CN111846213A - multi-rotor manned aircraft - Google Patents

Abstract

The invention discloses a multi-rotor manned aircraft, comprising a manned cabin, a lifting rotor, an equipment compartment and a steering rudder; the upper part of the manned cabin is provided with a viewing window, the bottom edge is provided with a landing gear, and the side wall is provided with a hatch door , the outer walls on both sides are also provided with side thrust rotors respectively, and the rear end of the side thrust rotors is provided with the first power equipment for driving the side thrust rotors to operate; the lift rotors are provided with at least two and are distributed circumferentially. On the upper part of the manned cabin, the lower end of each lift rotor is respectively provided with a second power device that drives the lift rotor to operate; the equipment compartment is arranged at the bottom of the manned cabin, inside A power source for the operation of the first power equipment and the second power equipment is provided; the steering rudder is provided at the rear of the manned cabin. The flight, take-off and landing of the present invention are similar to unmanned aerial vehicles, and have the advantages of small size and flexibility, low altitude and low speed, vertical lift, economical and practical advantages.

Description

multi-rotor manned aircraft

technical field

The invention relates to the technical field of aircraft, in particular to a multi-rotor manned aircraft.

Background technique

Looking at the world, there are almost no manned aircraft that can be owned and driven by ordinary people at present. The personal manned aircraft currently developed at home and abroad generally have the following problems: 1. It is difficult to control and requires professionals to operate; 2. It can fly well It can fly fast and is not suitable as a means of transportation for ordinary people in urban and rural areas; 3. It has a large wingspan and occupies a large space, and has high requirements for take-off and landing sites; 4. The design is complex and expensive. Therefore, small and flexible, low-altitude and low-speed, vertical lift, economical and practical intelligent aircraft will be the development direction of the future era of personal manned aircraft.

SUMMARY OF THE INVENTION

In view of the defects in the prior art, the present invention provides a multi-rotor manned aircraft that flies, take off and land similarly to an unmanned aircraft, which has the advantages of small size and flexibility, low altitude and low speed, vertical lift, economical and practical advantages.

A multi-rotor manned aircraft, comprising a manned cabin, a lift rotor, an equipment bay and a steering rudder;

The upper part of the manned cabin has a viewing window, the bottom edge is provided with a landing gear, the side walls are provided with hatches, and the outer walls on both sides are respectively provided with side thrust rotors, and the rear end of the side thrust rotors is provided with a drive to drive the side thrusters. The first power equipment for rotor operation;

The lift rotors are provided with at least two and are circumferentially distributed on the upper part of the manned cabin, and the lower end of each lift rotor is respectively provided with a second power device for driving the lift rotor to operate;

The equipment compartment is arranged at the bottom of the manned cabin, and a power source for the operation of the first power equipment and the second power equipment is arranged therein;

The steering rudder is arranged at the rear of the manned cabin.

Further, the manned cabin is a capsule-shaped structure, and its cross section is circular to accommodate a single person, or a strip shape to accommodate three people, or a rectangle to accommodate more than three people.

Further, the top of the manned cabin is provided with a parachute.

Further, a first deflector cover is vertically disposed outside the lift rotor.

Further, each of the lifting rotors is evenly distributed on the upper part of the manned cabin, and is connected to the corresponding outer wall of the manned cabin through a connecting arm.

Further, a second guide tube cover is horizontally arranged outside the side thrust rotor.

Further, both the first power equipment and the second power equipment use an engine or an electric motor.

Further, when both the first power equipment and the second power equipment use an engine, the power source is fuel; when both the first power equipment and the second power equipment use an electric motor, the power source is a battery pack.

Further, the bottom of the landing gear is provided with retractable skid wheels.

Further, the landing gear is a hood-shaped structure with a trapezoidal vertical section.

The beneficial effects of the present invention are embodied in:

1, compared with the jet aircraft of the prior art, the present invention adopts the lifting rotor to realize vertical take-off and landing and hovering, because the jet aircraft stalls and will fall, and the rotorcraft can take off and land vertically and hover, so the rotorcraft is more suitable as a The means of transportation for ordinary people to travel on a daily basis;

2. Compared with the single-rotor helicopter in the prior art, the present invention adopts at least two lifting rotors to provide lifting force, which has better controllability and higher safety, because the lifting force provided by multiple lifting rotors is more stable. Therefore, the controllability is better. At the same time, if one of the lifting rotors fails, the remaining lifting rotors can continue to provide lifting force, so the safety is higher;

3. Compared with the helicopter of the prior art, the present invention adopts the side thrust rotor to provide the side thrust, and the side thrust is stronger and easier to control the flight speed, because the helicopter of the prior art relies on the inclination of the rotor to generate the side thrust. , and the present invention directly provides side thrust by means of side thrust rotors installed on both sides of the manned cabin;

4. Compared with the helicopter of the prior art, the present invention adds a closed manned cabin design in the middle of the rotor of the multi-rotor unmanned aerial vehicle, which occupies a small area and is not restricted by the site for take-off and landing. Because the wingspan of the helicopter in the prior art is large, it needs a professional airport to take off and land, but the structure of the present invention is small and compact, and can achieve take-off and landing in conventional positions such as balcony/roof; at the same time, the manned cabin and lift The projected area of the lift rotor can be optimized to be small enough by calculation, which can be better suitable for ordinary people; in addition, compared with the existing open personal aircraft, it is more conducive to the safety and comfort of the pilots and passengers, and is suitable for all-weather flight.

5. Compared with the existing personal aircraft, the lifting rotor of the present invention is located at the upper part of the capsule-shaped manned cabin, and the center of gravity of the aircraft is located below the lifting rotor, which is beneficial to the stable flight of the aircraft;

6. Compared with the existing personal aircraft, the present invention adopts a steering rudder at the rear of the manned cabin, and the steering control of the aircraft is more flexible;

7. Compared with the existing personal aircraft, because the current domestic and foreign personal aircraft pursues to fly high and fast, so the cost is expensive, and ordinary people cannot afford it. It is affordable and can be used as a means of transportation for ordinary people to travel daily.

To sum up, the flight, take-off and landing of the present invention are similar to unmanned aerial vehicles, and have the advantages of small size and flexibility, low altitude and low speed, vertical lift, economical and practical advantages.

Description of drawings

In order to illustrate the specific embodiments of the present invention or the technical solutions in the prior art more clearly, the following briefly introduces the accompanying drawings that are required to be used in the description of the specific embodiments or the prior art. Similar elements or parts are generally identified by similar reference numerals throughout the drawings. In the drawings, each element or section is not necessarily drawn to actual scale.

Fig. 1 is the front view of embodiment 1;

Fig. 2 is the top view of embodiment 1;

Fig. 3 is the side view of embodiment 1;

Fig. 4 is the front view of embodiment 2;

Fig. 5 is the top view of embodiment 2;

Fig. 6 is the side view of embodiment 2;

Fig. 7 is the front view of embodiment 3;

Fig. 8 is the top view of embodiment 3;

FIG. 9 is a side view of Embodiment 3. FIG.

In the drawings, manned cabin 1, side thrust rotor 2, first power equipment 3, hatch 4, lift rotor 5, second power equipment 6, window 7, equipment compartment 8, landing gear 9, steering rudder 10, Parachute 11 , first deflector cover 12 , second deflector cover 13 .

Detailed ways

Embodiments of the technical solutions of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only used to more clearly illustrate the technical solutions of the present invention, and are therefore only used as examples, and cannot be used to limit the protection scope of the present invention.

It should be noted that, unless otherwise specified, the technical or scientific terms used in this application should have the usual meanings understood by those skilled in the art to which the present invention belongs.

Example 1

As shown in FIG. 1 , FIG. 2 and FIG. 3 , a multi-rotor manned aircraft includes a manned cabin 1 , a lift rotor 5 , an equipment compartment 8 and a steering rudder 10 ;

The upper part of the manned cabin 1 has a viewing window 7, the bottom edge is provided with a landing gear 9, the side walls are provided with a hatch 4, and the outer walls on both sides are respectively provided with a side thruster 2, and the rear end of the side thruster 2 is provided. A first power device 3 for driving the side thrust rotor 2 is provided; wherein, the manned cabin 1 is a capsule-shaped structure, and its cross-section is circular to accommodate a single person;

The lifting rotors 5 are provided with six and are circumferentially distributed on the upper part of the manned cabin 1, and the lower end of each lifting rotor 5 is respectively provided with a second power for driving the lifting rotor 5 to operate. equipment 6;

The equipment compartment 8 is arranged at the bottom of the passenger compartment 1, and is provided with a power source for the operation of the first power equipment 3 and the second power equipment 6; wherein the first power equipment 3 and the second power The equipment 6 adopts an electric motor, and the power source is a battery pack;

The steering rudder 10 is arranged at the rear of the passenger compartment 1 .

Specifically, a parachute 11 is provided on the top of the passenger compartment 1, which can ensure the safety of the driver and passenger in an emergency.

Specifically, a first deflector cover 12 is vertically arranged outside the lift rotor 5 to increase the degree of accumulation of the lifting force generated by the operation of the lift rotor 5, thereby improving the energy utilization rate of the power source and also protecting the lift. The role of the lift rotor 5.

Specifically, each of the lifting rotors 5 is evenly distributed on the upper part of the manned cabin 1, and is connected to the outer wall corresponding to the manned cabin 1 through the connecting arm. The center of gravity of the aircraft is located under the lifting rotor 5, and there are Conducive to the stable flight of the aircraft.

Specifically, the side thrust rotor 2 is horizontally provided with a second diversion cylinder cover 13 to improve the concentration of the side thrust generated by the operation of the side thrust rotor 2, thereby improving the energy utilization rate of the power source, and also protecting the side thrust The role of rotor 2.

Specifically, retractable skid wheels are provided at the bottom of the landing gear 9 to facilitate the short-distance transfer of the aircraft before take-off or after landing.

Specifically, the landing gear 9 is a hood-shaped structure with a trapezoidal vertical section, which improves the overall supporting effect of the landing gear 9 on the aircraft and improves the landing stability of the aircraft.

Example 2

As shown in Figure 4, Figure 5 and Figure 6, the difference from Embodiment 1 is:

The manned cabin 1 is a capsule-shaped structure, and its cross section is strip-shaped to accommodate three people, and ten lifting rotors 5 are provided, and are circumferentially distributed on the upper part of the manned cabin 1 and the viewing window. 7 above.

Specifically, the first power equipment 3 and the second power equipment 6 use engines, and the power source is fuel.

Example 3

As shown in Figure 7, Figure 8 and Figure 9, the difference from Embodiment 1 is:

The manned cabin 1 is a capsule-shaped structure, and its cross section is rectangular to accommodate more than three people, and eighteen lifting rotors 5 are provided, and are circumferentially distributed on the upper part of the manned cabin 1 and the Above the viewing window 7; two side thrust rotors 2 are respectively arranged on the outer walls of both sides of the manned cabin 1, and the two side thrust rotors 2 on the same side are located on the same axis.

Specifically, the first power equipment 3 and the second power equipment 6 use engines, and the power source is fuel.

In particular, the steering rudder 10 is arranged at the rear of the manned cabin 1. When the cabin of the manned cabin 1 is long and wide, the steering rudder 10 can be replaced when the steering control effect of the steering rudder 10 is not good. A steering rotor is formed, and the forward and reverse thrust is generated by the forward and reverse rotation of the steering rotor to push the cabin of the manned cabin 1 to turn.

The working principle of embodiment 1, embodiment 2 and embodiment 3:

The driver and passengers enter the manned cabin 1 and take a seat. The aircraft is controlled by the driver or the automatic flight program to fly. The flight principle is consistent with the flight principle of the unmanned aerial vehicle. The design of the capsule-shaped manned cabin 1 can reduce the footprint of the aircraft, enabling the aircraft to take off and land on a small site; the vertical layout of the capsule-shaped manned cabin 1 can reduce the center of gravity of the aircraft, thereby increasing the The stability of the aircraft; the vertical take-off, landing and hovering of the aircraft can be realized by controlling the rotation speed of the lift rotor 5; the horizontal flight speed of the aircraft can be controlled by controlling the rotation speed of the side thrust rotor 2; by simultaneously controlling the lift rotor 5 and the side thrust The rotor 2 can realize the low-altitude and low-speed running and vertical take-off and landing of the aircraft; the flight direction of the aircraft can be changed by adjusting the angle of the steering rudder 10 .

Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: The technical solutions described in the foregoing embodiments can still be modified, or some or all of the technical features thereof can be equivalently replaced; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the technical solutions of the embodiments of the present invention. The scope of the invention should be included in the scope of the claims and description of the present invention.

Claims (10)

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.

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