CN111846194A - Manned helicopter with multiple rotor wings - Google Patents
Manned helicopter with multiple rotor wings Download PDFInfo
- Publication number
- CN111846194A CN111846194A CN202010845917.7A CN202010845917A CN111846194A CN 111846194 A CN111846194 A CN 111846194A CN 202010845917 A CN202010845917 A CN 202010845917A CN 111846194 A CN111846194 A CN 111846194A
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- Prior art keywords
- manned
- cabin
- rotor
- lifting
- manned cabin
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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
- B64C1/22—Other structures integral with fuselages to facilitate loading, e.g. cargo bays, cranes
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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
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1476—Canopies; Windscreens or similar transparent elements
- B64C1/1484—Windows
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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
- B64C7/00—Structures or fairings not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- 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
- B64D17/00—Parachutes
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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Abstract
The invention discloses a multi-rotor manned helicopter, which comprises a manned cabin, lifting rotors, an equipment bin and a steering rudder, wherein the lifting rotors are arranged on the manned cabin; the upper part of the manned cabin is provided with a window, the edge of the bottom of the manned cabin is provided with a sliding wheel, the rear wall of the manned cabin is provided with a cabin door, the outer walls of two sides of the manned cabin are respectively provided with a side-push rotor wing, and the rear end of the side-push rotor wing is provided with a first power device for driving the side-push rotor wing to operate; the lifting rotor wings are arranged at least two and distributed on two sides of the manned cabin side by side, and the lower end of each lifting rotor wing is respectively provided with second power equipment for driving the lifting rotor wings to operate; the equipment bin is arranged at the bottom of the manned cabin, and a power source for the first power equipment and the second power equipment to run is arranged in the equipment bin; the steering rudder is arranged at the top of the manned cabin. The invention has the advantages of small size, flexibility, low altitude, low speed, vertical lifting, economy and practicality.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a manned helicopter with multiple rotors.
Background
Throughout the world, the manned helicopters which can be owned and driven by the common people are almost blank at present, and the personal manned helicopters researched and developed at present at home and abroad generally have the following problems: firstly, the operation difficulty is high, and professional operation is required; secondly, the vehicle flies high and quickly and is not suitable for being used as a vehicle for ordinary people in cities and villages to go out daily; thirdly, the wingspan is large, the occupied space is large, and the requirements on take-off and landing fields are high; fourthly, the design is complex and the price is high. Therefore, the smart helicopter which is small, flexible, low-altitude, low-speed, vertical-lifting, economical and practical will be the development direction of the future personal manned aircraft era.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a multi-rotor manned helicopter which has the same flying, taking off and landing types as an unmanned aircraft and has the advantages of small size, flexibility, low altitude, low speed, vertical lifting, economy and practicability.
A multi-rotor manned helicopter comprises a manned cabin, a lifting rotor, an equipment bin and a steering rudder;
the upper part of the manned cabin is provided with a window, the edge of the bottom of the manned cabin is provided with a sliding wheel, the rear wall of the manned cabin is provided with a cabin door, the outer walls of two sides of the manned cabin are respectively provided with a side-push rotor wing, and the rear end of the side-push rotor wing is provided with a first power device for driving the side-push rotor wing to operate;
the lifting rotor wings are at least two and are distributed on two sides of the manned cabin in parallel, and the lower end of each lifting rotor wing is respectively provided with second power equipment for driving the lifting rotor wings to operate;
the equipment bin is arranged at the bottom of the manned cabin, and a power source for the first power equipment and the second power equipment to run is arranged in the equipment bin;
the steering rudder is arranged at the top of the manned cabin.
Furthermore, the manned cabin is of a capsule-shaped structure, and the cross section of the manned cabin is ship-shaped so as to accommodate a plurality of people to sit.
Furthermore, a parachute is arranged at the top of the manned cabin.
Further, lift the outer vertical first draft tube cover that is provided with of rotor.
Furthermore, each lifting rotor wing is distributed on two sides of the manned cabin in parallel and is connected with the outer wall corresponding to the manned cabin through a connecting arm.
Further, a second guide cylinder cover is horizontally arranged outside the side-pushing rotor wing.
Further, the first power equipment and the second power equipment both adopt engines or motors.
Further, when the first power equipment and the second power equipment both adopt engines, the power source is fuel oil; when the first power equipment and the second power equipment both adopt motors, the power source is a storage battery.
Further, the sliding wheel is provided with a shock absorption function.
The invention has the beneficial effects that:
1. compared with the jet aircraft in the prior art, the lifting rotor wing is adopted to realize vertical take-off, landing and hovering, and the jet aircraft can fall down when stalled and can vertically take-off, land and hover, so that the jet aircraft is more suitable for being used as a vehicle for ordinary people to go out daily;
2. compared with the single-rotor helicopter in the prior art, the lifting rotor type helicopter has the advantages that at least two lifting rotors are adopted to provide lifting force, the controllability is better, the safety is higher, the plurality of lifting rotors provide the lifting force more stably, so the controllability is better, and meanwhile, if one of the plurality of lifting rotors breaks down, the other lifting rotors can still continue to provide the lifting force, so the safety is higher;
3. compared with the helicopter in the prior art, the helicopter in the prior art generates the side-push power by the aid of the inclination angle of the rotor wing, and the side-push rotor wings arranged on two sides of the manned cabin directly provide the side-push power;
4. compared with the helicopter in the prior art, the invention has the advantages that a closed manned cabin is additionally arranged in the middle of the rotor wings of the multi-rotor unmanned aircraft, the occupied area is small, and the takeoff and landing are not limited by the field; meanwhile, the projection occupied area of the manned cabin and the lifting rotor wing can be optimized to be small enough through calculation, and the lifting rotor wing can be better suitable for the common people; in addition, compared with the existing open type personal manned aircraft, the unmanned aircraft is more beneficial to the safety and comfort of drivers and passengers, and is suitable for all-weather flight.
5. Compared with the existing personal manned aircraft, the lifting rotor wing is positioned in the middle of the capsule manned cabin, and the gravity center of the aircraft is positioned below the lifting rotor wing, so that the aircraft can stably fly;
6. compared with the existing personal manned aircraft, the manned aircraft has the advantages that the steering rudder is arranged at the top of the manned cabin, so that the aircraft is more flexible to steer and control;
7. compared with the existing personal manned aircraft, the personal manned aircraft at home and abroad has the advantages of high flying speed, high manufacturing cost and low consumption of common people, and the personal manned aircraft is simple in design, stable and practical in pursuit and low in cost, can be purchased by common people and can be used as a vehicle for common people to go on a daily trip.
In conclusion, the flying and taking-off and landing device of the invention is similar to an unmanned aerial vehicle, and has the advantages of small size, flexibility, low altitude, low speed, vertical lifting, economy and practicability.
Drawings
In order to more clearly illustrate the detailed description of the invention or the technical solutions in the prior art, the drawings that are needed in the detailed description of the invention or the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.
FIG. 1 is a front view of the embodiment;
FIG. 2 is a top view of the embodiment;
FIG. 3 is a side view of the embodiment;
in the attached figure, a manned cabin 1, a side-push rotor 2, a first power device 3, a cabin door 4, a lifting rotor 5, a second power device 6, a window 7, an equipment cabin 8, a sliding wheel 9, a steering rudder 10, a parachute 11, a first air guide cylinder cover 12 and a second air guide cylinder cover 13.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and therefore are only examples, and the protection scope of the present invention is not limited thereby.
It is to be noted that, unless otherwise specified, technical or scientific terms used herein shall have the ordinary meaning as understood by those skilled in the art to which the invention pertains.
Examples
As shown in fig. 1, 2 and 3, a multi-rotor manned helicopter comprises a manned cabin 1, a lifting rotor 5, an equipment bin 8 and a steering rudder 10;
the manned cabin 1 is provided with a window 7 at the upper part, a sliding wheel 9 is arranged at the edge of the bottom, a cabin door 4 is arranged on the rear wall, two lateral pushing rotors 2 are respectively arranged on the outer walls of the two sides, the two lateral pushing rotors 2 on the same side are positioned on the same axis, and a first power device 3 for driving the lateral pushing rotors 2 to operate is arranged at the rear end of each lateral pushing rotor 2; the manned cabin 1 is of a capsule-shaped structure, and the cross section of the manned cabin is ship-shaped to accommodate a plurality of people to sit;
twelve lifting rotor wings 5 are arranged and distributed on two sides of the manned cabin 1 in parallel, and the lower end of each lifting rotor wing 5 is respectively provided with a second power device 6 for driving the lifting rotor wings 5 to operate;
the equipment bin 8 is arranged at the bottom of the manned cabin 1, and a power source for the first power equipment 3 and the second power equipment 6 to run is arranged in the equipment bin; the first power equipment 3 and the second power equipment 6 adopt motors, and the power source is a storage battery;
the rudder 10 is arranged at the top of the passenger compartment 1.
Specifically, the parachute 11 is arranged at the top of the manned cabin 1, so that the safety of drivers and passengers can be guaranteed in an emergency.
Specifically, lift rotor 5 outer vertical be provided with first kuppe 12, lift force gathering degree that lift rotor 5 operation produced to the energy utilization who promotes the power supply also can play the effect that the rotor 5 was lifted in the protection.
Specifically, each lift rotor 5 distribute in side by side manned cabin 1's both sides to through the linking arm with manned cabin 1 corresponds outer wall connection, helicopter's focus is located below lifting rotor 5, is favorable to helicopter's stable flight.
Specifically, the outer level of side thrust rotor 2 is provided with second draft tube cover 13, promotes the side thrust gathering degree that the operation of side thrust rotor 2 produced to promote the energy utilization of power supply, also can play the effect that the protection side pushed rotor 2.
Specifically, the glide wheel 9 has a shock absorption function, and is beneficial to short-distance transfer of the helicopter before takeoff or after landing.
Specially, the rudder 10 that turns to set up in manned cabin 1 top, when manned cabin 1's cabin body is longer broad, turn to rudder 10 and turn to and control under the not good condition of effect, can turn to rudder 10 and replace into the rotor that turns to, produce forward and reverse thrust through turning to the rotor and promote manned cabin 1's cabin body and turn to.
Working principle of the embodiment:
the driver and passengers enter the manned cabin 1 to take the seats, the helicopter is controlled by a pilot or an automatic flight program to fly, and the flying principle is consistent with that of the unmanned aircraft. The capsule manned cabin 1 can reduce the floor area of the helicopter and realize the take-off and landing of the helicopter in a smaller field; the capsule-shaped manned cabin 1 can be vertically arranged to reduce the gravity center of the helicopter, so that the stability of the helicopter is improved; vertical takeoff, landing and hovering of the aircraft can be realized by controlling the rotating speed of the lifting rotor wing 5; the horizontal flying speed of the helicopter can be controlled by controlling the rotating speed of the side-push rotor 2; the helicopter can realize low-altitude low-speed running, vertical takeoff and landing by simultaneously controlling the lifting rotor wing 5 and the side-pushing rotor wing 2; the flight direction of the helicopter can be changed by adjusting the angle of the rudder 10.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention, and they should be construed as being included in the following claims and description.
Claims (9)
1. The utility model provides a manned helicopter of many rotors which characterized in that: comprises a manned cabin (1), a lifting rotor wing (5), an equipment cabin (8) and a steering rudder (10);
a window (7) is arranged at the upper part of the manned cabin (1), a sliding wheel (9) is arranged at the edge of the bottom of the manned cabin, a cabin door (4) is arranged on the rear wall of the manned cabin, lateral thrust rotors (2) are respectively arranged on the outer walls of the two sides of the manned cabin, and a first power device (3) for driving the lateral thrust rotors (2) to operate is arranged at the rear ends of the lateral thrust rotors (2);
the lifting rotor wings (5) are arranged at least two and are distributed on two sides of the manned cabin (1) in parallel, and the lower end of each lifting rotor wing (5) is respectively provided with a second power device (6) for driving the lifting rotor wings (5) to operate;
the equipment bin (8) is arranged at the bottom of the manned cabin (1), and a power source for the first power equipment (3) and the second power equipment (6) to run is arranged in the equipment bin;
the steering rudder (10) is arranged at the top of the manned cabin (1).
2. A multi-rotor manned helicopter according to claim 1 wherein: the manned cabin (1) is of a capsule-shaped structure, and the cross section of the manned cabin is ship-shaped so as to accommodate a plurality of people to sit.
3. A multi-rotor manned helicopter according to claim 1 wherein: a parachute (11) is arranged at the top of the manned cabin (1).
4. A multi-rotor manned helicopter according to claim 1 wherein: a first guide cylinder cover (12) is vertically arranged outside the lifting rotor wing (5).
5. A multi-rotor manned helicopter according to claim 1 or 4, wherein: each lifting rotor wing (5) is distributed on two sides of the manned cabin (1) in parallel and is connected with the outer wall corresponding to the manned cabin (1) through a connecting arm.
6. A multi-rotor manned helicopter according to claim 1 wherein: and a second guide cylinder cover (13) is horizontally arranged outside the side-push rotor (2).
7. A multi-rotor manned helicopter according to claim 1 wherein: the first power equipment (3) and the second power equipment (6) both adopt engines or motors.
8. A multi-rotor manned helicopter according to claim 7 wherein: when the first power equipment (3) and the second power equipment (6) both adopt engines, the power source is fuel oil; when the first power equipment (3) and the second power equipment (6) both adopt motors, the power source is a storage battery.
9. A multi-rotor manned helicopter according to claim 1 wherein: the sliding wheel (9) is provided with a damping function.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010845917.7A CN111846194A (en) | 2020-08-20 | 2020-08-20 | Manned helicopter with multiple rotor wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010845917.7A CN111846194A (en) | 2020-08-20 | 2020-08-20 | Manned helicopter with multiple rotor wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111846194A true CN111846194A (en) | 2020-10-30 |
Family
ID=72968907
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010845917.7A Pending CN111846194A (en) | 2020-08-20 | 2020-08-20 | Manned helicopter with multiple rotor wings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111846194A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112193411A (en) * | 2020-10-31 | 2021-01-08 | 叶殊钨 | Multi-rotor aerocar |
| CN112693602A (en) * | 2021-01-25 | 2021-04-23 | 叶殊钨 | Many rotors manned vehicle that side pushes away power device for duct formula |
| WO2022040948A1 (en) * | 2020-08-26 | 2022-03-03 | 叶殊钨 | Multirotor manned aerial vehicle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2521121C1 (en) * | 2013-02-21 | 2014-06-27 | Дмитрий Сергеевич Дуров | Heavy-duty multirotor convertible rotorcraft |
| RU2014107956A (en) * | 2014-03-03 | 2015-09-10 | Андрей Зелимханович Парастаев | VERTICAL RETAINING VEHICLE WITH VERTICAL TAKEOFF |
| CN105905291A (en) * | 2016-06-04 | 2016-08-31 | 刘海涛 | Multi-rotor craft with tilting rotors |
| CN109229356A (en) * | 2018-10-30 | 2019-01-18 | 佛山市神风航空科技有限公司 | A kind of more rotor manned aircraft |
| RU2017143420A (en) * | 2017-12-12 | 2019-06-13 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли России | Unmanned aerial vehicle vertical takeoff and landing |
| CN111071438A (en) * | 2019-12-20 | 2020-04-28 | 文红军 | Double-duct manned aircraft |
-
2020
- 2020-08-20 CN CN202010845917.7A patent/CN111846194A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2521121C1 (en) * | 2013-02-21 | 2014-06-27 | Дмитрий Сергеевич Дуров | Heavy-duty multirotor convertible rotorcraft |
| RU2014107956A (en) * | 2014-03-03 | 2015-09-10 | Андрей Зелимханович Парастаев | VERTICAL RETAINING VEHICLE WITH VERTICAL TAKEOFF |
| CN105905291A (en) * | 2016-06-04 | 2016-08-31 | 刘海涛 | Multi-rotor craft with tilting rotors |
| RU2017143420A (en) * | 2017-12-12 | 2019-06-13 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли России | Unmanned aerial vehicle vertical takeoff and landing |
| CN109229356A (en) * | 2018-10-30 | 2019-01-18 | 佛山市神风航空科技有限公司 | A kind of more rotor manned aircraft |
| CN111071438A (en) * | 2019-12-20 | 2020-04-28 | 文红军 | Double-duct manned aircraft |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022040948A1 (en) * | 2020-08-26 | 2022-03-03 | 叶殊钨 | Multirotor manned aerial vehicle |
| CN112193411A (en) * | 2020-10-31 | 2021-01-08 | 叶殊钨 | Multi-rotor aerocar |
| CN112693602A (en) * | 2021-01-25 | 2021-04-23 | 叶殊钨 | Many rotors manned vehicle that side pushes away power device for duct formula |
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