CN207523932U - Tandem wing tilting rotor wing unmanned aerial vehicle - Google Patents
Tandem wing tilting rotor wing unmanned aerial vehicle Download PDFInfo
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- CN207523932U CN207523932U CN201721552434.8U CN201721552434U CN207523932U CN 207523932 U CN207523932 U CN 207523932U CN 201721552434 U CN201721552434 U CN 201721552434U CN 207523932 U CN207523932 U CN 207523932U
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Abstract
This disclosure relates to a kind of tandem wing tilting rotor wing unmanned aerial vehicle, including fuselage (10), front wing (21), rear wing (22), tiliting axis (30), first motor (41) and rotor (42), the tiliting axis (30) is rotationally laterally through the fuselage (10), the rotor (42) is fixed on the end of the tiliting axis (30) by first motor (41), the rotor (42) includes coaxial the first rotor (421) and the second rotor (422), first rotor (421) and second rotor (422) it is oppositely oriented.Through the above technical solutions, multi-rotor unmanned aerial vehicle and fixed-wing unmanned plane are integrated, and combine tandem-winged design so that unmanned plane there can be many attitude.In addition, the vortex generated during the blade rotation of coaxial and reversion two groups of rotors can cancel out each other, energy loss caused by so as to be vortexed is preferably minimized.
Description
Technical field
A kind of this disclosure relates to unmanned air vehicle technique field, and in particular, to tandem wing tilting rotor wing unmanned aerial vehicle.
Background technology
Tilting rotor wing unmanned aerial vehicle is that one kind has both gyroplane and fixed-wing aircraft advantage, both can vertically be risen as gyroplane
Before drop, hovering, low speed fly, and can as fixed-wing aircraft high speed cruise flight aircraft.Tilting rotor wing unmanned aerial vehicle
A set of rotor that can be rotated between horizontal position and upright position on similar to fixed-wing aircraft body is installed, works as rotor plane
During in horizontality, for rotor shaft perpendicular to ground, unmanned plane is more rotor modes, can be hovered in the air, front and rear flight and side
Fly, by changing the size of rotor climbing power and the direction of verting of rotor, unmanned plane holding or change of flight state can be made；When
When rotor plane is in vertical state, rotor shaft is horizontal, and rotor is then used as pulling force propeller, and unmanned plane is fixes
Wing pattern, generating lift by front wing can high speed cruise flight.Tandem wing unmanned plane refers to that unmanned plane sets two in front-rear direction
Group wing, provides lift respectively.
Utility model content
The purpose of the disclosure is to provide a kind of tandem wing tilting rotor wing unmanned aerial vehicle, which has both fixed-wing
The advantages of unmanned plane and multi-rotor unmanned aerial vehicle, and combine tandem-winged design so that unmanned plane can have many attitude.
To achieve these goals, the disclosure provides a kind of tandem wing tilting rotor wing unmanned aerial vehicle, including fuselage, front wing, after
The wing, tiliting axis, the first motor and rotor, rotationally laterally through the fuselage, the rotor passes through the tiliting axis
First motor is fixed on the end of the tiliting axis, and the rotor includes coaxial the first rotor and the second rotor, described
First rotor and second rotor it is oppositely oriented.
Optionally, first rotor and second rotor are symmetrical with the tiliting axis arrangement.
Optionally, the unmanned plane further includes vertical tail, is provided with rudder on the vertical tail, on the rear wing
It is provided with elevator.
Optionally, the front wing, the rear wing and the vertical tail are detachably connected to respectively on the fuselage.
Optionally, the tiliting axis, the front wing and the rear wing are staggeredly arranged in the height direction.
Optionally, the unmanned plane is provided with bird-repeller system, and the bird-repeller system includes being fixed on super on the front wing
Sonic horn and the audio horn and flashing light being fixed on the fuselage.
Optionally, the front end of the fuselage is provided with forward sight binocular, and the forward sight binocular vertically runs through the fuselage.
Optionally, the umbrella cabin for accommodating parachute is provided at the top of the fuselage.
Optionally, it is provided with camera on the fuselage；Pitot is provided on the fuselage；Friendship is provided on the fuselage
Mutual antenna.
Optionally, the bottom of the fuselage is provided with wheel undercarriage.
Through the above technical solutions, multi-rotor unmanned aerial vehicle and fixed-wing unmanned plane are integrated, and combine the tandem wing
Design so that unmanned plane can have many attitude.The unmanned plane both can be such as multi-rotor unmanned aerial vehicle VTOL, overhead suspension
Stop, fly at low speed, it can also be such as fixed-wing unmanned plane high-performance cruise.In addition, the blade rotation of coaxial and reversion two groups of rotors
When the vortex that generates can cancel out each other, energy loss caused by so as to be vortexed is preferably minimized.
Other feature and advantage of the disclosure will be described in detail in subsequent specific embodiment part.
Description of the drawings
Attached drawing is for providing further understanding of the disclosure, and a part for constitution instruction, with following tool
Body embodiment is used to explain the disclosure, but do not form the limitation to the disclosure together.In the accompanying drawings：
Fig. 1 is the structure diagram of tandem wing tilting rotor wing unmanned aerial vehicle in accordance with one embodiment of the present disclosure；
Fig. 2 is the structure of driving mechanism in tandem wing tilting rotor wing unmanned aerial vehicle in accordance with one embodiment of the present disclosure
Schematic diagram；
Fig. 3 is the internal structure schematic diagram of steering engine in Fig. 2.
Reference sign
10 fuselages
21 front wing, 22 rear wing, 23 vertical tail
221 elevator, 231 rudder
30 tiliting axis
41 first motor, 42 rotor, 421 first rotor
422 second rotors
50 wheel undercarriages
61 steering engine, 611 shell, 612 second motor
613 worm screw, 614 turbine, 615 gear train
62 first 63 second belt pulley of belt pulley, 64 belt
701 ultrasonic horn, 702 flashing light, 703 forward sight binocular
704 holder, 705 pitot, 706 figure passes antenna
707 receiver antenna, 708 3G antennas 709 number passes antenna
710 cameras
Specific embodiment
The specific embodiment of the disclosure is described in detail below in conjunction with attached drawing.It should be understood that this place is retouched
The specific embodiment stated is only used for describing and explaining the disclosure, is not limited to the disclosure.
In the disclosure, in the case where not making to illustrate on the contrary, the noun of locality that uses such as " on ", " under " refers to that unmanned plane exists
Real use state it is upper and lower, " interior ", " outer " are for profile of corresponding parts itself.In addition, in the disclosure
The term " first " that uses, " second " etc. are in order to distinguish an element and another element, without succession and importance.
As shown in Figure 1, the disclosure provides a kind of tandem wing tilting rotor wing unmanned aerial vehicle, including fuselage 10, front wing 21, rear wing
22nd, tiliting axis 30, the first motor 41 and rotor 42, rotationally laterally through fuselage 10, rotor 42 passes through tiliting axis 30
First motor 41 is fixed on the end of tiliting axis 30, and the driving machine for tiliting axis 30 to be driven to rotate is additionally provided in fuselage 10
Structure.Multi-rotor unmanned aerial vehicle and fixed-wing unmanned plane are integrated, and combine tandem-winged design so that unmanned plane can have
There are many postures.The unmanned plane both can be such as multi-rotor unmanned aerial vehicle VTOL, hovering, low-speed operations, can also be as admittedly
Determine wing unmanned plane high-performance cruise.That is, unmanned plane can be realized in more rotor modes and fixed-wing mould by the rotation of tiliting axis 30
Switch between formula.Specifically, when rotor 42 is when horizontal plane rotates, unmanned plane is in more rotor modes, when rotor 42 is perpendicular
During straight Plane Rotation, unmanned plane is in fixed-wing pattern.
In addition, rotor 42 can include coaxial the first rotor 421 and the second rotor 422, the first rotor 421 and second
Rotor 422 it is oppositely oriented, in this way, the vortex that generates can cancel out each other during the blade rotation of coaxial and reversion two groups of rotors,
Energy loss caused by so as to be vortexed is preferably minimized.Due to eliminating the air-swirl of blade tip, this DCB Specimen is compared to general
The structure of logical list rotor can improve the efficiency of about 6%-16%.First rotor 421 and the second rotor 422 are respectively by different
First motor 41 drives, and unmanned plane during the work time, even if some rotor 42 or motor 41 go wrong, still may be used by unmanned plane
With stabilized flight.
Further, the first rotor 421 and the second rotor 422 are symmetrical with tiliting axis 30 and arrange, it is ensured that on same axis
Size, the rotating speed of two rotors 42 etc. are all identical, are simply diverted to difference, so as to avoid generating other additional power and torque.
As shown in figure 3, in one embodiment, the driving mechanism that the disclosure provides can include being fixed in fuselage 10
Steering engine 61, be connected to steering engine 61 output shaft the first belt pulley 62 and be set in the second belt pulley of 30 periphery of tiliting axis
63, it is driven between the first belt pulley 62 and the second belt pulley 63 by belt 64.In this way, by way of belt transmission, vert
30 stability of rotation of axis, when work, are noiseless, and equipment operation is reliable, and by adjusting the first belt pulley 62 and the second belt pulley 63
Diameter ratio, can easily adjust gearratio.In addition, the distance between the first belt pulley 62 and the second belt pulley 63 can be with
It is adjusted according to practical type, the length of belt 64 is only needed to change, so as to improve the versatility of driving mechanism.
Further, steering engine 61 can include shell 611, the second motor 612, the output shaft for being connected to the second motor 612
Worm screw 613, with the worm gear 614 of the cooperation transmission of worm screw 613 and the gear train 615 that is driven by worm gear 614, the first belt pulley
62 are connected to the output shaft of gear train 615.By setting worm and gear component so that steering engine 61 has auto-lock function.It is specific and
Speech due to the one-way of Worm Wheel System form, can only be driven turbine 614 by worm screw 613, and powerdriven direction is second
Motor 612- worm screw 613- turbine 614- gear trains 615, in this way, when steering engine 61 is when a certain angle position load continuous works,
Input terminal can cut off input, can also cut off the power input of the second motor 612, not need to persistently consume energy maintenance again
Position, since Wen Sheng is too high to work normally when avoiding the steering engine 61 from loading for a long time.In this case, tiliting axis 30 can
Continually and steadily to work in any position that can be in tilt angle.On the other hand, 614 gear train 615 of turbine, can be full
Output torque is further amplified under the premise of sufficient self-locking property, efficient, compact-sized, reliable operation accurate with gearratio
The characteristics of, simultaneously because load is connected to the output shaft of gear train 615 so that load is transmitted to the active force of worm and gear component
Very little in this way, in the present embodiment, worm and gear component need to only provide smaller self-lock force, can realize steering engine oneself
Lock, prevents in load effect to the second motor 612, especially when unmanned plane during flying posture changes, what high-frequency alternating load generated
Vibratory impulse is buffered, and can extend the service life of the second motor 612, reduces energy consumption.
In order to reduce the aerodynamic drag on tiliting axis 30, the section of tiliting axis 30 can have the stream similar with front wing 21
Line style section.Under fixed-wing pattern, unmanned plane needs high-performance cruise, it is especially desirable to reduce resistance, in this mode, tiliting axis
The length of the short transverse of 30 section is less than length in the front-back direction.
As shown in Figure 1, tiliting axis 30, front wing 21 and rear wing 22 are staggeredly arranged in the height direction, tiliting axis 30 is at nobody
Machine-cut can avoid the slip-stream of the paddle disk of rotor 42 from beating on front wing 21 and make unmanned plane when changing the mold state has nose-down pitching moment,
And the air-flow that front wing 21 generates will not influence the action of rear wing 22.
In addition, rear wing 22 can be located at the tail portion of fuselage 10 using as empennage, be provided on the rear wing 22 elevator 221 with
Control the pitching movement of unmanned plane.Unmanned plane in present embodiment further includes vertical tail 23, is provided on vertical tail 23
Rudder 231 is to control the yawing rotation of unmanned plane.As shown in Figure 1, it is separately mounted to fuselage on rear wing 22 and vertical tail 23
10 tail portion, for the ease of packing and transporting, front wing 21, rear wing 22 and vertical tail 23 are detachably connected to fuselage respectively
10.Specifically, the curing molding respectively such as fuselage 10, front wing 21, rear wing 22 and vertical tail 23, there are main wings on fuselage 10
21st, the interface of rear wing 22 and vertical tail 23, each component assembling is integrated after molding.
As shown in Figure 1, the top of fuselage 10 can be provided with the umbrella cabin 13 for accommodating parachute, encountered in unmanned plane prominent
Umbrella cabin 13 can open during hair-like condition, to carry out parachuting, the damage that body and internal electronic equipment are subject to can not only be mitigated and
And it can ensure the safety of ground staff.
As shown in Figure 1, multiple interactive antennas can be provided on fuselage 10, believed so that remote controller signal or satellite can be received
Number etc., for example, interaction antenna, which can include figure biography antenna 706, receiver antenna 707,3G antennas 708 and number, passes antenna 709.
In addition, on the tandem wing tilting rotor wing unmanned aerial vehicle that the disclosure provides, carry equipment can be set, these equipment difference
It is removably mounted on unmanned plane, different tasks is performed to be adapted to.It is disassembled from body when not needing to use
To mitigate main screw lift.
Specifically, carry equipment can include bird-repeller system, as shown in Figure 1, bird-repeller system includes being fixed on front wing 21
Ultrasonic horn 701 and the audio horn and flashing light 702 that are fixed on fuselage 10.The set acousto-optic-electric bird-repeller system exists
Effectively the birds for influencing takeoff and landing operation can be driven to other than the range of airport during use, aforementioned aircraft can be the people
With aircraft or military aircraft, the bird-repeller system in present embodiment ensures the Normal Take-Off And Landing of aircraft.
Carry equipment further includes binocular vision system, can play the role of avoidance.Specifically, as shown in Figure 1, fuselage 10
Front end is provided with forward sight binocular 703, and for forward sight binocular 703 vertically through fuselage 10, two camera can be located at fuselage respectively
Above and below in the of 10.In addition, airflow design may be used in forward sight binocular 703, air drag can be preferably reduced.
Carry equipment as shown in Figure 1 further includes the holder 704 being arranged on fuselage 10, and camera is fixed on holder 704
710, camera 710 can be the Visible Light Camera used daytime, or the infrared camera that night uses.In addition, fuselage 10
On be also provided with pitot 705, pitot 705 is located at the front end of fuselage 10, can be to experience the stagnation pressure of air-flow and quiet
Pressure, and send the pressure data measured to flight control system.
As shown in Figure 1, the bottom of fuselage 10 is provided with wheel undercarriage 50, more take off so that unmanned plane can be slided, in this way,
In the case of without using VTOL function, unmanned plane can move ahead by the wheel on wheel undercarriage 50 on runway,
It is taken off with fixed-wing pattern.With 30 structure of tiliting axis similarly, wheel undercarriage 50 can also use airfoil to design, specifically
Ground, wheel undercarriage 50 include strut and the wheel positioned at strut bottom, and strut is designed as streamlined, the front-rear direction of section
Length be more than strut thickness.In addition, wheel undercarriage 50 can include the main landing gear in inverted V-type, positioned at fuselage
The centre position of 10 bottom and the nose-gear positioned at the front end of the bottom of fuselage 10, the nose-gear are direct rod shape.
The preferred embodiment of the disclosure is described in detail above in association with attached 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 to the technical solution of the disclosure
Monotropic type, these simple variants belong to the protection domain of the disclosure.
It is further to note that specific technical features described in the above specific embodiments, 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, arbitrary combination can also be carried out between a variety of different embodiments of the disclosure, as long as it is without prejudice to originally
Disclosed thought should equally be considered as disclosure disclosure of that.
Claims (10)
1. a kind of tandem wing tilting rotor wing unmanned aerial vehicle, which is characterized in that including fuselage (10), front wing (21), rear wing (22), vert
Axis (30), the first motor (41) and rotor (42), the tiliting axis (30) rotationally laterally through the fuselage (10),
The rotor (42) is fixed on the end of the tiliting axis (30) by first motor (41), and the rotor (42) is including altogether
The rotation direction phase of the first rotor (421) of axis and the second rotor (422), first rotor (421) and second rotor (422)
Instead.
2. tandem wing tilting rotor wing unmanned aerial vehicle according to claim 1, which is characterized in that first rotor (421) and
Second rotor (422) is symmetrical with the tiliting axis (30) arrangement.
3. tandem wing tilting rotor wing unmanned aerial vehicle according to claim 1, which is characterized in that the unmanned plane further includes vertically
Empennage (23) is provided with rudder (231) on the vertical tail (23), elevator (221) is provided on the rear wing (22).
4. tandem wing tilting rotor wing unmanned aerial vehicle according to claim 3, which is characterized in that the front wing (21), it is described after
The wing (22) and the vertical tail (23) are detachably connected to respectively on the fuselage (10).
5. tandem wing tilting rotor wing unmanned aerial vehicle according to claim 1, which is characterized in that the tiliting axis (30), described
Front wing (21) and the rear wing (22) are staggeredly arranged in the height direction.
6. tandem wing tilting rotor wing unmanned aerial vehicle according to claim 1, which is characterized in that the unmanned plane is provided with bird repellent
System, the bird-repeller system include the ultrasonic horn (701) being fixed on the front wing (21) and are fixed on the fuselage
(10) audio horn and flashing light (702) on.
7. tandem wing tilting rotor wing unmanned aerial vehicle according to claim 1, which is characterized in that the front end of the fuselage (10) is set
Forward sight binocular (703) is equipped with, the forward sight binocular (703) vertically runs through the fuselage (10).
8. tandem wing tilting rotor wing unmanned aerial vehicle according to claim 1, which is characterized in that set at the top of the fuselage (10)
It is equipped with the umbrella cabin (13) for accommodating parachute.
9. tandem wing tilting rotor wing unmanned aerial vehicle according to claim 1, which is characterized in that be provided on the fuselage (10)
Camera (710)；Pitot (705) is provided on the fuselage (10)；Interactive antenna is provided on the fuselage (10).
10. the tandem wing tilting rotor wing unmanned aerial vehicle according to any one of claim 1-9, which is characterized in that the fuselage
(10) bottom is provided with wheel undercarriage (50).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721552434.8U CN207523932U (en) | 2017-11-17 | 2017-11-17 | Tandem wing tilting rotor wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721552434.8U CN207523932U (en) | 2017-11-17 | 2017-11-17 | Tandem wing tilting rotor wing unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN207523932U true CN207523932U (en) | 2018-06-22 |
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ID=62582687
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721552434.8U Active CN207523932U (en) | 2017-11-17 | 2017-11-17 | Tandem wing tilting rotor wing unmanned aerial vehicle |
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| CN (1) | CN207523932U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110539874A (en) * | 2019-09-19 | 2019-12-06 | 中国航空工业集团公司西安飞机设计研究所 | wing mounting structure of tilt rotor aircraft |
| CN116853491A (en) * | 2023-09-01 | 2023-10-10 | 成都沃飞天驭科技有限公司 | Tilting device, design method thereof and aircraft |
-
2017
- 2017-11-17 CN CN201721552434.8U patent/CN207523932U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110539874A (en) * | 2019-09-19 | 2019-12-06 | 中国航空工业集团公司西安飞机设计研究所 | wing mounting structure of tilt rotor aircraft |
| CN116853491A (en) * | 2023-09-01 | 2023-10-10 | 成都沃飞天驭科技有限公司 | Tilting device, design method thereof and aircraft |
| CN116853491B (en) * | 2023-09-01 | 2023-11-07 | 成都沃飞天驭科技有限公司 | Tilting device, design method thereof and aircraft |
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