CN214138948U - Engine-driven vertical take-off and landing aircraft - Google Patents

Abstract

The utility model provides an engine drive VTOL aircraft, including aircraft main part, first screw, second screw and screw engine, first screw and the equal level of second screw forward reverse rotation setting in the aircraft main part, the interval sets up about first screw and the second screw, and screw engine sets up in the aircraft main part or in and connect first screw and second screw and be used for driving first screw and the forward reverse rotation of second screw level. Preferably, the first propeller and the second propeller are arranged perpendicular to each other in a cross shape. The aircraft main part is unmanned aerial vehicle, still includes vertical pivot of screw, first jet engine and second jet engine. Alternatively, the aircraft body comprises a vertical cylinder. The utility model discloses an engine drive VTOL aircraft compact structure, occupation space is little, is convenient for take off safely and land, design benefit, and the structure is succinct, makes portably, and is with low costs, is suitable for extensive popularization and application.

Description

Engine-driven vertical take-off and landing aircraft

Technical Field

The utility model relates to an aircraft technical field, in particular to VTOL aircraft technical field specifically indicates an engine drive VTOL aircraft.

Background

VTOL planes are the best airplanes or aircrafts that do not require large yards or airport runways to take off or land. Helicopters and top-rotor aircraft are the only vertical take-off and landing aircraft that are driven by rotatable propellers (blades), but they are still expensive, heavy and expensive.

Due to the urgent need, some vertical take-off and landing aircraft such as EHANG flying taxis have recently been disclosed in some inventions. Patent application publication US2016/0023754 discloses a vertical takeoff aircraft that uses a mechanism for stowing/adjusting the ducted propeller after the ducted propeller is used to assist the aircraft in taking off over a short span. Patent application publication US2016/0311522 discloses an aircraft wing with a rotatable engine for assisting in takeoff of the aircraft. However, EHANG flying taxi is a single passenger low speed aircraft, generating low propulsive power by rotating blades, while in the other two inventions, the jet engine is mounted on the fuselage of the aircraft, which causes uncomfortable noise and vibration to the aircraft. Moreover, many such engines are attached to the fuselage in a side-to-side arrangement, with a very short distance between them, where the balance will not be perfect when taking off or landing.

An Airborne Reconfigurable Embedded System (ARES) is a concept for unmanned vertical take-off and landing flight modules that can transport various payloads, initiated by the united states department of Defense Advanced Research Projects Agency (DARPA) as a DARPA TX project, or transformed into a usable aircraft, with limited interest in the concept of a flying vehicle discovered by the department of national Defense Advanced Research Projects review in 2013, and presents a new model, which is a drone without a fuselage, with a top wing with two rotatable ducted propellers for takeoff and cruise, and a vehicle between which to carry payloads in the open space of a conventional fuselage. However, the size of the vehicle is still so large, 9.0 meters x13.0 meters, not compact, does not provide stowable/deployable wings, even of low stature, e.g., 1.0 meter below a multi Task air transporter (MTA).

Furthermore, while military aircraft are using vertical take-off and landing (VTOL) mechanisms, such as the F-35 fighter relying on rotatable jet engines … … and the like, airbus companies have announced their flying electric taxis in which a large quad-rotor drone picks up one vehicle cockpit and transports it from one location to another, however, such a drone arrangement is very bulky and requires a large amount of space to work within.

Accordingly, it is desirable to provide an engine-driven VTOL aerial vehicle that is compact, occupies a small space, and facilitates safe takeoff and landing.

SUMMERY OF THE UTILITY MODEL

In order to overcome the defects in the prior art, the utility model discloses an object is to provide an engine drive VTOL aircraft, its compact structure, occupation space is little, is convenient for take-off safely and land, is suitable for extensive popularization and application.

Another object of the utility model is to provide an engine drive VTOL aircraft, its design benefit, the structure is succinct, makes portably, and is with low costs, is suitable for extensive popularization and application.

In order to achieve the above object, the utility model discloses an engine drive VTOL aircraft, its characteristics are, including aircraft main part, first screw, second screw and screw engine, wherein:

the first propeller and the second propeller are horizontally arranged on the aircraft main body in a forward and reverse rotating mode, the first propeller and the second propeller are arranged on the aircraft main body at intervals from top to bottom, and the propeller engine is arranged on the aircraft main body or arranged in the aircraft main body and connected with the first propeller and the second propeller to drive the first propeller and the second propeller to horizontally rotate in the forward and reverse direction.

Preferably, the first propeller and the second propeller are arranged perpendicular to each other in a cross shape.

Preferably, the propeller engine is a reciprocating engine, a turboshaft engine or an electric motor.

Preferably, the aircraft main part is unmanned aerial vehicle, engine drive VTOL aircraft still includes screw vertical rotating shaft, first jet engine and second jet engine, but the lower extreme level of screw vertical rotating shaft is positive reverse rotation and is inserted and establish on unmanned aerial vehicle, first screw with the equal level setting of second screw is in on the upper end of screw vertical rotating shaft, screw engine sets up on unmanned aerial vehicle or set up in the unmanned aerial vehicle and connect screw vertical rotating shaft is used for the drive screw vertical rotating shaft level positive reverse rotation, first jet engine sets up on unmanned aerial vehicle or set up in the unmanned aerial vehicle, second jet engine sets up on unmanned aerial vehicle or set up in the unmanned aerial vehicle.

Preferably, the vertical rotating shaft of the propeller is a vertical telescopic rotating shaft.

More preferably, the propeller engine, the first jet engine and the second jet engine are all disposed in the top of the front side of the unmanned aerial vehicle, the first jet engine and the second jet engine are respectively located on the left side and the right side of the propeller engine, the engine-driven vertical take-off and landing aircraft further comprises a first air inlet pipe, a second air inlet pipe, a third air inlet pipe, a first exhaust nozzle, a second exhaust nozzle and a third exhaust nozzle, the first air inlet pipe, the second air inlet pipe and the third air inlet pipe are all arranged through the top of the front side of the unmanned aerial vehicle and are respectively connected with the first exhaust nozzle, the second exhaust nozzle and the third exhaust nozzle through the propeller engine, the first jet engine and the second jet engine, the first exhaust nozzle, the second exhaust nozzle and the third exhaust nozzle are all disposed on the rear side of the unmanned aerial vehicle and are disposed rearward, the second exhaust nozzle and the third exhaust nozzle are located on the left and right sides of the first exhaust nozzle, respectively.

More preferably, the propeller engine is disposed in a middle position of a top of a front side of the unmanned aerial vehicle, the first jet engine and the second jet engine are disposed in a left side and a right side of a bottom of the front side of the unmanned aerial vehicle, respectively, the engine-driven vertical take-off and landing aircraft further includes a first air intake pipe, a second air intake pipe, a third air intake pipe, a first exhaust nozzle, a second exhaust nozzle, and a third exhaust nozzle, the first air intake pipe, the second air intake pipe, and the third air intake pipe penetrate through a middle position of the top of the front side of the unmanned aerial vehicle, a left side of the bottom of the front side of the unmanned aerial vehicle, and a right side of the bottom of the front side of the unmanned aerial vehicle, respectively, and are connected to the first exhaust nozzle, the second exhaust nozzle, and the third exhaust nozzle through air paths of the propeller engine, the first jet engine, and the second jet engine, first exhaust nozzle second exhaust nozzle with third exhaust nozzle all sets up unmanned aerial vehicle's rear side sets up towards the back, second exhaust nozzle with third exhaust nozzle is located respectively first exhaust nozzle's left side and right side.

Preferably, the engine-driven VTOL aerial vehicle further comprises an observation assembly, and the observation assembly is arranged on the unmanned aerial vehicle and used for scanning, shooting or taking pictures.

Preferably, the first screw with the cross setting is become to second screw mutually perpendicular, the second screw is followed the length direction of unmanned aerial vehicle's fuselage sets up, the first screw is along the perpendicular to the length direction's of unmanned aerial vehicle's fuselage direction sets up.

Preferably, the aircraft main body comprises a vertical cylinder, the first propeller and the second propeller are sleeved on the upper portion of the vertical cylinder and can rotate forward and backward relative to the upper portion level of the vertical cylinder, and the propeller engine is arranged in the middle of the vertical cylinder and connected with the first propeller and the second propeller to drive the first propeller and the second propeller to rotate forward and backward horizontally.

More preferably, the engine-driven VTOL aerial vehicle further comprises a first jet engine disposed at a lower portion of the vertical cylinder.

Preferably, the aircraft main body further comprises a left wing and a right wing, wherein the left wing and the right wing are respectively positioned on the left side and the right side of the middle part of the vertical cylinder and are respectively connected with the middle part of the vertical cylinder.

Still further, the engine-driven VTOL aerial vehicle further comprises a first jet engine and a second jet engine, the first jet engine and the second jet engine being respectively located under and connected to the left wing and the right wing.

Preferably, the engine-driven VTOL aerial vehicle further comprises a smooth aerodynamic object, the bottom of the vertical cylinder is arranged on the smooth aerodynamic object, and the smooth aerodynamic object is used for connecting an object to be carried.

Preferably, the engine-driven VTOL aerial vehicle further comprises a locking mechanism, and the locking mechanism is arranged at the bottom of the vertical cylinder and used for locking an object to be carried.

More preferably, the propeller engine is an electric motor, the engine-driven VTOL aerial vehicle further comprises a battery, the battery and the electric motor are both disposed in the vertical cylinder, and the battery is electrically connected to the electric motor.

Preferably, the engine-driven vertical take-off and landing aircraft further comprises a wing-provided pneumatic plate with double tail wings, the bottom of the vertical cylinder is arranged on the wing-provided pneumatic plate with double tail wings, and the wing-provided pneumatic plate with double tail wings is used for connecting an object to be carried.

Preferably, the engine-driven VTOL aircraft further comprises an article carrying support and a plurality of connecting ropes, the bottom of the vertical cylinder is connected with the article carrying support, the upper ends of the connecting ropes are connected with the article carrying support, and the lower ends of the connecting ropes are used for connecting an object to be carried.

The beneficial effects of the utility model mainly lie in:

1. the utility model discloses an engine drive VTOL aircraft includes the aircraft main part, first screw, second screw and screw engine, but first screw and the equal level of second screw forward reverse rotation setting in the aircraft main part, the interval sets up about first screw and the second screw, screw engine sets up in the aircraft main part or sets up in the aircraft main part and connects first screw and second screw to be used for driving first screw and the horizontal forward reverse rotation of second screw, realize VTOL based on dual drive screw (rotor) promptly, therefore, the steam generator is compact in structure, occupation space is little, be convenient for take off safely and land, be suitable for extensive popularization and application.

2. The utility model discloses an engine drive VTOL aircraft includes the aircraft main part, first screw, second screw and screw engine, but first screw and the equal level of second screw forward reverse rotation setting in the aircraft main part, the interval sets up about first screw and the second screw, screw engine sets up in the aircraft main part or sets up in the aircraft main part and connects first screw and second screw to be used for driving first screw and the horizontal forward reverse rotation of second screw, realize VTOL based on dual drive screw (rotor) promptly, therefore, its design benefit, the structure is succinct, simple manufacture, low cost, be suitable for extensive popularization and application.

These and other objects, features and advantages of the present invention will become more fully apparent from the following detailed description, the accompanying drawings and the appended claims, wherein like reference numerals refer to corresponding parts throughout the several views, and wherein like reference numerals refer to like parts throughout the several views.

Drawings

Fig. 1A is a first schematic perspective view of a first embodiment of the engine-driven vertical takeoff and landing aircraft of the present invention.

FIG. 1B is a second perspective view of the first embodiment shown in FIG. 1A.

Fig. 2A is a first schematic perspective view of a second embodiment of the engine-driven vertical takeoff and landing aircraft of the present invention.

Fig. 2B is a second perspective view of the second embodiment shown in fig. 2A.

Fig. 3A is a first schematic perspective view of a third embodiment of the engine-driven vertical takeoff and landing aircraft of the present invention.

FIG. 3B is a second perspective view of the third embodiment shown in FIG. 3A.

Fig. 3C is a third schematic perspective view of the third embodiment shown in fig. 3A.

Fig. 4 is a schematic perspective view of a fourth embodiment of the engine-driven vtol aircraft of the present invention.

Fig. 5 is a schematic perspective view of a fifth embodiment of the engine-driven vtol aircraft of the present invention.

Fig. 6A is an exploded perspective view of a sixth embodiment of the engine-driven vtol aircraft of the present invention.

Fig. 6B is a perspective view of the sixth embodiment shown in fig. 6A.

Fig. 7A is a first schematic perspective view of a seventh embodiment of the engine-driven vertical take-off and landing aircraft of the present invention.

Fig. 7B is a second perspective view of the seventh embodiment shown in fig. 7A.

Fig. 8A is a first schematic perspective view of an eighth embodiment of the engine-driven vertical take-off and landing aircraft of the present invention.

Fig. 8B is a second perspective view of the eighth embodiment shown in fig. 8A.

Fig. 9A is a first schematic perspective view of a ninth embodiment of the engine-driven vertical take-off and landing aircraft of the present invention.

Fig. 9B is a second perspective view of the ninth embodiment shown in fig. 9A.

Fig. 10 is a schematic perspective view of a tenth embodiment of the engine-driven vtol aircraft of the present invention.

Fig. 11A is an exploded perspective view of an eleventh embodiment of the engine-driven vtol aircraft of the present invention.

Fig. 11B is a schematic perspective view of the eleventh embodiment shown in fig. 11A.

Fig. 12A is a first schematic perspective view of a twelfth embodiment of the engine-driven vertical takeoff and landing aircraft of the present invention.

Fig. 12B is a second perspective view of the twelfth embodiment shown in fig. 12A.

Fig. 13A is a first perspective view of a thirteenth embodiment of the engine-driven vertical take-off and landing aircraft of the present invention.

Fig. 13B is a second perspective view of the thirteenth embodiment shown in fig. 13A.

Fig. 14A is a schematic perspective view of a fourteenth embodiment of the engine-driven vertical takeoff and landing aircraft according to the present invention.

Fig. 14B is a second perspective view of the fourteenth embodiment shown in fig. 14A.

Fig. 15 is a schematic perspective view of a fifteenth embodiment of the engine-driven vertical take-off and landing aircraft of the present invention.

Fig. 16A is an exploded perspective view of a sixteenth embodiment of the engine-driven vtol aircraft of the present invention.

Fig. 16B is a first perspective view of the sixteenth embodiment shown in fig. 16A.

Fig. 16C is a second perspective view of the sixteenth embodiment shown in fig. 16A.

Fig. 17A is a schematic front view of a seventeenth embodiment of the engine-driven vertical take-off and landing aircraft of the present invention.

Fig. 17B is a schematic perspective view of the seventeenth embodiment shown in fig. 17A.

Fig. 18 is a schematic perspective view of an eighteenth embodiment of the engine-driven vtol aircraft of the present invention.

(symbol description)

1 an aircraft body; 2a first propeller; 3a second propeller; 4a propeller engine; 5, unmanned aerial vehicle; 6, a propeller vertical rotating shaft; 7a first jet engine; 8a second jet engine; 9a first air inlet pipe; 10 a second air inlet pipe; 11a third air inlet pipe; 12a first exhaust nozzle; 13a second exhaust nozzle; 14a third exhaust nozzle; 15 an observation component; 16 vertical cylinders; 17a left wing; 18 right wing; 19 a smooth aerodynamic object; 20 an object to be carried; 21 smooth aerodynamic plates; 22 a rescue boat; 23 wheels; 24 open rescue boats; 25 a closed rescue boat; 26 a locking mechanism; 27 wing tanks; 28 vehicles; 293 human cars; 30 an aerodynamic container; 31 a reciprocating engine; a 32 motor; 33 a battery; 34 double tail wings; 35 a wing-carrying pneumatic plate; 36 an article carrying rack; 37 connecting the ropes; 38 an inverted V-shaped bracket; 39 wrapping; a 402 person automobile; 41 submarine; 42 ship.

Detailed Description

In order to clearly understand the technical contents of the present invention, the following embodiments are specifically illustrated in detail.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.

Referring to fig. 1A to 18, in the first to eighteenth embodiments of the present invention, the engine-driven vertical take-off and landing aircraft of the present invention includes an aircraft main body 1, a first propeller 2, a second propeller 3, and a propeller engine 4, wherein:

the first propeller 2 and the second propeller 3 are horizontally arranged on the aircraft body 1 in a forward and reverse rotating mode, the first propeller 2 and the second propeller 3 are arranged at intervals up and down, and the propeller engine 4 is arranged on the aircraft body 1 or arranged in the aircraft body 1 and connected with the first propeller 2 and the second propeller 3 to drive the first propeller 2 and the second propeller 3 to horizontally rotate in the forward and reverse direction.

Therefore, the utility model discloses a dual drive screw (rotor) promptly first screw 2 with the VTOL is realized to second screw 3. The adjustment of the first propeller 2 and the second propeller 3 may be achieved by a conventional swash plate (not shown).

The first propeller 2 and the second propeller 3 may be disposed along the same direction, or disposed along different directions to form a cross, as shown in fig. 1A to 18, in the first to eighteenth embodiments of the present invention, the first propeller 2 and the second propeller 3 are perpendicular to each other to form a cross.

The propeller engine 4 may be any suitable propeller engine, and may use fuel, such as a reciprocating engine 31 or a turboshaft engine, or electricity, such as an electric motor 32, as shown in fig. 1A to 2B, and in the first embodiment to the second embodiment of the present invention, the propeller engine 4 is a reciprocating engine 31.

The aircraft body 1 may be any suitable aircraft body, please refer to fig. 1A to 3C, in the first to third embodiments of the present invention, the aircraft body 1 is an unmanned aerial vehicle 5, the engine-driven vertical take-off and landing aircraft further includes a propeller vertical shaft 6, a first jet engine 7 and a second jet engine 8, a lower end of the propeller vertical shaft 6 is inserted on the unmanned aerial vehicle 5 in a horizontal forward and reverse direction rotation manner, the first propeller 2 and the second propeller 3 are both horizontally disposed on an upper end of the propeller vertical shaft 6, the propeller engine 4 is disposed on the unmanned aerial vehicle 5 or in the unmanned aerial vehicle 5 and connected to the propeller vertical shaft 6 for driving the propeller vertical shaft 6 to rotate horizontally in the forward and reverse direction, the first jet engine 7 is disposed on the unmanned aerial vehicle 5 or in the unmanned aerial vehicle 5, the second jet engine 8 is provided on the drone 5 or in the drone 5.

When in use, the first propeller 2 and the second propeller 3 are driven by the propeller engine 4 to horizontally rotate in forward and reverse directions so as to drive the unmanned aerial vehicle 5 to take off and land. Whereas the first jet engine 7 and the second jet engine 8 provide thrust during cruising and maneuvering after takeoff and before landing, such an arrangement would be more powerful, more stable, safer, in which if the propeller engines 4 were in a shutdown state, the flight would continue so that a safe landing could be carried out at the airport, and vice versa, if the first jet engine 7 and the second jet engine 8 were in a shutdown state, the propeller engines 4 would support the rotors for a safe landing.

The vertical rotating shaft 6 of the propeller can be a vertical telescopic rotating shaft or a vertical non-telescopic rotating shaft, please refer to fig. 3A to 3C, in the third embodiment of the present invention, the vertical rotating shaft 6 of the propeller is a vertical telescopic rotating shaft. This allows to get as close as possible to the drone 5 when the first propeller 2 and the second propeller 3 are not in use.

The propeller engine 4, the first jet engine 7 and the second jet engine 8 may be arranged at any suitable position of the drone 5, more preferably the propeller engine 4, the first jet engine 7 and the second jet engine 8 are all arranged on top of the front side of the drone 5, the first jet engine 7 and the second jet engine 8 being located on the left and right side of the propeller engine 4, respectively. Referring to fig. 1A to 1B, in a first embodiment of the present invention, the propeller engine 4, the first jet engine 7 and the second jet engine 8 are all disposed in the top of the front side of the unmanned aerial vehicle 5, the first jet engine 7 and the second jet engine 8 are respectively disposed on the left side and the right side of the propeller engine 4, the engine-driven vertical take-off and landing aircraft further includes a first air inlet pipe 9, a second air inlet pipe 10, a third air inlet pipe 11, a first exhaust nozzle 12, a second exhaust nozzle 13 and a third exhaust nozzle 14, the first air inlet pipe 9, the second air inlet pipe 10 and the third air inlet pipe 11 are all disposed through the top of the front side of the unmanned aerial vehicle 5 and are respectively connected to the first exhaust nozzle 12 through the propeller engine 4, the first jet engine 7 and the second jet engine 8 in an air path, Second exhaust nozzle 13 with third exhaust nozzle 14, first exhaust nozzle 12 second exhaust nozzle 13 with third exhaust nozzle 14 all sets up unmanned aerial vehicle 5's rear side sets up towards the back, second exhaust nozzle 13 with third exhaust nozzle 14 is located respectively the left side and the right side of first exhaust nozzle 12. Air enters the propeller engine 4, the first jet engine 7 and the second jet engine 8 through the first air inlet pipe 9, the second air inlet pipe 10 and the third air inlet pipe 11, respectively, and exhaust gas is discharged through the first exhaust nozzle 12, the second exhaust nozzle 13 and the third exhaust nozzle 14, respectively.

The propeller engine 4, the first jet engine 7 and the second jet engine 8 may be disposed at any suitable position of the unmanned aerial vehicle 5, and more preferably, the propeller engine 4 is disposed at a middle position of a top portion of a front side of the unmanned aerial vehicle 5, and the first jet engine 7 and the second jet engine 8 are respectively disposed at two sides of a bottom portion of the front side of the unmanned aerial vehicle 5. Referring to fig. 2A to 3C, in the second to third embodiments of the present invention, the propeller engine 4 is disposed in the middle of the top of the front side of the unmanned aerial vehicle 5, the first jet engine 7 and the second jet engine 8 are disposed in the left side and the right side of the bottom of the front side of the unmanned aerial vehicle 5, the engine-driven vertical take-off and landing aircraft further includes a first air inlet pipe 9, a second air inlet pipe 10, a third air inlet pipe 11, a first exhaust nozzle 12, a second exhaust nozzle 13, and a third exhaust nozzle 14, the first air inlet pipe 9, the second air inlet pipe 10, and the third air inlet pipe 11 are respectively disposed through the middle of the top of the front side of the unmanned aerial vehicle 5, the left side of the bottom of the front side of the unmanned aerial vehicle 5, and the right side of the bottom of the front side of the unmanned aerial vehicle 5, and pass through the propeller engine 4, the jet engine, the third air inlet pipe, First jet engine 7 with 8 gas circuit connections of second jet engine first exhaust nozzle 12 second exhaust nozzle 13 with third exhaust nozzle 14, first exhaust nozzle 12 second exhaust nozzle 13 with third exhaust nozzle 14 all sets up unmanned aerial vehicle 5's rear side sets up towards the back, second exhaust nozzle 13 with third exhaust nozzle 14 is located respectively the left side and the right side of first exhaust nozzle 12.

The engine-driven vertical take-off and landing aircraft may further include any other suitable components, as shown in fig. 1A to 1B and fig. 3A to 3C, in the first embodiment and the third embodiment of the present invention, the engine-driven vertical take-off and landing aircraft further includes an observation assembly 15, and the observation assembly 15 is disposed on the unmanned aerial vehicle 5 for scanning, photographing or photographing. In fact, by means of the unmanned aerial vehicle 5, it is possible to carry out a plurality of tasks, if the observation assembly 15 is carried, the observation assembly 15 can be compactly assembled by means of a series of tools, instruments or devices, such as cameras, sensors, lidar, radar, etc., and can be scanned or imaged from the high altitude by using the first jet engine 7 and the second jet engine 8 at high speed, or at low altitude when the first jet engine 7 and the second jet engine 8 are turned off and the propeller engine 4 is started, so that the present invention can be easily hovered, turned around or slowly approached to a small place.

Under the condition that first screw 2 with second screw 3 mutually perpendicular becomes the cross setting, first screw 2 with second screw 3 can follow any suitable direction setting, please see that fig. 1A ~ 3C show, in the utility model discloses a first concrete embodiment to third concrete embodiment, second screw 3 is followed the length direction setting of unmanned aerial vehicle 5's fuselage, first screw 2 is along the perpendicular to the direction setting of the length direction of unmanned aerial vehicle 5's fuselage. This arrangement provides more aerodynamic characteristics for high speed flight when the first and second jet engines 7, 8 are started and the propeller engine 4 is switched off.

The aircraft body 1 may have any suitable structure, as shown in fig. 4 to 18, in the fourth to eighteenth embodiments of the present invention, the aircraft body 1 includes a vertical cylinder 16, the first propeller 2 and the second propeller 3 are both sleeved on the upper portion of the vertical cylinder 16 and are disposed to be rotatable in forward and reverse directions relative to the upper level of the vertical cylinder 16, and the propeller engine 4 is disposed in the middle of the vertical cylinder 16 and connects the first propeller 2 and the second propeller 3 for driving the first propeller 2 and the second propeller 3 to rotate in forward and reverse directions horizontally. That is, the propeller engine 4 is not mounted on the drone 5 or within the drone 5, but is designed as a separate air vehicle for picking up and carrying other separate objects. In use the first and second propellers 2, 3 are driven by the propeller engine 4 to drive vertical take-off and landing, so that the arrangement has flight capabilities similar to a conventional helicopter but with a relatively different shape. This arrangement is intended to carry a load which is lighter than the load carried by a jet engine, i.e. a load weight of between 0.5 and 0.7 tonnes.

The propeller engine 4 may be disposed in the middle of the vertical cylinder 16 by any suitable structure, as shown in fig. 4 to 12B and fig. 15 to 18, and in the fourth embodiment to the twelfth embodiment and the fifteenth embodiment to the eighteenth embodiment of the present invention, the propeller engine 4 is inserted into the middle of the vertical cylinder 16 along the front-rear direction.

The engine-driven vertical take-off and landing aircraft may further include any other suitable configuration, as shown in fig. 9A to 9B, and in a ninth embodiment of the present invention, the engine-driven vertical take-off and landing aircraft further includes a first jet engine 7, and the first jet engine 7 is disposed at a lower portion of the vertical cylinder 16. In use, the first propeller 2 and the second propeller 3 are driven by the propeller engines 4 to drive vertical take-off and landing, and the first jet engine 7 provides thrust during cruise and maneuvering after takeoff and before landing. This arrangement is intended to carry a load which is lighter than the load carried by the two jet engines described below, that is to say an average load weight of between 0.5 and 1.0 tonne.

The first jet engine 7 is disposed at the lower portion of the vertical cylinder 16 and may adopt any suitable structure, please refer to fig. 9A-9B, in the ninth embodiment of the present invention, the first jet engine 7 is disposed at the lower portion of the vertical cylinder 16 along the front-back direction.

The aircraft body 1 may further include any other suitable structure, as shown in fig. 4 to 10 and 15 to 18, in the fourth to tenth, fifteenth and eighteenth embodiments of the present invention, the aircraft body 1 further includes a left wing 17 and a right wing 18, and the left wing 17 and the right wing 18 are respectively located at the left side and the right side of the middle portion of the vertical cylinder 16 and are respectively connected to the middle portion of the vertical cylinder 16.

The engine-driven vertical take-off and landing aircraft may further include any other suitable configuration, as shown in fig. 4 to 8B and fig. 15 to 17B, and in the first embodiment to the eighth embodiment and the fifteenth embodiment to the seventeenth embodiment of the present invention, the engine-driven vertical take-off and landing aircraft further includes a first jet engine 7 and a second jet engine 8, and the first jet engine 7 and the second jet engine 8 are respectively located under the left wing 17 and the right wing 18 and respectively connect the left wing 17 and the right wing 18. In use, the first propeller 2 and the second propeller 3 are driven by the propeller engines 4 to drive vertical take-off and landing, and the first jet engine 7 and the second jet engine 8 provide thrust during cruise and maneuvering after takeoff and before landing. If the engine is of the fuel type, the left wing 17 and the right wing 18 will be loaded with the fuel required for operating the engine, while the vertical cylinder 16 will contain the conventional drive shafts and mechanisms (not shown) for the first propeller 2 and the second propeller 3, by using double propellers, so that the rotational forces can be balanced without the need for a conventional tail fan. The other hollow parts of the vertical cylinder 16 can be used for unmanned remote control avionics equipment from bottom to top, and the bottom of the vertical cylinder 16 is used for connecting to objects 20 to be carried, and then the objects 20 to be carried are transported from one position to another position, and can carry heavy loads of more than 1 ton.

The engine-driven vertical take-off and landing aircraft may further include any other suitable configuration, as shown in fig. 5 and 7A to 8B, and in a fifth embodiment, a seventh embodiment to an eighth embodiment of the present invention, the engine-driven vertical take-off and landing aircraft further includes a smooth aerodynamic body 19, a bottom of the vertical cylinder 16 is disposed on the smooth aerodynamic body 19, and the smooth aerodynamic body 19 is used to connect with an object 20 to be carried.

The smooth aerodynamic object 19 may be any suitable smooth aerodynamic object, and the object 20 may be any suitable object, as shown in fig. 5 and fig. 7A to 8B, in a fifth embodiment, a seventh embodiment to an eighth embodiment of the present invention, the smooth aerodynamic object 19 is a smooth aerodynamic plate 21, and the object 20 is a rescue boat 22.

The rescue ship 22 can be an open rescue ship 24 or a closed rescue ship 25, as shown in fig. 7A to 7B, in a seventh embodiment of the present invention, the rescue ship 22 is an open rescue ship 24. Referring to fig. 8A to 8B, in an eighth embodiment of the present invention, the rescue boat 22 is a closed rescue boat 25 with wheels 23 at the bottom. The closed rescue vessel 25 with wheels 23 at the bottom can land at sea, flood or paved areas to perform rescue tasks.

The engine-driven vertical take-off and landing aircraft may further include any other suitable configuration, as shown in fig. 6A to 6B and fig. 11A to 14B, and in a sixth embodiment, an eleventh embodiment to a fourteenth embodiment of the present invention, the engine-driven vertical take-off and landing aircraft further includes a locking mechanism 26, and the locking mechanism 26 is disposed at the bottom of the vertical cylinder 16 for locking the object 20 to be carried.

The object 20 to be carried may be any suitable object to be carried, and further, the object 20 to be carried is a wing tank 27, a vehicle 28, a passenger compartment (not shown) or an aerodynamic container 30. Referring to fig. 6A to 6B, in a sixth embodiment of the present invention, the object 20 to be carried is a wing tank 27. Rely on first screw 2 with after the second screw 3 lands, the utility model discloses a vertical cylinder 16's bottom is passed through locking mechanical system 26 with wing cabin 27 is connected, picks up it, flies upwards perpendicularly, relies on first jet engine 7 with second jet engine 8 is upwards and fly suddenly forward, takes it to an area, in this area, if wing cabin 27 loads passenger or goods, then the utility model discloses land in a small airport, if wing cabin 27 loads fire extinguisher, sprinkler or pesticide, then spiral in the sky in specific area and put out a fire, irrigates crops, sprays crops etc..

More preferably, the vehicle 28 is a 2-person automobile 40 or a 3-person automobile 29, the passenger compartment is a 1-person compartment or a 2-person compartment, and the aerodynamic container 30 is a 1-person aerodynamic container or a 2-person aerodynamic container, that is, less than 0.25 ton. Referring to fig. 11A to 11B, in an eleventh embodiment of the present invention, the vehicle 28 is a 3-person automobile 29. Referring to fig. 12A to 12B, in a twelfth embodiment of the present invention, the vehicle 28 is a 2-person automobile 40.

The aerodynamic container 30 may have any suitable shape, as shown in fig. 13A-13B, and in a thirteenth embodiment of the present invention, the aerodynamic container 30 is in the shape of a tent. Referring to fig. 14A-14B, in a fourteenth embodiment of the present invention, the aerodynamic container 30 is a bottle shape.

As mentioned above, the propeller engine 4 may be any suitable propeller engine, and may use fuel, such as a reciprocating engine 31 or a turboshaft engine, or electricity, such as an electric motor 32, as shown in fig. 13A to 14B, in the thirteenth to fourteenth embodiments of the present invention, the propeller engine 4 is an electric motor 32, the engine-driven vertical take-off and landing aircraft further includes a battery 33, the battery 33 and the electric motor 32 are both disposed in the vertical cylinder 16, and the battery 33 is electrically connected to the electric motor 32.

The engine-driven vertical take-off and landing aircraft may further include any other suitable configuration, as shown in fig. 15 to 17B, and in the fifteenth embodiment to the seventeenth embodiment of the present invention, the engine-driven vertical take-off and landing aircraft further includes a wing-equipped air panel 35 having a double tail wing 34, the bottom of the vertical cylinder 16 is disposed on the wing-equipped air panel 35 having the double tail wing 34, and the wing-equipped air panel 35 having the double tail wing 34 is used for connecting the object 20 to be carried. The described winged pneumatic plate 35 with double tail 34 may be sized and shaped to carry any item, luggage, compartment, container, vehicle …, etc.

The object 20 to be carried may be any suitable object to be carried, and further, the object 20 to be carried is a submarine 41 or a ship 42, as shown in fig. 16A to 16C, and in a sixteenth embodiment of the present invention, the object 20 to be carried is the submarine 41. Referring to fig. 17A to 17B, in a seventeenth embodiment of the present invention, the object 20 to be carried is a ship 42.

The engine-driven vertical take-off and landing aircraft may further include any other suitable components, as shown in fig. 18, in an eighteenth embodiment of the present invention, the engine-driven vertical take-off and landing aircraft further includes an article carrying bracket 36 and a plurality of connecting ropes 37, the article carrying bracket 36 is connected to the bottom of the vertical cylinder 16, the article carrying bracket 36 is connected to the upper ends of the plurality of connecting ropes 37, and the lower ends of the plurality of connecting ropes 37 are used for connecting the object 20 to be carried.

The article carrier rack 36 may have any suitable shape, and the object 20 may be any suitable object to be carried, as shown in fig. 18. in an eighteenth embodiment of the present invention, the article carrier rack 36 is an inverted V-shaped rack 38, and the object 20 is a package 39.

Therefore, the utility model relates to an engine and two propeller configurations, built-in the unmanned aerial vehicle or form the isolated plant and pick up the object that awaits carrying, realize VTOL. Thus, the present invention provides a vertical take-off and landing arrangement with a single, dual or triple engine arrangement, wherein at least one is used to drive the twin propellers in order to support take-off and landing, these arrangements can be permanently installed in an aircraft, unmanned aerial vehicle, or temporarily installed on small land vehicles or the like in order to support their flight. And simultaneously, the utility model also provides a safe landing and setting of taking off under various conditions, because do not need the airport runway, consequently, on the runway that has sand, frozen, skid, have the fog, especially under the stormy weather, high-speed landing can not cause danger.

To sum up, the utility model discloses an engine drive VTOL aircraft compact structure, occupation space is little, is convenient for take off safely and land, design benefit, and the structure is succinct, makes portably, and is with low costs, is suitable for extensive popularization and application.

Therefore, the purpose of the utility model is completely and effectively realized. The functional and structural principles of the present invention have been shown and described in the embodiments, and the embodiments may be modified without departing from the principles. Therefore, the present invention includes all modifications within the spirit and scope of the appended claims.

Claims (18)

1. An engine-driven VTOL aerial vehicle comprising an aerial vehicle body, a first propeller, a second propeller and a propeller engine, wherein:

the first propeller and the second propeller are horizontally arranged on the aircraft main body in a forward and reverse rotating mode, the first propeller and the second propeller are arranged on the aircraft main body at intervals from top to bottom, and the propeller engine is arranged on the aircraft main body or arranged in the aircraft main body and connected with the first propeller and the second propeller to drive the first propeller and the second propeller to horizontally rotate in the forward and reverse direction.

2. The engine-driven VTOL aerial vehicle of claim 1, wherein the first and second propellers are arranged perpendicular to each other in a cruciform arrangement.

3. The engine driven vtol aerial vehicle of claim 1, wherein the propeller engine is a reciprocating engine, a turboshaft engine, or an electric motor.

4. The engine-driven VTOL aerial vehicle of claim 1, wherein the aircraft body is a drone, the engine-driven vertical take-off and landing aircraft also comprises a propeller vertical rotating shaft, a first jet engine and a second jet engine, the lower end of the propeller vertical rotating shaft can be horizontally inserted on the unmanned aerial vehicle in a forward and reverse rotating manner, the first propeller and the second propeller are both horizontally arranged on the upper end of the propeller vertical rotating shaft, the propeller engine is arranged on the unmanned aerial vehicle or in the unmanned aerial vehicle and is connected with the propeller vertical rotating shaft for driving the propeller vertical rotating shaft to horizontally rotate forwards and reversely, the first jet engine is arranged on the unmanned aerial vehicle or in the unmanned aerial vehicle, and the second jet engine is arranged on the unmanned aerial vehicle or in the unmanned aerial vehicle.

5. The engine driven VTOL aerial vehicle of claim 4, wherein the propeller vertical axis of rotation is a vertically retractable axis of rotation.

6. The engine driven VTOL aerial vehicle of claim 4, wherein the propeller engine, the first jet engine, and the second jet engine are all disposed in a top portion of a front side of the UAV, the first jet engine and the second jet engine are respectively located at left and right sides of the propeller engine, the engine driven VTOL aerial vehicle further comprises a first air intake pipe, a second air intake pipe, a third air intake pipe, a first exhaust nozzle, a second exhaust nozzle, and a third exhaust nozzle, the first air intake pipe, the second air intake pipe, and the third air intake pipe are all disposed through the top portion of the front side of the UAV and are air-connected to the first exhaust nozzle, the second exhaust nozzle, and the third exhaust nozzle through the propeller engine, the first jet engine, and the second jet engine, respectively, first exhaust nozzle second exhaust nozzle with third exhaust nozzle all sets up unmanned aerial vehicle's rear side sets up towards the back, second exhaust nozzle with third exhaust nozzle is located respectively first exhaust nozzle's left side and right side.

7. The engine driven VTOL aerial vehicle of claim 4, wherein the propeller engine is disposed in a middle position of a top of a front side of the UAV, the first and second jet engines are disposed in left and right sides of a bottom of the front side of the UAV, respectively, the engine driven VTOL aerial vehicle further comprises a first air intake pipe, a second air intake pipe, a third air intake pipe, a first exhaust nozzle, a second exhaust nozzle, and a third exhaust nozzle, the first air intake pipe, the second air intake pipe, and the third air intake pipe respectively penetrate through the middle position of the top of the front side of the UAV, the left side of the bottom of the front side of the UAV, and the right side of the bottom of the front side of the UAV and are in air circuit connection with the first exhaust nozzle through the propeller engine, the first jet engine, and the second jet engine, respectively, Second exhaust nozzle with third exhaust nozzle, first exhaust nozzle second exhaust nozzle with third exhaust nozzle all sets up unmanned aerial vehicle's rear side sets up towards the back, second exhaust nozzle with third exhaust nozzle is located respectively first exhaust nozzle's left side and right side.

8. The engine driven vtol aerial vehicle of claim 4, further comprising an observation assembly disposed on the drone for scanning, imaging, or photographing.

9. The engine driven VTOL aerial vehicle of claim 4, wherein the first and second propellers are arranged in a cross shape perpendicular to each other, the second propeller is arranged along a length direction of the fuselage of the UAV, and the first propeller is arranged along a direction perpendicular to the length direction of the fuselage of the UAV.

10. The engine driven vtol aerial vehicle of claim 1, wherein the vehicle body comprises a vertical cylinder, the first propeller and the second propeller both fit over the upper portion of the vertical cylinder and are arranged to rotate in a forward and reverse direction with respect to the upper portion of the vertical cylinder, and the propeller engine is disposed in the middle of the vertical cylinder and connects the first propeller and the second propeller for driving the first propeller and the second propeller to rotate in a forward and reverse direction horizontally.

11. The engine driven vtol aircraft of claim 10, further comprising a first jet engine disposed at a lower portion of the vertical cylinder.

12. The engine-driven vtol aerial vehicle of claim 10, wherein the vehicle body further comprises a left wing and a right wing, the left wing and the right wing being located to the left and right of the middle of the vertical cylinder and connected to the middle of the vertical cylinder, respectively.

13. The engine driven vtol aircraft of claim 12, further comprising first and second jet engines positioned under and connecting the left and right wings, respectively.

14. The engine-driven vtol aerial vehicle of claim 10, further comprising a slick aerodynamic body on which the bottom of the vertical cylinder is disposed, the slick aerodynamic body for attachment to an object to be carried.

15. The engine-driven VTOL aerial vehicle of claim 10, further comprising a locking mechanism disposed at a bottom of the vertical cylinder for locking an object to be carried.

16. The engine-driven vtol aerial vehicle of claim 10, wherein the propeller engine is an electric motor, the engine-driven vtol aerial vehicle further comprising a battery, the battery and the electric motor both disposed within the vertical cylinder, the battery electrically connected to the electric motor.

17. The engine-driven VTOL aerial vehicle of claim 10, further comprising a winged pneumatic plate having a double tail wing, wherein a bottom of the vertical cylinder is disposed on the winged pneumatic plate having a double tail wing for connecting an object to be carried.

18. The engine-driven vtol aerial vehicle of claim 10, further comprising an article carrier bracket and a plurality of connecting lines, wherein the bottom of the vertical cylinder is connected to the article carrier bracket, the upper ends of the plurality of connecting lines are connected to the article carrier bracket, and the lower ends of the plurality of connecting lines are used for connecting to an object to be carried.

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