CN112607021A - Manned unmanned aerial vehicle - Google Patents
Manned unmanned aerial vehicle Download PDFInfo
- Publication number
- CN112607021A CN112607021A CN202011561177.0A CN202011561177A CN112607021A CN 112607021 A CN112607021 A CN 112607021A CN 202011561177 A CN202011561177 A CN 202011561177A CN 112607021 A CN112607021 A CN 112607021A
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- CN
- China
- Prior art keywords
- manned
- unmanned aerial
- duct
- aerial vehicle
- cabin
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8227—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising more than one rotor
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention relates to the technical field of unmanned aerial vehicles, and discloses a manned unmanned aerial vehicle, which comprises: a manned drone, comprising: the aircraft comprises an aircraft body, wherein the aircraft body comprises a duct and a manned cabin, the duct is positioned in the middle of the aircraft body, the manned cabin is positioned outside the duct, and the duct is isolated from the manned cabin; a ducted fan located within the duct; the vertical balance assembly is arranged on the machine body and used for keeping the machine body balanced in flight; the tangential control assembly is arranged on the machine body and used for controlling the plane flight and the steering of the machine body. This manned unmanned aerial vehicle can be nimble various demands of realization scenic spot sightseeing.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a manned unmanned aerial vehicle.
Background
At present, the domestic tourism industry is rapidly developed, and more tourism is carried out in holidays along with the continuous improvement of the living standard of people. Most of domestic scenic spots are mainly outdoor close nature (mountains, islands, canyons and grasslands) and urban sightseeing, and low-altitude sightseeing in the scenic spots is more and more popular due to extraordinary experience, so that the scenic spots are key items for tourism development of future scenic spots. When high-altitude experience projects in scenic spots are realized by manned helicopters or fixed-wing airplanes, the airplanes need to be equipped with drivers with flight qualifications. In view of the shortage and high culture cost of domestic navigation flight drivers, the cost of pilots is high, so that the price of low-altitude sightseeing experience items is high, and the popularization is difficult to achieve.
The unmanned aerial vehicle that is applied to manned at present mainly has fixed wing unmanned aerial vehicle, and wherein fixed wing unmanned aerial vehicle has the place requirement, and it must have longer runway just can take off, and the time of taking off is longer. Scenic spots with low-altitude sightseeing requirements are mostly in mountainous areas, canyons, urban areas and the like, and the terrains in the places are complex, so that professional runways and airports with enough areas are difficult to construct. Therefore, the fixed wing unmanned aerial vehicle with high requirements on the field is difficult to apply.
Disclosure of Invention
The invention provides a manned unmanned aerial vehicle which can flexibly meet various requirements of scenic spot sightseeing.
In order to achieve the purpose, the invention provides the following technical scheme:
a manned drone, comprising:
the aircraft comprises an aircraft body, wherein the aircraft body comprises a duct and a manned cabin, the duct is positioned in the middle of the aircraft body, the manned cabin is positioned outside the duct, and the duct is isolated from the manned cabin;
a ducted fan located within the duct;
the vertical balance assembly is arranged on the machine body and used for keeping the machine body balanced in flight;
the tangential control assembly is arranged on the machine body and used for controlling the plane flight and the steering of the machine body.
The manned unmanned aerial vehicle comprises a vehicle body, a duct fan, a vertical balance assembly and a tangential control assembly, wherein the vehicle body comprises a duct and a manned cabin, the duct is located in the middle of the cabin, the manned cabin is located on the outer side of the duct, the duct is isolated from the manned cabin, the duct fan is located in the duct fan, and the vertical balance assembly and the tangential control assembly are arranged on the vehicle body. Among the above-mentioned manned unmanned aerial vehicle, the duct fan can take off and land and the operation in narrow and small environment, and its air resistance is little when flying, adopts the duct fan to provide lift, can make the fuselage keep balance in the flight through vertical balanced subassembly, can realize taking off and land perpendicularly fast under any environment, can hover in the not co-altitude realization simultaneously, do not receive the place restriction, can adapt to the place of different scenic spots. The free steering when flying and suspending through the tangential control subassembly can realize the plane of fuselage, various demands that realization scenic spot control sightseeing that can be nimble to, the ducted fan is in the duct, can make the running noise of complete machine by the separation, and the impinging stream of the rotor thick liquid apex of ducted fan also can be effectively retrained by the duct wall, can also avoid the paddle of high-speed rotation and the risk of people contact, can also reduce thermal radiation to a certain extent simultaneously.
Optionally, the fuselage comprises a machine bottom and a hatch cover positioned on the machine bottom, the hatch cover cooperates with the machine bottom and the duct to enclose the manned cabin, and the hatch cover is provided with a hatch door.
Optionally, the vertical balance assembly includes a plurality of independently controllable vertical balance rotors, and is a plurality of the vertical balance rotors are in the outer fringe of the bottom is equidistant evenly distributed, every the extending direction of the rotation axis of vertical balance rotor with the extending direction of the rotation axis of duct fan is parallel.
Optionally, the tangential control assembly comprises a plurality of individually controllable tangential control rotors, the plurality of tangential control rotors are evenly distributed at equal intervals on the outer edge of the bottom of the machine, and the extension directions of the rotation axes of the plurality of tangential control rotors are the same and are perpendicular to the extension direction of the rotation axis of the ducted fan.
Optionally, the hatch is a transparent hatch.
Optionally, the manned nacelle is disposed around the duct.
Optionally, the machine bottom is provided with a plurality of evenly distributed footrests.
Optionally, the body is shaped as a circular dish.
Optionally, at least one seat is disposed within the passenger cabin.
Optionally, the ducted fan further comprises a control device for controlling the actions of the ducted fan, the vertical balancing assembly and the tangential control assembly.
Drawings
Fig. 1 is a schematic structural view of a manned unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic structural view of a manned unmanned aerial vehicle according to an embodiment of the present invention;
fig. 3 is a schematic structural view of a manned unmanned aerial vehicle according to an embodiment of the present invention.
Icon:
1-a fuselage; 11-machine bottom; 12-a hatch; 121-hatch door; 2-ducted fans; 3-vertically balancing the rotor; 4-tangential control rotor; 5-a foot support; 6-a seat; a-a duct; b-manned cabin.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1 to 3, the present invention provides a manned unmanned aerial vehicle, including:
a manned drone, comprising:
the aircraft comprises an aircraft body 1, wherein the aircraft body 1 comprises a duct A and a manned cabin B, the duct A is positioned in the middle of the aircraft body 1, the manned cabin B is positioned outside the duct A, and the duct A is isolated from the manned cabin B;
the ducted fan 2 is positioned in the duct A;
the vertical balance assembly is arranged on the machine body 1 and is used for keeping the machine body 1 balanced in flight;
and the tangential control assembly is arranged on the machine body 1 and is used for controlling the plane flight and the steering of the machine body 1.
The manned unmanned aerial vehicle comprises a vehicle body 1, a ducted fan 2, a vertical balance assembly and a tangential control assembly, wherein the vehicle body 1 comprises a duct A and a manned cabin B, the duct A is located in the middle of the cabin, the manned cabin B is located on the outer side of the duct A, the duct A is isolated from the manned cabin B, the ducted fan 2 is located in the ducted fan 2, and the vertical balance assembly and the tangential control assembly are arranged on the vehicle body 1. Among the above-mentioned manned unmanned aerial vehicle, duct fan 2 can take off and land and the operation in narrow and small environment, and air resistance is little when its flight, adopts duct fan 2 to provide lift, can make fuselage 1 keep balance in the flight through vertical balanced subassembly, can realize taking off and land perpendicularly fast under any environment, can hover in the not co-altitude realization simultaneously, does not receive the place restriction, can adapt to the place in different scenic spots. The free steering when flying and suspending of the plane that can realize fuselage 1 through the tangential control subassembly turns to, various demands that realization scenic spot control sightseeing that can be nimble to, duct fan 2 can make the running noise of complete machine by the separation in duct A, and the impact air current of duct fan 2's rotor thick liquid apex also can be effectively retrained by the duct lateral wall, can also avoid the paddle of high-speed rotation and the risk of people contact, can also reduce thermal radiation to a certain extent simultaneously.
In the above embodiment of the invention, as shown in fig. 1 and fig. 2, the fuselage 1 may include a machine bottom 11 and a cover 12 disposed on the machine bottom 11, the cover 12 cooperates with the machine bottom 11 and the duct a to enclose a passenger compartment B, and the cover 12 has a door 121.
In the above embodiment of the invention, as shown in fig. 1, the vertical balancing unit may be a plurality of individually controllable vertical balancing rotors 3; a plurality of vertical balanced rotor 3 can equidistant evenly distributed at the outer fringe of bottom 11, and the extending direction of the rotation axis of every vertical balanced rotor 3 is parallel with the extending direction of the rotation axis of duct fan 2. As shown in fig. 3, four vertical balance rotors 3 are uniformly distributed on the fuselage 1 at equal intervals. Specifically, the vertical balanced rotor 3 of a plurality of equidistant evenly distributed of simultaneous control is rotatory, can be according to the actual fuselage mass distribution condition, and the paddle rotational speed of each vertical balanced rotor 3 of control produces the equilibrium moment to the barycenter, can not receive manned cabin interior personnel mass distribution's influence, keeps the fuselage balanced. Alternatively, the vertically balanced rotor 3 may be an electrically driven rotor.
In the above-described embodiment of the invention, as shown in fig. 1, the tangential control assembly may comprise a plurality of individually controllable tangential control rotors 4; the plurality of tangential control rotary wings 4 can be evenly distributed at equal intervals on the outer edge of the machine bottom 11, and the extension directions of the rotary shafts of the plurality of tangential control rotary wings 4 are the same and are vertical to the extension direction of the rotary shaft of the ducted fan 2. As shown in fig. 3, the fuselage 1 is provided with two tangential control rotors 4 distributed uniformly. Specifically, according to the flight route, the paddle of a plurality of tangential control rotors 4 is controlled rotatory, provides horizontal thrust, realizes unmanned aerial vehicle horizontal direction's removal. When the unmanned aerial vehicle needs to turn to change the flight direction and hover in the air, the rotation generates a rotation speed difference through adjusting the rotation speed of the blades of the plurality of tangential control rotors 4 when the unmanned aerial vehicle rotates to meet the requirement of multi-angle sightseeing of personnel in the manned cabin, and the rotation torque can be generated to realize the steering of the unmanned aerial vehicle. Alternatively, the tangential control rotor 4 may be an electrically driven rotor.
In the embodiment of the invention, the manned unmanned aerial vehicle further comprises a control device, and the control device is used for controlling the ducted fan 2, the vertical balance assembly and the tangential control assembly to act. Specifically, be provided with the first drive arrangement that is used for driving the rotatory rotation axis of ducted fan 2 on ducted fan 2, be provided with the rotatory second drive arrangement of rotation axis that is used for driving vertical balanced rotor 3 on every vertical balanced rotor 3 in the vertical balanced subassembly, be provided with the rotatory third drive arrangement of rotation axis that is used for driving tangential control rotor 4 on every tangential control rotor 4 in the tangential control subassembly, controlling means can with first drive arrangement, second controlling means and third controlling means signal connection. At the in-process of operation manned unmanned aerial vehicle flight, send flight instruction by the ground satellite station, controlling means receives the flight instruction that the ground satellite station sent, and according to the action of first drive arrangement of flight instruction control, second drive arrangement and third drive arrangement, and then control duct fan 2, the action of vertical balanced subassembly and tangential control subassembly, the control of realization unmanned aerial vehicle that can convenient and fast reduces the high altitude sightseeing and experiences the cost of project. Alternatively, the first driving device may be an engine, and the second and third driving devices may be driving motors.
In the above embodiment of the invention, the hatch cover 12 may be a transparent hatch cover 12, which can widen and unblock the view of passengers inside the passenger compartment, and is convenient for sightseeing. Specifically, manned cabin can set up around the duct, can guarantee passenger's the field of vision for the passenger has higher sightseeing in unmanned aerial vehicle inside and experiences, and, unmanned aerial vehicle overall structure is compact, and space utilization is high, and area is little.
In the embodiment of the invention, the machine body 1 can be set into a circular disk shape, has a unique and scientific shape, and has strong visual impact force and new attraction.
Specifically, at least one seat 6 is provided in the passenger cabin B. Alternatively, four seats 6 may be evenly arranged at equal intervals inside the passenger cabin B for carrying passengers.
In the above-described embodiment of the invention, the door 121 may be a slidable door to facilitate passengers to enter and exit the passenger cabin B.
In the embodiment of the invention, the base 11 is provided with the plurality of uniformly distributed foot supports 5, so that the unmanned aerial vehicle can conveniently stop on the scenic spot.
It will be apparent to those skilled in the art that various changes and modifications may be made in the embodiments of the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (10)
1. A manned unmanned aerial vehicle, comprising:
the aircraft comprises an aircraft body, wherein the aircraft body comprises a duct and a manned cabin, the duct is positioned in the middle of the aircraft body, the manned cabin is positioned outside the duct, and the duct is isolated from the manned cabin;
a ducted fan located within the duct;
the vertical balance assembly is arranged on the machine body and used for keeping the machine body balanced in flight;
the tangential control assembly is arranged on the machine body and used for controlling the plane flight and the steering of the machine body.
2. The manned unmanned aerial vehicle of claim 1, wherein the fuselage comprises a base and a deck lid positioned on the base, the deck lid cooperating with the base and a duct to enclose the manned cabin, the deck lid having a door thereon.
3. The manned unmanned aerial vehicle of claim 2, wherein the vertical balancing assembly comprises a plurality of individually controllable vertical balancing rotors, the plurality of vertical balancing rotors are evenly distributed at equal intervals on the outer edge of the bottom of the unmanned aerial vehicle, and the extension direction of the rotation axis of each vertical balancing rotor is parallel to the extension direction of the rotation axis of the ducted fan.
4. The manned unmanned aerial vehicle of claim 2, wherein the tangential control assembly comprises a plurality of individually controllable tangential control rotors, the plurality of tangential control rotors are evenly distributed at equal intervals on the outer edge of the bottom of the aircraft, and the extension directions of the rotation axes of the plurality of tangential control rotors are the same and are perpendicular to the extension direction of the rotation axis of the ducted fan.
5. The manned unmanned aerial vehicle of claim 2, wherein the hatch is a transparent hatch.
6. The manned drone of claim 5, wherein the manned nacelle is disposed about the duct.
7. The manned unmanned aerial vehicle of claim 2, wherein the machine base is provided with a plurality of evenly distributed footrests.
8. The manned unmanned aerial vehicle of claim 1, wherein the fuselage is shaped as a circular dish.
9. The manned unmanned aerial vehicle of claim 1, wherein at least one seat is disposed within the manned cabin.
10. The manned unmanned aerial vehicle of claim 1, further comprising a control device for controlling the action of the ducted fan, vertical balancing component, and tangential control component.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011561177.0A CN112607021A (en) | 2020-12-25 | 2020-12-25 | Manned unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011561177.0A CN112607021A (en) | 2020-12-25 | 2020-12-25 | Manned unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112607021A true CN112607021A (en) | 2021-04-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011561177.0A Pending CN112607021A (en) | 2020-12-25 | 2020-12-25 | Manned unmanned aerial vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN112607021A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113212770A (en) * | 2021-05-25 | 2021-08-06 | 象限空间（天津）科技有限公司 | Aircraft power plant control system |
| CN113581475A (en) * | 2021-08-31 | 2021-11-02 | 王智强 | Circular disc wing solar electric airplane |
| CN115258145A (en) * | 2022-04-19 | 2022-11-01 | 上海电气集团股份有限公司 | Unmanned aerial vehicle and unmanned aerial vehicle cruise system |
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| CN106986028A (en) * | 2017-03-14 | 2017-07-28 | 西华大学 | A kind of disc-shaped flying craft |
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| CN111717382A (en) * | 2020-05-27 | 2020-09-29 | 西南科技大学 | Many rotor crafts of medium are striden to empty amphibious of water |
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2020
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| CN105109686A (en) * | 2015-09-15 | 2015-12-02 | 长沙冠创控制科技有限公司 | Saucer-shaped aircraft and autonomous flight system |
| CN105217027A (en) * | 2015-09-24 | 2016-01-06 | 苏州大闹天宫机器人科技有限公司 | Vertical takeoff and landing formula bimodal airflight equipment and control method thereof |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113212770A (en) * | 2021-05-25 | 2021-08-06 | 象限空间（天津）科技有限公司 | Aircraft power plant control system |
| CN113581475A (en) * | 2021-08-31 | 2021-11-02 | 王智强 | Circular disc wing solar electric airplane |
| CN115258145A (en) * | 2022-04-19 | 2022-11-01 | 上海电气集团股份有限公司 | Unmanned aerial vehicle and unmanned aerial vehicle cruise system |
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Application publication date: 20210406 |