CN115743529A - Multi-rotor electric manned aircraft - Google Patents
Multi-rotor electric manned aircraft Download PDFInfo
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- CN115743529A CN115743529A CN202211282889.8A CN202211282889A CN115743529A CN 115743529 A CN115743529 A CN 115743529A CN 202211282889 A CN202211282889 A CN 202211282889A CN 115743529 A CN115743529 A CN 115743529A
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- rotor
- nacelle
- motor
- cabin
- support arm
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention discloses a multi-rotor electric manned aircraft, which comprises: a cabin for carrying a person; one end of each rotor wing support arm is fixedly connected to the top of the cabin through a central connecting piece, the other end of each rotor wing support arm is provided with a motor support, a motor is fixedly installed on each motor support, and a rotor wing is installed on an output shaft of each motor; each rotor wing support arm is also fixedly connected with the top of the cabin through a fixing piece; and the landing gear is fixedly arranged at the bottom of the cabin. The invention improves the safety of passengers in the flying process and in and out through the design of the overhead multi-rotor wing; the rotor support arm adopts two connection structure, has both reduced the concentrated condition of mounted position load, has optimized load distribution, has improved the structural rigidity of rotor support arm again, realizes the lightweight design.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a multi-rotor electric manned aircraft.
Background
At present, a multi-rotor aircraft mainly uses an unmanned aerial vehicle and cannot realize a manned function. With technological advances and market demands, multi-rotor manned aircraft are beginning to be researched and produced.
In the prior art, a multi-rotor electric manned vehicle is arranged below, wherein the rotor working face of the manned vehicle is positioned at the lower part of a passenger cabin, 8 rotor support arms are arranged in total, the rotor support arms are connected with a lower cabin assembly of a vehicle body, the connection positions are 4, 2 rotor support arms are arranged at each position, and a power battery is integrated in the lower cabin assembly. It has problems in that: the height of the rotor wing is at the leg position of the passenger, so that the risk of cutting injury caused by the rotation of the rotor wing when the passenger enters or exits the cabin door on the ground can be avoided, or the body injury of the passenger can be caused under the condition that the rotor wing rotates due to abnormal electrification when the passenger enters or exits the cabin door; the rotor wing support arm is arranged on the lower cabin assembly through a single point, the local load is concentrated, and the connection design needs to be strengthened; power battery installs cabin assembly down, and the rotor load passes through the mounted position and transmits power battery, and power battery bears the high frequency load effect for a long time, NVH and structural strength difference.
In the other overhead multi-rotor electric manned aircraft, the rotor working face is positioned at the top of a passenger cabin, the rotor support arm is connected with an upper cabin assembly of an aircraft body, and only one position is positioned at the connection position and is positioned in the center of the top; whole rotor structure connects Y type support arm through circular structure to promote rotor support arm structural rigidity. However, this aircraft still has problems: the rotor support arm links together a plurality of rotors through Y type structure and circular structure, though promoted structural rigidity, has increased extra additional strengthening, has increased cost and structure weight.
Disclosure of Invention
The technical problem to be solved by the embodiment of the invention is to provide a multi-rotor electric manned vehicle, so as to ensure the safety of passengers entering and exiting, improve the structural rigidity and realize light weight design.
In order to solve the above technical problem, the present invention provides a multi-rotor electric manned vehicle, comprising:
a cabin for carrying a person;
one end of each rotor wing support arm is fixedly connected to the top of the cabin through a central connecting piece, the other end of each rotor wing support arm is provided with a motor support, a motor is fixedly installed on each motor support, and a rotor wing is installed on an output shaft of each motor; each rotor wing support arm is also fixedly connected with the top of the cabin through a fixing piece;
and the landing gear is fixedly arranged at the bottom of the cabin.
Further, an upper elevation angle is formed between the rotor wing support arm close to the rotor wing and the horizontal plane.
Further, the central connecting member has connection sleeves corresponding to the number of the rotor arms, and the end of each of the rotor arms is connected to the connection sleeve.
Further, the mounting specifically includes last fixed block and lower fixed block through bolted connection, it is the type of falling U to go up the fixed block, the fixed block is the U type down, it is in with lower fixed block parcel jointly to go up the fixed block the intermediate position of rotor support arm, and with the top fixed connection in cabin.
Further, the nacelle includes an upper nacelle, a lower nacelle and a column connected between the upper nacelle and the lower nacelle, the upper nacelle includes an upper frame structure composed of a plurality of cross beams and longitudinal beams and an X-shaped beam located inside the upper frame structure, and the lower nacelle is specifically a lower frame structure composed of a plurality of longitudinal beams and cross beams.
Further, the central connecting piece is connected with the X-shaped beam of the upper cabin through a bottom bolt, and the fixing piece is connected with the upper frame structure of the upper cabin through a bolt.
Further, a power battery is installed inside the lower cabin and assembled with the longitudinal beam of the lower cabin.
Further, the motor support is installed the rotor support arm is kept away from the tip of central connecting piece be close to on the rotor support arm motor controller support is still installed to motor support department for installation control the motor controller of motor.
Furthermore, the landing gear is of a skid-type structure and comprises two arched beams and a sliding barrel, a layer of anti-skid plate is mounted on the lower portion of the sliding barrel, and the arched beams and the sliding barrel are both of a hollow structure.
Further, its characterized in that, the rotor support arm is hollow pipe structure, many the rotor support arm respectively with many rotor electric manned aircraft's fuselage length direction and fuselage width direction symmetrical arrangement.
The implementation of the invention has the following beneficial effects: through the design of multiple overhead rotors, the working surface of the rotor is positioned at the top of the cabin, so that the damage of the broken rotor to passengers under emergency is avoided, and the safety of the passengers in the flying process is improved; the height of the rotor wing working surface from the ground is higher than the height of passengers, and a certain margin is provided, so that the passengers are prevented from being injured when the rotor wing rotates after the rotor wing is electrified, and the safety of the passengers in and out is improved; the rotor support arm adopts two connection structure, has both reduced the concentrated condition of mounted position load, has optimized load distribution, has improved the structural rigidity of rotor support arm again, realizes the lightweight design.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic top view of a multi-rotor electric manned vehicle according to an embodiment of the invention.
Fig. 2 is a schematic structural diagram of a frame of a multi-rotor electric manned vehicle according to an embodiment of the invention.
Fig. 3 is a schematic structural diagram of the frame of the upper nacelle according to the embodiment of the invention.
Figure 4 is a schematic top view of the rotor arm and central link assembly of an embodiment of the present invention.
Figure 5 is an enlarged partial top view of a rotor arm and central attachment assembly according to an embodiment of the present invention.
Figure 6 is a side view of the assembly of a rotor arm and central link assembly according to an embodiment of the present invention.
Figure 7 is a schematic view of the assembly of a rotor arm with a motor mount and a motor controller mount according to an embodiment of the present invention.
Fig. 8 is a schematic side view of an electric manned vehicle with multiple rotors according to an embodiment of the invention.
Detailed Description
The following description of the embodiments refers to the accompanying drawings, which are included to illustrate specific embodiments in which the invention may be practiced.
Referring to fig. 1, an embodiment of the invention provides a multi-rotor electric manned vehicle, including:
a nacelle 1 for carrying a person;
one end of each rotor wing support arm 2 is fixedly connected to the top of the engine room 1 through a central connecting piece 7, the other end of each rotor wing support arm 2 is provided with a motor support 3, a motor 4 is fixedly installed on each motor support 3, and a rotor wing 5 is installed on an output shaft of each motor 4; each rotor wing support arm 2 is also fixedly connected with the top of the cabin 1 through a fixing piece 8;
a landing gear 6 fixedly mounted at the bottom of the nacelle 1.
According to the structure, the rotor support arms 2 and the rotors 5 thereon are arranged at the top of the cabin 1 in an overhead mode, so that the rotors 5 are arranged on the passenger cabin, the height above the ground is higher than the height of a passenger, a certain margin is provided, and the safety of the passenger in and out is ensured; the rotor wing support arms 2 are installed in a double-connection mode, the end part of each rotor wing support arm 2 is connected to the top of the cabin through a central connecting piece 7, the middle position of each rotor wing support arm 2 is fixedly connected with the top of the cabin 1 through a fixing piece 8, the problem caused by load concentration of the installation position is greatly reduced, the structural rigidity is improved, and the light-weight design is realized.
It should be noted that, in the embodiments of the present invention, terms of direction and position such as "up", "down", "front", "back", "left", "right", "inside", "outside", "top", "bottom", "side", and the like refer to only directions or positions in the drawings. Accordingly, the use of directional and positional terms is intended to illustrate and understand the present invention and is not intended to limit the scope of the present invention. Specifically, taking fig. 1 as an example, the X-axis is the length direction of the fuselage of the multi-rotor electric manned vehicle in the embodiment, wherein the + X direction faces the nose; the Y-axis is the fuselage width direction of the multi-rotor electric manned vehicle of this embodiment, with the + Y direction facing the left side of the fuselage.
As shown in fig. 2, the nacelle 1 includes an upper nacelle 11, a lower nacelle 12, and a column 10 connected between the upper nacelle 11 and the lower nacelle 12, where the column 10 is used to ensure structural rigidity of the nacelle 1, the column is made of 7075 aluminum alloy, and is formed by extrusion molding, and the structural shape is a hollow square tube. A passenger seat 91 (see fig. 8) is provided in the nacelle 1, and the passenger seat is an independent structure. The upright 10 is mounted with the upper nacelle 11 and the lower nacelle 12 by means of a connection element by gluing and riveting. The upper nacelle 11 includes an upper frame structure 110 composed of a plurality of cross members and longitudinal members, and an X-shaped beam 111 located inside the upper frame structure 110; the lower nacelle 12 is embodied as a lower frame structure composed of three longitudinal beams and a plurality of cross beams, and a power battery 92 (see fig. 8) is mounted inside the lower nacelle 12 to be assembled with the longitudinal beams of the lower nacelle 12. The central connection member 7 is connected to the X-beam 111 of the upper nacelle 11 by means of bottom bolts and the fixation member 8 is connected to the upper frame structure 110 of the upper nacelle 11 by means of bolts.
The landing gear 6 is of a skid type structure and comprises two arched beams 61 and a sliding cylinder 62, and a layer of anti-skid plate made of wear-resistant high-strength steel is arranged on the lower portion of the sliding cylinder 62. In order to ensure the structural rigidity and realize the lightweight design, the bow beam 61 and the sliding cylinder 62 are both hollow structures. The landing gear 6 is assembled with the nacelle 1 by means of a bolt connection by means of a connecting piece.
Referring again to fig. 4-6, the present embodiment employs a dual connection for the assembly of the rotor arm 2 and the nacelle 1: the top of the nacelle 1 is fixedly connected with a central connecting piece 7 and a fixing piece 8 respectively, wherein the central connecting piece 7 is provided with connecting sleeves 70 corresponding to the number of the rotor arms 2, and the end part of each rotor arm 2 is connected with the connecting sleeves 70 of the central connecting piece 7 in a blind rivet connection mode; mounting 8 specifically includes last fixed block 81 and lower fixed block 82 through bolted connection, and for the appearance of adaptation rotor support arm 2, it is the type of falling U to go up fixed block 81, and lower fixed block 82 is the U type, goes up fixed block 81 and lower fixed block 82 and wraps up in the intermediate position of rotor support arm 2 jointly to with the top fixed connection in cabin 1. Central authorities ' connecting piece 7 mainly undertakes along 2 axial pulling forces of rotor support arm, and mounting 8 mainly undertakes the pulling force of aircraft vertical direction, adopts aforementioned dual connection structure can avoid vertical direction's pulling force and axial pulling force to concentrate on the end of rotor support arm 2, improves rotor support arm 2's durability.
Referring to fig. 7 and 8, the rotor arm 2 is a hollow circular tube structure with an inclined angle, and is made of a carbon fiber composite material. In order to not increase the height and weight of the member cabin and ensure the safety of passengers stepping in, an upper elevation angle theta is formed between the rotor wing support arm 2 close to the rotor wing 5 and the horizontal plane, and the angle range is 2-10 degrees. It should be noted that, the number of the rotor arms 2 is not limited in this embodiment, and the rotor arms may be four rotors, six rotors, eight rotors, twelve rotors, sixteen rotors, etc.; and the structures of the rotor support arms 2 are the same, so that the rotor support arms are interchangeable. The present embodiment will be described with reference to six rotors as an example. The six rotor arms 2 are arranged symmetrically about the X and Y axes shown in figure 1.
The motor support 3 is installed at the end part of the rotor wing support arm 2 far away from the central connecting piece 7 in a gluing and riveting mode, and a motor 4 for driving the rotor wing 5 to rotate is installed in the motor support 3. A motor controller support 30 is also arranged on the rotor wing support arm 2 near the motor support 3 and used for installing a motor controller for controlling the motor 4. Motor controller mount 30 is also attached to rotor arm 2 by gluing or riveting.
The working principle and the process of the vertical take-off and landing aircraft are as follows:
the multi-rotor electric manned aircraft is a pure electric aircraft, and the power battery 92 supplies power for the propulsion system. The propulsion system adopts a distributed structure, the motor 4 and the motor controller are arranged at the outermost periphery of the rotor wing support arm 2, and the action surface of the rotor wing 5 is parallel to the ground. In the taking-off and landing process, the aircraft generates upward lift force under the action of gas through the rotation of the rotor wing 5, so that the aircraft vertically ascends or lands; in the cruising stage, the aircraft enables the action surface of the rotor wing 5 to form a certain angle with the vertical surface in a certain forward tilting posture, and the aircraft can provide upward lift force and forward thrust force. The pneumatic force is transmitted to the position of the double-connecting structure through the rotor wing support arm 2, and the pneumatic load is transmitted to the aircraft body through the double-connecting structure, so that the load concentration of a single installation position is reduced, and the structural rigidity of the rotor wing support arm 2 is improved.
Before the passengers enter the cabin 1, the aircraft is in a power-off state; after the passengers enter the cabin 1, the power is supplied through the starting key, namely, the passengers enter the rear rotor 5 to work again, thereby ensuring the safety of the passengers.
As can be seen from the above description, compared with the prior art, the beneficial effects of the present invention are: through the design of multiple overhead rotors, the working surface of the rotor is positioned at the top of the cabin, so that the damage of the broken rotor to passengers under emergency is avoided, and the safety of the passengers in the flying process is improved; the height of the rotor wing working surface from the ground is higher than the height of passengers, and a certain margin is provided, so that the passengers are prevented from being injured when the rotor wing rotates after the rotor wing is electrified, and the safety of the passengers in and out is improved; the rotor support arm adopts two connection structure, has both reduced the concentrated condition of mounted position load, has optimized load distribution, has improved the structural rigidity of rotor support arm again, realizes the lightweight design.
The above disclosure is only for the purpose of illustrating the preferred embodiments of the present invention, and it is therefore to be understood that the invention is not limited by the scope of the appended claims.
Claims (10)
1. The utility model provides an electronic manned aircraft of many rotors which characterized in that includes:
a cabin for carrying a person;
one end of each rotor wing support arm is fixedly connected to the top of the cabin through a central connecting piece, the other end of each rotor wing support arm is provided with a motor support, a motor is fixedly installed on each motor support, and a rotor wing is installed on an output shaft of each motor; each rotor wing support arm is also fixedly connected with the top of the cabin through a fixing piece;
and the landing gear is fixedly arranged at the bottom of the cabin.
2. The multi-rotor electric manned vehicle of claim 1, wherein the rotor arms adjacent the rotors form an upper elevation angle with respect to a horizontal plane.
3. The multi-rotor electric manned vehicle of claim 1, wherein the central link has a connection sleeve corresponding to the number of rotor arms, the end of each of the rotor arms being connected to the connection sleeve.
4. The multi-rotor electric manned vehicle of claim 3, wherein the mounting specifically includes an upper fixing block and a lower fixing block that are connected by bolts, the upper fixing block is of an inverted U shape, the lower fixing block is of a U shape, the upper fixing block and the lower fixing block wrap the middle position of the rotor arm together, and are fixedly connected to the top of the nacelle.
5. The multi-rotor electric manned vehicle of claim 4, wherein the nacelle includes an upper nacelle including an upper frame structure comprised of a plurality of cross members and longitudinal members and an X-shaped member positioned within the upper frame structure, a lower nacelle, in particular a lower frame structure comprised of a plurality of longitudinal members and cross members, and a vertical post connected between the upper nacelle and the lower nacelle.
6. The multi-rotor electric manned vehicle of claim 5, wherein the central connection member is bolted to the X-beam of the upper nacelle and the attachment member is bolted to the upper frame structure of the upper nacelle.
7. The multi-rotor electric manned vehicle of claim 5, wherein a power battery is mounted inside the lower nacelle and assembled with the stringers of the lower nacelle.
8. A multi-rotor electric manned vehicle according to claim 1, wherein the motor mounts are mounted on the ends of the rotor arms remote from the central link, and motor controller mounts are mounted on the rotor arms adjacent the motor mounts for mounting motor controllers for controlling the motors.
9. The multi-rotor electric manned vehicle of claim 1, wherein the landing gear is of a skid-type structure and comprises two bow-shaped beams and a sliding barrel, a layer of anti-skid plate is mounted on the lower portion of the sliding barrel, and the bow-shaped beams and the sliding barrel are both of a hollow structure.
10. The multi-rotor electric manned vehicle of any of claims 1-9, wherein the rotor arms are hollow round tubes and are symmetrically arranged in the length direction and width direction of the fuselage of the multi-rotor electric manned vehicle.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211282889.8A CN115743529A (en) | 2022-10-19 | 2022-10-19 | Multi-rotor electric manned aircraft |
| PCT/CN2023/115952 WO2024082833A1 (en) | 2022-10-19 | 2023-08-30 | Multirotor electric-manned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211282889.8A CN115743529A (en) | 2022-10-19 | 2022-10-19 | Multi-rotor electric manned aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115743529A true CN115743529A (en) | 2023-03-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211282889.8A Pending CN115743529A (en) | 2022-10-19 | 2022-10-19 | Multi-rotor electric manned aircraft |
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| Country | Link |
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| CN (1) | CN115743529A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024082833A1 (en) * | 2022-10-19 | 2024-04-25 | 广州汽车集团股份有限公司 | Multirotor electric-manned aerial vehicle |
-
2022
- 2022-10-19 CN CN202211282889.8A patent/CN115743529A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024082833A1 (en) * | 2022-10-19 | 2024-04-25 | 广州汽车集团股份有限公司 | Multirotor electric-manned aerial vehicle |
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