CN206446794U - A kind of hybrid power unmanned plane - Google Patents
A kind of hybrid power unmanned plane Download PDFInfo
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- CN206446794U CN206446794U CN201720090522.4U CN201720090522U CN206446794U CN 206446794 U CN206446794 U CN 206446794U CN 201720090522 U CN201720090522 U CN 201720090522U CN 206446794 U CN206446794 U CN 206446794U
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Abstract
The utility model belongs to unmanned air vehicle technique field, disclose a kind of hybrid power unmanned plane, including fuselage, hollow shaft on fuselage and the primary spindle for being set in hollow shaft and being coaxial therewith the heart, rotor is connected with the primary spindle, lower rotor is connected with the hollow shaft, the hollow shaft and primary spindle are rotated backward by the drive mechanism driving in fuselage simultaneously, some small rotors are arranged with the fuselage, the small rotor is driven by motor to be rotated, and the drive mechanism and motor are all connected to controlling organization.The utility model on fuselage by being arranged with some small rotors, produced between upper rotor and lower rotor torsional forces it is poor when, can be poor to offset the torsional forces that is produced between upper rotor and lower rotor by the rotation of small rotor, enable unmanned plane normal flight, it is to avoid unmanned plane is out of control.
Description
Technical field
The utility model is related to unmanned air vehicle technique field, more particularly to a kind of hybrid power unmanned plane.
Background technology
With the fast development of the development of unmanned air vehicle technique, especially gyroplane technology, its application surface is more and more wider, in the people
Indispensable importance is embodied with field and military domain.Current several unmanned gyroplanes include single rotor and (gone straight up to
Machine), coaxial anti-oar helicopter and many rotors, wherein " card -50 helicopters " of the coaxial anti-oar helicopter such as Russia, its work
Principle is that the axle of lower rotor is hollow shaft, and the axle of upper rotor is concentric to be passed through from hollow shaft, double-deck rotor diameter size phase
With and can be adjusted by blade pitch control mechanism to identical pitch, then by bevel gear drive above and below two driven gears,
Rotor is rotated with opposite rotation direction above and below drive, and the opposite other conditions identical rotor in two direction of rotation just can phase
Anti-twisted torque is mutually offset, thus does not need tail pipe and tail-rotor.This design improves unmanned plane power performance to a certain extent, letter
Changed afterbody design, but this kind design manipulation is complicated, and rotor keeps high consistency above and below its needs, i.e., above and below rotor
Size structure is identical, and pitch also needs identical, and so rotor can cancel out each other anti-twisted torque up and down, and then make coaxial
Anti- oar helicopter smoothly flies, when there is the difference of pitch, and rotor can not just cancel out each other anti-twisted torque up and down, causes altogether
The anti-oar helicopter of axle is out of control can not normal flight.
Utility model content
The purpose of this utility model is to provide a kind of hybrid power unmanned plane, existed with solving existing coaxial anti-oar helicopter
Rotor is not away from also resulting in the problem of anti-oar helicopter is out of control up and down.
For up to this purpose, the utility model uses following technical scheme：
A kind of hybrid power unmanned plane, including fuselage, hollow shaft on fuselage and be set in hollow shaft and
It is coaxial therewith on the primary spindle of the heart, the primary spindle being connected with rotor, the hollow shaft and is connected with lower rotor, it is described hollow
Axle and primary spindle are rotated backward by the drive mechanism driving in fuselage simultaneously, and some small rotations are arranged with the fuselage
The wing, the small rotor is driven by motor to be rotated, and the drive mechanism and motor are all connected to controlling organization.
Preferably, the upper rotor is away from fixation, the lower rotor is connected with blade pitch control mechanism.
Preferably, the upper rotor and lower rotor are respectively connected with blade pitch control mechanism.
Preferably, the diameter of the upper rotor is less than the diameter of lower rotor.
Preferably, the oil that the drive mechanism includes being connected to controlling organization moves engine, and by the dynamic hair of the oil
The driving bevel gear of motivation driving, the driving bevel gear, which is engaged with, to be respectively and fixedly connected with hollow shaft and primary spindle and setting up and down
Driven bevel pinion.
Preferably, being provided with power supply in the fuselage, the power supply is rechargable power supplies, and it is connected to described
Motor.
Preferably, if the fuselage is circumferentially provided with dry support arm, the motor is arranged on the support arm, and defeated
Go out the end connection small rotor.
Preferably, the small rotor is horizontally disposed or with respect to the horizontal plane in angle setting.
Preferably, the controlling organization includes remote manipulator and is communicated to connect with remote manipulator and be located at fuselage
Internal circuit board, the circuit board is connected to the drive mechanism, blade pitch control mechanism and motor.
Preferably, being arranged with pitch in the hollow shaft.
The utility model produces moment of torsion by being arranged with some small rotors on fuselage between upper rotor and lower rotor
, can be poor to offset the torsional forces that is produced between upper rotor and lower rotor so that unmanned plane by the rotation of small rotor when power is poor
Being capable of normal flight, it is to avoid unmanned plane is out of control.
Brief description of the drawings
Fig. 1 is the dimensional structure diagram of the utility model hybrid power unmanned plane；
Fig. 2 is the side view of the utility model hybrid power unmanned plane (hiding fuselage and small rotor)；
Fig. 3 is the decomposing schematic representation of the utility model hybrid power unmanned plane (hiding fuselage).
In figure：
1st, fuselage；2nd, hollow shaft；3rd, primary spindle；4th, upper rotor；5th, lower rotor；6th, drive mechanism；7th, small rotor；8th, it is electric
Machine；9th, power supply；10th, pitch；11st, support arm；61st, the dynamic engine of oil；62nd, driving bevel gear；63rd, driven bevel pinion；
64th, belt.
Embodiment
Further illustrate the technical solution of the utility model below in conjunction with the accompanying drawings and by embodiment.
Embodiment one：
The present embodiment provides a kind of hybrid power unmanned plane, as Figure 1-3, and the hybrid power unmanned plane includes fuselage 1,
The hollow shaft 2 for being equipped with primary spindle 3 in the middle position of fuselage 1 and being set in outside primary spindle 3, the hollow shaft 2 and small master
Axle 3 is concentric to be set.Above-mentioned primary spindle 3 and hollow shaft 2 drive synchronous axial system by the drive mechanism 6 inside fuselage 1 simultaneously,
And primary spindle 3 is opposite with the rotation direction of hollow shaft 2.Rotor 4 is installed on primary spindle 3, and driven by the primary spindle 3
Rotor 4 rotates, and lower rotor 5 is provided with hollow shaft 2, and drive lower rotor 5 to rotate by the hollow shaft 2.Pass through the upper He of rotor 4
The reverse rotation of lower rotor 5, realizes the flight of the unmanned plane.
Fig. 2 is can refer to, above-mentioned drive mechanism 6 includes the dynamic engine 61 of oil, and is fixed in the dynamic output end of engine 61 of oil
Driving bevel gear 62, the driving bevel gear 62, which is engaged with, to be respectively and fixedly connected with hollow shaft 2 and primary spindle 3 and setting up and down driven
Bevel gear 63.The above-mentioned dynamic engine 61 of oil is connected with controlling organization (not shown), starts by the way that controlling organization control oil is dynamic
The operation of machine 61, then drives driving bevel gear 62 to rotate, and then driven and it by driving bevel gear 62 by the dynamic engine 61 of oil
Two driven bevel pinions 63 synchronous axial system in a reverse direction of engagement, also allows for primary spindle 3 and hollow shaft 2 and drives respectively
Rotor 4 and lower rotor 5 synchronous axial system in a reverse direction, realize the flight of unmanned plane.It should be noted that in the present embodiment,
The above-mentioned dynamic engine 61 of oil can also drive driving bevel gear 62 to rotate (shown in Fig. 3) by belt 64.
In the present embodiment, the diameter of above-mentioned upper rotor 4 is less than the diameter of lower rotor 5, so that the diameter of lower rotor 5 is big
In the downwash flow area of upper rotor 4, it is to avoid air-flow phase caused by the diameter of rotor 5 is identical above and below existing coaxial anti-oar class unmanned plane
Mutually influence, improves the power performance of unmanned plane.
In the present embodiment, above-mentioned upper rotor 4 is fixedly mounted on primary spindle 3, that is, the pitch fixation of upper rotor 4 can not
Regulation, lower rotor 5 is connected with blade pitch control mechanism (not shown), and the blade pitch control mechanism is used for the oar for adjusting lower rotor 5
Away from.Specifically, the pitch of the present embodiment refers to blade angle, that is, rotor blade and Plane of rotation inclination angle, in certain limit
Interior, blade angle is bigger, and the windward side of blade is bigger, and the lift of generation is bigger, and torsional forces is also bigger, passes through the change of the blade angle
Change, by increasing capacitance it is possible to increase or reduce thrust or pulling force that lower rotor 5 is produced, so as to realize the control in unmanned plane course.Above-mentioned pitch is adjusted
Section mechanism is prior art, therefore its structure is not repeated herein, as long as the structure of the lower pitch of rotor 5 regulation can be realized,
It may be considered blade pitch control mechanism.
In the present embodiment, because the pitch of upper rotor 4 is fixed, the lower pitch of rotor 5 is adjustable, and the diameter of upper rotor 4 is small
In the diameter of lower rotor 5, it is different with the torsional forces that lower rotor 5 is produced now to inevitably result in rotor 4, there is torsional forces difference
Situation, now, in order to which offset torque power is poor, preferably realizes the balance of unmanned plane, the present embodiment is symmetrically set in the circumference of fuselage 1
If there is dry support arm 11, motor 8 is provided with each support arm 11, each motor 8 is all connected to controlling organization, and each
The output end of motor 8 is respectively connected with small rotor 7, and drives the small rotor 7 to rotate.By setting small rotor 7, when there is torsional forces
When poor, the torsional forces that upper rotor 4 and the generation of lower rotor 5 can be balanced by the rotation of small rotor 7 is poor, and then realizes nothing
Man-machine smooth flight.
In the present embodiment, above-mentioned small rotor 7 is preferably provided with 6, and above-mentioned 6 small rotor 7 rotates simultaneously, passes through control
The speed discrepancy of each small rotor 7 of system, both provided lift for unmanned plane, assists lower rotor 5 to control direction, can balance again
Torsional forces between rotor 4 and lower rotor 5 is poor.
According to statistics, unmanned plane cause of accident is that the dynamic failure of engine 61 of oil makes rotor run out of steam mostly, it is uncontrolled from
And cause air crash accident.And the setting of the above-mentioned small rotor 7 of the present embodiment, cause the He of rotor 4 in the dynamic failure of engine 61 of oil
When lower rotor 5 runs out of steam, small rotor 7 can be driven to rotate by motor 8, aid in unmanned plane safe falling, it is to avoid existing
When rotor 4 and lower rotor 5 run out of steam on unmanned plane, unmanned plane is caused to crash or injure surface structures and crowd because out of control.
In the present embodiment, above-mentioned small rotor 7 is horizontally disposed or with respect to the horizontal plane in angle setting, specifically can be according to need
Set, preferably to realize the lifting of unmanned plane performance.
Fig. 2 is can refer to, power supply 9 is provided with fuselage 1, above-mentioned power supply 9 is connected to motor 8, for motor 8
It is powered.In the present embodiment, above-mentioned power supply 9 is rechargable power supplies, and wherein charging modes can be entered when unused
Row charging or the setting generator in fuselage 1, the generator can be connected to the dynamic engine 61 of oil, for being moved
Electric energy can be converted into, to be charged to power supply 9.
Above-mentioned controlling organization includes remote manipulator (not shown) and communicates to connect and be located at remote manipulator
Circuit board (not shown) inside fuselage 1, the circuit board be connected to above-mentioned drive mechanism 6, blade pitch control mechanism with
And motor 8.By remote manipulator come remotely pilotless machine two sets of self-driving systems (rotation of i.e. upper rotor 4 and lower rotor 5, with
And the rotation of small rotor 7), enable to two sets of self-driving systems separate, again can be with mutually coordinated auxiliary in work.
In the present embodiment, pitch 10 is arranged with hollow shaft 2, the pitch 10 can coordinate above-mentioned small rotor 7, come more
The heading of the good control hybrid power unmanned plane, because pitch 10 is existing structure, will not be repeated here.
The hybrid power unmanned plane of the present embodiment, by being arranged with some small rotors 7 on the fuselage 1, in the upper He of rotor 4
Produced between lower rotor 5 torsional forces it is poor when, can be produced by the rotation of small rotor 7 to offset between upper rotor 4 and lower rotor 5
Raw torsional forces is poor so that unmanned plane normal flight.
By only setting blade pitch control mechanism at lower rotor 5, and the upper pitch of rotor 4 is fixed, needed in unmanned plane during flying
, can be by the cooperation of small rotor 7 when adjusting the pitch of lower rotor 5, balance paddle is poor away from the torsional forces that regulation is brought, to cause nothing
Man-machine normal flight, and the present embodiment only needs to control the pitch of lower rotor 5, is not necessary to consider the oar of the upper rotor 4 of control
Away from simplifying the operation difficulty of the coaxial anti-oar design of tradition, user's manipulation gets up to be more prone to.
Embodiment two：
The present embodiment is differed only in embodiment one：
In the present embodiment, the pitch of above-mentioned upper rotor 4 is equally adjustable, i.e., it is respectively connected with pitch tune as lower rotor 5
Mechanism is saved, by the blade pitch control mechanism, the pitch of rotor 4 can be adjusted, in order to improve the performance of unmanned plane.Need to refer to
Go out, when upper rotor 4 and lower rotor 5 are provided with blade pitch control mechanism, also occur between rotor 4 and lower rotor 5
The situation of torsional forces difference is produced, now the small rotor 7 in the present embodiment can still offset and be produced between rotor 4 and lower rotor 5
Raw torsional forces is poor so that unmanned plane normal flight.
Remaining structure of the hybrid power unmanned plane of the present embodiment and all same of embodiment one, therefore will not be repeated here.
Obviously, above-described embodiment of the present utility model is used for the purpose of clearly illustrating the utility model example, and
It is not the restriction to embodiment of the present utility model.For those of ordinary skill in the field, in described above
On the basis of can also make other changes in different forms.There is no need and unable to give all embodiments
It is exhaustive.All any modifications, equivalent substitutions and improvements made within spirit of the present utility model and principle etc., should be included in
Within the utility model scope of the claims.
Claims (10)
1. a kind of hybrid power unmanned plane, it is characterised in that including fuselage (1), hollow shaft (2) on fuselage (1) with
And be set in hollow shaft (2) and be coaxial therewith to be connected with rotor (4), institute on the primary spindle (3) of the heart, the primary spindle (3)
State and lower rotor (5) is connected with hollow shaft (2), the hollow shaft (2) and primary spindle (3) are while by the drive in fuselage (1)
Motivation structure (6) driving is rotated backward, and some small rotors (7) is arranged with the fuselage (1), the small rotor (7) passes through electricity
Machine (8) drives rotation, and the drive mechanism (6) and motor (8) are all connected to controlling organization.
2. hybrid power unmanned plane according to claim 1, it is characterised in that upper rotor (4) pitch is fixed, described
Lower rotor (5) is connected with blade pitch control mechanism.
3. hybrid power unmanned plane according to claim 1, it is characterised in that the upper rotor (4) and lower rotor (5) are
It is connected with blade pitch control mechanism.
4. hybrid power unmanned plane according to claim 1, it is characterised in that under the diameter of the upper rotor (4) is less than
The diameter of rotor (5).
5. hybrid power unmanned plane according to claim 1, it is characterised in that the drive mechanism (6) includes being connected to
The oil of controlling organization moves engine (61), and by the driving bevel gear (62) of dynamic engine (61) driving of the oil, the master
Dynamic bevel gear (62), which is engaged with, to be respectively and fixedly connected with hollow shaft (2) and primary spindle (3) and driven bevel pinion (63) setting up and down.
6. hybrid power unmanned plane according to claim 1, it is characterised in that power supply is provided with the fuselage (1)
(9), the power supply (9) is rechargable power supplies, and it is connected to the motor (8).
7. hybrid power unmanned plane according to claim 1, it is characterised in that the fuselage (1) is circumferentially provided with some
Support arm (11), the motor (8) is arranged on the support arm (11), and output end connects the small rotor (7).
8. hybrid power unmanned plane according to claim 1, it is characterised in that the small rotor (7) it is horizontally disposed or
With respect to the horizontal plane set in angle.
9. the hybrid power unmanned plane according to Claims 2 or 3, it is characterised in that the controlling organization includes long-range distant
Control device and communicated to connect with remote manipulator and be located at the internal circuit board of fuselage (1), the circuit board is connected to institute
State drive mechanism (6), blade pitch control mechanism and motor (8).
10. hybrid power unmanned plane according to claim 1, it is characterised in that be arranged with inclination on the hollow shaft (2)
Disk (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720090522.4U CN206446794U (en) | 2017-01-24 | 2017-01-24 | A kind of hybrid power unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720090522.4U CN206446794U (en) | 2017-01-24 | 2017-01-24 | A kind of hybrid power unmanned plane |
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| Publication Number | Publication Date |
|---|---|
| CN206446794U true CN206446794U (en) | 2017-08-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201720090522.4U Active CN206446794U (en) | 2017-01-24 | 2017-01-24 | A kind of hybrid power unmanned plane |
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| CN (1) | CN206446794U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741903A (en) * | 2017-01-24 | 2017-05-31 | 天津曙光天成科技有限公司 | A kind of hybrid power unmanned plane |
| JPWO2018139661A1 (en) * | 2017-01-30 | 2019-11-14 | 日本電産株式会社 | Unmanned aerial vehicle |
-
2017
- 2017-01-24 CN CN201720090522.4U patent/CN206446794U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741903A (en) * | 2017-01-24 | 2017-05-31 | 天津曙光天成科技有限公司 | A kind of hybrid power unmanned plane |
| CN106741903B (en) * | 2017-01-24 | 2023-12-15 | 天津凤凰智能科技有限公司 | Hybrid unmanned aerial vehicle |
| JPWO2018139661A1 (en) * | 2017-01-30 | 2019-11-14 | 日本電産株式会社 | Unmanned aerial vehicle |
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Effective date of registration: 20221017 Address after: 300457 No. 105, Building 9, Zone B3 (formerly Zone 2, Ronghui Business Park), Binhai Zhongguancun Science and Technology Park, Tianjin Binhai New Area Technology Development Zone Patentee after: Tianjin Phoenix Intelligent Technology Co.,Ltd. Address before: Floor 1, block B, No.3, Tengfei Road, Junliang City, Dongli District, Tianjin Patentee before: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. |