JP2022066645A - Multiple rotor manned aircraft - Google Patents

Abstract

To provide a multiple rotor manned aircraft including a manned cabin, a lifting rotor, an equipment cabin, and a steering wheel.SOLUTION: In the multiple rotor manned aircraft, a window 7 is arranged on an upper part of a manned cabin 1, a landing gear or a sliding wheel is arranged at a bottom part, and a cabin door 4 is arranged on an outer wall. Side thrust rotors 2 are arranged on both sides of the outer wall or on the top, and a first power device for driving the side thrust rotors is arranged at a rear end thereof. At least two lifting rotors 5 are arranged on the periphery of the manned cabin or on both sides in parallel, and a second power device 6 for driving the lifting rotors is arranged at a lower end thereof. An equipment cabin 8 is arranged in a bottom part of the manned cabin. In the equipment cabin, a power source is arranged for operating the first power device and the second power device. A steering wheel is arranged in a rear part of or on the top of the manned cabin. Flight, takeoff, and landing are almost the same as those of unmanned aircrafts. The multiple rotor manned aircraft has advantages in compactness and flexibility, low altitude and low speed, vertical lifting, and economical efficiency and practical utility.SELECTED DRAWING: Figure 1

Description

The present invention relates to the technical field of aircraft, particularly to multirotor manned aircraft.

In today's world, there are few manned aircraft that are owned and suitable for the general public, and personal manned aircraft currently being developed at home and abroad have the following problems: 1. It is difficult to operate and can only be operated by a professional operator. Second, it is not suitable as a means of transportation for ordinary people in cities and villages because it flies high and fast. Third, the wingspan is large and the site space is large, so a place for takeoff and landing is required. Fourth, the design is complicated and expensive. Therefore, small, flexible, low altitude, low speed, vertical lift, and economical and practical smart aircraft are heading towards the future development of personal manned aircraft.

In response to the defects of the prior art, the present invention provides a multi-rotor manned aircraft whose flight, takeoff and landing are similar to those of an unmanned aerial vehicle, and is compact and flexible, low altitude and low speed, vertical ascent and descent, economical and practical. It is characterized by the advantage.

It is a multi-rotor manned aircraft. Includes manned cabins, lifting rotors, equipment cabins, steering wheels, etc.

The top of the described manned cabin has a window, its bottom age is equipped with landing gear or gliding wheels, the outer wall is equipped with cabin doors, and both sides or top of the outer wall are provided with side thrust rotors, respectively. , A first power unit for driving the described side thrust rotor is provided at the rear end of the described side thrust rotor.

There are at least two described lifting rotors, arranged side by side around or on either side of the described manned cabin, at the lower end of each of the described lifting rotors a second power unit that operates the described lifting rotors. Are provided respectively.

The described equipment cabin is located at the bottom of the described manned cabin, in which a power source for operating the first and second power units is provided.

The described steering wheel is located behind or at the top of the described manned cabin.

Further, the described manned cabin is a capsule-shaped structure, and if its cross section is circular, it can be ridden by one person, if it is strip-shaped, it can be ridden by three people, or if it is rectangular, it can be rided by three or more people. Alternatively, in the case of a ship type, it is characterized by being able to carry three or more people.

In addition, there is a parachute on the top of the listed manned cabin.

In addition, a first baffle tube cover is arranged perpendicularly to the outside of the described lifting rotor.

Further, each of the described lifting rotors is arranged in parallel around or on both sides of the manned cabin and is connected to the outer wall of the corresponding manned cabin via a connecting arm.

Further, on the outside of the described side thrust rotor, a second baffle tube cover is horizontally arranged.

Further, the first and second power units described all employ an engine or an electric motor.

Further, if the described first and second power units all employ an engine, the described power source is fuel oil and the described first and second power units all employ an electric motor. If so, the power source listed is a battery pack.

In addition, the landing gear and gliding wheels described are equipped with a shock absorbing function.

The beneficial effects of the present invention are embodied as follows:

1. Compared to the conventional jet aircraft, the present invention employs a lifting rotor to achieve vertical takeoff, landing and hovering. Rotorcraft are adapted to the everyday routine of the general public, as jet planes fall when they stall, allowing them to take off, land and hover vertically.

2. Compared to conventional helicopters, the present invention employs at least two lifting rotors to provide better controllability and higher safety, the lifting force provided by multiple lifting rotors. It is more gentle and more controllable, and if one of the lifting rotors fails at the same time, the remaining lifting rotors can continue to provide lift, which makes them safer.

3. Compared with the conventional helicopter, the present invention provides the side thrust force by adopting the side thrust rotor, the side thrust force is stronger and the flight speed can be easily controlled. This is because the side thrust propulsion force is generated by the thrust inclination angle. The present invention relies on side thrust rotors installed on both sides or at the top of a manned cabin to directly provide side thrust forces.

4. Compared to conventional helicopters, the present invention is designed to install a closed manned cabin in the center of the rotor, which is similar to a multi-rotor unmanned aerial vehicle, so the site area is small, and takeoff and landing is a space. I can't get the restrictions from. On the other hand, current helicopters have a large wingspan and require a specialized airport for takeoff and landing. The design of the present invention has a compact structure and can realize takeoff and landing even in a normal place, and at the same time, the projection area of the manned cabin and the lifting rotor can be optimized by calculation and made smaller to be more adapted to the general public. .. In addition, it enhances the safety and comfort of drivers and passengers compared to existing open personal air vehicles and is suitable for all-weather flights.

5. Compared to existing personal air vehicles, the lifting rotors of the present invention are located around or on both sides of the capsule-type manned cabin, and the center of gravity of the aircraft is under the lifting rotor, which is for stable flight of the aircraft. It is beneficial.

6. Compared with the existing personal air vehicle, the present invention installs the steering handle behind or above the manned cabin, which makes the steering control of the aircraft more flexible.

7. Compared to existing personal air vehicles, current domestic and overseas personal air vehicles are pursuing high and high speed flight, so the manufacturing cost is high and the general public can afford to consume them. There is no. Since the present invention has a simple design, is gentle and pursues practical use, it can be bought by the general public at an affordable price and can be used as an ordinary means of transportation.

As mentioned above, the invention is similar in flight, takeoff and landing to an unmanned aerial vehicle, with advantages such as compactness and flexibility, low altitude and low speed, vertical lifting, economy and practicality.

In order to more clearly illustrate a particular embodiment or prior art solution of the invention, the following briefly introduces the drawings that need to be used in the description of a particular embodiment or prior art. In all drawings, similar elements or parts are generally identified by similar reference numerals. In the drawings, each element or part is not necessarily drawn to the actual scale.
FIG. 1 is a front view of the first embodiment. FIG. 2 is a top view of Example 1. FIG. 3 is a side view of the first embodiment. FIG. 4 is a front view of the second embodiment. FIG. 5 is a top view of Example 2. FIG. 6 is a side view of the second embodiment. FIG. 7 is a front view of the third embodiment. FIG. 8 is a top view of Example 3. FIG. 9 is a side view of the third embodiment. FIG. 10 is a front view of the fourth embodiment. FIG. 11 is a top view of Example 4. FIG. 12 is a side view of the fourth embodiment. FIG. 13 is a rear view of Example 5. FIG. 14 is a top view of Example 5. FIG. 15 is a side view of the fifth embodiment.

Next, examples of the technical solution of the present invention will be described in detail below together with the accompanying drawings. The following examples are used only to more clearly illustrate the technical solutions of the invention and are therefore used only as exemplary examples, but the scope of protection of the invention cannot be limited.
It should be noted that unless otherwise noted, the technical or scientific terms used in this application have the usual meanings understood by those skilled in the art of the present invention.

Example 1

As shown in FIGS. 1, 2 and 3, it includes a multirotor manned aircraft, a manned cabin 1, a lifting rotor 5, an equipment cabin 8 and a steering handle 10.

There is a window 7 at the top of the described manned cabin 1, a landing gear 9 at the bottom age, a cabin door 4 on the outer wall, side thrust rotors 2 on each of the outer walls on both sides, and side thrusts. At the rear end of the rotor 2, there is a first power unit 3 that drives the side thrust rotor 2, and the first power unit 3 is arranged at the rear end of the side thrust rotor 2 to facilitate heat dissipation of the power unit. It is. The manned cabin 1 is a capsule structure in which the cross section is circular enough to accommodate one person, and the side thrust rotor 2 is located below the lifting rotor 5.

There are six described lifting rotors 5, distributed above the described manned cabin 1 and above the described window 7, at the lower end of each described lifting rotor 5, respectively, to drive lifting. The second power unit 6 to which the second power unit 6 is installed facilitates heat dissipation of the power unit by installing the second power unit 6 at the lower end of the lifting rotor 5.

The described equipment cabin 8 is located at the bottom of the described manned cabin 1 in which the power sources for operating the first power equipment 3 and the second power equipment 6 are located, in which the first power equipment 3 is located. And the second power equipment 6 adopts an electric motor, and the power source is a battery pack.

The described steering wheel 10 is located behind the described manned cabin 1.

Specifically, a parachute 11 is provided above the described manned cabin 1 to ensure the safety of drivers and passengers in an emergency.

Specifically, a first baffle cover 12 is vertically provided on the outside of the described lifting rotor 5, thereby increasing the lifting concentration generated by the operation of the lifting rotor 5 and utilizing the energy of the power source. It also has the role of increasing the rate and protecting the lifting rotor 5.

Specifically, each of the described lifting rotors 5 is placed circumferentially above the described manned cabin 1 and above the described window 7 and to the outer wall of the described 1 via a connecting arm. Correspondingly connected, the center of gravity of the aircraft is below the lifting rotor 5, which is beneficial for the stable flight of the aircraft.

Specifically, by arranging the second baffle cover 13 horizontally on the outside of the described side thrust rotor 2, the concentration of the side thrust generated by the operation of the side thrust rotor 2 is increased, and the energy of the power source is used. It can also play a role in increasing the rate and protecting the side thrust 2.

Specifically, the landing gear 9 described is equipped with retractable gliding wheels to facilitate short-distance travel before or after takeoff by the aircraft.

Specifically, the landing gear 9 described is a cover-like structure having a vertically trapezoidal vertical cross section, whereby the landing gear 9 improves the support effect on the entire aircraft and the landing stability of the aircraft is improved. Was done.

In particular, the upper part of the described manned cabin 1 may not be provided with a window 7 for carrying cargo.

Example 2

As shown in FIGS. 4, 5 and 6, the differences from Example 1 are as follows:

The described manned cabin 1 has a capsule-shaped structure, the cross section of which can accommodate 3 people, and 10 lifting rotors 5 are arranged, and the upper part of the described manned cabin 1 and the description. It is distributed in the circumferential direction above the window 7.
Specifically, when the described first power unit 3 and the second power unit 6 employ an engine, the described power source is fuel oil.

Example 3

As shown in FIGS. 7, 8 and 9, the differences from Example 1 are as follows:

The described manned cabin 1 is a capsule-shaped structure, and if its cross section is rectangular, 18 lifting rotors 5 are installed to accommodate 3 or more people, and the described manned cabin 1 It is distributed in the circumferential direction above the upper part and the window 7 described in, and two side thrust rotors 2 are provided on the outer walls on both sides of the manned cabin 1, and two side thrust rotors on the same side are provided. 2 is on the same axis.

Specifically, when the described first power unit 3 and the second power unit 6 employ an engine, the described power source is fuel oil.

In particular, the steering wheel 10 is located behind the described manned cabin 1. When the manned cabin 1 is long and wide, the steering handle 10 can be replaced with a steering rotor when the steering control effect of the steering handle 10 is poor. The forward and reverse thrust of the steering rotor rotates forward and reverse to push forward the turning of the manned cabin 1.

In particular, the landing gear 9 is located below the described manned cabin 1. If the manned cabin 1 is long and wide, the landing gear 9 can be replaced with a gliding wheel if the aircraft itself is stable enough. Allows aircraft to travel short distances before takeoff and after landing.

Example 4

As shown in FIGS. 10, 11 and 12, the differences from Example 1 are as follows:

The described manned cabin 1 has a capsule-shaped structure, the cross section of which is in the shape of a ship and can accommodate three or more people, and has twelve lifting rotors 5, both sides of the described cabin 1 and below the described window 7. It is distributed in parallel to. Two side thrust rotors 2 are installed on the outer walls on both sides of the manned cabin 1, two side thrust rotors 2 on the same side are on the same axis, and two side thrust rotors 2 on the same side are on the upper part of the lifting rotor 5. It is in.

Specifically, when the described first power unit 3 and the second power unit 6 employ an engine, the described power source is fuel oil.

Specifically, the gliding wheel 9 is provided with a shock absorbing function in order to facilitate short-distance movement of the aircraft before takeoff and after landing.

In particular, the steering handle 10 is located above the described manned cabin 1. When the manned cabin 1 is long and wide, if the operation effect of the steering handle 10 is not so good, the steering handle 10 can be changed to the steering rotor. Push forward.

Example 5

As shown in FIGS. 13, 14, and 15, the differences from Example 1 are as follows:

The described manned cabin 1 is a capsule-like structure, and if its cross section is hull-shaped, it can accommodate 3 or more people, has 40 lifting rotors 5, and is divided into two layers and described as manned. It is distributed on both sides of cabin 1 and above and below the described windows 7. Three side thrust rotors 2 are provided on both sides of the upper outer wall of the described manned cabin 1. The three side thrust rotors 2 on the same side are on the same axis, and the three side thrust rotors 2 on the same side are on the lifting rotor 5.

Specifically, when the first power unit 3 and the second power unit 6 employ an engine, the described power source is fuel oil.

Specifically, the gliding wheel 9 is provided with a shock absorbing function in order to facilitate short-distance movement of the aircraft before takeoff and after landing.

In particular, the steering handle 10 is located above the described manned cabin 1. When the manned cabin 1 is long and wide, if the operation of the steering handle 10 is not very good, the steering handle 10 can be replaced with the steering rotor. Push forward.

Operating Principles of Example 1, Example 2, Example 3, Example 4 and Example 5:

The pilot and crew are seated in manned cabin 1, the plane is controlled by a pilot or an automated flight program, and its flight principle is the same as an unmanned aerial vehicle. The design of the capsule-shaped cabin 1 reduced the land area of the aircraft and made it possible for the aircraft to land and take off in a small field. The vertical layout of the capsule-shaped cabin 1 makes the aircraft more stable because it can reduce the center of gravity of the aircraft; it can achieve vertical takeoff, landing, and hover of the aircraft by controlling the rotation speed of the lifting rotor 5. The horizontal flight speed of the aircraft can be controlled by controlling the rotation speed of the side thrust rotor 2. By operating the lifting rotor 5 and the side rotor 2 at the same time, it is possible to realize low altitude / low speed running of the aircraft and vertical takeoff and landing. By adjusting the angle of the steering handle 10, the flight direction of the aircraft can be changed.

Finally, it should be noted that the above embodiments are used only to illustrate the technical solutions of the invention, but do not limit them. The invention has been described in detail with reference to the embodiments described above, but one of ordinary skill in the art should understand that the technical solutions described in the embodiments described above can be modified, or the like thereof. It is still possible to replace part or all of the technical features equally, nevertheless, these changes or replacements bring the essence of the corresponding technical solution from the technical solution of the embodiments of the invention. Do not deviate. All of them shall be covered by the claims of the invention and the protection of the instructions.

In the main technique of the present invention, a closed cabin for carrying people and things is installed in the center of the geometric plane of the aircraft, and the cabin for carrying people is called a manned cabin, which is a cabin for carrying things. Is characterized by being called a cargo cabin. The present invention takes a manned aircraft as an example, with multiple lifting rotors parallel and circumferential to provide lift around or on both sides of the geometric plane of the manned cabin, except where it interferes with the installation of the cabin door. It is installed in. Side thrust power is provided by installing side thrust rotors on both sides or above the manned cabin. By installing a landing gear or gliding wheel at the bottom of the manned cabin, which provides steering force by setting the steering handle or steering rotor on the back or top of the manned cabin, the aircraft can be parked and traveled short distances while landing. Useful for. The biggest difference from the existing manned aircraft design is that the lifting rotors provide the lifting power, the side thrust rotors provide the side thrusts, each rotor has a deflector cover, and each deflector cover is on the outer wall of the manned cabin. Be closely connected. Lifting rotors are installed around or on both sides of the manned cabin's geometric plane, and the guide tube covers outside the lifting rotors are all tightly connected, thereby providing relatively large lift if the aircraft has a relatively small site projection area. Was realized so that By arranging the lifting rotor in the center or top of the manned cabin, the center of gravity of the aircraft is below the lifting rotor, which is advantageous for stable flight of the aircraft.

The manned cabin can be designed as a closed three-dimensional structure of any shape such as capsule, sphere, ellipse, cube, rectangular parallelepiped, and cylinder. Taking the shape of an existing traffic vehicle as an example, a manned cabin can be designed similar to a manned cabin of an existing aircraft or spacecraft, except that the wings have been replaced by a lifting rotor. Manned cabins can also be designed to look like existing vehicles (passenger cars, jeep, vans, buses, etc.), but have multiple lifting rotors around or on either side of their outer wall just to provide lifting power. , The side thrust rotor is placed at the top to provide the side thrust. When an aircraft is used to carry cargo, the cargo cabin can be designed to resemble the shape of an existing container or van.

The length of the guide tube covers of the lifting rotor and the side thrust rotor along the airflow direction can be determined by calculation if necessary. As the length of the guide tube cover in the airflow direction increases, the guide tube cover becomes an advantageous airflow duct and can generate stronger thrust. The rotor of the guide tube cover can be designed as a single group, a double group, or multiple groups as needed. Multiple groups of rotors can generate stronger thrust like jet engine rotors by coaxial superposition rotation.

The lifting rotor and side thrust rotors are powered by power units located at the lower and rear ends of the rotor or from a central power unit (eg, a central engine) via a transmission shaft.

Manned cabin 1, side thrust rotor 2, first power unit 3, door 4, lifting rotor 5, second power unit 6, window 7, equipment cabin 8, landing gear or sliding wheel 9, steering handle 10, parachute 11, first One baffle cover 12, second baffle cover 13.

Claims (9)

Multirotor manned aircraft, including manned cabin (1), lifting rotor (5), equipment cabin (8) and steering handle (10).
The described manned cabin (1) has a window (7) at the top, a landing gear or gliding wheel (9) at the bottom age, and a cabin door (4) on its outer wall. Side thrust rotors (2) are provided on the outer walls or top on both sides, respectively, and at the rear end of the described side thrust rotor (2), the first power unit (2) for driving the described side thrust rotor (2) is provided. 3) is provided,
At least two of the described lifting rotors (5) are provided, arranged in parallel around or on either side of the manned cabin (1), with the lower ends of each of the described lifting rotors (5) being the lifting rotors (5), respectively. A second power unit (6) is placed to drive the
The equipment cabin (8) described is located at the bottom of the manned cabin (1) described, in which the power source for operating the first power unit (3) and the second power unit (6) described is located. Placed,
The described steering handle (10) is a multi-rotor manned aircraft characterized by being located at the rear or top of the described manned cabin (1). The multirotor manned aircraft according to claim 1, wherein the manned cabin (1) has a capsule-shaped structure, and its cross section is circular enough to accommodate one person, or has a band shape capable of accommodating three people, or A multi-rotor manned aircraft characterized by being a rectangle that can accommodate three or more people, or a boat type that can accommodate three or more people. The multi-rotor manned aircraft according to claim 1, wherein a parachute (11) is provided on the top of the described manned cabin (1). The multi-rotor manned aircraft according to claim 1, wherein a first guide tube cover (12) is vertically installed on the outside of the described lifting rotor (5). .. The multirotor manned aircraft according to claim 1 or 4, wherein the described lifting rotors (5) are arranged side by side around or on both sides of the manned cabin (1), respectively, and are described via a connecting arm. A multi-rotor manned aircraft characterized by being connected corresponding to the manned cabin (1). The multirotor manned aircraft according to claim 1, wherein a second guide tube cover (13) is horizontally arranged outside the side thrust rotor (2) described. Manned aircraft. The multirotor manned aircraft according to claim 1, wherein the first power unit (3) and the second power unit (6) described all use an engine or an electric motor. aircraft. If the multi-rotor manned aircraft of claim 7 and the first power unit (3) and the second power unit (6) described all employ an engine, the power source described is: A multi-rotor manned aircraft that is fuel oil and the described power source is a battery pack if the described first power unit (3) and second power unit (6) all employ motors. .. The multi-rotor manned aircraft according to claim 1, wherein the landing gear or the sliding wheel (9) described is provided with a shock absorbing function.

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