CN106976552A - Tilting rotor wing unmanned aerial vehicle - Google Patents
Tilting rotor wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN106976552A CN106976552A CN201710160878.5A CN201710160878A CN106976552A CN 106976552 A CN106976552 A CN 106976552A CN 201710160878 A CN201710160878 A CN 201710160878A CN 106976552 A CN106976552 A CN 106976552A
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- rotor
- aerial vehicle
- driving shaft
- unmanned aerial
- universal driving
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- 230000009467 reduction Effects 0.000 claims description 46
- 230000005540 biological transmission Effects 0.000 claims description 25
- 239000000446 fuel Substances 0.000 claims description 5
- 238000006073 displacement reaction Methods 0.000 claims description 3
- 238000011217 control strategy Methods 0.000 abstract description 4
- 230000007246 mechanism Effects 0.000 description 9
- 230000008901 benefit Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 208000032370 Secondary transmission Diseases 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000010006 flight Effects 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
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Gear Transmission (AREA)
Abstract
This disclosure relates to a kind of tilting rotor wing unmanned aerial vehicle, including fuselage (100), wing (200), it is arranged on multiple rotors (300) on the wing with can verting, and the drive device (400) of the driving rotor (300), linkage unit is connected between the rotor (300), can rotate simultaneously.Due to driving the drive device of rotor wing rotation to only have one, and it can be linked between rotor so that drive device can control multiple rotors simultaneously, simplify control strategy.Further, since the quantity of drive device is one, the weight of the body of unmanned plane in itself can be mitigated, so as to improve the ability that it loads other equipment.
Description
Technical field
This disclosure relates to unmanned air vehicle technique field, in particular it relates to a kind of tilting rotor wing unmanned aerial vehicle.
Background technology
Tilting rotor wing unmanned aerial vehicle be one kind can as helicopter VTOL, hovering, again can be as fixed wing aircraft
The same winged unique aircraft preceding at a high speed, combines the advantage of helicopter and fixed rotor and propeller aircraft.Operator can pass through
Control lift of each rotor etc. to realize the various state of flights of tilting rotor wing unmanned aerial vehicle, each rotor is according to winged control signal
Control in terms of lift, it is necessary to make quick response, and in the related art, tilting rotor structure is generally that each motor drives respectively
Rotor, and by the steering wheel that verts, realize verting for rotor.This structure is in terms of load-carrying, voyage, endurance, it is difficult to meet nothing
Man-machine some use requirements.
The content of the invention
The purpose of the disclosure is to provide a kind of tilting rotor wing unmanned aerial vehicle, complicated to solve unmanned aerial vehicle (UAV) control strategy, loads energy
The problems such as power is poor.
To achieve these goals, the disclosure provides a kind of tilting rotor wing unmanned aerial vehicle, including fuselage, wing, can vert ground
Multiple rotors on the wing, and the driving rotor drive device, be connected with linkage between the rotor
Component, can rotate simultaneously.
Alternatively, the linkage unit includes the rotatable universal driving shaft for extending transversely through the fuselage and the wing, with
And the gearbox installed in the universal driving shaft two ends, the rotor is connected on the gearbox, the drive device with it is described
Universal driving shaft drive connection.
Alternatively, the gearbox includes the first bevel gear being set on the universal driving shaft, and bores tooth with described first
The second bevel gear of engaged transmission is taken turns, the second bevel gear is coaxial with the rotor with rotation simultaneously.
Alternatively, it is connected with reduction box between the drive device and the universal driving shaft.
Alternatively, the reduction box includes being set in third hand tap gear on the universal driving shaft, and with the triconodont
The 4th bevel gear of engaged transmission is taken turns, the 4th bevel gear is connected with the drive shaft of the drive device.
Alternatively, the unmanned plane is tandem wing unmanned plane, and the universal driving shaft includes preceding universal driving shaft and rear universal driving shaft, described
The rotor that reduction box is included on front reduction gear case and rear reduction box, the front wing of the tandem wing unmanned plane is joined by the preceding universal driving shaft
Dynamic, the rotor on rear wing is linked by the rear universal driving shaft, and the front reduction gear case is connected with the preceding universal driving shaft, the rear deceleration
Case is connected with the rear universal driving shaft, and the front reduction gear case and the rear reduction box are linked by the power transmission shaft of front and rear extension.
Alternatively, the drive device is arranged on the rear end of the fuselage, and the rear reduction box is additionally provided with and described
Third hand tap meshed transmission gear and positioned at the 4th bevel gear offside the 5th bevel gear, one end of the power transmission shaft with it is described
5th bevel gear is connected, and the other end is connected with the 4th bevel gear on the front reduction gear case.
Alternatively, the steering wheel that verts is fixed with the wing, the gearbox includes shell, the servo driving institute of verting
Shell is stated so that the rotor verts, it is preferable that the first travelling gear is provided with the output shaft of the steering wheel that verts, it is described outer
The second travelling gear, first travelling gear and the second travelling gear engaged transmission are fixed with shell.
Alternatively, the rotor is connected with pitch-changing mechanism.
Alternatively, the drive device is fuel engines.
By above-mentioned technical proposal, due to driving the drive device of rotor wing rotation to only have one, and can between rotor
Linkage so that drive device can control multiple rotors simultaneously, simplify control strategy.Further, since the quantity of drive device
For one, the weight of the body of unmanned plane in itself can be mitigated, so as to improve the ability that it loads other equipment.
Other feature and advantage of the disclosure will be described in detail in subsequent embodiment part.
Brief description of the drawings
Accompanying drawing is, for providing further understanding of the disclosure, and to constitute a part for specification, with following tool
Body embodiment is used to explain the disclosure together, but does not constitute limitation of this disclosure.In the accompanying drawings：
Fig. 1 is the structural representation of the tilting rotor wing unmanned aerial vehicle of an embodiment according to the disclosure；
Fig. 2 is the internal structure schematic diagram of tilting rotor wing unmanned aerial vehicle corresponding with Fig. 1；
Fig. 3 is according to the structural representation at gearbox in the tilting rotor wing unmanned aerial vehicle of an embodiment of the disclosure；
Fig. 4 is the structural representation at the front reduction gear case of the tilting rotor wing unmanned aerial vehicle of an embodiment according to the disclosure
Figure；
Fig. 5 is the structural representation at the rear reduction box of the tilting rotor wing unmanned aerial vehicle of an embodiment according to the disclosure
Figure.
Description of reference numerals
The front wing of 100 fuselage, 200 wing 201
The drive device of 202 rear wing, 300 rotor 400
Universal driving shaft before the universal driving shaft 511 of 410 drive shaft 510
The gearbox of 513 power transmission shaft of universal driving shaft 520 after 512
The shell of 521 first bevel gear, 522 second bevel gear 523
The bevel gear of 600 reduction box, 610 third hand tap gear 620 the 4th
Reduction box after the front reduction gear case 602 of 630 the 5th bevel gear 601
710 vert the travelling gear of 720 first travelling gear of steering wheel 730 second
800 pitch-changing mechanisms
Embodiment
It is described in detail below in conjunction with accompanying drawing embodiment of this disclosure.It should be appreciated that this place is retouched
The embodiment stated is merely to illustrate and explained the disclosure, is not limited to the disclosure.
In the disclosure, in the case where not making opposite explanation, the noun of locality used such as " upper and lower " typically refers to unmanned plane
It is upper and lower under flat winged state, Fig. 3 page is specifically referred to, " forward and backward " refers to the front and rear of unmanned plane, " interior,
Refer to outside " for profile of corresponding parts itself.In addition, the term " first " used in the disclosure, " second " etc.
It is in order to distinguish a key element and another key element, without succession and importance.
The tilting rotor wing unmanned aerial vehicle that the disclosure is provided, refers to set the rotor that can be verted on fixed wing aircraft so that nothing
It is man-machine to realize the switching of fixed-wing pattern and helicopter mode.Specifically, tilting rotor wing unmanned aerial vehicle includes fuselage 100, machine
The wing 200, is arranged on multiple rotors 300 on wing in which can vert, and drives the drive device 400 of rotor 300, wherein, rotation
Verting for the wing 300 refers to that the Plane of rotation of its propeller can realize horizontal direction to the switching of vertical direction, and rotor 300 can
With installed in the wing of wing 200 slightly.In originally opening, linkage unit is connected between rotor 300, can rotate simultaneously, here,
The rotation of rotor 300 refers to the rotation of propeller.Due to driving the drive device of rotor wing rotation to only have one, and rotor it
Between can link so that drive device can control multiple rotors simultaneously, simplify control strategy.Further, since drive device
Quantity be one, the weight of the body of unmanned plane in itself can be mitigated, so as to improve its load other equipment ability.
Further, as shown in figure 3, rotor 300 is connected with pitch-changing mechanism 800.For each rotor, pitch-changing mechanism is designed
800, so that in the case of each rotating speed identical of rotor 300, by always away from adjustment, realizing to each lift variation of rotor 300
Quick response.Pitch-changing mechanism 800 is structure well known to those skilled in the art, can use conventional setting form,
Displacement motor and the rod assembly being connected with displacement motor output end can for example be included, rod assembly connects with rotor 300 again
Connect, the lift of the generation of rotor 300 is adjusted by changing the angle of rotor 300.The disclosure to the concrete structure of pitch-changing mechanism not
It is limited, as long as the lift of rotor 300 can be adjusted in real time.
As shown in Figures 2 and 3, linkage unit can include the rotatable linkage for extending transversely through fuselage 100 and wing 200
Axle 510, and the gearbox 520 installed in the two ends of universal driving shaft 510, rotor 300 are connected on gearbox 520, drive device 400
With the drive connection of universal driving shaft 510.That is, the driving of drive device 400 universal driving shaft 510 is rotated, and universal driving shaft 510 drives the speed change at its two ends
Case 520, gearbox 520 is transferred to power is exported on rotor 300.The rotating ratio of gearbox 520 can be according to actual type knot
Depending on structure, it is not limited here.Wherein, the gearbox 520 at the two ends of universal driving shaft 510 is symmetrical with fuselage arrangement so that the rotation of both sides
The wing 300 acts synchronization, can rotate simultaneously.
The structure of gearbox can be a variety of, reference picture 3, and in a kind of embodiment of the disclosure, gearbox 520 includes
Shell 523, is set in the first bevel gear 521 on universal driving shaft 510, and bore tooth with the second of the engaged transmission of first bevel gear 521
Wheel 522, second bevel gear 522 is coaxial with rotor 300 to rotate simultaneously, first bevel gear 521 and the difference shape of second bevel gear 522
Into in shell 523.To mention below, the shell 523 can as inclining rotary mechanism a part, rotor 300 can be driven
Vert, meanwhile, above-mentioned pitch-changing mechanism 800 can also be arranged on the shell 523, so that compact conformation.Using this set,
The direction of power transmission can not only be changed, while speed-changing gear box has a compact conformation, stable drive, high excellent of reliability
Point.
Further, as shown in Fig. 2 being connected with reduction box 600 between drive device 400 and universal driving shaft 510.So, from
The power that drive device 400 is exported is transmitted to rotor 300, and centre is at least provided with secondary transmission, it is possible to achieve higher turns
Speed ratio.
Drive device 400 and reduction box 600 can be separately positioned on the center line of unmanned plane, to cause the weight of unmanned plane
The heart at the center line on, lifted flight stability.
With gearbox 520 similarly, reduction box 600 can use the form of Bevel Gear Transmission, and its advantage has been described above
Mention, do not repeat here.Specifically, as shown in Figure 4 and Figure 5, reduction box 600 can include being set on universal driving shaft 510
Third hand tap gear 610, and the 4th bevel gear 620 with the engaged transmission of third hand tap gear 610, the 4th bevel gear 620 fill with driving
The drive shaft 410 for putting 400 is connected.It should be noted that the 4th bevel gear 620 can not be and be connected directly between in drive shaft 410,
For example in following embodiment, after being also associated between the 4th bevel gear 620 and drive shaft 410 on front reduction gear case 601
Reduction box 602 and power transmission shaft 513.
Shown in Fig. 4 and Fig. 5 is the structure of two reduction boxes in the embodiment being mentioned below respectively, on slowing down
The specific type of attachment of case 600 and other parts will be described further in the embodiment.
Referring to Figures 1 and 2, according to the disclosure embodiment, unmanned plane can be tandem wing unmanned plane, i.e. bag
Include front wing 201 and rear wing 202.So, rotor 300 can be four, can be by each when unmanned plane is in helicopter mode
The cooperation of rotor 300 completes a variety of flight attitudes, when unmanned plane is in fixed-wing pattern, can provide stronger motive force.
As shown in Fig. 2 in this case, universal driving shaft 300 includes preceding universal driving shaft 511 and rear universal driving shaft 512, before reduction box 600 includes
Rotor 300 on reduction box 601 and rear reduction box 602, front wing 201 is linked by preceding universal driving shaft 511, the rotor on rear wing 202
300 are linked by rear universal driving shaft 512, and front reduction gear case 601 is connected with preceding universal driving shaft 511, rear reduction box 602 and rear universal driving shaft 512
Connection, front reduction gear case 601 and rear reduction box 602 are linked by the power transmission shaft 513 of front and rear extension.So, drive device 400 will be dynamic
Power is transferred to one of front reduction gear case 601 and rear reduction box 602, passes through power transmission shaft 523, preceding universal driving shaft 511 and rear linkage
The linkage effect of axle 512 enables four rotors 300 while rotating.It should be noted that in order that four rotors 300
Rotating speed is consistent, and front reduction gear case 601 and rear reduction box 602 need to carry out the matching of rotating ratio, its especially by bevel gear tooth form
It is designed with the number of teeth, the design method is conventional means in the art, does not do excessive explanation here.
In addition, in above-mentioned tandem wing unmanned plane, the direction of rotation of four rotors can be by between each bevel gear
Matching relationship is adjusted so that it is left front with it is right after rotor wing rotation direction it is identical, it is right before it is identical with lower-left rotor wing rotation direction, this
Two groups of rotors are turned on the contrary, when four rotor lifts are identical, realizing the balance of complete machine moment of torsion.It should be noted that here
For " left and right " is the preceding line direction of relative unmanned plane.
Specifically, reference picture 2 and Fig. 5, drive device 400 can be arranged on the rear end of fuselage 100, and rear reduction box 602 is also
It is provided with the engaged transmission of third hand tap gear 610 and positioned at the 5th bevel gear 630 of the offside of the 4th bevel gear 620, power transmission shaft
513 one end is connected with the 5th bevel gear 630, and the other end is connected with the 4th bevel gear 620 on front reduction gear case 601.
As shown in figure 3, above-mentioned gearbox 520 can as the inclining rotary mechanism of rotor 300 a part, i.e. due to rotor
300 are arranged on gearbox 520, and verting for gearbox 520 can drive rotor 300 to vert.Specifically, can be with wing 200
The steering wheel 710 that verts is fixed with, verts and transmission component is set between steering wheel 710 and shell 523 so that the steering wheel 710 that verts can drive
Dynamic shell 523 verts.
In embodiment as shown in Figure 3, the first travelling gear 720 is provided with the output shaft for the steering wheel 710 that verts, outside
The second travelling gear 730, the first travelling gear 720 and the engaged transmission of the second travelling gear 730 are fixed with shell 523.In order that
Compact overall structure, the second travelling gear 730 can be set in the outside of universal driving shaft 510, and be fixedly connected with shell 523, here
It should be noted that without direct-drive relation between the second travelling gear 730 and universal driving shaft 510.In this case, shell
523 can be verted centered on universal driving shaft 510, and Stability Analysis of Structures is reliable, by controlling the realization control speed change of steering wheel 710 of verting
Case 520 verts, and then in the case where ensureing power transmission, realizes verting for rotor 300.
In the disclosure, drive device 400 can be fuel engines, and fuel engines power is more sufficient, can be simultaneously steady
Surely power is provided for multiple rotors 300.Using fuel engines, the power output of drive device 400 can be increased substantially,
So that unmanned plane can all improve a lot in terms of voyage and endurance.
The preferred embodiment of the disclosure is described in detail above in association with accompanying drawing, still, the disclosure is not limited to above-mentioned reality
The detail in mode is applied, in the range of the technology design of the disclosure, a variety of letters can be carried out with technical scheme of this disclosure
Monotropic type, these simple variants belong to the protection domain of the disclosure.
It is further to note that each particular technique feature described in above-mentioned embodiment, in not lance
In the case of shield, can be combined by any suitable means, in order to avoid unnecessary repetition, the disclosure to it is various can
The combination of energy no longer separately illustrates.
In addition, can also be combined between a variety of embodiments of the disclosure, as long as it is without prejudice to originally
Disclosed thought, it should equally be considered as disclosure disclosure of that.
Claims (10)
1. a kind of tilting rotor wing unmanned aerial vehicle, it is characterised in that including fuselage (100), wing (200) is arranged on institute with can verting
State multiple rotors (300) on wing, and the driving rotor (300) drive device (400), the rotor (300) it
Between be connected with linkage unit, can rotate simultaneously.
2. tilting rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that the linkage unit includes extending transversely through institute
The rotatable universal driving shaft (510) of fuselage (100) and the wing (200) is stated, and installed in the universal driving shaft (510) two ends
Gearbox (520), the rotor (300) is connected on the gearbox (520), the drive device (400) with it is described
Moving axis (510) drive connection.
3. tilting rotor wing unmanned aerial vehicle according to claim 2, it is characterised in that the gearbox (520) includes being set in
First bevel gear (521) on the universal driving shaft (510), and bore tooth with the second of the first bevel gear (521) engaged transmission
Take turns (522), the second bevel gear (522) is coaxial with the rotor (300) with rotation simultaneously.
4. tilting rotor wing unmanned aerial vehicle according to claim 2, it is characterised in that the drive device (400) and described
Reduction box (600) is connected between moving axis (510).
5. tilting rotor wing unmanned aerial vehicle according to claim 4, it is characterised in that the reduction box (600) includes being set in
Third hand tap gear (610) on the universal driving shaft (510), and bore tooth with the 4th of the third hand tap gear (610) engaged transmission
Take turns (620), the 4th bevel gear (620) is connected with the drive shaft (410) of the drive device (400).
6. tilting rotor wing unmanned aerial vehicle according to claim 5, it is characterised in that the unmanned plane is tandem wing unmanned plane,
The universal driving shaft (510) includes preceding universal driving shaft (511) and rear universal driving shaft (512), and the reduction box (600) includes front reduction gear case
(601) and rear reduction box (602), the rotor on the front wing (201) of the tandem wing unmanned plane passes through the preceding universal driving shaft (511)
Rotor on linkage, rear wing (202) is linked by the rear universal driving shaft (512), the front reduction gear case (601) and the preceding linkage
Axle (511) is connected, and the rear reduction box (602) is connected with the rear universal driving shaft (512), the front reduction gear case (601) and described
Reduction box (602) is linked by the power transmission shaft (513) of front and rear extension afterwards.
7. the tilting rotor wing unmanned aerial vehicle stated according to claim 6, it is characterised in that the drive device (400) is arranged on described
The rear end of fuselage (100), the rear reduction box (602) is additionally provided with and the third hand tap gear (610) engaged transmission and position
In the 5th bevel gear (630) of the 4th bevel gear (620) offside, one end of the power transmission shaft (513) and the described 5th cone
Gear (630) is connected, and the other end is connected with the 4th bevel gear (620) on the front reduction gear case (601).
8. tilting rotor wing unmanned aerial vehicle according to claim 2, it is characterised in that be fixed with the rudder that verts on the wing (200)
Machine (710), the gearbox (520) includes shell (523), and the steering wheel that verts (710) drives the shell (523) so that institute
State rotor (300) to vert, it is preferable that be provided with the first travelling gear (720), institute on the output shaft of the steering wheel that verts (710)
State and the second travelling gear (730) is fixed with shell (523), first travelling gear (720) and second travelling gear
(730) engaged transmission.
9. tilting rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that the rotor (300) is connected with displacement machine
Structure (800).
10. the tilting rotor wing unmanned aerial vehicle according to any one of claim 1-9, it is characterised in that the drive device
(400) it is fuel engines.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710160878.5A CN106976552A (en) | 2017-03-17 | 2017-03-17 | Tilting rotor wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710160878.5A CN106976552A (en) | 2017-03-17 | 2017-03-17 | Tilting rotor wing unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN106976552A true CN106976552A (en) | 2017-07-25 |
Family
ID=59338206
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|---|---|---|---|
| CN201710160878.5A Pending CN106976552A (en) | 2017-03-17 | 2017-03-17 | Tilting rotor wing unmanned aerial vehicle |
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Cited By (14)
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| CN107891978A (en) * | 2017-10-23 | 2018-04-10 | 上海歌尔泰克机器人有限公司 | Transmission mechanism and tilting rotor wing unmanned aerial vehicle |
| CN107963209A (en) * | 2017-11-17 | 2018-04-27 | 沈阳无距科技有限公司 | Tandem wing tilting rotor wing unmanned aerial vehicle |
| CN108100272A (en) * | 2017-12-18 | 2018-06-01 | 赵锡军 | A kind of aircraft dynamic transfer system |
| CN108146629A (en) * | 2018-02-07 | 2018-06-12 | 深圳市旗客智能技术有限公司 | Tilting rotor wing unmanned aerial vehicle |
| CN108177766A (en) * | 2017-11-27 | 2018-06-19 | 沈阳无距科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN108313285A (en) * | 2018-03-15 | 2018-07-24 | 中国人民解放军国防科技大学 | Propeller tilting mechanism |
| CN109896008A (en) * | 2019-03-29 | 2019-06-18 | 武汉理工大学 | A kind of empty amphibious unmanned plane of adaptive water using rotor inclining rotary mechanism |
| CN110058601A (en) * | 2019-03-19 | 2019-07-26 | 沈阳无距科技有限公司 | The method, apparatus and electronic equipment that unmanned helicopter landing quickly determines |
| CN110615094A (en) * | 2018-12-17 | 2019-12-27 | 吴华锋 | Multi-shaft multi-directional tilting type multi-rotor aircraft transmission system |
| CN113184177A (en) * | 2021-05-17 | 2021-07-30 | 朱世友 | Tilt-rotor aircraft and power transmission device thereof |
| CN113911378A (en) * | 2021-11-23 | 2022-01-11 | 南京航空航天大学 | Transmission mechanism of longitudinal tilt rotorcraft |
| CN114426102A (en) * | 2022-02-24 | 2022-05-03 | 重庆大学 | Transmission system of tilt rotorcraft |
| CN114435607A (en) * | 2022-02-24 | 2022-05-06 | 重庆大学 | Belt transmission type transmission system of tilt-rotor aircraft |
| CN114750937A (en) * | 2022-05-19 | 2022-07-15 | 重庆大学 | High-precision magnetic transmission tilt rotor aircraft |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107891978A (en) * | 2017-10-23 | 2018-04-10 | 上海歌尔泰克机器人有限公司 | Transmission mechanism and tilting rotor wing unmanned aerial vehicle |
| CN107963209A (en) * | 2017-11-17 | 2018-04-27 | 沈阳无距科技有限公司 | Tandem wing tilting rotor wing unmanned aerial vehicle |
| CN107963209B (en) * | 2017-11-17 | 2020-03-20 | 沈阳无距科技有限公司 | Tandem wing rotor unmanned aerial vehicle that verts |
| CN108177766A (en) * | 2017-11-27 | 2018-06-19 | 沈阳无距科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN108100272A (en) * | 2017-12-18 | 2018-06-01 | 赵锡军 | A kind of aircraft dynamic transfer system |
| CN108146629A (en) * | 2018-02-07 | 2018-06-12 | 深圳市旗客智能技术有限公司 | Tilting rotor wing unmanned aerial vehicle |
| CN108313285A (en) * | 2018-03-15 | 2018-07-24 | 中国人民解放军国防科技大学 | Propeller tilting mechanism |
| CN110615094A (en) * | 2018-12-17 | 2019-12-27 | 吴华锋 | Multi-shaft multi-directional tilting type multi-rotor aircraft transmission system |
| CN110058601A (en) * | 2019-03-19 | 2019-07-26 | 沈阳无距科技有限公司 | The method, apparatus and electronic equipment that unmanned helicopter landing quickly determines |
| CN109896008A (en) * | 2019-03-29 | 2019-06-18 | 武汉理工大学 | A kind of empty amphibious unmanned plane of adaptive water using rotor inclining rotary mechanism |
| CN109896008B (en) * | 2019-03-29 | 2022-08-05 | 武汉理工大学 | Self-adaptive water-air amphibious unmanned aerial vehicle adopting rotor wing tilting mechanism |
| CN113184177A (en) * | 2021-05-17 | 2021-07-30 | 朱世友 | Tilt-rotor aircraft and power transmission device thereof |
| CN113911378A (en) * | 2021-11-23 | 2022-01-11 | 南京航空航天大学 | Transmission mechanism of longitudinal tilt rotorcraft |
| CN113911378B (en) * | 2021-11-23 | 2022-11-01 | 南京航空航天大学 | Transmission mechanism of longitudinal tilt rotorcraft |
| CN114426102A (en) * | 2022-02-24 | 2022-05-03 | 重庆大学 | Transmission system of tilt rotorcraft |
| CN114435607A (en) * | 2022-02-24 | 2022-05-06 | 重庆大学 | Belt transmission type transmission system of tilt-rotor aircraft |
| CN114750937A (en) * | 2022-05-19 | 2022-07-15 | 重庆大学 | High-precision magnetic transmission tilt rotor aircraft |
| CN114750937B (en) * | 2022-05-19 | 2024-04-19 | 重庆大学 | High-precision magnetic transmission tilting rotary wing aircraft |
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