CN112141342A - Cargo aircraft with multiple rotary wings - Google Patents
Cargo aircraft with multiple rotary wings Download PDFInfo
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- CN112141342A CN112141342A CN202011128827.2A CN202011128827A CN112141342A CN 112141342 A CN112141342 A CN 112141342A CN 202011128827 A CN202011128827 A CN 202011128827A CN 112141342 A CN112141342 A CN 112141342A
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- 239000000295 fuel oil Substances 0.000 claims description 5
- 239000002775 capsule Substances 0.000 claims description 3
- 238000013016 damping Methods 0.000 claims 1
- 108010066057 cabin-1 Proteins 0.000 description 19
- 230000000694 effects Effects 0.000 description 5
- 230000002349 favourable effect Effects 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 238000010521 absorption reaction Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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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
- B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
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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
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/60—UAVs specially adapted for particular uses or applications for transporting passengers; for transporting goods other than weapons
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
Abstract
The invention discloses a multi-rotor cargo aircraft, which comprises a cargo carrying cabin, lifting rotors, an equipment cabin and a steering rudder, wherein the lifting rotors are arranged on the cargo carrying cabin; a window is arranged in front of the upper part of the cargo carrying cabin, a sliding wheel is arranged on the edge of the bottom of the cargo carrying cabin, a cabin door is arranged on the outer wall of the cargo carrying cabin, side-push rotors are respectively arranged on the outer walls of two sides or the top of the side-push rotors, and first power equipment for driving the side-push rotors to operate is arranged at the rear ends of the side-push rotors; the lifting rotor wings are at least two and are distributed around or on two sides of the cargo carrying compartment 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 cargo carrying 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 cargo carrying cabin. The invention has the advantages of flexible control, 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 multi-rotor cargo aircraft.
Background
Throughout the world, the existing cargo aircraft applicable to common people is almost blank, and the cargo aircraft developed at present at home and abroad generally has the following problems: firstly, the operation difficulty is high, and professional operation is required; secondly, the high-flying vehicle flies fast and is not suitable for being used as a daily cargo carrying transport tool for common people in cities and villages; 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 intelligent cargo aircraft which is flexible to control, low in altitude, low in speed, capable of vertically lifting and economical and practical is the development direction of future cargo aircraft.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a multi-rotor cargo aircraft which is similar to an unmanned aircraft in flying and taking off and landing and has the advantages of flexible control, low altitude, low speed, vertical lifting, economy and practicability.
A multi-rotor cargo aircraft comprises a cargo carrying cabin, lifting rotors, an equipment cabin and a steering rudder;
a window is arranged in front of the upper part of the cargo carrying cabin, a sliding wheel is arranged on the edge of the bottom of the cargo carrying cabin, a cabin door is arranged on the outer wall of the cargo carrying cabin, side-push rotors are respectively arranged on the outer walls of two sides or the top of the side-push rotors, and first power equipment for driving the side-push rotors to operate is arranged at the rear ends of the side-push rotors;
the lifting rotor wings are at least two and are distributed around or on two sides of the cargo carrying compartment 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 cargo carrying 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 cargo carrying cabin.
Furthermore, the cargo carrying cabin is of a closed three-dimensional structure, and the cross section of the cargo carrying cabin is square to accommodate low-tonnage cargo, or rectangular to accommodate medium-tonnage cargo, or rectangular to accommodate high-tonnage cargo, or is in a capsule shape to carry people or cargo.
Further, lift the outer vertical first draft tube cover that is provided with of rotor.
Furthermore, the lifting rotor wings are distributed around or on two sides of the cargo carrying cabin in parallel and are connected with the corresponding outer walls of the cargo carrying cabin through connecting arms.
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.
Further, lift rotor and the first draft tube cover and the second draft tube cover of side thrust rotor, the length of draft tube cover along the air current direction can be confirmed through calculating as required, along with the length extension of draft tube cover along the air current direction, thereby the draft tube cover forms the air current duct and is favorable to the air current to produce stronger thrust.
Further, lift rotor and the first kuppe and the second kuppe of side thrust rotor, the rotor in the kuppe also can be designed as required to singly organize, two or multiunit, and multiunit rotor is rotatory like jet aircraft's engine rotor through coaxial stack and is favorable to the air current to produce stronger thrust.
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 descend when stalled and can vertically take-off, land and hover, so that the jet aircraft is more suitable for being used as a common daily cargo carrying transport tool for people;
2. compared with the helicopter in the prior art, the invention adopts at least two lifting rotors to provide the lifting force, has better controllability and higher safety, because the plurality of lifting rotors provide the lifting force more stably, the controllability is better, and simultaneously, 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 invention adopts the side-push rotor wings to provide the side-push power, and the side-push power is stronger and easier to control the flight speed, because the helicopter in the prior art generates the side-push power by the inclination angle of the rotor wings, and the invention directly provides the side-push power by the side-push rotor wings arranged at the two sides or the top of the cargo hold;
4. compared with the helicopter in the prior art, the helicopter is similar to the helicopter in the prior art, the closed cargo carrying 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 cargo carrying 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 cargo aircraft, the cargo aircraft is more beneficial to the safety of cargos and is more suitable for all-weather flight.
5. Compared with the existing personal aircraft, the lifting rotor wings are positioned at the periphery or two sides of the closed three-dimensional cargo carrying cabin, and the gravity center of the aircraft is positioned below the lifting rotor wings, so that the stable flight of the aircraft is facilitated;
6. compared with the existing personal aircraft, the steering rudder is arranged at the top of the cargo carrying cabin, so that the aircraft is more flexible to steer and control;
7. compared with the existing personal aircrafts, the personal aircrafts at home and abroad are high in flying speed, so that the cost is high, the consumption of the common people cannot be realized, the design is simple, the pursuit is stable and practical, the cost is low, the personal aircrafts can be bought by the common people, and the personal aircrafts can be used as daily cargo-carrying transportation tools of the common people.
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 flexible control, low altitude, low speed, vertical lifting, economy and practicality.
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 embodiment 3;
FIG. 10 is a front view of embodiment 4;
FIG. 11 is a top view of example 4;
FIG. 12 is a side view of example 4.
In the drawing, the cargo carrying cabin 1, the side-push rotor 2, the first power equipment 3, the cabin door 4, the lifting rotor 5, the second power equipment 6, the window 7, the equipment cabin 8, the sliding wheel 9, the steering rudder 10, the parachute 11 (the cargo aircraft can be not arranged), the first air guide cylinder cover 12 and the 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 cargo aircraft includes a cargo compartment 1, a lift rotor 5, an equipment compartment 8, and a rudder 10;
a window 7 is arranged in front of the upper part of the cargo carrying cabin 1, a sliding wheel 9 is arranged on the edge of the bottom of the cargo carrying cabin, a cabin door 4 is arranged in front of the outer wall of the cargo carrying cabin, side-push rotors 2 are respectively arranged on the outer walls of two sides of the cargo carrying cabin, a first power device 3 for driving the side-push rotors 2 to operate is arranged at the rear ends of the side-push rotors 2, and the first power device 3 is arranged at the rear ends of the side-push rotors 2 and is beneficial to heat; the cargo carrying cabin 1 is of a closed three-dimensional structure, and the cross section of the cargo carrying cabin is square so as to contain low-tonnage cargo; the side-pushing rotor 2 is located below the lifting rotor 5.
Twelve lifting rotor wings 5 are arranged and are circumferentially distributed at the upper part of the cargo carrying compartment 1 and above the window 7 in parallel, the lower end of each lifting rotor wing 5 is respectively provided with a second power device 6 for driving the lifting rotor wing 5 to operate, and the second power devices 6 are arranged at the lower ends of the lifting rotor wings 5 to facilitate the heat dissipation of the power devices;
the equipment bin 8 is arranged at the bottom of the cargo carrying 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 provided at the top of the cargo tank 1.
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 side by side circumference distribute in carry the upper portion of cargo hold 1 and the top of window 7 to through the linking arm with carry the outer wall connection that cargo hold 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 gliding wheel 9 is provided with a shock absorption function, so that the aircraft can be transferred in a short distance before taking off or after landing.
In particular, the upper front face of the cargo hold 1 may also be provided without a window 7.
Example 2
As shown in fig. 4, 5 and 6, the difference from embodiment 1 is that:
the cargo carrying cabin 1 is of a closed three-dimensional structure, the cross section of the cargo carrying cabin is rectangular so as to contain middle-position and lower-position cargo, twenty lifting rotary wings 5 are arranged and are circumferentially distributed on the upper portion of the cargo carrying cabin 1 and above the window 7 in parallel. The outer wall of the two sides of the cargo carrying cabin 1 is respectively provided with two side-push rotors 2, and the two side-push rotors 2 on the same side are positioned on the same axis.
Specifically, the first power device 3 and the second power device 6 adopt engines, and the power source is fuel oil.
Particularly, the steering rudder 10 is arranged at the top of the cargo carrying cabin 1, when the cabin body of the cargo carrying cabin 1 is longer and wider, the steering rudder 10 can be replaced by a steering rotor under the condition of poor steering control effect, and the forward and reverse thrust generated by the forward and reverse rotation of the steering rotor pushes the cabin body of the cargo carrying cabin 1 to turn.
Example 3
As shown in fig. 7, 8 and 9, the difference from embodiment 1 is that:
carry cargo hold 1 and be closed spatial structure, its cross section is the rectangle in order to hold high position volume goods, and lifts rotor 5 and be provided with twenty six, parallel circumference distribution in carry cargo hold 1's upper portion and window 7's top. Carry the top outer wall both sides of cargo hold 1 to be provided with three side and push away rotor 2 respectively, the three side of homonymy pushes away rotor 2 and is located the same axis, and the three side of homonymy pushes away rotor 2 and is located the top that lifts rotor 5.
Specifically, lift first draft tube cover 12 of rotor 5, the length extension of draft tube cover along the air current direction, the draft tube cover forms the air current duct and is favorable to the air current to produce stronger thrust.
Specifically, lift first kuppe 12 of rotor 5, the kuppe forms the air current duct, and the rotor design in the kuppe is the multiunit, and the multiunit rotor is rotatory just like jet aircraft's engine rotor through coaxial stack to be favorable to the air current to produce stronger thrust.
Specifically, the first power device 3 and the second power device 6 adopt engines, and the power source is fuel oil.
Particularly, the steering rudder 10 is arranged at the top of the cargo carrying cabin 1, when the cabin body of the cargo carrying cabin 1 is longer and wider, the steering rudder 10 can be replaced by a steering rotor under the condition of poor steering control effect, and the forward and reverse thrust generated by the forward and reverse rotation of the steering rotor pushes the cabin body of the cargo carrying cabin 1 to turn.
Example 4
As shown in fig. 10, 11 and 12, the difference from embodiment 1 is that:
carry cargo hold 1 and be closed spatial structure, its cross section is capsule-shaped can carry people and also can carry cargo, carries cargo hold 1 and can reduce air resistance like the design in aircraft cabin, and lifts rotor 5 and be provided with twelve, distribute side by side in carry cargo hold 1's both sides middle part and window 7's below. The rear parts of the outer walls of the two sides of the cargo carrying cabin 1 are respectively provided with a side-push rotor wing 2, and the side-push rotor wings 2 are positioned above the lifting rotor wings 5.
Specifically, the first power device 3 and the second power device 6 adopt engines, and the power source is fuel oil.
Particularly, the steering rudder 10 is arranged at the top of the cargo carrying cabin 1, when the cabin body of the cargo carrying cabin 1 is longer and wider, the steering rudder 10 can be replaced by a steering rotor under the condition of poor steering control effect, and the forward and reverse thrust generated by the forward and reverse rotation of the steering rotor pushes the cabin body of the cargo carrying cabin 1 to turn.
Working principle of embodiment 1, embodiment 2, embodiment 3 and embodiment 4:
the cargo aircraft 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 design of the closed type three-dimensional cargo carrying cabin 1 can reduce the occupied area of the aircraft, and the aircraft can take off and land in a smaller field; the gravity center of the aircraft can be lowered through the vertical layout of the closed type three-dimensional cargo carrying cabin 1, 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; the modifications or substitutions do not cause the essence of the corresponding technical solutions to depart from the scope of the technical solutions of the embodiments of the present invention, and the technical solutions are all covered by the claims and the protection scope of the specification of the present invention.
The invention is mainly technically characterized in that: the invention relates to a cargo aircraft, which is characterized in that an enclosed cabin body is arranged in the middle of the geometric plane of the aircraft and is used for carrying people or cargo, a manned cabin is used for carrying people and a cargo cabin is used for carrying cargo, the cargo aircraft is taken as an example, a plurality of lifting rotors can be arranged in parallel and circumferentially except for a place where a cabin door is arranged on the periphery or two sides of the geometric plane of the cargo cabin to provide lifting power, side pushing rotors are arranged on two sides or the top of the cargo cabin to provide side pushing power, steering rudders or steering rotors are arranged on the rear part or the top of the cargo cabin to provide steering power, and gliding wheels are arranged on the bottom of the cargo cabin to facilitate the parking and short-distance transfer of the aircraft in a landing state. The biggest difference from the existing cargo aircraft design is that: the lifting rotor provides lifting power, the side-pushing rotor provides side-pushing power, a guide cylinder cover is arranged outside each rotor, each guide cylinder cover is tightly connected with the outer wall of the cargo compartment, the lifting rotor is arranged around the geometric plane of the cargo compartment or on two sides of the geometric plane of the cargo compartment, and the guide cylinder covers outside each lifting rotor are tightly connected, so that the aircraft can obtain relatively large lifting power under the condition of relatively small occupied projection area. The lifting rotor wing is arranged in the middle or on the upper part of the cargo carrying 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.
The cargo (or man) carrying compartment can be designed into a closed three-dimensional structure of any shape, such as capsule, sphere, ellipsoid, cube, cuboid, cylinder, etc. Taking the shape of an existing vehicle as an example, the cargo tank can be designed to be similar to the tank body part of an existing airplane or airship, except that the wings of the cargo tank are replaced by lifting rotors; the cargo compartment may also be designed to resemble an existing vehicle (e.g., a sedan, a jeep, a minibus, a bus, etc.) except that a plurality of lift rotors are circumferentially arranged side-by-side around or on either side of its outer wall to provide lift power, and side thrust rotors are arranged on either side or on top of its outer wall to provide side thrust power. Cargo aircraft cargo compartments can also be designed to resemble existing containers or vans.
The power for lifting the rotor and pushing the rotor laterally can be provided by power equipment arranged at the lower end and the rear end of the rotor, and can also be obtained from central power equipment (such as a central engine and a motor) through a transmission shaft.
Claims (10)
1. The utility model provides a many rotors cargo aircraft which characterized in that: comprises a cargo carrying cabin (1), a lifting rotor wing (5), an equipment cabin (8) and a steering rudder (10);
a window (7) is arranged in front of the upper part of the cargo carrying cabin (1), a sliding wheel (9) is arranged on the edge of the bottom of the cargo carrying cabin, a cabin door (4) is arranged on the outer wall of the cargo carrying cabin, side-push rotors (2) are respectively arranged on the outer walls of two sides or on the top of the two sides, and a first power device (3) for driving the side-push rotors (2) to operate is arranged at the rear end of each side-push rotor (2);
the lifting rotor wings (5) are at least two and are distributed around or on two sides of the cargo carrying compartment (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 cargo carrying 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 cargo carrying cabin (1).
2. The multi-rotor cargo aircraft of claim 1, wherein: the cargo carrying cabin (1) is of a closed three-dimensional structure, and the cross section of the cargo carrying cabin is square to contain low-tonnage cargo, or is rectangular to contain medium-tonnage cargo, or is rectangular to contain high-tonnage cargo, or is in a capsule shape to carry people or cargo.
3. The multi-rotor cargo aircraft of claim 1, wherein: a first guide cylinder cover (12) is vertically arranged outside the lifting rotor wing (5).
4. The multi-rotor cargo aircraft of claim 1 or 3, wherein: each lifting rotor wing (5) is distributed on the periphery or two sides of the cargo carrying cabin (1) in parallel and is connected with the corresponding outer wall of the cargo carrying cabin (1) through a connecting arm.
5. The multi-rotor cargo aircraft of claim 1, wherein: and a second guide cylinder cover (13) is horizontally arranged outside the side-push rotor (2).
6. The multi-rotor cargo aircraft of claim 1, wherein: the first power equipment (3) and the second power equipment (6) both adopt engines or motors.
7. The multi-rotor cargo aircraft of claim 6, 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.
8. The multi-rotor cargo aircraft of claim 1, wherein: the sliding wheel (9) is provided with a damping function.
9. The multi-rotor cargo aircraft of claim 1, wherein: lift rotor (5) and the first draft tube cover (12) and second draft tube cover (13) of side thrust rotor (2), the length of draft tube cover along the air current direction can be confirmed through calculating as required, along with the length extension of draft tube cover along the air current direction, thereby the draft tube cover forms the air current duct.
10. The multi-rotor cargo aircraft of claim 1, wherein: lift rotor (5) and the first draft tube cover (12) and second draft tube cover (13) of side thrust rotor (2), the rotor in the draft tube cover also can be designed as single group, two groups or multiunit as required.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011128827.2A CN112141342A (en) | 2020-10-20 | 2020-10-20 | Cargo aircraft with multiple rotary wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011128827.2A CN112141342A (en) | 2020-10-20 | 2020-10-20 | Cargo aircraft with multiple rotary wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112141342A true CN112141342A (en) | 2020-12-29 |
Family
ID=73954224
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011128827.2A Pending CN112141342A (en) | 2020-10-20 | 2020-10-20 | Cargo aircraft with multiple rotary wings |
Country Status (1)
| Country | Link |
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| CN (1) | CN112141342A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114228913A (en) * | 2021-12-30 | 2022-03-25 | 苏州得尔达国际物流有限公司 | Cargo ship for transporting unmanned aerial vehicle and cargo |
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2020
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|---|---|---|---|---|
| CN102114914A (en) * | 2011-01-21 | 2011-07-06 | 文杰 | Distributed power multi-rotor VTOL (vertical take off and landing) aircraft and control method thereof |
| CN204548500U (en) * | 2015-03-13 | 2015-08-12 | 张澎 | A kind of can vertical takeoff and landing, hovering, flight and road driving aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114228913A (en) * | 2021-12-30 | 2022-03-25 | 苏州得尔达国际物流有限公司 | Cargo ship for transporting unmanned aerial vehicle and cargo |
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Application publication date: 20201229 |