DE202018000429U1 - Vertical take-off (vertical whistle), horizontal aerodynamic flying unmanned aerial vehicle (UAV, unmanned aerial Verhicle), transport drone in special flying wing hybrid design - Google Patents

Abstract

Aircraft preferably after-hull, with a central support surface (1) and additionally rigidly mounted wings (6,11). This is a hybrid aircraft that can carry the largest possible cargo (2), and one or more parcels. It can be made in different sizes, depending on the dimensions and the weight of the cargo to be transported.

Description

Technical area

The present invention relates to a UAV (unmanned aerial vehicle) or UAS (unmanned aerial vehicle system), also referred to as a drone.

State of the art

Especially in recent years, a lot has happened in the development of transport drones. There are several concepts that have their advantages and disadvantages. There are the different Copter versions to call, in different sizes. For example, there are Copter, which can be up to max. Transport 3 kg of packages. The disadvantage is that they can not fly aerodynamically and therefore have a fairly high energy requirement. The package is usually mounted below the rotors in the center of gravity and offers great air resistance. Therefore, the flight speed and the flight time is very limited, and the mission radius is quite low. Among other things, this depends on the state of the battery technology. These copters land on a flat surface, which has to be closed more and more frequently for safety reasons.

On the other hand, there are also the tilting wings. After vertical launch with vertical wings, they are placed horizontally at safety altitude and increasing airspeed, providing lift for aerodynamic horizontal flight. The package is transported in a conventional fuselage with tail units, which is currently max. Weight is 2 kg, the package size is very limited by the hull. The technical complexity is very high due to the tilt mechanism, the range is higher than that of the copter. There is a packed station with full automation required where the packetcopter can land. The package must then be picked up by the customer from the station.

Also known is a so-called Blended Wing Body, a fuselage that merges into a flying wing. This starts vertically with 4 engines on the wings, the package is located in the fuselage and is lowered with a winch. Packages up to 2.5 kg are possible. The package size depends on the total size of the delivery drone. The dazzling wing body is more aerodynamic, the hull carries a portion of the load with, but with larger packages, the entire drone is very large and heavy. It can also come through the construction to center of gravity problems, which greatly limits the location of the package in the fuselage, and thereby the size of the package.

There is also a fixed-wing aircraft with a very good aerodynamics, this is designed for longer distances and surveillance and agricultural applications. Loads up to 2 kg are possible, larger packages can not be transported. This UAV has VTOL (vertical take-off and landing) characteristics because the motors mounted on the rigid wings are pivotable. The front drives are pivoted forward in forward flight, the front drives provide propulsion. This UAV is very energy efficient and has very long ranges. In order to enable the transport of large packages, the hull must be very large, which in turn affects the overall aerodynamics.

Furthermore, there is also a new drone concept, such as a copter has 4 pairs of rotors and an aerodynamic, profile shaped similar hull with a wing. However, the hull and the wing do not contribute completely to the buoyancy in horizontal flight, so the rotors are employed in horizontal flight still at 45 degrees, so that a horizontal flight is possible.

As can be seen from the above examples, the demand for optimized UAVs increases, and there are usually different concepts for the different tasks. There is no concept yet of delivering packages of dimensions e.g. 375x300x135 DHL Pakset M with up to 5 kg to transport with a UAV.

Description of the invention

This object is achieved by an aircraft with the features of the present invention protection. Advantageous developments emerge from the appended claims.

The purpose of the present invention is to create a good aerodynamics with the greatest possible transport space, with the lowest possible total resistance by a clever combination of proportionate wings. This is completely dispensed with a hull. This aircraft requires due to the relatively small dimensions only a very small area to take off and land.

It concerns the flight mechanics around a Nurflügel, with wings attached at the wing middle part. It is not a conventional flying wing, in which the wing is continuous. Since this invention is more of a hybrid, is here selected for the wing center part, the term central wing to avoid misunderstandings.

The elevator for stabilizing the transverse axis are located at the end of the central wing, as in a flying wing. By the missing hull and the short lever arms relatively large vertical stabilizers are provided for stabilizing the vertical axis. The control surfaces on the wings serve to stabilize the longitudinal axis in flight.

Depending on the size and task of the aircraft, fixed motors can also be attached to the wings in the direction of flight.

The wings attached to the central airfoil can be made rectangular, trapezoidal or delta as shown. The central support surface has a minimum profile thickness of approx. 20%. The package to be transported is located exactly in the center of gravity, so that there are no attitude changes or stability problems when ejecting the package. This also depends on the exact position of the attached wings in the longitudinal axis. The thickness of the profile depends on the package size to be transported, and thus also the required surface depth. This in turn determines the overall size of the aircraft, this results in the required power and the corresponding total weight.

It is proposed to implement as compact and effective as possible the aircraft in different sizes, so that a good utilization of the battery capacity can be achieved. Calculations have shown that with a span of 1m already a package of size 240x200x90 with a max. Weight of 1kg can be transported. This with a cruising speed of 70km / h and a range of 40 km.

With a span of 2m, packages with a size from 450x350x160 to max. 5 kg are transported. This is a significant increase over the previously known concepts. These package sizes and weights are possible only by this invention, since the central support surfaces of the basic version forms about 50% of the supporting surface.

To start the aircraft is on the vertical tail, vertical. After a vertical acceleration phase, it goes into horizontal flight. For landing, the aircraft is aligned vertically again and the electronic stabilization reduces the altitude to landing. This is done by the 3D vector control and stabilization electronics, with which the aircraft can also stand vertically in the air. Even wind is compensated automatically to a certain extent. The aircraft can autonomously start, fly, drop off and land via the integrated control. Due to the aerodynamic design, a high range can be achieved in a short time. The aircraft can also be operated manually, for testing and setting purposes with a customized remote control.

The cargo is loaded by hand into the central wing, automation is also possible. The cargo is either thrown in the slow high-hired flight through the open hatch, from about 30 cm above ground level, or it is landed vertically and the cargo ejected. This process can be checked with cameras and corresponding sensors. Then the aircraft climbs back up to flight altitude and returns to the starting point.

As a drive so-called brushless or BLDC motors are used with an electronic controller. It can be flown from 1 drive unit already, with larger aircraft and heavier weights additional motors / controllers can be mounted on the wing leading edge in the direction of flight. Also advantageous is the arrangement of the motors, so the wing is already flowed by the propellers, so the minimum airspeed is lower.

The aircraft can also be used for other tasks. Due to the overall design, the aircraft can be used even in difficult weather conditions.

Also conceivable are disasters and rescue operations with emergency care, and the transport of medical utensils in rough terrain. Cameras, microphones and speakers can also be used to assess the situation for these applications. Searchlights are also possible.

The aircraft can also be built for manned aviation, for transport, as well as for passenger transport. Here, a biped (or retractable) with 2 tail wheels is used. This is started and landed horizontally. Passengers and pilots are in the central wing, as well as luggage and cargo. The engines are then on the wings and depending on the application also on the central wing. Turbines as well as turboprop or electric drives and hybrid drives can be used.

list of figures

• 1 zeigt das Fluggerät mit 1 Antriebseinheit im Horizontalflug
• 2 zeigt das Fluggerät in der Draufsicht mit Rechtecktragflächen
• 3 zeigt das Fluggerät im Schnitt
• 4 zeigt das Fluggerät in der Draufsicht mit Trapeztragflächen
• 5 zeigt das Fluggerät mit 3 Antriebseinheiten in der Startposition
• 6 zeigt das Fluggerät in der Seitenansicht, in Startposition

Preferred further embodiments of the invention are explained in more detail by the descriptions of the figures.

• 1 shows the aircraft with 1 drive unit in horizontal flight
• 2 shows the aircraft in plan view with rectangular wings
• 3 shows the aircraft in section
• 4 shows the aircraft in plan view with trapezoidal wings
• 5 shows the aircraft with 3 drive units in the start position
• 6 shows the aircraft in the side view, in start position

Detailed description of preferred embodiments

In the following preferred embodiments will be described with reference to FIGS. In this case, identical, similar or equivalent elements are denoted by identical reference numerals and a repeated description of these elements is omitted in this description.

In the 1 to 3 Fig. 3 shows a side view, a plan view and a section according to an embodiment of the present invention.

In general, the aircraft can be built in different sizes, the overall design remains for different versions. The aircraft can also be built for large loads of several tons or even manned in various sizes, up to the passenger machine.

The illustrated aircraft is shown here in the basic version with 1 drive unit, the central wing ( 1 ) has a wing profile, which can be adjusted depending on the required performance. Therefore, the aircraft from the flight mechanics forth a flying wing, the control of the transverse axis is done by the elevator ( 8th ) at the end of the profile. The elevators are divided in this version and equipped redundantly with 1 servo each.

The freight (package) ( 2 ) is placed in the center of gravity of the aircraft to avoid a change of position and center of gravity problems. For this purpose, in the central wing from below a hatch ( 3 ), through which the cargo can be loaded and ejected. You can clearly see how big the cargo space is in relation to the central wing.

The wings (6,11) are attached to the central support surface, in this case, there are rectangular wings. These have a setting angle to the central wing, the central wing contributes in this embodiment to about 50% of the total buoyancy. As a result, very short spans and small overall dimensions are possible. The wing is equipped with ailerons for stabilization about the longitudinal axis, in the illustrated embodiment also redundant.

The 2 Vertical stabilizers ( 7 ) stabilize the aircraft about the vertical axis, also these turrets are at the same time the land supports on which the aircraft lands and stands on the ground. Due to the design and the overall center of gravity, a safe standing is possible even at medium wind speeds.

The drive unit consists of two parts, the fixed part connected to the central support surface ( 4 ), and the movable part controlled by a 3D vector control by servos ( 5 ). In the fixed part is the vector control, in the moving the drive motor and the rigid or folding propeller ( 9 ) with spinners. The length of the forward drive is determined by the length of the folded propeller, which must not touch the wing. The forward propellers allow for quiet operation, the drive can be greatly throttled in the horizontal flight, this results in long flight times. With the 3D vector control and integrated controls, the aircraft is able to stand vertically in the air, take off from the ground and land again. The slow flying with high angle of attack is made possible by the autonomous control and 3D vector control.

The aircraft is modular, all parts are interchangeable, either individually or in pairs, allowing easy service and quick on-site repair. In addition, due to the small packaging dimensions of this aircraft can also be sent and transported inexpensively. The drive unit is easy to disassemble from the central support surface, and the wings and tail units can be easily disassembled. The controls, servos and drive motors / controllers can be easily replaced.

The batteries are located above the cargo hold, these are easily accessible through a maintenance flap. Li-ion batteries are used for most applications, as is the case with e-bikes and the automotive industry. These are adjusted according to the needs of weight and capacity to the different versions. If necessary, a fuel cell or solar cells can also be used. Meanwhile, the inductive charging state of the art, which means, with appropriate charging technology, the aircraft can be recharged automatically after landing. With less weight can be increased for a longer range and the drive battery, this can then take part of the parcel compartment.

The 4 shows an aircraft as described above, but it was provided with a trapezoidal wing, also a delta wing is possible. Decisive for the wing used, the position and shape is the required overall center of gravity. An increase in the span is possible up to twice the span. It also 4 motors can be attached to the wing.

The 5 shows an extended version of the in 1 - 3 shown aircraft. Here are additionally mounted on the wing drive units ( 12 ) assembled. This allows the max. Cargo weight can be increased, or the range can be significantly increased, since the front engine can then be turned off in level flight, the wing motors can then be operated with optimized for best travel speed propellers. The wing motors are fixed to the nacelle, making it possible to also use adjustable propellers, this significantly improves the overall efficiency of the drive. In addition, a redundancy is given by the 2 wing motors and the front engine, that is, even in case of failure of a propulsion system, the aircraft is still aviation suitable and can land safely. The required battery for the wing drives are located in the nacelle under the wing. It is also the starting position in the view of, seen in this figure.

The 6 shows the execution of 5 in the side view. A peculiarity of the invention is also that does not necessarily have to be started and landed by the vertical start, vector control and electronic control against the wind. This means that when the wind is strong, the aircraft can launch and land vertically, including across the wind. This significantly reduces the area covered by the wind.

LIST OF REFERENCE NUMBERS

1

Central wing

2

Package (freight)

3

Freight (parcel) hatch in the central wing

4

fixed drive part

5

movable drive part

6

Wing left

7

fin

8th

elevator

9

Propeller / spinner

10

aileron

11

Wing right

12

Drive / battery / motor nacelle

Claims (11)

Aircraft preferred after 1 - 3 without hull, with a central support surface (1) and additionally rigidly mounted wings (6,11). This is a hybrid aircraft that can carry the largest possible cargo (2), and one or more parcels. It can be made in different sizes, depending on the dimensions and the weight of the cargo to be transported. The aircraft can start with 1 drive (4) vertical (vertical), fly aerodynamically horizontally, drop the load and land again vertically. This is done completely autonomously with the help of the electronic control and the 3D vector control (4,5). If required, the aircraft can also be controlled manually via a remote control. There may be other motors with gondolas (12) mounted on the wings as needed and required power. If engines are additionally attached to the wings, a 2D control for the transverse axis of the front engine is sufficient. The additional motors are then integrated into the control circuit. The drives are mainly lithium ion batteries, as used for e-bikes and in the automotive industry. Depending on the state of battery technology, other accumulators can be used. The installation of a fuel cell or a solar cell is also possible, depending on the size of the aircraft. The aircraft is modular, consisting mainly of the central support surface (1), the attached wings (6,11), and the 2 vertical vanes (7). This can also be easily disassembled for transportation. Also, various configurations of central wing and wings, vertical stabilizers in different designs are possible. The drive motor, battery, regulator and electronic control with their components are quick and easy to replace. This also applies to repairs. The propellers (9) (propellers) to the drive are hinged, which means that when the engine is switched off, they aerodynamically contact the front pylon or the engine nacelle. As a result, in the case of several drives, the front engine or optionally the area motors (12) can also be switched off, energy-saving operation becomes possible in this way. But it can also be used depending on the purpose and rigid air screws. Different wings with different geometry can be used on the aircraft, depending on the conditions of use. These can be rectangle, trapezoid, delta, or other shapes. An enlargement of the wing is also possible up to twice the span, thereby also up to 4 motors can be provided on the wings. The aircraft may also be used for other purposes, e.g. for camera shots. Various sensors and scanners for monitoring and processing data can also be mounted. The aircraft can also be optimized for autonomous rescue operations, e.g. Use a searchlight, camera, microphone and loudspeaker to contact injured people in rough terrain. Likewise, medicines or other medical devices can be transported. The aircraft can also be built for manned aviation, for transport tasks, as well as for passenger transport. Here, a biped (or retractable) with 2 tail wheels is used. It is started and landed horizontally in this version. Passengers and pilots are in the central wing, as well as luggage and cargo. The engines are then on the wings and depending on the application also on the central wing. Turbines as well as turboprop or electric drives and hybrid drives can be used.

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