CN211568305U - Aircraft with multiple propulsion devices - Google Patents

Abstract

The utility model provides an aircraft with many advancing device, including microscler aerodynamic container and a plurality of advancing device, have storage space or manned space in the microscler aerodynamic container, storage space is used for storing fluid or parcel, and a plurality of advancing device set up on microscler aerodynamic container. Preferably, a plurality of propelling devices are arranged on the long aerodynamic container at intervals along the length direction. And at least one combination of a battery and backup battery, a sensor and backup sensor, an autopilot and backup autopilot, and a communication device and backup communication device, disposed on the elongated aerodynamic container. The device also comprises a first connecting piece, a first pipe fitting, a first nozzle, a second connecting piece, a second pipe fitting and a second nozzle. The utility model discloses payload is big, single cargo transport ability is strong, thereby noise reduction duration reduces the air transportation cost, design benefit, and the structure is succinct, makes portably, and is with low costs.

Description

Aircraft with multiple propulsion devices

Technical Field

The utility model relates to an air transportation technical field, in particular to aircraft technical field specifically indicates an aircraft with many advancing device.

Background

Current research on single or single multi-winged aircraft (drone), Unmanned Aerial Vehicle (UAV), unmanned aerial vehicle (drone), etc. shows that these machines present many problems when put into mass civilization and cause other problems, such as:

a-faults or accidents that may halt a mission, crash a multi-wing aircraft, injure or even kill people due to temporary landings or falls at civilian sites caused by system failures (propulsion systems, sensors, autopilot circuit boards, etc.);

b-noise and annoyance due to the use of multiple separate discrete individual devices;

c-especially the risk of fire when falling on crops;

d-limited single cargo transport capacity, consuming 10 times the power compared to a land truck;

e-limited ability to carry heavy objects such as water tanks for plant irrigation or pesticide spraying on agricultural fields;

f-high traffic volume due to limited payload, where one express truck can carry tens of packages, and the delivery of such a number requires tens of scattered multi-wing aircraft.

At the heart of the problem, even if multi-winged aircraft also use multiple rotors, some fault types, limited payload, noise, overhead transportation costs are still negative factors that may limit their widespread use in the future.

It is therefore desirable to provide an aircraft with a large payload and high single cargo capacity to reduce the duration of noise and reduce air transportation costs.

SUMMERY OF THE UTILITY MODEL

In order to overcome the shortcomings in the prior art, the utility model discloses an aim at provides an aircraft with many advancing device, thereby its payload is big, single cargo transport ability is strong, noise reduction duration reduces the air transportation cost, is suitable for extensive popularization and application.

Another object of the utility model is to provide an aircraft with many advancing device, 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 present invention provides an aircraft with multiple propulsion devices, which is characterized by comprising a long aerodynamic container and multiple propulsion devices, wherein the long aerodynamic container is internally provided with a storage space or a manned space, the storage space is used for storing fluid or wrapping, and the propulsion devices are arranged on the long aerodynamic container.

Preferably, a plurality of said propulsion devices are sequentially spaced along the length of said elongate aerodynamic container.

Preferably, the plurality of propelling devices are divided into two propelling device groups, each propelling device group comprises at least 2 propelling devices, the propelling devices of the propelling device group are sequentially arranged at intervals along the length direction of the elongated aerodynamic container, and the two propelling device groups are respectively arranged on two sides of the elongated aerodynamic container.

Preferably, the propulsion device includes a rotor blade, a motor connected to the rotor blade for controlling rotation of the rotor blade, and an Electronic Speed Controller (ESC) signally connected to the motor for controlling operation of the motor, the motor being disposed on the elongated aerodynamic body.

Preferably, said aircraft with multiple propulsion devices further comprises at least one combination of batteries and backup batteries, sensors and backup sensors, autopilots and backup autopilots, and communication equipment and backup communication equipment, said at least one combination being provided on said elongated aerodynamic container.

Preferably, the elongate aerodynamic container has an aerodynamic surface.

Preferably, the aircraft with multiple propulsion devices further includes a first connection member, a first pipe, a first nozzle, a second connection member, a second pipe, and a second nozzle, the first pipe and the second pipe are both located below the long aerodynamic container and are connected to the long aerodynamic container through the first connection member and the second connection member, the first pipe and the second pipe are both disposed along a length direction of the long aerodynamic container, the first pipe and the second pipe are at the same height and are disposed at intervals, the first nozzle and the second nozzle are disposed on the first pipe and the second pipe, respectively, and the first pipe and the second pipe are both in fluid communication with the long aerodynamic container.

Preferably, the aircraft with multiple propulsion devices further comprises a third connection, and the propulsion devices are arranged on the first pipe fitting or the second pipe fitting through the third connection.

Preferably, said aircraft with multiple propulsion devices further comprises a fourth connection by means of which said propulsion devices are arranged on said elongated aerodynamic container.

Preferably, the aircraft with multiple propelling devices further comprises a partition frame body, and the storage space is divided into a plurality of storage chambers through the partition frame body.

Preferably, the aircraft with multiple propelling devices further comprises a chamber door, a rope reel-up and reel-down mechanism and a cargo clamp, wherein the chamber door is vertically and rotatably arranged at the bottom of the storage chamber and used for opening and closing the storage chamber, the rope reel-up and reel-down mechanism is arranged in the storage chamber and connected with one end of the rope for reeling in and unreeling the rope, and the cargo clamp is arranged at the other end of the rope and used for clamping cargo.

More preferably, the aircraft with multiple propulsion devices further comprises a door, a rope, and a rope reeling and unreeling mechanism, wherein the door is detachably arranged at the bottom of the storage chamber and used for opening and closing the storage chamber, the rope reeling and unreeling mechanism is arranged in the storage chamber and connected with one end of the rope for reeling and unreeling the rope, and the other end of the rope is connected with the door.

Preferably, the aircraft with multiple propulsion devices further comprises a high-rise building and a reception center, wherein the reception center is positioned at the top of the high-rise building.

Preferably, the propulsion device is selected from at least one of a turbojet and a ducted propeller.

Preferably, said propulsion means comprises a ducted propeller and two turbojet engines, one of said turbojet engine, said ducted propeller and the other of said turbojet engines being located in succession along the length of said elongate aerodynamic body, and one of said turbojet engines being lower than said ducted propeller and the other of said turbojet engines being higher than said ducted propeller.

Preferably, the aircraft with multiple propelling devices further comprises a high-rise building, an aerial elevator and an aerial platform, wherein each layer of the high-rise building is provided with the aerial platform, and the aerial elevator is arranged in the high-rise building and connected with the aerial platform.

Preferably, the aircraft with multiple propulsion devices further comprises a wing, said wing being connected to said elongated aerodynamic vessel, said wing being provided with at least one of said propulsion devices.

More preferably, the wing is provided with more than two propelling devices, and the more than two propelling devices are arranged at intervals along the length direction of the wing.

More preferably, the aircraft with multiple propulsion devices further comprises a first jet duct disposed on the wing and in fluid communication with the wing, the wing being in fluid communication with the elongated aerodynamic vessel.

More preferably, the wing is vertically pivotally connected to the elongate aerodynamic vessel such that the wing rotates from a horizontal position to a vertical position and from the vertical position to the horizontal position.

Furthermore, the wing is an annular wing, and the propulsion device is inserted into an annular hole in the middle of the annular wing.

Further, the wing wraps an outer side of the propulsion device.

More preferably, said aircraft with multiple propulsion devices further comprises a second jet duct, transversely connected to and in fluid communication with said elongated aerodynamic container.

Preferably, said propulsion means are provided at both ends of said elongated aerodynamic container.

Preferably, the propulsion device is a propulsion engine, jet engine or rotor.

Preferably, the aircraft with multiple propulsion devices further comprises a heater, the elongated aerodynamic container has the storage space therein, the storage space stores fluid, and the heater is disposed in the storage space and located in the fluid.

Preferably, the aircraft with multiple propelling devices further comprises a take-off landing platform, an embedded pipeline and an exhaust pipeline, wherein a hole is formed in the take-off landing platform, the embedded pipeline is embedded in the take-off landing platform, one end of the embedded pipeline is communicated with the air passage of the hole, one end of the exhaust pipeline penetrates through the take-off landing platform and is communicated with the air passage at the other end of the embedded pipeline, and the other end of the exhaust pipeline is exposed on the take-off landing platform.

Preferably, the exhaust pipe is arranged obliquely, and the upper end of the exhaust pipe is far away from the hole relative to the lower end of the exhaust pipe.

The beneficial effects of the utility model mainly lie in:

1. the utility model discloses an aircraft with many advancing device includes microscler aerodynamic container and a plurality of advancing device, have storing space or manned space in the microscler aerodynamic container, storing space is used for storing fluid or parcel, a plurality of advancing device set up on microscler aerodynamic container, thereby ensure to carry a large amount of payloads through a plurality of advancing device, consequently, its payload is big, single cargo transport ability is strong, thereby noise reduction duration, reduce the air transportation cost, be suitable for extensive popularization and application.

2. The utility model discloses an aircraft with many advancing device includes microscler aerodynamic container and a plurality of advancing device, has storage space or manned space in the microscler aerodynamic container, and storage space is used for storing fluid or parcel, and a plurality of advancing device set up on microscler aerodynamic container to ensure to carry a large amount of payloads through a plurality of advancing device, consequently, its design benefit, the structure is succinct, and it is simple and convenient to make, and is with low costs, is 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, taken in conjunction with the accompanying drawings and the accompanying claims, wherein like reference numerals refer to like elements throughout.

Drawings

Fig. 1 is a block diagram of the components of the aircraft with multiple propulsion devices of the present invention.

Fig. 2 is a schematic perspective view of a first embodiment of the aircraft with multiple propulsion devices according to the present invention.

Fig. 3 is a perspective view of a second embodiment of the aircraft with multiple propulsion devices according to the present invention.

Fig. 4 is a schematic side view of a third embodiment of the aircraft with multiple propulsion devices according to the present invention.

Fig. 5 is a schematic perspective view of a fourth embodiment of the aircraft with multiple propulsion devices according to the present invention.

Fig. 6A is a first schematic perspective view of a fifth embodiment of the aircraft with multiple propulsion devices according to the present invention.

Fig. 6B is a schematic perspective view of a fifth embodiment of the aircraft with multiple propulsion devices according to the present invention.

Fig. 7A is a first schematic perspective view of a sixth embodiment of the aircraft with multiple propulsion devices according to the present invention.

Fig. 7B is a schematic perspective view of a sixth embodiment of the aircraft with multiple propulsion devices according to the present invention.

Fig. 8A is a first perspective view of a seventh embodiment of the aircraft with multiple propulsion devices of the present invention.

Fig. 8B is a schematic side view of a seventh embodiment of the aircraft with multiple propulsion devices of the present invention.

Fig. 8C is a schematic perspective view of a seventh embodiment of the aircraft with multiple propulsion devices according to the present invention.

Fig. 8D is a schematic side view of a seventh embodiment of the aircraft with multiple propulsion devices of the present invention.

Fig. 9 is a schematic perspective view of an eighth embodiment of the aircraft with multiple propulsion devices according to the present invention.

Fig. 10 is a schematic perspective view of a ninth embodiment of the aircraft with multiple propulsion devices according to the present invention.

Fig. 11 is a schematic front view of a tenth embodiment of the aircraft with multiple propulsion devices of the present invention unloading cargo.

Fig. 12A is a schematic illustration of a first front view of an eleventh embodiment of the aircraft with multiple propulsion devices of the present invention unloading cargo.

Fig. 12B is a schematic front view of an eleventh embodiment of the aircraft with multiple propulsion devices of the present invention unloading cargo.

Fig. 13 is a schematic perspective view of a twelfth embodiment of the aircraft with multiple propulsion devices of the present invention.

(symbol description)

1 an elongated aerodynamic container; 2, a propulsion device; 3, a storage space; 4 a manned space; 5 rotor blades; 6, a motor; 7a first connecting member; 8a first tubular member; 9 a first nozzle; 10 a second connecting member; 11 a second tube member; 12a second nozzle; 13 a third connecting member; 14 a fourth connection member; 15 partitioning the frame body; 16 a storage chamber; 17 goods; 18 high-rise buildings; 19 a reception center; 20 turbojet engine; 21 a ducted propeller; 22 an airfoil; 23 a first injection conduit; 24 a second injection conduit; 25 chamber doors; 26 ropes; 27 a cord reel-up mechanism; 28 a cargo clamp; 29 a conventional pushing mechanism; 30 take-off and landing platforms; 31 burying a pipeline; 32 an exhaust conduit; 33 holes; 34 exhaust gas.

Detailed Description

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

Referring to fig. 1 to 13, in the first to twelfth embodiments of the present invention, the aircraft with multiple propulsion devices of the present invention includes a long aerodynamic container 1 and multiple propulsion devices 2, the long aerodynamic container has a storage space 3 or a passenger space 4 therein, the storage space 3 is used for storing fluid or packages, and the multiple propulsion devices 2 are disposed on the long aerodynamic container 1. For example, referring to fig. 2-5 and 7A-13, in the first to fourth and sixth to twelfth embodiments of the invention, the elongated aerodynamic container 1 has a storage space 3 therein, which can be used to carry any type of liquid for any task, such as for agricultural irrigation, fire fighting, clean water, or for cleaning, pesticides, or fire fighting chemicals, as well as fuel, fire extinguishing powder, packaged food for dispensing supplies, or even for batteries charged either wired or wirelessly. The utility model discloses a this kind of new setting can adopt a more actual name, be Long Unmanned Aerial Vehicle (Unmanned Aerial Vehicle) for short UALV for short. Referring to fig. 6A-6B, in a fifth embodiment of the present invention, the elongated aerodynamic container 1 has a passenger compartment 4 therein, which can be used to carry human passengers, and can be used as a train of single-seat mini-airbuses or connected to other vehicles as a train configuration.

The presence of a plurality of said propulsion devices 2 will ensure that a large number of payloads can be carried, reducing the need for a plurality of individual discrete noisy multi-wing aircraft.

A plurality of said propulsion devices 2 may be arranged on said elongated aerodynamic container 1 in any suitable shape, for example, a plurality of said propulsion devices 2 may be arranged on said elongated aerodynamic container 1 at intervals in sequence along the length direction of said elongated aerodynamic container 1 to form a row of said propulsion devices 2, a plurality of said propulsion devices 2 may also be divided into two propulsion device groups, said propulsion device groups include at least 2 of said propulsion devices 2, said propulsion devices 2 of said propulsion device groups are arranged at intervals in sequence along the length direction of said elongated aerodynamic container 1, two of said propulsion device groups are arranged on each side of said elongated aerodynamic container 1, i.e. to form two rows of said propulsion devices 2, obviously, three or even more rows of said propulsion devices 2 may also be formed. Referring to fig. 2, in the first embodiment of the present invention, there are 12 propulsion devices 2, which are divided into 2 groups on average, and 6 propulsion devices 2 in each group. Referring to fig. 3 and 5, in the second and fourth embodiments of the present invention, there are 24 propulsion devices 2, which are divided into 4 groups on average, and 6 propulsion devices 2 in each group, which are distributed two by two on both sides of the long aerodynamic container 1. Referring to fig. 4 and fig. 11 to 12B, in the third, tenth and eleventh embodiments of the present invention, there are 24 propelling devices 2 in total, and the propelling devices 2 are divided into 2 groups on average, and each group has 12 propelling devices 2. Referring to fig. 6A to 6B, in a fifth embodiment of the present invention, there are 14 propelling devices 2 in total, and the propelling devices are divided into 2 groups, and each group has 7 propelling devices 2.

The propulsion device 2 may be any suitable propulsion device, such as a propulsion engine, jet engine or rotor, etc. may be used.

The propulsion device 2 may have any suitable structure, as shown in fig. 2 to 5 and fig. 11 to 12B, in the first to fourth and tenth to eleventh embodiments of the present invention, the propulsion device 2 comprises a rotor blade 5, a motor 6 and an electronic speed controller (not shown), the motor 6 is connected to the rotor blade 5 for controlling the rotation of the rotor blade 5, the electronic speed controller is in signal connection with the motor 6 for controlling the action of the motor 6, and the motor 6 is disposed on the elongated aerodynamic container 1.

The rotor blade 5 may be a single rotor blade or a dual rotor blade, as shown in fig. 2, in the first embodiment of the present invention, the rotor blade 5 is a single rotor blade. Referring to fig. 3 to 5 and 11 to 12B, in the second to fourth and tenth to eleventh embodiments of the present invention, the rotor blade 5 is a dual rotor blade.

The presence of a plurality of said propulsion devices 2 is itself capable of avoiding temporary landings due to failure of said propulsion devices 2 and, in order to avoid temporary landings due to failure of other components, preferably said aircraft with multiple propulsion devices further comprises at least one combination of batteries (not shown) and backup batteries (not shown), sensors (not shown) and backup sensors (not shown), autopilots (not shown) and backup autopilots (not shown), and communication equipment (not shown) and backup communication equipment (not shown), said at least one combination being arranged on said elongated aerodynamic container 1. In the first to twelfth embodiments of the present invention, the aircraft with multiple propulsion devices further comprises a battery and a backup battery, a sensor and a backup sensor, an autopilot and a backup autopilot, and a communication device and a backup communication device. It does not matter, for example, if one of said propulsion means 2 fails, that there are also a number of said propulsion means 2, such as 11, 13, 23 or more, in operation, that said backup communication device is available if said communication device fails, and that said backup sensor is available if said sensor fails.

The sensor may be any suitable sensor, for example, a three-axis accelerometer, a three-axis gyroscope, a three-axis magnetometer, an ultrasonic range finder, a barometer, a 2D laser range finder, a lidar, a GPS, a camera, a compass, or the like.

It may seem that the spare parts add a lot of extra costs to the invention, but in fact this quick judgement is wrong if we make a systematic comparison, considering that the elongated aerodynamic vessel 1+ a number of the propulsion devices 2 do not require spare parts, then if we roughly estimate the cost of the autopilot + the sensor + the battery to be about 30.0% of the price of a single multi-wing aircraft, this does not mean that if the propulsion devices 2 being used in the invention are 5 times more than a single multi-wing aircraft, the cost of the spare parts is 5 times the number of required spare components, which is wrong, because in the invention only one spare part is needed instead of 5, while the size and cost of these parts will not be different whether the drone is large or small, because they are doing the same work, if we roughly estimate that the utility model is about 5 times more expensive than a single multi-wing aircraft, then the cost of 30.0% spare parts would only be 30%/5 ═ 6.0% of the utility model. This means that the cost of the spare parts in the invention is 6.0% of the cost of the invention, which is only a small part compared to the huge benefit of harvesting (see fig. 1).

In order to facilitate the flight, the elongated aerodynamic container 1 has an aerodynamic surface, as shown in fig. 2 to 13, in the first to twelfth embodiments of the invention. Typically a streamlined surface.

The cross section of the long aerodynamic container 1 may be determined as desired, and as shown in fig. 2 to 7B and fig. 11 to 12B, in the first to sixth and tenth to eleventh embodiments of the present invention, the cross section of the long aerodynamic container 1 is an elliptical cross section.

In order to facilitate the spraying of the liquid in the elongated aerodynamic container 1, please refer to fig. 2 to 5 and fig. 11 to 12B, in the first to fourth and tenth to eleventh embodiments of the present invention, the aircraft with multiple propulsion devices further comprises a first connecting member 7, a first pipe member 8, a first nozzle 9, a second connecting member 10, a second pipe member 11 and a second nozzle 12, wherein the first pipe member 8 and the second pipe member 11 are located below the elongated aerodynamic container 1 and are connected to the elongated aerodynamic container 1 through the first connecting member 7 and the second connecting member 10, respectively, the first pipe member 8 and the second pipe member 11 are located along the length direction of the elongated aerodynamic container 1, the first pipe member 8 and the second pipe member 11 are located at the same height and are spaced from each other, the first nozzle 9 and the second nozzle 12 are arranged on the first pipe 8 and the second pipe 11, respectively, the first pipe 8 and the second pipe 11 both being in fluid communication with the elongated aerodynamic vessel 1.

The first and second tubular members 8, 11 act as landing gear at rest (see fig. 2 and 3) and, in operation, eject liquid through their first and second nozzles 9, 12.

Thus, the direction of flight of the elongated aerodynamic container 1 towards the farmland or any civil facility will be along its length direction, whereas when the elongated aerodynamic container 1 is in use it flies or hovers towards its width direction, so that it can spray crops, extinguish fires, clean building facades or electric towers at relatively low speeds according to mission requirements.

Furthermore, by adjusting the angular speed of the propulsion device 2 to provide a yaw moment clockwise or counterclockwise, so that the elongated aerodynamic container 1 turns around, or adjusting the pitch moment to move the elongated aerodynamic container 1 longitudinally, or laterally, i.e. laterally, forward, so as to fly towards a direction perpendicular to the longitudinal direction of the elongated aerodynamic container 1, the spray width will be maximized many times more than with a conventional single multi-winger, so that spraying along the span of the elongated aerodynamic container 1, scanning the extra area of the crop, saving time many times more than with a conventional single multi-winger, which almost performs single row or single column spraying. Since time saving is the primary requirement for the irrigation process, since the irrigation time per day is limited, only to certain limited periods of the day, which is an added benefit for the present invention to avoid malfunctions and accidents, etc.

It is to be noted here how the elongated aerodynamic container 1 provides an optimal solution for irrigation, where no water pipes, sprinklers, nozzles, timers etc. need to be built along and across the farm, which will save a lot of infrastructure costs, using the elongated aerodynamic container 1 as a flying fire engine in emergency situations, or even using heaters, such as heating coils, inside the elongated aerodynamic container 1 to heat the water and use it to remove ice or snow from crops and roads. This arrangement of the elongated aerodynamic container 1 with heaters can also be used to form a lower cloud above areas such as fairgrounds in hot summer days.

The propulsion device 2 may be arranged on the elongated aerodynamic container 1 in any suitable configuration, see fig. 3-5 and 11-12B, and in the second to fourth and tenth to eleventh embodiments of the present invention, the aircraft with multiple propulsion devices further comprises a third connection 13, and the propulsion device 2 is arranged on the first pipe 8 or the second pipe 11 through the third connection 13.

The third connecting member 13 may have any suitable shape, as shown in fig. 3 and 5, in the second and fourth embodiments of the present invention, the third connecting member 13 is a T-shaped connecting member, the lower end of the T-shaped connecting member is disposed on the first pipe 8 or the second pipe 11, and both ends of the upper portion of the T-shaped connecting member are respectively connected to the propelling device 2. Referring to fig. 4 and fig. 11 to 12B, in a third, tenth and eleventh embodiment of the present invention, the third connecting member 13 is an inverted L-shaped connecting member, a lower end of the inverted L-shaped connecting member is disposed on the first pipe 8 or the second pipe 11, and an upper end of the inverted L-shaped connecting member is connected to the propelling device 2.

The propulsion device 2 may be arranged on the aerodynamic elongated container 1 in any suitable configuration, as shown in fig. 2, and in a first embodiment of the invention, the aircraft with multiple propulsion devices further comprises a fourth connection 14, and the propulsion device 2 is arranged on the aerodynamic elongated container 1 via the fourth connection 14.

The fourth connecting element 14 may have any suitable shape, as shown in fig. 2, in a first embodiment of the invention, the fourth connecting element 14 is a 7-shaped connecting element, the lower end of the 7-shaped connecting element is arranged on the elongated aerodynamic container 1, and the upper end of the 7-shaped connecting element is connected to the propulsion device 2.

In order to load a plurality of goods 17 separately into the storage space 3, instead of being stacked together, to avoid crushing and to facilitate searching, please refer to fig. 4 and fig. 11 to 12B, in the third, tenth and eleventh embodiments of the present invention, the aircraft with multiple propulsion devices further includes a partition frame body 15, and the storage space 3 is partitioned into a plurality of storage chambers 16 by the partition frame body 15. A plurality of the cargos 17 are stored in the plurality of storage chambers 16, respectively.

In order to facilitate the transportation of the cargo 17, it is shown in fig. 5 that in a fourth embodiment of the present invention, the aircraft with multiple propulsion devices further comprises a high-rise building 18 and a reception center 19, and the reception center 19 is located on top of the high-rise building 18.

The elongated aerodynamic container 1 will fly forward along its length, carrying the cargo 17 to be transported by air through the reception centre 19 at the top of the high-rise building 18, the transported cargo 17 possibly being limited to one building (tower) or one building complex, wherein each of the storage compartments 16 in the elongated aerodynamic container 1 is normally open from the underside in order to drop a given parcel to a given address of the reception centre 19 at the top of the high-rise building 18. Of course, the cargo 17 shipped in the lowermost storage chamber 16 is transported first before the cargo 17 shipped in the upper storage chamber 16 is transported.

In order to facilitate the dropping of the cargo 17, please refer to fig. 11, in a tenth embodiment of the present invention, the aircraft with multiple propelling devices further comprises a chamber door 25, a rope 26, a rope reeling and unreeling mechanism 27 and a cargo clamp 28, wherein the chamber door 25 is vertically and rotatably disposed at the bottom of the storage chamber 16 for opening and closing the storage chamber 16, the rope reeling and unreeling mechanism 27 is disposed in the storage chamber 16 and connected to one end of the rope 26 for reeling and unreeling the rope 26, and the cargo clamp 28 is disposed at the other end of the rope 26 for clamping the cargo 17. In use, the goods 17 are gripped by the goods gripper 28, the door 25 is rotated downwards to open the storage chamber 16, the rope 26 is gradually unwound and lowered from a wound state by the rope unwinding mechanism 27, the goods 17 are sent downwards to the reception center 19, then the goods gripper 28 is opened, the goods 17 are released, and then the rope unwinding mechanism 27 winds the rope 26 to pull the goods gripper 28 upwards to its original position.

Another structure may be adopted, as shown in fig. 12A and 12B, in an eleventh embodiment of the present invention, the aircraft with multiple propulsion devices further includes a door 25, a rope 26, and a rope reeling and unreeling mechanism 27, wherein the door 25 is detachably disposed at the bottom of the storage chamber 16 for opening and closing the storage chamber 16, the rope reeling and unreeling mechanism 27 is disposed in the storage chamber 16 and connected to one end of the rope 26 for reeling and unreeling the rope 26, and the other end of the rope 26 is connected to the door 25. In use, the door 25 is detached from the bottom of the storage chamber 16, the rope 26 is gradually unwound and lowered from the wound state by the rope unwinding mechanism 27, the goods 17 and the door 25 are dropped together until the reception center 44 is reached, the goods 17 can be horizontally pushed away from the door 25 by the conventional pushing mechanism 29 in the reception center 44, and then the rope unwinding mechanism 27 winds the rope 26 to pull the door 25 up to its original closed position.

The rope pay-off mechanism 27 may be any suitable rope pay-off mechanism, such as an electric tubular motor or a spring-loaded motor (tension-loaded tubular motor), and the goods gripper 28 may be, for example, an electric gripper.

It is to be noted here that the propulsion device 2 may even employ discrete individual multi-wingers to co-operate in transporting the elongated aerodynamic container 1, which means that the elongated aerodynamic container 1 may be carried (lifted) using the rotor blades 5 which are always fixed or by a combination of discrete multi-wingers. Again, this new arrangement of the present invention may be one that adopts a more realistic name: long Unmanned Aerial Vehicle (Unmanned Aerial Vehicle), UALV for short.

The propulsion device 2 may also be any other suitable propulsion device, preferably the propulsion device 2 is selected from at least one of a turbojet 20 and a ducted propeller 21. Referring to fig. 6A-6B, in a fifth embodiment of the present invention, the propulsion device 2 is a turbojet engine 20 and a ducted propeller 21. Referring to fig. 7A to 7B, in a sixth embodiment of the present invention, the propulsion device 2 is a ducted propeller 21. Referring to fig. 8A to 10 and 13, in the seventh to ninth and twelfth embodiments of the present invention, the propulsion device 2 is a turbojet engine 20.

In a fifth embodiment of the present invention, as shown in fig. 6A-6B, said propulsion device 2 comprises a ducted propeller 21 and two turbojet engines 20, wherein one of said turbojet engines 20, said ducted propeller 21 and the other of said turbojet engines 20 are arranged in sequence along the length of said elongated aerodynamic vessel 1, and wherein one of said turbojet engines 20 is lower than said ducted propeller 21 and the other of said turbojet engines 20 is higher than said ducted propeller 21.

I.e. using a hybrid model, two of said turbojet engines 20 are located at the bottom. Since the turbojet engine 20 is more expensive, heavier, consumes additional electric power, and is intended for high-speed use, two sets of propulsion devices 2 can be used, one on each side of the elongated aerodynamic vessel 1, while the ducted propellers 21, which provide vertical lift and forward thrust, are located between the two turbojet engines 20, but at the top level, so that the ducted propellers 21 do not interfere with the turbojet engine 20 when the turbojet engine 20 is cruising in a horizontal configuration.

The use of a hybrid propulsion system by adding the turbojet 20 increases the ability of the turbojet 20 to maximize vertical lift (VTOL) by adding lift and climb or cruise by adding thrust. The hybrid propulsion system is preferably used for long distances and at medium speeds, wherein the turbojet engine 20, such as a rotatable electric turbojet engine, is very powerful in optimizing vertical lift and medium speed requirements.

In order to facilitate the passengers to be dropped or picked up, in an eighth embodiment of the present invention, the aircraft with multiple propulsion devices further comprises a high-rise building 18, an aerial elevator (not shown in the figure) and an aerial platform (not shown in the figure), each floor of the high-rise building 18 is provided with the aerial platform, and the aerial elevator is arranged in the high-rise building 18 and connected with the aerial platform.

The hybrid propulsion system can be used to fly at high or low levels so that it can drop or pick up passengers from any level through the air platforms located and connected to the high-rise building 18. Wherein the aerial lift takes passengers down to a street platform or up to the aerial platform.

Furthermore, the elongated aerodynamic containers 1 may be connected together like an air train or follow each other as a fleet of vehicles, and when they are so arranged and transported only from the high levels of the aerial lift of the high-rise building 18, the noise they produce will be limited to certain specific periods of the day, will be directed upwards away from the ground, unlike sending discrete individual multi-wing aircraft which will produce noise throughout the day and detour at low levels between building and house.

The aircraft with multiple propulsion devices may also comprise any other suitable structure, and preferably, the aircraft with multiple propulsion devices further comprises a wing 22, the wing 22 is connected with the elongated aerodynamic vessel 1, and at least one propulsion device 2 is arranged on the wing 22. More preferably, the wing 22 is provided with more than two propelling devices 2, and the more than two propelling devices 2 are arranged at intervals along the length direction of the wing 22. Referring to fig. 6A to 6B, in a fifth embodiment of the present invention, the wing 22 is provided with one propulsion device 2. Referring to fig. 7A to 7B, in a sixth embodiment of the present invention, four propelling devices 2 are disposed on the wing 22. Referring to fig. 8A to 10, in the seventh to ninth embodiments of the present invention, three propelling devices 2 are disposed on the wing 22.

In the case of the wing 22, in order to facilitate the liquid spraying, please refer to fig. 7A to 7B, in a sixth embodiment of the present invention, the aircraft with multiple propulsion devices further comprises a first injection duct 23, the first injection duct 23 is disposed on the wing 22 and is in fluid communication with the wing 22, and the wing 22 is in fluid communication with the elongated aerodynamic vessel 1. Which may be used for example for agricultural purposes, aerial irrigation, insecticide spraying, fire fighting, the liquid in the elongated aerodynamic container 1 flows into the wing 22 and is sprayed out of the first spray pipe 23.

The wing 22 may be a rotatable wing or a non-rotatable wing, as shown in fig. 8A to 10, in the seventh to ninth embodiments of the present invention, the wing 22 is vertically and rotatably connected to the elongated aerodynamic container 1, so that the wing 22 rotates from the horizontal position to the vertical position and from the vertical position to the horizontal position. I.e. the wing 22 is a rotatable wing, the elongated aerodynamic vessel 1 is in cruise condition with the wing 22 in the horizontal position, and the elongated aerodynamic vessel 1 is in vertical lift condition with the wing 22 in the vertical position.

In the case where the wing 22 is a rotatable wing, the wing 22 may have any suitable shape, as shown in fig. 9, and in an eighth embodiment of the invention, the wing 22 is a ring-shaped wing, and the propulsion device 2 is inserted into an annular hole in the middle of the ring-shaped wing. Referring to fig. 10, in a ninth embodiment of the present invention, the wing 22 wraps the outer side of the propulsion device 2.

In the case where the wing 22 is a rotatable wing, as shown in fig. 8A to 10, in the seventh to ninth embodiments of the present invention, the aircraft with multiple propulsion devices further comprises a second injection duct 24, the second injection duct 24 being transversely connected to the elongated aerodynamic container 1 and being in fluid communication with the elongated aerodynamic container 1.

In order to provide additional forward thrust, fig. 7A-7B show that in a sixth embodiment of the present invention, the propulsion devices 2 are disposed at both ends of the elongated aerodynamic container 1.

When the aircraft takes off and lands, in order to prevent dust and waste gas from being sucked back inside advancing device 2 and greatly reduce advancing device 2's efficiency even leads to advancing device 2 breaks down, please see fig. 13, in the twelfth embodiment of the utility model, the aircraft that has many advancing devices still include take off landing platform 30, bury pipeline 31 and exhaust duct 32 underground, be provided with hole 33 on the take off landing platform 30, bury underground pipeline 31 bury underground in take off landing platform 30 just bury the one end of pipeline 31 underground with hole 33 gas circuit intercommunication, exhaust duct 32's one end is worn to establish take off landing platform 30 and with bury underground pipeline 31's other end gas circuit intercommunication, exhaust duct 32's the other end exposes take off landing platform 30. Exhaust gases 34 from the take-off and landing of the aircraft are thus exhausted from the exhaust duct 32 through the buried duct 31 via the holes 33.

The exhaust duct 32 may be vertically disposed or obliquely disposed, as shown in fig. 13, in a twelfth embodiment of the present invention, the exhaust duct 32 is obliquely disposed, and an upper end of the exhaust duct 32 is far away from the hole 33 relative to a lower end of the exhaust duct 32.

Accordingly, the present invention relates to a plurality of propulsion devices for longitudinally or transversely carrying an elongated aerodynamic container to perform a wide variety of tasks.

To sum up, the utility model discloses an aircraft payload with many advancing device is big, single cargo transportation ability is strong, thereby noise reduction duration reduces the air transportation cost, 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 (28)

1. An aircraft with multiple propulsion devices, comprising an elongated aerodynamic container with a storage space or passenger space inside, for storing a fluid or a package, and a plurality of propulsion devices arranged on the elongated aerodynamic container.

2. The vehicle according to claim 1, wherein a plurality of said propulsion devices are arranged on said elongated aerodynamic container at sequential intervals along the length of said elongated aerodynamic container.

3. The vehicle according to claim 1, wherein said plurality of propulsion devices is divided into two propulsion device groups, said propulsion device groups comprising at least 2 of said propulsion devices, said propulsion devices of said propulsion device groups being spaced apart in sequence along the length of said elongated aerodynamic container, and said two propulsion device groups being disposed on opposite sides of said elongated aerodynamic container.

4. The aircraft of claim 1 wherein said propulsion means comprises rotor blades, motors connected to said rotor blades for controlling rotation of said rotor blades, and electronic speed controllers signally connected to said motors for controlling operation of said motors disposed on said elongated aerodynamic body.

5. The vehicle according to claim 1, wherein said vehicle further comprises at least one combination of a battery and backup battery, a sensor and backup sensor, an autopilot and backup autopilot, and a communication device and backup communication device, said at least one combination being disposed on said elongated aerodynamic container.

6. The aircraft with multiple propulsion devices according to claim 1, characterized in that said elongated aerodynamic container has an aerodynamic surface.

7. The vehicle having multiple propulsion devices of claim 1, wherein the vehicle further comprises a first coupling member, a first tube member, a first nozzle, a second coupling member, a second tube member, and a second nozzle, the first and second tubes are both located below the elongated aerodynamic container and are connected to the elongated aerodynamic container by the first and second connectors, respectively, the first tube member and the second tube member are both disposed along a length of the elongate aerodynamic vessel, the first pipe fitting and the second pipe fitting are positioned at the same height and are arranged at intervals, the first nozzle and the second nozzle are respectively arranged on the first pipe fitting and the second pipe fitting, the first and second tubes are both in fluid communication with the elongate aerodynamic vessel.

8. The vehicle according to claim 7, wherein said vehicle further comprises a third connection, said propulsion device being disposed on said first or said second tubular member via said third connection.

9. The vehicle according to claim 1, characterised in that it further comprises a fourth connection by means of which said propulsion means are arranged on said elongated aerodynamic container.

10. The vehicle with multiple propulsion devices of claim 1, further comprising a divider body, wherein the storage space is divided into a plurality of storage compartments by the divider body.

11. The vehicle according to claim 10, wherein said vehicle further comprises a door, a rope reel-off mechanism and a cargo clamp, said door is vertically rotatably disposed at the bottom of said storage chamber for opening and closing said storage chamber, said rope reel-off mechanism is disposed in said storage chamber and connected to one end of said rope for reeling off said rope, and said cargo clamp is disposed at the other end of said rope for clamping cargo.

12. The vehicle having multiple propulsion devices of claim 10, further comprising a door removably disposed at the bottom of the storage chamber for opening and closing the storage chamber, a rope reel and reel mechanism disposed within the storage chamber and connected to one end of the rope for reeling in and unreeling the rope, the other end of the rope being connected to the door.

13. The vehicle according to claim 1, wherein said vehicle further comprises a high-rise building and a service center, said service center being located at the top of said high-rise building.

14. The aircraft having multiple propulsion devices of claim 1, wherein the propulsion devices are selected from at least one of turbojet engines and ducted propellers.

15. The aircraft of claim 1 wherein said propulsion means comprises a ducted propeller and two turbojet engines, one of said turbojet engine, said ducted propeller and the other of said turbojet engines being located sequentially along the length of said elongate aerodynamic vessel, and wherein one of said turbojet engines is lower than said ducted propeller and the other of said turbojet engines is higher than said ducted propeller.

16. The vehicle according to claim 1, wherein said vehicle further comprises a high-rise building, an aerial lift and an aerial platform, each floor of said high-rise building being provided with said aerial platform, said aerial lift being disposed in said high-rise building and connected to said aerial platform.

17. The vehicle of claim 1 wherein said vehicle further comprises a wing, said wing being attached to said elongated aerodynamic vessel, said wing having at least one of said propulsion devices disposed thereon.

18. The vehicle of claim 17 wherein said wing has two or more of said propulsion devices disposed thereon, said two or more propulsion devices being spaced apart along the length of said wing.

19. The multi-propulsion-unit aircraft of claim 17, further comprising a first jet stack disposed on and in fluid communication with the wing, the wing being in fluid communication with the elongated aerodynamic vessel.

20. The aircraft with multiple propulsion devices of claim 17, wherein the wing is vertically rotatably connected to the elongated aerodynamic vessel such that the wing rotates from a horizontal position to a vertical position and from the vertical position to the horizontal position.

21. The aircraft of claim 20 wherein the wing is an annular wing and the propulsion devices are inserted in an annular hole in the middle of the annular wing.

22. The aircraft having multiple propulsion devices of claim 20, wherein the wing wraps around an outboard side of the propulsion device.

23. The vehicle according to claim 17, wherein said vehicle further comprises a second jet duct, said second jet duct being connected transversely to and in fluid communication with said elongated aerodynamic container.

24. The aircraft with multiple propulsion devices according to claim 1, characterized in that said propulsion devices are provided at both ends of said elongated aerodynamic container.

25. The aircraft with multiple propulsion devices of claim 1, wherein the propulsion devices are propulsion engines, jet engines, or rotors.

26. The vehicle according to claim 1, wherein said vehicle further comprises a heater, said elongated aerodynamic container having said storage space therein, said storage space having a fluid stored therein, said heater being disposed within said storage space and within said fluid.

27. The aircraft with multiple propellers of claim 1, wherein the aircraft with multiple propellers further comprises a takeoff landing platform, an embedded pipeline and an exhaust pipeline, the takeoff landing platform is provided with a hole, the embedded pipeline is embedded in the takeoff landing platform, one end of the embedded pipeline is communicated with the air passage of the hole, one end of the exhaust pipeline penetrates through the takeoff landing platform and is communicated with the air passage at the other end of the embedded pipeline, and the other end of the exhaust pipeline is exposed on the takeoff landing platform.

28. The aircraft with multiple propulsion devices of claim 27, wherein the exhaust duct is disposed at an angle, an upper end of the exhaust duct being distal from the hole relative to a lower end of the exhaust duct.

Images