CN111846213A

CN111846213A - Many rotors manned vehicle

Info

Publication number: CN111846213A
Application number: CN202010738739.8A
Authority: CN
Inventors: 叶殊钨
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-07-28
Filing date: 2020-07-28
Publication date: 2020-10-30

Abstract

The invention discloses a multi-rotor manned aircraft, which comprises a manned cabin, a lifting rotor, an equipment bin and a steering rudder, wherein the equipment bin is 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 an undercarriage, the side 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 circumferentially distributed on the upper part of the manned cabin, 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 rear part of the manned cabin. The invention has the advantages of small size, flexibility, low altitude, low speed, vertical lifting, economy and practicality.

Description

Many rotors manned vehicle

Technical Field

The invention relates to the technical field of aircrafts, in particular to a manned aircraft with multiple rotor wings.

Background

Throughout the world, the existing manned aircraft suitable for being owned and driven by the general public is almost blank, and the existing personal manned aircraft researched and developed at home and abroad commonly has 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 aircraft which is small, flexible, low-altitude, low-speed, vertical-lifting, economical and practical is the development direction of the future era of the personal manned aircraft.

Disclosure of Invention

Aiming at the defects in the prior art, the invention provides a multi-rotor manned aircraft which has the same flying 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 aircraft 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 an undercarriage, the side 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 circumferentially distributed on the upper part of the manned cabin, 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 rear part of the manned cabin.

Furthermore, the manned cabin is of a capsule-shaped structure, and the cross section of the manned cabin is circular to accommodate single people for riding, or is in a strip shape to accommodate three people for riding, or is in a rectangular shape to accommodate more than three people for riding.

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 uniformly distributed on the upper part of the manned cabin 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.

Furthermore, the bottom of the undercarriage is provided with a telescopic sliding wheel.

Furthermore, the undercarriage is of a cover-shaped structure with a trapezoidal vertical section.

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 closed manned cabin is additionally arranged in the middle of the rotor 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 aircraft, the 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 aircraft, the lifting rotor wing is positioned at the upper part of the capsule manned cabin, and the gravity center of the aircraft is positioned below the lifting rotor wing, so that the stable flight of the aircraft is facilitated;

6. compared with the existing personal aircraft, the invention adopts the steering rudder arranged at the rear part of the manned cabin, so that the aircraft is more flexible to steer and control;

7. compared with the existing personal aircraft, the personal aircraft at home and abroad is expensive in cost because the personal aircraft at present pursues to fly high and fast, and the common people cannot consume the personal aircraft.

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 embodiment 1;

FIG. 2 is a top view of embodiment 1;

FIG. 3 is a side view of embodiment 1;

FIG. 4 is a front view of embodiment 2;

FIG. 5 is a plan view of embodiment 2;

FIG. 6 is a side view of embodiment 2;

FIG. 7 is a front view of embodiment 3;

FIG. 8 is a top view of example 3;

FIG. 9 is a side view of example 3.

In the attached drawings, 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, an undercarriage 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.

Example 1

As shown in fig. 1, 2 and 3, a multi-rotor manned aircraft comprises a manned cabin 1, a lifting rotor 5, an equipment bin 8 and a steering rudder 10;

the upper part of the manned cabin 1 is provided with a window 7, the bottom edge is provided with an undercarriage 9, the side wall is provided with a cabin door 4, the outer walls of the two sides are respectively provided with a side pushing rotor wing 2, and the rear end of the side pushing rotor wing 2 is provided with a first power device 3 for driving the side pushing rotor wing 2 to operate; the manned cabin 1 is of a capsule-shaped structure, and the cross section of the manned cabin is circular so as to accommodate a single person to sit;

the number of the lifting rotor wings 5 is six, the lifting rotor wings are circumferentially distributed on the upper part of the manned cabin 1, 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 rear 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 evenly distributed in manned cabin 1's upper portion to through the linking arm with the outer wall connection that manned cabin 1 corresponds, the focus of aircraft is located below lifting rotor 5, is favorable to the stable flight of aircraft.

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 bottom of the undercarriage 9 is provided with a retractable gliding wheel, which facilitates short-distance transfer of the aircraft before takeoff or after landing.

Specifically, undercarriage 9 is trapezoidal cover column structure for erecting the cross-section, promotes undercarriage 9 and to the holistic support effect of aircraft, promotes aircraft stability of taking off and landing.

Example 2

As shown in fig. 4, 5 and 6, the difference from embodiment 1 is that:

manned cabin 1 is the capsule column structure, and its cross section is the bar in order to hold three people and take, and lifts rotor 5 and be provided with ten to circumference distributes in manned cabin 1's upper portion and window 7's top.

Specifically, the first power device 3 and the second power device 6 adopt engines, and the power source is fuel oil.

Example 3

As shown in fig. 7, 8 and 9, the difference from embodiment 1 is that:

the manned cabin 1 is of a capsule-shaped structure, the cross section of the manned cabin is rectangular so as to accommodate more than three persons to sit, and eighteen lifting rotor wings 5 are arranged and circumferentially distributed on the upper part of the manned cabin 1 and above the window 7; the outer wall of the two sides of the manned cabin 1 is respectively provided with two side-push rotor wings 2, and the two side-push rotor wings 2 at the same side are positioned on the same axis.

Specially, the rudder 10 sets up in manned cabin 1's rear portion, when manned cabin 1's cabin body is longer broad, the rudder 10 turns to and controls the not good condition of effect, can turn to rudder 10 and replace into the rotor that turns to, through turning to rotor forward and reverse rotation production forward and reverse thrust and promote manned cabin 1's cabin body to turn to.

Working principle of embodiment 1, embodiment 2 and embodiment 3:

the driver and passengers enter the manned cabin 1 to take the seats, the aircraft is controlled by a driver 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 occupied area of the aircraft, and the aircraft can take off and land in a smaller field; the capsule-shaped manned cabin 1 can be vertically arranged to lower the center of gravity of the aircraft, so that the stability of the aircraft 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 aircraft can be controlled by controlling the rotating speed of the side-thrust rotor 2; the low-altitude low-speed running, vertical takeoff and landing of the aircraft can be realized by simultaneously controlling the lifting rotor 5 and the side-pushing rotor 2; the flight direction of the aircraft can be changed by adjusting the angle of the rudder 10.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; 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

1. The utility model provides a many rotors manned vehicle 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), an undercarriage (9) is arranged at the edge of the bottom of the manned cabin, a cabin door (4) is arranged on the side 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 first power equipment (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 at least two and are circumferentially distributed on the upper part of the manned cabin (1), 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 rear part of the manned cabin (1).

2. The multi-rotor manned vehicle of claim 1, wherein: the manned cabin (1) is of a capsule-shaped structure, and the cross section of the manned cabin is circular to accommodate single people for riding, or is in a strip shape to accommodate three people for riding, or is in a rectangular shape to accommodate more than three people for riding.

3. The multi-rotor manned vehicle of claim 1, wherein: a parachute (11) is arranged at the top of the manned cabin (1).

4. The multi-rotor manned vehicle of claim 1, wherein: a first guide cylinder cover (12) is vertically arranged outside the lifting rotor wing (5).

5. A multi-rotor manned vehicle according to claim 1 or 4 wherein: each lift rotor (5) evenly distributed in the upper portion of manned cabin (1) to through the linking arm with the outer wall connection that manned cabin (1) corresponds.

6. The multi-rotor manned vehicle of claim 1, wherein: and a second guide cylinder cover (13) is horizontally arranged outside the side-push rotor (2).

7. The multi-rotor manned vehicle of claim 1, wherein: the first power equipment (3) and the second power equipment (6) both adopt engines or motors.

8. The multi-rotor manned vehicle of 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. The multi-rotor manned vehicle of claim 1, wherein: the bottom of the landing gear (9) is provided with a telescopic sliding wheel.

10. A multi-rotor manned vehicle according to claim 1 or 9 wherein: the undercarriage (9) is of a cover-shaped structure with a trapezoidal vertical section.