CN206218219U - A kind of MAV of column coaxial double-oar layout - Google Patents
A kind of MAV of column coaxial double-oar layout Download PDFInfo
- Publication number
- CN206218219U CN206218219U CN201621244848.XU CN201621244848U CN206218219U CN 206218219 U CN206218219 U CN 206218219U CN 201621244848 U CN201621244848 U CN 201621244848U CN 206218219 U CN206218219 U CN 206218219U
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- China
- Prior art keywords
- rotor
- column
- oar
- coaxial
- fuselage
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Abstract
The utility model discloses a kind of MAV of column coaxial double-oar layout, including：Load-carrying construction, load-carrying construction includes column fuselage, and flight controller and battery are provided with column fuselage；One end of column fuselage is disposed with mission payload, the other end is provided with coaxial reverse motor by cardan mounting, it is provided with that rotor is foldable to be close to double oar rotor heads of column fuselage, double oar rotor heads, coaxial reverse motor and the coaxial setting of column fuselage on coaxial reverse motor.The utility model controls UAV Attitude by the rotor face of the double oar rotor heads of cardan mounting tiltable；Double oar rotor heads can be close to fuselage folding, with portability and ease for use higher；Double oar rotor heads can be stored in transmitting tube after folding, it is easy to deployment and release.
Description
Technical field
The utility model is related to unmanned air vehicle technique field, and in particular to it is micro-unmanned that a kind of column coaxial double-oar is laid out
Machine.
Background technology
Rotor wing unmanned aerial vehicle is a class multipurpose vertically taking off and landing flyer.Compared with fixed-wing unmanned plane, rotor wing unmanned aerial vehicle can
It is less demanding to landing site with VTOL, it is easy to use efficient.Rotor wing unmanned aerial vehicle is widely used, and can perform aviation and take the photograph
The tasks such as shadow, medical aid, meteorological detection, aerial inspection.
Conventional helicopters layout is configured with a secondary main rotor and a secondary tail-rotor.The tail-rotor of lateral arrangement is anti-twisted for offsetting
Square, and for controlling to go off course.Conventional helicopters layout employs a set of extremely complex pitch and linkage control rotor
Face inclines, and using freely twists or it is semi-free twist rotor wave in preceding the flying eliminate before winged middle generation rolling moment.It is traditional straight
The machine of liter layout is because the mechanical mechanism of complexity, maintenance time more long and high use cost, are only suitable for big-and-middle-sized rotor
Unmanned plane.
In recent years, gradually come into vogue with many rotor class rotor wing unmanned aerial vehicles that four rotors are representative.Compared to conventional helicopters
Layout, many rotors offset reaction torque using the rotor that paired opposite direction rotates, and lift is not produced without extra driving
Tail-rotor, improves the effective utilization of energy.Many rotors abandon the mechanical mechanism of complexity and freely twist rotor, using regulation rigidity rotation
The inclination in the method control rotor face of wing rotating speed, so as to control the attitude of aircraft.In preceding flying, the rotation of paired opposite direction rotation
The wing also counteracts rolling moment.Easy to maintenance due to simple structure, cost of use is cheap, many rotor-hub configurations be more suitable for it is small-sized just
The formula unmanned plane of taking is used.
However, in long-term use, multi-rotor unmanned aerial vehicle also exposes its intrinsic problem.Driven using multiple motors
Dynamic rotor causes that electric energy is converted into the efficiency reduction of mechanical energy, have impact on the endurance of multi-rotor unmanned aerial vehicle.Meanwhile, by turning
The strategy that speed control changes attitude needs rotor ceaselessly to do acceleration and deceleration motion so that regulation attitude needs to pay substantial amounts of energy
Amount, it is particularly especially pronounced when rotor diameter and larger rotary inertia.Excessive rotor quantity also leverages many rotors
The portability of unmanned plane.
Utility model content
Weak point present in regarding to the issue above, the utility model provides a kind of the miniature of column coaxial double-oar layout
Unmanned plane.
The utility model discloses a kind of MAV of column coaxial double-oar layout, including：Load-carrying construction, it is described to hold
Power structure includes column fuselage, and flight controller and battery are provided with the column fuselage；
One end of the column fuselage is disposed with mission payload, and the other end is provided with coaxial reverse electricity by cardan mounting
Machine, be provided with the coaxial reverse motor it is foldable be close to double oar rotor heads of column fuselage, it is the described pair of oar rotor head, coaxial
Reverse motor and the coaxial setting of column fuselage.
Used as further improvement of the utility model, the load-carrying construction also includes center girder, and the center girder sets
Put in the column fuselage.
Used as further improvement of the utility model, the flight controller, battery and mission payload are attached to the post
On shape fuselage and/or center girder.
Used as further improvement of the utility model, the coaxial reverse motor has two coaxially arranged rotors, point
Indescribably supply positive and negative two reverse driving revolving forces；The coaxial reverse motor is connected by rotating shaft with described pair of oar rotor head.
Used as further improvement of the utility model, described pair of oar rotor head includes propeller hub and rotor, the rotor and institute
Propeller hub is stated to be connected by limit hinge；
When rotor is folded, the rotor is locked in the position for being close to column fuselage；
Launch when rotor and when being rotated around propeller hub, the rotor is locked in perpendicular to the position of column fuselage, and with it is described
Propeller hub is rigidly connected.
Used as further improvement of the utility model, the mission payload includes photoelectric nacelle, first-aid medicine bag and meets an urgent need
One kind in communication apparatus.
Compared with prior art, the beneficial effects of the utility model are：
It is double by cardan mounting tiltable the utility model discloses a kind of MAV of column coaxial double-oar layout
The rotor face of oar rotor head, controls UAV Attitude；Double oar rotor heads can be close to fuselage folding, with portability higher and
Ease for use；Double oar rotor heads can be stored in transmitting tube after folding, it is easy to deployment and release；
The utility model drives the rigid hingeless rotor for reversely turning (to launch when rotor and around propeller hub by coaxial reverse motor
During rotation, rotor is rigidly connected with propeller hub) reaction torque is offset, flight efficiency is improve, improve the endurance of unmanned plane.
Brief description of the drawings
Fig. 1 is the structure chart of the MAV of column coaxial double-oar layout disclosed in a kind of embodiment of the utility model；
Fig. 2 is the sectional view of A-A in Fig. 1；
Fig. 3 is the structure connection between coaxial reverse motor and column fuselage disclosed in a kind of embodiment of the utility model
Figure；
Fig. 4 is the deployed condition of the MAV of column coaxial double-oar layout disclosed in a kind of embodiment of the utility model
Figure；
Fig. 5 is the folded state of the MAV of column coaxial double-oar layout disclosed in a kind of embodiment of the utility model
Figure.
In figure：
1st, coaxial reverse motor；2nd, double oar rotor heads；21st, rotor；22nd, propeller hub；23rd, limit hinge；3rd, cardan mounting；4、
Load-carrying construction；41st, column fuselage；42nd, center girder；5th, flight controller；6th, battery；7th, mission payload.
Specific embodiment
It is new below in conjunction with this practicality to make the purpose, technical scheme and advantage of the utility model embodiment clearer
Accompanying drawing in type embodiment, is clearly and completely described, it is clear that retouched to the technical scheme in the utility model embodiment
The embodiment stated is a part of embodiment of the present utility model, rather than whole embodiments.Based on the reality in the utility model
Apply example, the every other embodiment that those of ordinary skill in the art are obtained on the premise of creative work is not made, all
Belong to the scope of the utility model protection.
The utility model is described in further detail below in conjunction with the accompanying drawings：
As shown in Figure 1-2, the utility model provides a kind of MAV of column coaxial double-oar layout, including：It is coaxial
Reverse motor 1, double oar rotor heads 2, cardan mounting 3, load-carrying construction 4, flight controller 5, battery 6 and mission payload 7；Wherein：
Load-carrying construction 4 makes the MAV that column coaxial double-oar is laid out turn into one has the structure for undertaking load, holds
Power structure 4 includes column fuselage 41 and the center girder 42 that is arranged in column fuselage 41, center girder 42 preferably with column machine
The axis of body 41 coincides setting.
Flight controller 5 and battery 6 are provided with column fuselage 41, flight controller 5 and battery 6 are attached to load-carrying construction
On 4 (column fuselage 41 and/or center girders 42)；Wherein, flight controller 5 is the MAV of column coaxial double-oar layout
Gesture stability and flight course planning are provided, autonomous flight ability is made it have；Battery 6 is the micro-unmanned of column coaxial double-oar layout
Machine provides electric energy.
There is mission payload 7 in one end arrangement (carry) of column fuselage 41, mission payload 7 is attached to the (column of load-carrying construction 4
Fuselage 41 and/or center girder 42) on；The need for task, it is photoelectric nacelle, first-aid medicine that mission payload 7 can change the outfit
The load such as bag, emergency communication equipment.
Coaxial reverse motor 1 is provided with by cardan mounting 3 in the other end of column fuselage 41, as shown in Figure 3；It is coaxial anti-
Foldable it is close to double oar rotor heads 2 of column fuselage, double oar rotor heads 2, coaxial reverse motor 1 and post to being provided with motor 1
The coaxial setting of shape fuselage 41.Wherein, coaxial reverse motor 1 drives the power of double oar rotor heads 2 rotation for the utility model is provided；
Coaxial reverse motor 1 has two coaxially arranged rotors, and the rotary driving force of positive and negative both direction is provided respectively；It is coaxial reverse
Motor 1 is connected by rotating shaft with double oar rotor heads 2, drives the rotor opposite direction rotation of double oar rotor heads.
Cardan mounting 3 is the bindiny mechanism between coaxial reverse motor 1 and load-carrying construction 4, and cardan mounting 3 is in flight control
Under the control of device 5 the rotor face of double oar rotor heads 2 can incline, it is angled with fuselage axis；The utility model and biography
System helicopter layout is compared, and with simplified mechanical structure and cheap cost of use, compared with many rotor-hub configurations, does not use electricity
Machine speed governing, improves capacity usage ratio, and cardan mounting 3 has the premium properties such as simple structure, maintenance are simple, consumed energy is few.
Double oar rotor heads 2 include two propeller hubs 22 setting up and down and multiple rotors 21, and the number that rotor is set can basis
Actual demand is configured；Rotor 21 is connected with propeller hub 22 by limit hinge 23；When rotor 21 is folded, rotor 21 is locked in
It is close to the position of column fuselage 41, as shown in Figure 5；When rotor 21 launches and is rotated around propeller hub 22, rotor 21 is locked in vertically
In the position of column fuselage 41, and it is rigidly connected with propeller hub 22, with rigidity without the high-effect characteristic for twisting rotor；As shown in Figure 4.
The technical performance of the MAV of column coaxial double-oar layout is disclosed in the utility model：
Bare weight：800g；
Maximum take-off weight：2000g；
Payload capacity：500g；
Rotor diameter：432mm；
Fuselage diameter：92mm；
Cruising time：45 minutes (load-carrying 500g is equipped with 1 group of 4s lithium battery), 1 hour 10 points of (2 groups of 4s of load-carrying 500g outfits
Lithium battery)；
Max level speed：20m/s：Maximum ceiling：1000m；
Remote control distance：1.5Km (does not increase journey), 5Km (increasing journey)；
Power：Brshless DC motor (peak power output 1.5kw)；
Feature：Autonomous landing, autonomous flight is equipped with modularization multitask gondola, endurance long, overall life cycle cost
It is low.Rotor is close to fuselage after folding, with stronger portability；Can be stored in transmitting tube, it is easy to deployment and release.
Advantage of the present utility model is：The MAV of column coaxial double-oar layout is double by cardan mounting tiltable
The rotor face of oar rotor head, controls UAV Attitude；Double oar rotor heads can be close to fuselage folding, with portability higher and
Ease for use；Double oar rotor heads can be stored in transmitting tube after folding, it is easy to deployment and release；Driven by coaxial reverse motor
The rigid hingeless rotor (when rotor launches and rotated around propeller hub, rotor is rigidly connected with propeller hub) for reversely turning offsets reaction torque,
Flight efficiency is improve, the endurance of unmanned plane is improve.
Preferred embodiment of the present utility model is these are only, the utility model is not limited to, for this area
Technical staff for, the utility model can have various modifications and variations.It is all it is of the present utility model spirit and principle within,
Any modification, equivalent substitution and improvements made etc., should be included within protection domain of the present utility model.
Claims (6)
1. the MAV that a kind of column coaxial double-oar is laid out, it is characterised in that including：Load-carrying construction (4), the load knot
Structure (4) includes column fuselage (41), and flight controller (5) and battery (6) are provided with the column fuselage (41)；
One end of the column fuselage (41) is disposed with mission payload (7), and the other end is provided with coaxial anti-by cardan mounting (3)
To motor (1), it is provided with that rotor is foldable to be close to double oar rotor heads (2) of column fuselage, institute on the coaxial reverse motor (1)
State double oar rotor head (2), coaxial reverse motor (1) and column fuselage (41) coaxial settings.
2. the MAV that column coaxial double-oar as claimed in claim 1 is laid out, it is characterised in that the load-carrying construction
(4) center girder (42) is also included, the center girder (42) is arranged in the column fuselage (41).
3. the MAV that column coaxial double-oar as claimed in claim 2 is laid out, it is characterised in that the flight controller
(5), battery (6) and mission payload (7) are attached on the column fuselage (41) and/or center girder (42).
4. the MAV that column coaxial double-oar as claimed in claim 1 is laid out, it is characterised in that the coaxial reverse electricity
Machine (1) provides positive and negative two reverse driving revolving forces respectively with two coaxially arranged rotors；The coaxial reverse motor
(1) it is connected with described pair of oar rotor head (2) by rotating shaft.
5. the MAV that column coaxial double-oar as claimed in claim 1 is laid out, it is characterised in that described pair of oar rotor head
(2) including propeller hub (22) and rotor (21), the rotor (21) is connected with the propeller hub (22) by limit hinge (23)；
When rotor (21) is folded, the rotor (21) is locked in the position for being close to column fuselage (41)；
When rotor (21) launches and rotated around propeller hub (22), the rotor (21) is locked in the position perpendicular to column fuselage (41)
Put, and be rigidly connected with the propeller hub (22).
6. the MAV that column coaxial double-oar as claimed in claim 1 is laid out, it is characterised in that the mission payload
(7) including the one kind in photoelectric nacelle, first-aid medicine bag and emergency communication equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621244848.XU CN206218219U (en) | 2016-11-21 | 2016-11-21 | A kind of MAV of column coaxial double-oar layout |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621244848.XU CN206218219U (en) | 2016-11-21 | 2016-11-21 | A kind of MAV of column coaxial double-oar layout |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206218219U true CN206218219U (en) | 2017-06-06 |
Family
ID=58790070
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621244848.XU Withdrawn - After Issue CN206218219U (en) | 2016-11-21 | 2016-11-21 | A kind of MAV of column coaxial double-oar layout |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206218219U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347651A (en) * | 2016-11-21 | 2017-01-25 | 北京瀚科瑞杰科技发展有限公司 | Columnar and coaxial double-propeller miniature unmanned aerial vehicle |
| CN111003170A (en) * | 2019-12-24 | 2020-04-14 | 湖南韬讯航空科技有限公司 | Self-adaptive unfolding coaxial rotor system |
| CN111169630A (en) * | 2020-02-20 | 2020-05-19 | 山东蜂巢航空科技有限公司 | Vector coaxial double-propeller unmanned aerial vehicle |
-
2016
- 2016-11-21 CN CN201621244848.XU patent/CN206218219U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347651A (en) * | 2016-11-21 | 2017-01-25 | 北京瀚科瑞杰科技发展有限公司 | Columnar and coaxial double-propeller miniature unmanned aerial vehicle |
| CN106347651B (en) * | 2016-11-21 | 2018-07-13 | 北京瀚科瑞杰科技发展有限公司 | A kind of miniature drone of column coaxial double-oar layout |
| CN111003170A (en) * | 2019-12-24 | 2020-04-14 | 湖南韬讯航空科技有限公司 | Self-adaptive unfolding coaxial rotor system |
| CN111003170B (en) * | 2019-12-24 | 2021-09-28 | 湖南韬讯航空科技有限公司 | Self-adaptive unfolding coaxial rotor system |
| CN111169630A (en) * | 2020-02-20 | 2020-05-19 | 山东蜂巢航空科技有限公司 | Vector coaxial double-propeller unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170606 Effective date of abandoning: 20180713 |