane of rotation of empennage less than main oar, control is got up more flexible and convenient.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to institute in embodiment
The accompanying drawing for needing to use is briefly described, it should be apparent that, drawings in the following description are only some implementations of the invention
Example, for those of ordinary skill in the art, without having to pay creative labor, can also be according to these accompanying drawings
Obtain other accompanying drawings.
Fig. 1 is a kind of structure chart of quadrotor embodiment of the invention.
Specific embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation is described, it is clear that described embodiment is only a part of embodiment of the invention, rather than whole embodiments.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of creative work is not made
Embodiment, belongs to the scope of protection of the invention.
It is below in conjunction with the accompanying drawings and specific real to enable the above objects, features and advantages of the present invention more obvious understandable
The present invention is further detailed explanation to apply mode.
Fig. 1 is a kind of structure chart of quadrotor embodiment of the invention.
Referring to Fig. 1, the quadrotor includes fuselage 1, main oar 2, the first flank 3, the second flank 4, empennage 5, main hair
Motivation 6, substrate 7, head rod 8, the second connecting rod 9, the 3rd connecting rod 10, the first motor 11, the first motor erecting bed 12,
Second motor 13, the second motor erecting bed 14, the 3rd motor 15, the 3rd motor erecting bed 16, undercarriage 17；
The surface of the fuselage 1 is installed by the substrate 7；The substrate 7 is sheet metal component, can reduce the sky of aircraft
Weight；The substrate 7 is connected by the head rod 8 with the first motor erecting bed 12, and the substrate 7 is by described the
Two connecting rods 9 are connected with the second motor erecting bed 12, and the substrate 7 is by the 3rd connecting rod 10 and the described 3rd electricity
Machine erecting bed 16 is connected；The sustainer 6 is arranged on the surface of the substrate 7, and the sustainer 6 is oil machine, is used for
Drive main oar 2；The main oar 2 is arranged on the surface of the sustainer 6, for controlling quadrotor in vertical direction
On speed and displacement；First motor 11 is arranged on the surface of the first motor erecting bed 12, described for driving
First flank 3；First flank 3 is arranged on the surface of first motor 11；Second motor 13 is arranged on described
The surface of the second motor erecting bed 14, for driving second flank 4；Second flank 4 is arranged on the described second electricity
The surface of machine 13；First flank 3 and second flank 4 are symmetricly set on the both sides of the fuselage 1, by changing
State the rotating speed of the first flank 3 and second flank 4 to obtain rolling control moment, the quadrotor can be adjusted
Roll attitude；3rd motor 15 is arranged on the 3rd motor erecting bed 16, for driving the empennage 5；The tail
The wing 5 is arranged on the afterbody of fuselage 1, and the empennage 5 is arranged on the 3rd motor 15, is obtained by changing the rotating speed of empennage 5
Must be gone off course control moment, can adjust the course attitude of the quadrotor；The undercarriage 17 is arranged on described rising and falling
In frame base plate (not shown), the undercarriage 17 uses tricycle layout, the undercarriage 17 to use dome-like roof, institute
The stage casing for stating undercarriage 17 is connected with reinforcing steel wire, the undercarriage 17 it is static, take off, navigate by water and descent in, will not
Make a difference normal applicable gross distortion；The undercarriage base plate is arranged on the underface of the fuselage 1, the undercarriage bottom
Plate is sheet metal component.
The bottom of the sustainer 6 is connected with sustainer mounting bracket, and the sustainer 6 is pacified with the sustainer
Damping device is provided between shelving, sustainer 6 is the engine of 3W-275XiB2TS models, sustainer 6
Power is 19.1kw, and weight is 7.04kg, and rotating speed is 1000~7000rpm, and oil mass is about 13kg~17kg, according to main
The model of engine 6, the 0.864 × 0.305m of size selection of the blade of the main oar 2 of quadrotor, i.e., main oar 2
Rotating diameter is 0.864m, and the pitch of main oar 2 is 0.305m, the slurry disk load of quadrotorFuel consumption is estimated for 5.7kg/h, main paddle point velocity interval is 160~
240m/s, the range of speeds is 3537~5308rpm, and the flight time is 2.3~3 hours.
The main oar 2, first flank 3, second flank 4 and the empennage 5 are three-bladed propeller；Described
The rotating diameter of one flank 3, second flank 4 and the empennage 5 is 0.376m, the main oar 2, first flank 3,
The rotating diameter of second flank 4 and the empennage 5 is relatively small so that the overall structure profile of the quadrotor
Size is smaller, and bare weight is also relatively reduced, and compact conformation, and aerodynamic drag is smaller, more economically.
The Plane of rotation of first flank 3 and second flank 4 less than the main oar 2 Plane of rotation and with it is described
The Plane of rotation of main oar 2 is parallel, and the Plane of rotation of the empennage 5 is vertical with the Plane of rotation of the main oar 2 so that four rotation
Rotor aircraft control gets up more flexible and convenient.
The volume of the fuselage 1 is 26L, and the fuselage 1 carries fuel tank, Aerial Electronic Equipment and task system, the fuel tank bag
Preceding fuel tank and rear fuel tank are included, the leading portion and back segment of the fuselage 1 is respectively placed in, the Aerial Electronic Equipment and the task system are located at
The stage casing of the fuselage 1, the Aerial Electronic Equipment is located at the bottom in the stage casing of the fuselage 1, and the task system is located at the machine
Separated with dividing plate in the middle of the top in the stage casing of body 1, the Aerial Electronic Equipment and the task system, prevent the quadrotor
Whole machine rock and oil consumption after the fuel oil that brings shake.
The fuel tank uses the first hatch door, first hatch door to be located at the one of close described first flank 3 of the fuselage 1
Side.
The Aerial Electronic Equipment and the task system share the second hatch door, and second hatch door is located at leaning on for the fuselage 1
The side of the nearly empennage 5.
First motor 11, second motor 13 and the 3rd motor 15 are equipped with independent current source.
Specific case used herein is set forth to principle of the invention and implementation method, and above example is said
It is bright to be only intended to help and understand the method for the present invention and its core concept；Simultaneously for those of ordinary skill in the art, foundation
Thought of the invention, will change in specific embodiments and applications.In sum, this specification content is not
It is interpreted as limitation of the present invention.
Claims (10)
1. a kind of quadrotor, it is characterised in that including：
Fuselage, main oar, the first flank, the second flank, empennage, sustainer, substrate, head rod, the second connecting rod, the 3rd
Connecting rod, the first motor, the first motor erecting bed, the second motor, the second motor erecting bed, the 3rd motor, the 3rd motor are installed
Platform；
The surface of the fuselage is installed by the substrate；The substrate is installed by the head rod with first motor
Platform is connected, and the substrate is connected by second connecting rod with the second motor erecting bed, and the substrate passes through described the
Three connecting rods are connected with the 3rd motor erecting bed；The sustainer is arranged on the surface of the substrate, the main hair
Motivation is oil machine, for driving main oar；The main oar is arranged on the surface of the sustainer, for controlling four rotor flyings
Device speed in vertical direction and displacement；First motor is arranged on the surface of the first motor erecting bed, is used for
Drive first flank；First flank is arranged on the surface of first motor；Second motor is arranged on institute
The surface of the second motor erecting bed is stated, for driving second flank；Second flank is arranged on second motor
Surface；First flank and second flank are symmetricly set on the fuselage both sides, for adjusting four rotor
The roll attitude of aircraft；3rd motor is arranged on the 3rd motor erecting bed, for driving the empennage；It is described
Empennage is arranged on afterbody, and the empennage is arranged on the 3rd motor, the boat for adjusting the quadrotor
To attitude.
2. a kind of quadrotor according to claim 1, it is characterised in that the bottom of the sustainer and main hair
Motivation mounting bracket is connected, and damping device is provided between the sustainer and the sustainer mounting bracket.
3. a kind of quadrotor according to claim 1, it is characterised in that the sustainer is 3W-
The engine of 275XiB2TS models.
4. a kind of quadrotor according to claim 1, it is characterised in that the main oar, first flank, institute
State the second flank and the empennage is three-bladed propeller；The rotating diameter of the main oar is 0.864m, first flank, institute
The rotating diameter for stating the second flank and the empennage is 0.376m.
5. a kind of quadrotor according to claim 1, it is characterised in that first flank and second side
The Plane of rotation of the wing is less than the Plane of rotation of the main oar and parallel with the Plane of rotation of the main oar；The rotary flat of the empennage
Face is vertical with the Plane of rotation of the main oar.
6. a kind of quadrotor according to claim 1, it is characterised in that the fuselage volume is 26L, the machine
Body carries fuel tank, Aerial Electronic Equipment and task system, and the fuel tank includes preceding fuel tank and rear fuel tank, before being respectively placed in the fuselage
Section and back segment, the Aerial Electronic Equipment and the task system are located at the stage casing of the fuselage, and the Aerial Electronic Equipment is located at the machine
The bottom in body stage casing, the task system is located at the top of the middle fuselage, in the Aerial Electronic Equipment and the task system
Between separated with dividing plate.
7. a kind of quadrotor according to claim 1, it is characterised in that the fuel tank uses the first hatch door, institute
The first hatch door is stated positioned at the side of close described first flank of the fuselage.
8. a kind of quadrotor according to claim 1, it is characterised in that the Aerial Electronic Equipment and the task system
The second hatch door, second hatch door is altogether used to be located at the side of the close described empennage of the fuselage.
9. a kind of quadrotor according to claim 1, it is characterised in that first motor, second electricity
Machine and the 3rd motor are equipped with independent current source.
10. a kind of quadrotor according to claim 1, it is characterised in that also include：Undercarriage and undercarriage bottom
Plate；The undercarriage is arranged on the undercarriage base plate, and the undercarriage uses tricycle layout, the undercarriage to use
Dome-like roof, the stage casing of the undercarriage is connected with reinforcing steel wire；The undercarriage base plate is arranged on immediately below the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611252846.XA CN106741896A (en) | 2016-12-30 | 2016-12-30 | A kind of quadrotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611252846.XA CN106741896A (en) | 2016-12-30 | 2016-12-30 | A kind of quadrotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106741896A true CN106741896A (en) | 2017-05-31 |
Family
ID=58927808
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611252846.XA Pending CN106741896A (en) | 2016-12-30 | 2016-12-30 | A kind of quadrotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106741896A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108750126A (en) * | 2018-07-26 | 2018-11-06 | 瀚伦贝尔通用航空器有限公司 | A kind of dynamic quadrotor of double hair oil |
| CN112455701A (en) * | 2020-11-26 | 2021-03-09 | 广东国士健科技发展有限公司 | Aircraft convenient to control flight gesture |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103921936A (en) * | 2014-02-12 | 2014-07-16 | 无锡汉和航空技术有限公司 | Oil and power mixed small unmanned helicopter and its power principle |
| CN104943857A (en) * | 2015-06-29 | 2015-09-30 | 哈尔滨盛世特种飞行器有限公司 | Petrol-electric hybrid five-rotor unmanned aerial vehicle |
| CN204979218U (en) * | 2015-07-18 | 2016-01-20 | 辽宁力德航空科技有限公司 | Many rotors of oil -electricity hybrid vehicle unmanned vehicles |
| CN105584630A (en) * | 2016-02-10 | 2016-05-18 | 刘海涛 | Multi-rotor type aircraft |
| CN105882954A (en) * | 2016-05-25 | 2016-08-24 | 沈阳航空航天大学 | Hybrid-power unmanned aerial vehicle with four auxiliary wings and control method thereof |
-
2016
- 2016-12-30 CN CN201611252846.XA patent/CN106741896A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103921936A (en) * | 2014-02-12 | 2014-07-16 | 无锡汉和航空技术有限公司 | Oil and power mixed small unmanned helicopter and its power principle |
| CN104943857A (en) * | 2015-06-29 | 2015-09-30 | 哈尔滨盛世特种飞行器有限公司 | Petrol-electric hybrid five-rotor unmanned aerial vehicle |
| CN204979218U (en) * | 2015-07-18 | 2016-01-20 | 辽宁力德航空科技有限公司 | Many rotors of oil -electricity hybrid vehicle unmanned vehicles |
| CN105584630A (en) * | 2016-02-10 | 2016-05-18 | 刘海涛 | Multi-rotor type aircraft |
| CN105882954A (en) * | 2016-05-25 | 2016-08-24 | 沈阳航空航天大学 | Hybrid-power unmanned aerial vehicle with four auxiliary wings and control method thereof |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108750126A (en) * | 2018-07-26 | 2018-11-06 | 瀚伦贝尔通用航空器有限公司 | A kind of dynamic quadrotor of double hair oil |
| CN112455701A (en) * | 2020-11-26 | 2021-03-09 | 广东国士健科技发展有限公司 | Aircraft convenient to control flight gesture |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170531 |
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