VTOL aircraft

Abstract

The invention relates to a VTOL aircraft having (a) a cruise flight system having at least one airfoil configured to generate dynamic lift during a cruise flight, (b) a hover flight system having at least one lift element and at least one stabilizing element, where (i) the lift element is configured to provide lift for a hover flight, and (ii) the stabilizing element is configured to stabilize the dynamic lift during the cruise flight. And (ii) the stabilizing element is configured to provide at least one stabilizing force with respective levers relative to the longitudinal, transverse and / or vertical axis of the VTOL aircraft during the hover flight and during the transition from the hover flight to the cruise flight and during the transition from the cruise flight to the hover flight.

Description

Technical Field

[0001] The present invention relates to a VTOL aircraft, that is to say a vertical take-off and landing aircraft (the English abbreviation VTOL stands for Vertical Take-Off and Landing), or in other words an aircraft suitable for vertical take-off and vertical landing.

[0002] This type of VTOL aircraft is equipped with airfoils for primarily horizontal cruising flight. Sometimes also called wings) and hovering flight is generally only used for vertical take-off and vertical landing. Horizontal take-off and landing are obviously also possible. The VTOL aircraft according to the present invention can be manned or unmanned. Background Art

[0003] Winged aircraft Allows efficient level cruise flight because it exploits the dynamic lift made possible by the airfoil profile.However, these aircraft require a large amount of space for take-off and landing and a certain amount of airspace for approach and departure.

[0004] In contrast, rotorcraft (especially helicopters or multirotors) are extremely precise and maneuverable during takeoff and landing, but require relatively more energy for cruising. Therefore, rotorcraft cannot achieve long cruising range and high speed.

[0005] There are a large number of applications for combining vertical takeoff and landing characteristics with pure fixed-wing aircraft. Such a combined system is more complex and therefore also has disadvantages relative to pure fixed-wing aircraft in terms of system determination.

[0006] The prior art includes completely different designs.

[0007] A pivot rotor aircraft, for example, tilts the airfoil and the engine at approximately 90 degrees.

[0008] The pivot drive merely tilts the individual engines mounted at the aircraft (wings / fuselage / tail) by approximately 90 degrees.

[0009] Other systems work with cantilevers at the sides of the fuselage and / or at the wings, in order to combine, for example, four points of lift similar to a quadrotor with a fixed-wing aircraft.

[0010] However, such a cantilever arm and / or propeller suspended in cruising flight causes considerable air resistance and the unfavorable distribution of mass away from the center of gravity causes an undesirable mass inertia of the entire system, wherein the cantilever arm may also be susceptible to vibrations or oscillations.

[0011] Furthermore, the requirements for the thrust drive units for generating high thrust for hovering flight and for generating high cruising flight speeds are significantly different. Therefore, pivoting drives that are to function optimally both in hovering flight and in cruising flight often require adjustment mechanisms (e.g., variable propeller pitch, variable cross-section of the thrust nozzle, etc.), which in turn increase complexity, maintenance costs, and the risk of failure. Summary of the Invention

[0012] A fixed-wing aircraft with vertical takeoff and landing capabilities can therefore also be optimized in such a way that as little additional mass as possible is generated, the mass distribution of the entire system does not appear unfavorable, the air resistance during cruising flight is low, the system or mechanical structure is simple and fail-safe or redundant, stable hovering / maneuvering is possible, and there is sufficient space and sufficient carrying capacity for the payload.

[0013] Therefore, it is an object of the present invention to provide an improved VTOL aircraft. The solution to this object is defined by the features of claim 1 .

[0014] The present invention relates to a VTOL aircraft comprising (a) a cruising flight system having at least one airfoil, wherein the airfoil is configured to generate dynamic lift during cruising flight, and (b) a hovering flight system having at least one lift element and at least one stabilizing element, wherein (i) the lift element is configured to provide lift for hovering flight and (ii) the stabilizing element is configured to provide at least one stabilizing force relative to a longitudinal axis, a transverse axis and / or a vertical axis of the VTOL aircraft with corresponding levers during hovering flight and during the transition from hovering flight to cruising flight and vice versa.

[0015] In particular, the lift element and the stabilizing element are separate elements, which means that the lift element and the stabilizing element are actually two different elements.

[0016] In particular, the lift element is not designed for stabilization and the stabilization element is not designed for lift.

[0017] In particular, the lift element is designed only to provide a lift force for hovering flight, and the stabilizing element is designed only to provide a stabilizing force.

[0018] In particular, the expression “relative to the longitudinal axis, the transverse axis and / or the vertical axis” is to be understood as “relative to at least one axis of the group consisting of the longitudinal axis, the transverse axis and the vertical axis”.

[0019] In particular, a VTOL aircraft may have a computer that controls or regulates a cruise flight system and / or a hover flight system.

[0020] In particular, the lift element or one of the lift elements can be designed to be bendable, pivotable or steerable in such a way that it is designed to provide thrust for cruising flight.

[0021] In particular, the cruise flight system also has at least one, particularly specifically provided propulsion element, which is configured to provide thrust for the cruise flight. In an embodiment without such a propulsion element, an unpowered gliding flight can be achieved at most as an alternative to the cruise flight.

[0022] In particular, the longitudinal axis, the transverse axis, and the vertical axis extend through the center of mass of the VTOL aircraft.

[0023] In particular, the at least one stabilization element is arranged in a plane spanned by the longitudinal axis and the vertical axis.

[0024] In particular, at least one stabilization element is pivotable and is arranged such that a pivot axis of the stabilization element is arranged in a plane spanned by the longitudinal axis and the vertical axis. The other pivot axis can be designed parallel to the transverse axis.

[0025] In particular, the at least one stabilizing element is located above the airfoil in the extended state, in particular so that no lift can be generated by the stabilizing element, but only a rolling moment and / or a pitching moment.

[0026] In some embodiments, the lift element is designed such that the vector of the lift force is pivotable about a longitudinal axis, a transverse axis, and / or an axis parallel to the transverse axis.

[0027] In particular, the hovering flight system may have a lift element arranged in the fuselage of the VTOL aircraft, which is designed to provide a lift force and is arranged such that the lift force acts on the center of mass of the VTOL aircraft.

[0028] In some embodiments, the hovering flight system, however, includes two lift elements arranged in the fuselage of the VTOL aircraft, which are correspondingly constructed to provide lift and are arranged in such a way that one of the two lift forces acts before the center of mass of the VTOL aircraft and the other acts behind the center of mass of the VTOL aircraft relative to the longitudinal axis.

[0029] In another embodiment, the hovering flight system comprises at least two lift elements arranged in the fuselage of the VTOL aircraft, which are respectively designed to provide lift. This is preferably combined with at least two lift elements arranged laterally on the fuselage of the VTOL aircraft.

[0030] In another preferred embodiment, the hovering flight system comprises 4-20, in particular 4-16, specifically 4-12 lift elements arranged in the fuselage of the VTOL aircraft.

[0031] In a particularly preferred embodiment, the hovering flight system comprises exactly 4 or 12 lift elements arranged in the fuselage of the VTOL aircraft.

[0032] In particular, the 4-20 lift elements arranged in the fuselage of the VTOL aircraft are arranged such that at least two lift elements are arranged before the center of mass of the VTOL aircraft and at least two lift elements are arranged after the center of mass of the VTOL aircraft relative to the longitudinal axis.

[0033] In particular, 4-20 lift elements arranged in the fuselage of the VTOL aircraft are arranged such that 50% of the lift elements are arranged before the center of mass of the VTOL aircraft and 50% are arranged after the center of mass of the VTOL aircraft.

[0034] At least two lift elements arranged in the fuselage of the VTOL aircraft and / or at least two lift elements arranged laterally on the fuselage of the VTOL aircraft are in particular arranged such that at least one lift force acts in front of the center of mass of the VTOL aircraft and at least one lift force acts behind the center of mass of the VTOL aircraft relative to the longitudinal axis.

[0035] This has proven to be practical for redundancy reasons. In the event of, for example, a technical fault and / or a bird strike, a trouble-free operation or at least a safe emergency operation can thus be ensured.

[0036] In particular, the lift elements are arranged in compartments in the fuselage that can be opened and closed by flaps and / or other coverings. For cruising flight, in which the lift is generated by the fixed wing's airfoil profile, the flaps are closed and the fuselage obtains an aerodynamically favorable surface, whereas for hovering flight the flaps remain open.

[0037] In particular, flaps can also be used to deflect the airflow generated by the lift elements.

[0038] In some embodiments, the two lift elements or their corresponding, in particular specially provided, steering elements can be pivoted in such a way that the two lift forces generate a yawing moment acting on the VTOL aircraft. This is achieved, in particular, by pivoting the lift elements / steering elements in opposite directions relative to the longitudinal axis.

[0039] In particular, a pivoting of the lift element and / or a pivoting of the steering element along the longitudinal axis and / or the transverse axis can be achieved by the deflecting flap.

[0040] In some embodiments, the two lift elements can be controlled in such a way that a pitching moment can be provided by means of a thrust difference.

[0041] In particular, the two lift elements can also be designed to be pivotable about an axis parallel to the transverse axis in such a way that a pitching moment can be provided by means of a difference in thrust direction.

[0042] In some embodiments, at least one stabilizing element and in particular at least one lifting element can be stored in the fuselage of the VTOL aircraft and can be extended therefrom.

[0043] In particular, the compartment in which the stabilizing element is sunken can here also be embodied so as to be closable by means of flaps, that is, the fuselage obtains an aerodynamically optimized surface. During the use of the stabilizing element, the flaps can be open.

[0044] In some embodiments, the hovering flight system has a lever arrangement, which is pivotably mounted at a first end in the fuselage and at whose second end at least one stabilizing element is arranged.

[0045] In particular, the lever arrangement is designed as a connecting rod or a bracket.

[0046] In a further preferred embodiment, the lever arrangement is foldable.

[0047] In particular, the lever arrangement has at least one joint. Preferably, the joint is arranged on the half length of the lever arrangement in the extended state of the lever arrangement.

[0048] This has the advantage that a longer lever arm is available, thereby enabling a greater rolling moment and / or pitching moment to be generated.

[0049] In some embodiments, the hovering flight system has an extension device, which is fixed with a first end in the fuselage and whose second end, at which the at least one stabilizing element is arranged, is designed to be telescopically extended from the fuselage.

[0050] In particular, the lever device or the extension device (like the stabilizing element) can be sunk into the aforementioned compartment in the fuselage and can be extended.

[0051] In some embodiments, the stabilization element is pivotably mounted at the second end about at least one axis in such a manner that the stabilization force generates at least one rolling moment acting on the VTOL aircraft.

[0052] In particular, the stabilization element can be mounted at the second end so as to be pivotable about an axis parallel to the longitudinal axis.

[0053] In some embodiments, the hovering flight system is configured to pivot the lever arrangement or the extension arrangement.

[0054] In particular, the pivot axis of the pivotability is arranged in the fuselage and parallel to the transverse axis.

[0055] In particular, this pivotability can be used for stowing and extending the lever device or the extension device or, however, also for stabilizing the hovering flight.

[0056] In some embodiments, the hovering flight system includes at least two stabilizing elements arranged one after the other relative to the longitudinal axis.

[0057] In particular, the two stabilizing elements can be arranged at a single lever device or extension device or at corresponding separate lever devices or extension devices, which can be stored in separate compartments in the fuselage, in particular one stabilizing element in front of the center of mass and one stabilizing element behind the center of mass (relative to the longitudinal axis), in particular one stabilizing element in front of the cockpit and one stabilizing element behind the cockpit (relative to the longitudinal axis).

[0058] Overall, a stabilization element is thus provided which is easily producible and flexible and requires few resources for production and only little maintenance.

[0059] In some embodiments, the stabilizing element includes an electric propeller, a foldable propeller, a rotor, a ducted propeller, an impeller, and / or a turbojet engine (eg, a jet engine with / without ducted airflow, a fan jet engine).

[0060] In particular, the lift element and / or the propulsion element can also be designed as an electric propeller, a foldable propeller, a rotor, a ducted fan, an impeller or a turbojet (jet engine with / without ducted airflow, propeller fan engine).

[0061] In some embodiments, the stabilization element and / or the lift element is configured for cyclic and / or global blade adjustment.

[0062] In particular, a torque onto the transverse or longitudinal axis can be generated by a periodic and / or total blade adjustment, without the stabilizing element being designed to be non-pivotable relative to the lever arrangement or the extension arrangement.

[0063] In some implementations, the hover flight system is configured to control the rotational speed and pivot angle (and therefore thrust vector) of the stabilizing element.

[0064] In particular, the pivot angle of the stabilization element can be controlled here by at least one servo motor.

[0065] In particular, the aforementioned computer is designed for this control and is correspondingly connected to the at least one stabilization element.

[0066] In particular, the lift elements and / or propulsion elements can also be regulated / controlled by a computer.

[0067] In a preferred embodiment, the lift elements and / or propulsion elements can be regulated / controlled by a computer in such a way that each individual lift element and / or propulsion element can be individually actuated.

[0068] In particular, the lift element and / or the propulsion element can be controlled by a computer in such a way that the lift element and / or the propulsion element can be pivoted independently of one another respectively around a transverse axis, around an axis parallel to the transverse axis, around a vertical axis, around an axis parallel to the vertical axis, around a longitudinal axis and / or around an axis parallel to the longitudinal axis.

[0069] Flexible control of the individual lift elements and / or thrust elements can thus be ensured, so that the most efficient possible adaptation of the lift and / or thrust forces is possible.

[0070] In some embodiments, the stabilizing element is designed as a multirotor. In the case of a multirotor, the pivot angle can be controlled by at least one servo motor or, alternatively, by the thrust difference of the individual drives of the multirotor. Due to the aerodynamic, i.e., slender and narrow, design of the fuselage, the arrangement of the individual drives of the multirotor relative to its longitudinal axis can be implemented in two rows with two or more drives on each side of the longitudinal axis.

[0071] In particular, the multirotor can be connected to the lever arrangement or the extension arrangement via a joint, in particular by means of an articulated joint or a universal joint.

[0072] Particularly preferably, the multirotor is pivotably connected at its center of gravity to the lever device and / or the extension device.

[0073] In particular, the hovering flight system can have a lift element that also has the properties of a stabilizing element, and a stabilizing element that also has the properties of a lift element. Thus, there are two similar elements, which are in particular designed as electric propellers, foldable propellers, rotors, ducted fans, impellers, turbojets (jet engines with or without ducted airflow, propeller fans), and which provide both lift and hovering flight stabilization.

[0074] In particular, the lift element, the propulsion element and / or the stabilization element can optionally be an electric motor and / or an internal combustion engine.

[0075] In other words, the invention enables a modern aerodynamic design of the airfoils and fuselage, in particular the selection of modern thin airfoil profiles without aerodynamically disruptive appendages (such as cantilevers with engines and propellers suspended in the airflow).

[0076] In particular, at least one thrust device with thrust mainly parallel to the vertical axis (impeller, propeller, straightening fan, jet turbine, etc.) is introduced on the longitudinal axis in the fuselage before and after the center of gravity at a specific distance from the center of gravity.

[0077] In particular, the two thrust devices can be pivoted in parallel or in opposite directions relative to the longitudinal axis. Likewise, the two thrust devices can be pivoted in parallel relative to the transverse axis.

[0078] As an alternative to or in combination with the above-described pivotable embodiment, the thrust of the above-described thrust device can also be deflected partially to the side and / or forwards or backwards by means of flaps, blades or the like.

[0079] The two thrust devices according to the above embodiment can realize translation along the vertical axis (vertical ascent and descent or hovering), along the longitudinal axis (hovering forward or backward) and along the transverse axis (hovering to one side or the other), as well as yaw around the vertical axis.

[0080] The above-mentioned translational movement is possible without a pitching or rolling movement of the aircraft if the thrust of the above-mentioned thrust device is derived for control purposes by pivoting or by means of flaps, blades, etc.

[0081] In the case of vector control without thrust, that is, with thrust always parallel to the vertical axis, translational movement along the longitudinal axis (hovering forward or backward) can be achieved through a pitching movement. This pitching movement is achieved by the thrust difference of the two thrust devices. Similarly, in the case of vector control without thrust, that is, with thrust always parallel to the vertical axis, translational movement along the transverse axis (hovering to one side or the other) can be achieved through a rolling movement. To control and stabilize the rolling movement, at least one stabilizing element is used, which can also be implemented as a lift element if necessary.

[0082] Preferably, to control the rolling movement, at least one thrust device relative to the transverse axis (thrust to each side) is provided on at least one cantilever in the plane formed by the longitudinal axis and the vertical axis. The thrust parallel to the transverse axis (to one side or the other) at a defined distance from the center of gravity can be achieved by pivoting the thrust device parallel to the longitudinal axis, by redirecting the thrust, or by separate thrust devices for each side, or by variable positive or negative pitch.

[0083] Preferably, the aforementioned means for controlling the rolling movement for cruising flight (cantilever with separate thrust means) and, if present, the ailerons for controlling the rolling movement can be retracted by means of a pivoting movement or pivotally stored in one or more accommodation chambers in the fuselage.

[0084] For cruising flight (lift of the wing surface), a separate thrust device with thrust in the longitudinal direction can be selectively used, or the pivoting of the thrust device necessary for hovering flight can be used. Optionally, a separate elevator or rudder can be eliminated by controlling the above-mentioned thrust vector.

[0085] The fuselage is a streamlined object that is relatively large in volume relative to the wing surface and is suitable for accommodating the thrust device. The relatively large fuselage is suitable for accommodating the necessary load-bearing structures and for accommodating the thrust, lateral force and torsion of the thrust device.

[0086] Space for a cockpit, passengers and / or cargo is available, for example, in the vicinity of the center of gravity.

[0087] Preferably, the booms with the thrust units are screwed into a housing in the fuselage for controlling and steering at least one roll axis for cruising and for reducing air resistance. The front and rear thrust units in the fuselage can be closed for cruising by means of flaps, provided that the individual thrust units provide thrust for cruising.

[0088] Due to the inflow in cruising flight, lift is provided by the airfoil and control of the rolling movement about the longitudinal axis is provided by the ailerons.

[0089] The boom with a separate thruster is preferably used only for controlling and steering the rolling motion. Therefore, it can be dimensioned much smaller than a boom with a thruster that also needs to provide lift for hovering flight. It can therefore be mounted on a simple boom or rod in a pivotable or telescopically pushable manner, without drawbacks, using smaller components.

[0090] Therefore, the airfoil does not have to accommodate separate thrust devices and can be designed aerodynamically optimally and with low drag for cruise flight.

[0091] In a further preferred embodiment, the hovering flight system comprises at least two lift elements arranged laterally on the fuselage of the VTOL aircraft, which are each designed to provide lift.

[0092] Therefore, in the case of a tumbling motion, the tumbling axis can be additionally stabilized and / or controlled. In addition, such an embodiment proves to be practical for redundancy reasons. Therefore, trouble-free operation can be ensured in the case of, for example, technical failures and / or bird strikes.

[0093] In particular, at least two lift elements are arranged on opposite longitudinal sides of the fuselage.

[0094] A longitudinal side of the fuselage is understood to be a side of the fuselage running parallel to the longitudinal axis.

[0095] In a particularly preferred embodiment, at least two lift elements are arranged along the transverse axis and / or along an axis parallel to the transverse axis.

[0096] In particular, at least two lift elements arranged laterally on the fuselage of the VTOL aircraft are designed to be bendable, pivotable or steerable in such a way that they are designed to provide thrust for cruising flight.

[0097] In some embodiments, at least two lift elements arranged laterally on the fuselage of the VTOL aircraft may be arranged such that they can be pivoted about a transverse axis, about an axis parallel to the transverse axis, about a vertical axis, about an axis parallel to the vertical axis, about a longitudinal axis and / or about an axis parallel to the longitudinal axis in hovering flight and / or in cruising flight.

[0098] In particular, at least two lift elements may be mounted so as to be pivotable about an axis parallel to the longitudinal axis, in particular so that a lateral translational movement and / or a yawing moment can be generated during hovering flight.

[0099] In another special embodiment, at least two lift elements are pivotably mounted about axes parallel to the transverse axis, in particular so that forward translational movements, backward translational movements, pitching moments and / or yawing moments can be generated during hovering flight.

[0100] Preferably, at least two lift elements are mounted continuously pivotably about an axis parallel to the transverse axis, in particular such that they can provide thrust for cruising flight.

[0101] In a further embodiment, at least two lift elements arranged laterally on the fuselage of the VTOL aircraft can each be pivoted by at least 90 degrees, in particular at least 180 degrees.

[0102] In particular, at least two lift elements arranged laterally on the fuselage of the VTOL aircraft can be pivoted through 360 degrees about a transverse axis and / or about an axis parallel to the transverse axis.

[0103] In a particular embodiment, at least two lift elements arranged laterally on the fuselage of the VTOL aircraft provide lift and / or thrust for cruising flight.

[0104] This ensures flexibility in flight direction, since hovering flight (that is to say vertical movement), cruising flight (that is to say horizontal movement) or a combination thereof are possible.

[0105] Furthermore, it is thereby possible to generate yaw, pitch and / or roll moments during hovering flight and / or during cruising flight.

[0106] In particular, at least two lift elements, in particular all lift elements, are arranged such that they are spaced from the longitudinal axis by a maximum of 50%, in particular a maximum of 30%, particularly preferably a maximum of 20% of the total length of the half span of the airfoil.

[0107] This results in a favorable distribution of the mass close to the fuselage or the center of gravity, which leads to a lower inertia of the entire system.

[0108] The half span of an airfoil is the distance between a point on the longitudinal axis and the wing tip, wherein the distance is perpendicular to the longitudinal axis. The wing tip is the corresponding end of the airfoil.

[0109] In a further preferred embodiment, the hovering flight system comprises two lift elements arranged in the fuselage of the VTOL aircraft and at least two lift elements arranged laterally on the fuselage of the VTOL aircraft.

[0110] In particular, the hovering flight system comprises at least two lift elements arranged in the fuselage of the VTOL aircraft and at least two lift elements arranged laterally on the fuselage of the VTOL aircraft.

[0111] In particular, no lift elements are arranged at and / or in the airfoil.

[0112] In a further preferred embodiment, no stabilizing elements are arranged on and / or in the airfoil. BRIEF DESCRIPTION OF THE DRAWINGS

[0113] Additional advantages of the present invention will become apparent from the detailed description and accompanying drawings.

[0114] Figure 1 shows a side view of a VTOL aircraft according to a first exemplary embodiment of the present invention, wherein the stabilizing element is extended for hovering flight;

[0115] Figure 2 Shows the Figure 1 Front view of the VTOL aircraft;

[0116] Figure 3 Shows the Figure 1 and 2 A top view of the VTOL aircraft;

[0117] Figure 4 Shows the Figures 1 to 3 A side view of a VTOL aircraft with the stabilizing element retracted for cruise flight;

[0118] Figure 5 shows a side view of a VTOL aircraft according to a second embodiment of the present invention, wherein the stabilizing elements and the lifting elements are extended for hovering flight; and

[0119] Figure 6 Shows the Figure 5 A top view of a VTOL aircraft. DETAILED DESCRIPTION

[0120] Figure 1 1 is a side view of a VTOL aircraft 1 according to a first exemplary embodiment of the present invention, wherein the stabilizing elements 5 and 6 are extended for hovering flight. The stabilizing elements 5 and 6 are designed here as propellers and are mounted so as to be motor-rotatable at the first end of a lever arrangement 9 designed as a bracket. The two propellers 5 and 6 are also pivotable about axes parallel to the longitudinal axis L. This pivotability is Figures 1 to 3 The axes L, Q and H extend through the center of mass M of the aircraft 1 . The aircraft 1 has a cockpit 23 .

[0121] The support 9 is a double-rod structure that can be folded like a parallelogram. The two propellers 5 and 6 are respectively equidistant from the vertical axis H. The lift elements 3 and 4 are placed in the fuselage R of the VTOL aircraft 1 and their force vectors V3 and V4 always act on the longitudinal axis L despite their pivotability. The generation of a rolling moment is therefore impossible for the lift elements 3 and 4. The main task of the stabilizing elements 5 and 6 is therefore to compensate for the generation of a rolling moment for stable hovering flight. For this purpose, the propellers 5 and 6 can be turned to the left or right at an angle between 0 and 90 degrees as required (see Figure 2 ) and changes the rotation speed. At least one servo motor controls the left and right rotation angles. The lever device can be retracted into or extended from the fuselage by the servo motor. Alternatively, or in combination, the lever device can be extended using a thrust drive of a stabilizing element and retracted using gravity. In particular, the computer 10 is configured to implement the necessary control and regulation.

[0122] The described pivotability of lift elements 3 and 4 occurs about a longitudinal axis L and an axis parallel to transverse axis Q. Thus, translational movement along longitudinal axis L or transverse axis Q is possible. Lift elements 3 and 4 are fixedly embedded in fuselage R, and airflow can enter and exit via flaps 7 and 8. In this example, lift elements 3 and 4 are impellers and / or turbines.

[0123] Likewise, the stabilizing elements 5 and 6 are stored within the fuselage R (see Figure 4 ) compartment using flaps 21 (see Figure 1 ) to close. Figure 2 and Figure 3 , the flaps are not shown for simplification. Thus, the aircraft 1 is aerodynamically optimized for cruising flight. For this purpose, the aircraft 1 also has a propulsion element 22, which is implemented as a propeller here.

[0124] Figure 2 Shows the Figure 1 Front view of a VTOL aircraft 1. The wing surface 2 is used for the subsequent cruising flight and is introduced with the transition from hovering flight. The connecting rod 9 does not protrude substantially along the transverse axis Q, thereby ensuring good stowage in the fuselage R. The pivotability of the stabilizing elements 5 and 6 is indicated by curved arrows and by dashed lines in four further different orientations of the propellers. The vector arrows represented by dashed lines belonging to these different orientations point to the stabilizing forces that are then generated accordingly. In the basic position shown, the propellers 5 and 6 are oriented horizontally and rotate only in idling, for example. As soon as there is a need to compensate for an undesired rolling movement, the stabilizing elements 5, 6 pivot relative to the corresponding side and generate the required thrust. With this pivoting, very fast reaction capabilities can also be achieved due to the relatively small mass to be moved or the low mass inertia.

[0125] Figure 3 Shows the Figure 1 and 2 VTOL aircraft 1 from above. Lift elements 3 and 4 can be seen, which are arranged centrally in fuselage R. Extended stabilizing elements 5 and 6 are located above cockpit 23 for the duration of hovering flight and during the transition from / to cruising flight. During these times, pitch and yaw moments are (primarily) generated by lift elements 3 and 4, while roll moments are generated by stabilizing elements 5 and 6. Stable hovering flight is thus ensured without the need for heavy, complex elements that are not schematically distributed relative to the mass inertia. The design according to the invention saves weight in particular, which is a very important criterion for vertical take-off.

[0126] Figure 4 Shows the Figures 1 to 3 Side view of a VTOL aircraft, wherein the stabilizing elements 5, 6 are retracted for cruising flight. The lift is now generated exclusively by the airfoil 2.

[0127] Figure 5A side view of an unmanned VTOL aircraft 11 according to a second embodiment of the present invention is shown, with stabilizing and lift elements 13 / 15, 14 / 16 extended for hovering flight. The stabilizing element 15 of the aircraft 11 is also designed as a lift element 13, with the foldable propeller or rotor being significantly larger in size. The propeller blades are foldable, allowing them to be placed parallel to the boom and requiring less storage space. The lift element 14 is also designed as a stabilizing element 16, pivoting about an axis parallel to the longitudinal axis L, just like the stabilizing element 15. In the example shown, the pivot point for this pivotability is in the rotor plane (marked with a cross in the figure). Yaw, pitch, and roll moments can thus be provided by the two propellers. The lower cross symbol indicates the pivot axis for the lever arrangement 19, 20 stored in the fuselage R. Lift can be achieved largely unimpeded, as air can flow through the fuselage R. Lift vectors V3 and V4 extend here through the pivot axis of the stabilizing or lifting element, which is parallel to the longitudinal axis L.

[0128] Figure 6 Shows the Figure 5 VTOL aircraft 11 from above. During the transition to cruising flight, the thrust elements 24 are activated and build up translational speed along the longitudinal axis L. The lift / stabilization elements 15 / 13 and 16 / 14 are brought to a standstill, run into the fuselage R, and the flaps 17 and 18 are closed.

[0129] The lever arrangement 19 , 20 is thus pivotably mounted in the fuselage. This pivotability and the pivotability of the propeller are provided by servomotors and controlled / regulated by the computer 25 .

[0130] Although the present invention has been described with reference to one or more preferred embodiments, many other modifications and variations are possible without departing from the scope of the invention. It is therefore intended that the appended patent claims cover modifications and variations that fall within the true scope of the invention.

[0131] Reference Signs List

[0132] 1,11VTOL aircraft

[0133] 2,12 wing

[0134] 3,13 lift element

[0135] 4,14 lift elements

[0136] 5,15 stabilizing elements

[0137] 6,16 stabilizing elements

[0138] 7,17 flaps / steering elements

[0139] 8,18 flaps / steering elements

[0140] 9,19,20 lever device

[0141] 10,25 computers

[0142] 21 flaps

[0143] 22,24 propulsion elements

[0144] 23 cockpit

[0145] H vertical axis

[0146] L longitudinal axis

[0147] M Centroid

[0148] Q horizontal axis

[0149] R Body

[0150] V3 lift vector

[0151] V4 lift vector

Claims

1. A VTOL aircraft (1,11) having A cruising flight system having at least one airfoil (2, 12), wherein: The airfoils (2, 12) are configured to generate dynamic lift during cruise flight, A hovering flight system having at least one lift element (3, 4, 13, 14) and at least one stabilizing element (5, 6, 15, 16), wherein: The lift elements (3, 4, 13, 14) are configured to provide lift for hovering flight, and The stabilizing elements (5, 6, 15, 16) are designed to provide at least one stabilizing force with corresponding levers relative to the longitudinal axis (L), the transverse axis (Q) and / or the vertical axis (H) of the VTOL aircraft (1, 11) during hovering flight and during the transition from hovering flight to cruising flight and from cruising flight to hovering flight.

2. The VTOL aircraft (1, 11) according to claim 1, wherein: The lift elements (3, 4, 13, 14) are designed such that the vectors (V3, V4) of the lift force are pivotable about the longitudinal axis (L), the transverse axis (Q) and / or an axis parallel to the transverse axis (Q).

3. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein The hovering flight system comprises two lift elements (3, 4, 13, 14) arranged in the fuselage of the VTOL aircraft, which are respectively constructed to provide lift and are arranged in such a way that one of the two lift forces acts in front of the center of mass (M) of the VTOL aircraft (1, 11) and the other acts behind the center of mass (M) of the VTOL aircraft (1, 11) relative to the longitudinal axis (L).

4. The VTOL aircraft (1, 11) according to claim 3, wherein: The two lift elements (3, 4, 13, 14) or the corresponding deflection elements (7, 8, 17, 18) of the lift elements (3, 4, 13, 14) are pivotable in such a way that two lift forces generate a yawing moment acting on the VTOL aircraft (1, 11).

5. The VTOL aircraft (1, 11) according to claim 3 or 4, wherein: The two lift elements (3, 4, 13, 14) can be controlled in such a way that a pitching moment can be provided by means of a thrust difference.

6. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein The at least one stabilizing element (5, 6, 15, 16), in particular the at least one lifting element (3, 4, 13, 14), can be stored in a fuselage (R) of the VTOL aircraft (1, 11) and can be configured to be extendable from the fuselage.

7. The VTOL aircraft (1, 11) according to claim 6, wherein: The hovering flight system comprises a lever arrangement (9, 19, 20) which is pivotably supported at a first end in the fuselage (R) and at whose second end at least one stabilizing element (5, 6, 15, 16) is arranged.

8. The VTOL aircraft (1, 11) according to claim 6, wherein: The hovering flight system has an extension device, which is fixed with a first end in the fuselage (R), and the second end of which the at least one stabilizing element (5, 6, 15, 16) is arranged thereon is designed to be extended from the fuselage (R) in a telescopic manner.

9. The VTOL aircraft (1, 11) according to claim 7 or 8, wherein: The stabilizing element (5, 6, 15, 16) is pivotably mounted at a second end about at least one axis in such a manner that the stabilizing force generates at least one rolling moment acting on the VTOL aircraft (1, 11).

10. The VTOL aircraft (1, 11) according to any one of claims 7 to 9, wherein The hovering flight system is configured to pivot the lever device (9, 19, 20) or the extension device.

11. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein The hovering flight system comprises at least two stabilizing elements (5, 6, 15, 16) arranged in sequence relative to the longitudinal axis (L).

12. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein The stabilizing elements (5, 6, 15, 16) include electric propellers, foldable propellers, rotors, ducted propellers, impellers and / or turbojets.

13. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein The stabilizing elements (5, 6, 15, 16) are designed for periodic and / or total blade adjustment.

14. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein The hovering flight system is configured to control the rotation speed and pivot angle of the stabilizing element (5, 6, 15, 16).

15. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein The stabilizing elements (5, 6, 15, 16) are configured as a multi-rotor aircraft.

16. The VTOL aircraft (1, 11) according to claim 15, wherein: The multirotor aircraft is pivotably connected to the lever device and / or the extension device at its center of gravity.

17. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein The hovering flight system comprises at least two lift elements arranged laterally on the fuselage (R) of the VTOL aircraft, which are respectively designed to provide lift.

18. The VTOL aircraft (1, 11) according to claim 17, wherein The at least two lift elements are arranged on opposite longitudinal sides of the fuselage (R).

19. The VTOL aircraft (1, 11) according to any one of claims 17-18, wherein The at least two lift elements are pivotably mounted about an axis parallel to the longitudinal axis (L), in particular such that a lateral translational movement and / or a yawing moment can be generated during the hovering flight.

20. The VTOL aircraft (1, 11) according to any one of claims 17-19, wherein The at least two lift elements are pivotably mounted about an axis parallel to the transverse axis (Q), in particular such that a forward translational movement, a backward translational movement, a pitching moment and / or a yawing moment can be generated during the hovering flight.

21. The VTOL aircraft (1, 11) according to any one of claims 17 to 20, wherein: The at least two lift elements are mounted continuously pivotably about an axis parallel to the transverse axis (Q), in particular such that they can provide thrust for cruising flight.

22. The VTOL aircraft (1, 11) according to any one of claims 17 to 21, wherein: The at least two lift elements arranged laterally on the fuselage of the VTOL aircraft can each be pivoted by at least 90 degrees, in particular by at least 180 degrees.

23. The VTOL aircraft (1, 11) according to any one of claims 17 to 22, wherein: The at least two lift elements are arranged along the transverse axis (Q) and / or along an axis parallel to the transverse axis.

24. The VTOL aircraft (1, 11) according to any one of claims 17 to 23, wherein: The at least two lift elements, in particular all lift elements, are arranged such that they are spaced from the longitudinal axis by a maximum of 50%, in particular a maximum of 30%, particularly preferably a maximum of 20% of the total length of the half span of the airfoil (2, 12).

25. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein No lift elements are arranged on and / or in the airfoils (2, 12).

26. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein No stabilizing elements (5, 6, 15, 16) are arranged on and / or in the airfoil (2, 12).

27. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein The at least one stabilizing element (5, 6, 15, 16) is arranged in a plane spanned by the longitudinal axis (L) and the vertical axis (H).

28. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein a) the at least one stabilizing element (5, 6, 15, 16) is arranged in a plane spanned by the longitudinal axis (L) and the vertical axis (H), b) wherein the at least one stabilizing element (5, 6, 15, 16), in particular the at least one lifting element (3, 4, 13, 14), can be stored in a fuselage (R) of the VTOL aircraft (1, 11) and is designed to be extendable from the fuselage, c) wherein the hovering flight system comprises a lever arrangement (9, 19, 20) which is pivotably supported at a first end in the fuselage (R) and at whose second end the at least one stabilizing element (5, 6, 15, 16) is arranged, d) wherein the stabilizing element (5, 6, 15, 16) is pivotably mounted at the second end about at least one axis in such a manner that the stabilizing force generates at least one rolling moment acting on the VTOL aircraft (1, 11).

29. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein a) the at least one stabilizing element (5, 6, 15, 16) is arranged in a plane spanned by the longitudinal axis (L) and the transverse axis (H), b) The hovering flight system comprises two lift elements (3, 4, 13, 14) arranged in the fuselage of the VTOL aircraft, which are respectively constructed to provide lift and are arranged in such a way that one of the two lift forces acts in front of the center of mass (M) of the VTOL aircraft (1, 11) and the other acts behind the center of mass (M) of the VTOL aircraft (1, 11) relative to the longitudinal axis (L).

30. The VTOL aircraft (1, 11) according to any one of the preceding claims, wherein a) the at least one stabilizing element (5, 6, 15, 16) is arranged in a plane spanned by the longitudinal axis (L) and the vertical axis (H), b) wherein the at least one stabilizing element (5, 6, 15, 16) is located above the airfoil (2, 12) in the extended state, in particular so that no lift can be generated by the stabilizing element, but only a rolling moment and / or a pitching moment can be generated, c) wherein the at least one stabilizing element (5, 6, 15, 16), in particular the at least one lifting element (3, 4, 13, 14), can be stored in a fuselage (R) of the VTOL aircraft (1, 11) and is designed to be extendable from the fuselage, d) wherein the hovering flight system comprises a lever arrangement (9, 19, 20) which is pivotably supported at a first end in the fuselage (R) and at whose second end the at least one stabilizing element (5, 6, 15, 16) is arranged, e) wherein the stabilizing element (5, 6, 15, 16) is pivotably mounted at the second end about at least one axis in such a manner that the stabilizing force generates at least one rolling moment acting on the VTOL aircraft (1, 11).

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