EP2137061B1 - Flexible impact blade and drive device for a flexible impact blade - Google Patents

Abstract

A watercraft having a plurality of flexible section secured to a mount, having a drive assembly, wherein the water craft can move the flexible section upwardly and downwardly to propel the watercraft through the water.

Description

The present invention relates to a drive device in particular for a bending blade, a bending blade with such a drive device and a watercraft with a drive and / or control member.

The drive device for a bending blade is designed connectable on one side with a drive and has a substantially formed in the form of a wedge bending element, which has at least two, away from the drive away and on the side of the drive spaced from each other bending sections whose distance from each other decreases in the direction away from the drive and are coupled in a force-transmitting manner in the region of the end remote from the drive of the bending element.

The invention further relates to a bending blade, which can deform elastically three-dimensionally, wherein a change in shape with continuous contour transition is infinitely adjustable.

The invention has been inspired in several aspects by observations of bird flight and underwater flight of penguins, sea turtles, manta rays, which have interesting flight characteristics and sometimes exceptional maneuvering capabilities, which are relatively rigid with those commonly used in the art Systems could not be reached so far.

It arises from the desire to create a technical solution that approximates the nature models (especially the manta wings) in motion kinematics and flow dynamic behavior and - without wanting to copy the biology in detail - in the simplest possible way with the in the Technology available funds and materials can be realized.

Constructions in which remarkable properties are achieved in the interaction of flexible composite structures with the environment are known in the art, for example, under the trade name Fin Ray Effect®, and include, for example, toothbrushes, lever designs, pliers, flippers, etc. These have the same with others common profile elements for sails and aircraft wings in common that they deform passively under external force on advantageous for the application in question way. Some constructions are tiltable or pivotable about an axis of rotation at the base or can -. B. in the case of a backrest of a seat - are also braced form change.

In AU 6563380 A (MC Kinlay IB) a rudder construction is described, which is held on an axis and has a variable in the cross-sectional plane profile shape.

Also known are profile elements - especially for ship sails ( LU 88 528 A , Thirkell Laurent) and wings ( EP 0 860 355 A1 Flavio Campanile) - with a flexible outer skin and internal spacers, which are held by a rigid middle part to length or curved laterally, and wing ribs with a closed - and thus constant length - flexible outer belt, the curvature to a limited extent on an active change of the Tilt angle of inner stiffening elements relative to the outer belt can be varied. The variation aims in the said cases on an influence of the profile geometry in the direction of flow, the blade geometry in mast or Spannweiterichtung is not addressed.

The document US 6089178 , which is considered to be the closest prior art, describes a driving device for underwater driving, wherein on each side of the vehicle, a Biegeschschlaglamelle is arranged.

The present invention has for its object to provide by simple constructive measures an elastically flexible wing and a drive device for such a wing, which can deform in several directions and in which a stepless change in shape with flowing contour transition is adjustable, so that these z. B. can be used in the fluid dynamic application for control functions or for propulsion generation, with respect to the use in the broader sense, other application functions are to be made possible.

It is also desirable to combine two or more wings into a system for traverse, propulsion and / or lift generation, such as a "bionic flying wing" watercraft, which can perform complex flight maneuvers with ray-like mobility.

In particular, the aim is to make all parts of the wing, in particular its drive device, the parts of its skeleton as flexible as possible, soft and articulated to connect with each other and yet to achieve a high structural strength.

This object is achieved by the drive device for a bending blade according to the invention that the bending sections are held on the side of the drive substantially along the longitudinal axis of the wedge relative to each other and the movable movable element in dependence on the relative position of the bending sections on the side of the drive a different, in the thickness direction of the bending blade, d. h., perpendicular to the cross section of the formed in the form of a wedge bending element, pointing curvature is configured convertible.

The bending blade according to the invention solves the above object in that at least one of the drive devices according to the invention is provided for changing the outer contour of the bending blade, wherein the drive-side ends of the bending sections are arranged in the wing root.

The watercraft according to the invention solves this problem in that the drive and / or control member is an inventive Bielaglagflügel. The term watercraft also includes vehicles that move in other fluids, including gases, including aircraft.

Under a bending section are both tension elements, e.g. Tensile forces transmitting ropes, as well as pressure elements which transmit tensile and compressive forces to understand how push rods or spars. These bending sections can also be sheet-like elements, e.g. to be a flexible plate. The shape of a wedge is to be understood as a body in which two elements or side surfaces, defining one another at an acute angle, converge. Wedge shape in the sense of the present invention may include, but does not assume, that the converging elements also meet at an acute angle.

This object is achieved by the fact that a bending impact blade - z. B. in the flow dynamic sense, a wing or control element - is equipped with a flexible support member as a bending section which extends in the interior of the wing spanwise and acts as a bending beam, which is connected to an actuator which can bend the bending beam transversely to the wing surface steplessly.

It follows that when the bending beam defining a bending section is bent in the said arrangement, the deflection in the spanwise direction increases non-linearly and reaches its greatest value at the distal end, ie at the wing tip. Such a movement is for the drive and / or the control with a z. B. at the rear of a vehicle mounted wing according to the invention and / or in the propulsion generation with a cyclic impact movement of a wing arranged transversely to the flow or to stabilize a flow body of great advantage, since in the outer wing area the greatest effect is achieved.

In contrast to the otherwise common practice that is rotated to generate a wing rash of the wing at the root as a rigid body about a hinge axis or, resulting in a high root bending moment, which must be absorbed by a correspondingly rigid and massive spar design, and the wing under the influence of fluid dynamic forces at best passive, d. H. deformed contrary to the direction of impact, a significant feature of the present invention is that the adjusting not at the root and not transverse to the spar, but at the top of the support element or approximately in the region of the center of gravity of the fluid dynamics forces in the outer region of the wing into the structure is introduced to selectively actuate the outside of the wing.

The drive device according to the invention, the bending blade according to the invention and the aircraft and watercraft according to the invention can be further developed by different, mutually independent, each advantageous embodiments. These refinements and the advantages associated with the respective embodiments will be briefly discussed below.

The power transmission to the outside of the wing can be done according to the invention by tension members or push rods as bending portions of the bending element, which are guided from the proximal end, ie from the wing root in the form of a wedge at an acute angle to the side facing away from the output side, eg a tip of the bending element, where the bending sections are connected in a force-transmitting manner at the end facing away from the drive. By means of corresponding actuators of a drive, at least one of the output-side sections of a bending section can be operated, tensile elements, etc. are generally slimmer and lighter than push rods, and in view of the lightweight and also for various other reasons usually preferred are. Since the adjusting force depends on the angle of attack, which is limited in the case of a bending impact wing but by the profile height at the root of the wing, can in central arrangement of Carrier elements, ie supporting bending sections and only half the profile or wing height as the base distance, ie the output side distance between two coupled bending sections can be used. At a large base distance, the tensile force is correspondingly larger and at the same time the adjustment path is smaller. Depending on the application, specifications and influencing factors, including: strength of the acting or applied forces, length-thickness ratio of the wing to be moved, actuator principle, sensory requirements and other conditions, to decide which embodiment is the most suitable.

In one-sided force or an application situation in which the wing only has to be actively moved in one direction of impact, it offers z. Example, at least as far as possible to relocate at least one bending portion of the bending element to the outer contour of the wing and to realize the curvature preferably via one or more tension members, which are arranged as far as possible in the vicinity or in the opposite outer contour. In this way, the largest possible base distance is reduced. In the case of force relationships which are symmetrical on both sides or in both directions of movement, a pressure-stable bending section can be coupled to a further pressure-stable bending section for force transmission.

In general, it should be noted that when using the available installation space for the arrangement of the straps as far as possible in the outer area and a correspondingly large base distance, the area moment of inertia and thus the structural strength of the wing is increased.

Thus, a portion of at least one bending section at the drive end in a bearing can be held tilt-proof. Non-tilting means that the held section can not be tilted relative to the bearing. A rotational movement about the longitudinal axis of the held portion as well as an axial displacement along the longitudinal axis are permissible and in some embodiments also desirable. In other embodiments, the held portion can also be fixed in the camp.

Thus, the invention can also provide a storage, which means in the most general sense any kind of component on which the drive device according to the invention or the drive-side bending sections of the invention wings can be attached, held or guided -. As a plate, an open frame structure, a clamping element or a closed shell, a fuselage segment, etc., possibly also another Wing. Thus, the bending element according to the invention of the wing according to the invention or its drive device in the drive-side base region, ie at its root, in a predetermined orientation with respect to the holder tip over - which is not pivotally about a pivot joint - is guided. For the sake of completeness, it should be mentioned that the component used for storage can then in turn be movably mounted in a form known from the prior art and overall a variety of possible combinations with known constructions arise, to which, however, will not be discussed here.

In the following, the description is essentially concerned with an advantageous embodiment for wings with relatively slim profiles, which can be actuated on both sides and can be actuated on both sides with little effort in the case of continuous contour progression.

In the said advantageous embodiment, the bending support serving as a bending section is arranged on the upper or lower profile edge and is preferably held in its base region in a suitable receptacle on the fuselage such that its upper edge merges approximately tangentially into the fuselage contour. At the opposite ie corresponding lower or upper profile edge, a flexible push rod is inserted as a further bending section, which is connected in the outer region of the wing at an acute angle to the bending beam and in the projection on the median plane of the wing has the same orientation as the above-mentioned bending beam, is frictionally connected with selbigem at the desired point, and is slidably guided in its base region on the relevant fuselage side in a corresponding receptacle so that it can be moved in its longitudinal direction. For the axial displacement, an actuator is provided which engages in the base region or at least in the vicinity thereof or at the end of the pressure rod directly or by means of a suitable mechanical connection. Since the wing is to be deflected in both directions, the push rod acts in the opposite direction as a tension element, -action reaction is clear that the bending rod is also loaded in its longitudinal direction alternately times train and sometimes pressure. From the Symmetrieb condition it is clear that the bending beam and the pressure or tension rod as bending sections in the wing area can also be designed identically, which is why they are generally referred to in other than "spars" or "straps". It should be made clear that the straps or spars may optionally also be flexible planar elements, composites or functional units, which consist of several juxtaposed structural components or composing fiber elements which have finer differentiations with respect to their individual design and fiber orientation, if necessary, can also be designed individually replaceable, which z. B. a variable adaptation to different conditions of use is made possible and service and repair can be facilitated. Apart from the alternating in the load change as tensile or compressive voltage sign of the direction of tension in the direction of the spars or straps, the mechanical properties and in particular the bending properties of the bending beam or the bending blade are always combined in the interaction of the mechanical properties and the geometric arrangement of all subcomponents certainly. In the construction according to the invention, the wing carrier contains two physically or at least functionally differentiable structural elements which can be variably controlled or actuated individually or in combination in a suitable / inventive manner. In other words, both spars together form the bending element of a preferred embodiment of the construction according to the invention.

The curvature or bending movement of the wing which is brought about in the arrangement according to the invention in that the two spars are axially displaced in their base region relative to each other. This implies two possibilities. So z. B. a spar fixed at its root, while the other is movably mounted. Likewise, both spars may be movable, i. be slidably mounted in the axial direction. The guide can be unilaterally z. B. inside or outside, front or rear, for example, in a guide groove, slide o. Ä. or in a sleeve possibly also ball or roller bearings or free-hanging, d. H. be realized without direct solid contact, for example via a suitable alignment or tension of tension elements, which can be coupled in an advantageous manner with the actuator system.

The bending curve, d. H. the bending curve of a bent bending section can be influenced in an advantageous manner by constructive measures (material distribution, geometry, etc.) and / or by operative measures.

According to a further advantageous embodiment, the bending element can be designed substantially in the form of a pyramidal wedge and have at least three, on the drive side spaced-apart bending sections whose distances from each other decreases in the direction away from the drive. In this arrangement, the bending element be bent not only in a bending plane, but can be curved by appropriately actuated relative movements of the drive-side bending sections of the bending element in a further spatial axis, ie also from the bending plane out. The end remote from the drive of the bending element can thus be bent in intersecting planes of curvature, which can be achieved, for example, circular bending movements.

Two bar-shaped bending sections, which are formed as a wedge, can only be curved in the bending plane, which span the longitudinal axes of the wedge. Coupling now to the top of this wedge another bending section, which is spaced on the side of the drive of this bending plane, the original V-shaped bending wedge can be curved out of its bending plane, if on the third bending section, a tensile or compressive force the tip of the wedge is exerted.

Alternatively, the bending element can also have four bending sections, which form a wedge in the form of a pyramid with a quadrangular base.

In a further advantageous embodiment, the drive facing away from the end of the bending element in the direction away from the drive continue as a flexible extension.

In this way, a natural looking movement kinematics of the bending element or driven by these bending impact blade can be achieved. This can be achieved, for example, in that the connection point of the bending elements, for. B. two flexible spars, at about 2/3 to 4/5 of the maximum distance of the maximum length of the bending element, whereby the bending element from the connection point as a flexible extension to the wing tip towards softer, ie more flexible and easier connectable continues, so that can distinguish between an "arm area" and a "hand area", which have different properties and differ in the movement kinematics and in their flow dynamic behavior insofar as the hand area in the up and down each track elastically and viewed from the front, compared to the arm In the interaction with the fluid, for example, a superimposed bending vibration or, in the impact cycle, a wave motion occurs without the need for additional actuator technology, and the flow behavior at the tip is improved in particular by the S-stroke in an arrangement as a tail, the tear behavior of the flow at the trailing edge. A soft wing tip is also shatterproof and can cause damage in the event of a collision on the outside.

In a further variant, the hand area can in turn be designed as a smaller bending blade or a drive device for this, which can be controlled separately, so that more complex movements, or targeted control functions and maneuvers can be realized in the interaction of arm and hand wing and the flow behavior incl. Randwirbelbildung active as controlled on a controllable winglet or be influenced.

Another important degree of freedom of movement can be achieved in that the wing can be wound elastically in the spanwise direction. This is especially important in the production of propulsion. In this context, it is helpful that in a preferred embodiment, the bending element itself is designed torsionally elastic. The torsion properties can be predetermined or adjusted by the material and constructional design of the bending section (s) and can be influenced to a certain extent by the structure stress, different tensile forces or also a variable internal pressure in the bending sections.

The torsion can be done passively on the one hand, z. B. by asymmetric action of external forces on the front and rear wing area, on the other hand, but also - for example, for controlling and navigating actively brought about. By means of a controllable actuator, the torsional stiffness of the wing can be changed in a simple manner and attenuation, amplification or active induction of a twisting of the wings can be achieved.

The Flügelverwindung can be actively controlled according to the invention in various ways. For example, the drive device according to the invention may comprise tension elements which run spirally in or around at least one bending section, at least in one section. Alternatively, at a distance from the bending element, two spaced-apart profiles can be diagonally braced with respect to their profile height and shorten the diagonal spacing when the cable is pulled, so that the profile elements are rotated relative to one another about the longitudinal axis of the actuator arm and the surface spanned by the profile elements is correspondingly twisted.

In another preferred embodiment, the transmission of a torsional force can be achieved by means of a flexible shaft.

On the other hand, it may be favorable in certain applications that two or more drive devices are present per wing, which are spaced apart and movably connected to profile elements which define the outer contour of the wing, wherein the support elements are individually controlled with respect to their vertical deflection can be. As a result, the front and rear bending element can be curved differently and thus the wing surface can be vertwistet in different ways. With two or more load-bearing bending elements even more complex kinematic processes can be realized - z. B. undulatory movements etc.

In a particularly advantageous manner, a combined bending and torsional movement can be achieved in that at least one bending section at least partially extends substantially helically from the drive end of the bending element to the end remote from the drive of the bending element.

It should also be mentioned that a combined lateral and elevator effect can be achieved in this way by means of a controllable lateral twisting of a bending impact wing according to the invention arranged in the stern region of a watercraft, the advantages of which are sufficiently known from bird flight.

An S-blow and possibly improved Abströmverhallten can also also in the profile direction, i. from the drive end to the output end, can be achieved by z. B. profile elements are equipped with a flexible trailing edge, which are arranged at the output side end of the wing. Flexible trailing edges are also suitable for z. B. in a manta ray-like construction with two triangular wings and a tail and a total construction spanning elastic skin - bionic flying wings - to allow a uniform continuous 3D deformation of the entire, in many ways curvilinear surface.

In a further advantageous embodiment, it is possible to provide a drive which can be connected with the drive-side end of at least one bending section in order to introduce into the bending section a drive component directed toward the end of the bending element facing away from the drive during operation.

The introduction of force for the axial displacement substantially along the longitudinal axis of the wedge of one or more bending sections, for. B. spars, in the root area can be done according to the invention in different ways, for example by means of appropriate lever constructions or other means of movement implementation or directly by means of linear drive: z. As linear motors, hydraulic, pneumatic functional elements, artificial muscles, etc., which may also act as a guiding or holding elements at the same time. Again, the prior art offers a variety of design options and ongoing developments that can be addressed here only as an example, but are included equally in the invention.

By way of example, an advantageous embodiment of the drive will be explained in more detail, in which the connection or force introduction via pull ropes, straps, belts or transmission belt, which are connected to a suitable actuator.

A favorable force introduction results in this case, in particular, when these tension elements engage in axial alignment or tangential as possible to the relevant bending section, wherein longitudinal displacement can be done by train in the distal or proximal direction or alternately in both directions. The connection to the bending section can, for. B. by means of suitable joining techniques form, material and / or non-positively realized. On the other hand, similar to biological objects bones and tendons are connected to each other, the tension elements spring the respective spar as a bending section laterally or in axial extension, z. B. in the form of flexible fibers, which can then suitably bundled, braided, woven, glued and / or if necessary also be surrounded with a protective cover. About traction cables, the movement forces space and weight saving can be transmitted over long distances and z. B. on rollers, guide channels, Bowden cables, etc. are directed in the desired direction, so that the associated actuator can be arranged almost anywhere, for example in the fuselage or in the wing itself and the rest of space is not blocked by the mechanical transmission elements. At the same time, maximum mobility of the overall construction can be ensured. In a further analogy to biology, the fibers can of course also be connected to the type of fascia with an artificial muscle element whose actuator principle z. B. based on length or volume change.

In addition to their adjustment function, the force-transmitting elements can be used advantageously for fastening a wing, for example, on a carrier or fuselage segment.

In particular, the drive may have at least one reversible force transmission element which connects at least two bending sections on the drive side. This embodiment comprises z. B. that at least one spar is attached as an example of a bending section with a loop-shaped tension band, which is connected at both ends or as a circumferential loop with a motor element for longitudinal displacement of the spar and in the drive-side base region of the bending element to a suitable receptacle or the fuselage contour is guided - preferably in a slide, a wheel or a multi-membered roller bearings - so that the train of the loop-shaped drawstring in one or the other direction of the attachment point of the spar z. B. is moved tangentially along the outer contour of the support structure.

Since transverse forces also occur with every tensile and compressive load and corresponding bending movement, a suitable measure is provided according to the invention which prevents the bars or straps from becoming detached from the wing body / profile body.

This can be achieved according to the invention in that at least one shape stabilizer is provided which limits the maximum distance between two bending sections at at least one point of the bending element.

When the actuator force is applied, the pressure rod curves convexly outward, while the tension belt is tightened, ie pulled into the straight line. The task to obtain the distance between the bending sections and thus the profile height distribution of the wing in the predetermined shape can be solved in various ways. This can be z. B. by a formed in the outer contour region or outside resting skin, which is held together in a suitable manner by external or internal clasp elements, circumferential contour bands, special leadership pockets on or in the profile body, an attachment to profile ribs or other spacers done which connect the spars directly or indirectly, without hindering the relative longitudinal displacement of the spars to each other.

In particular, connecting means may be provided which each hold two locations of the bending sections independent of the deformation of the bending element at the same distance from each other.

It is helpful to know that between the bending sections under normal load actually only tensile forces must be transmitted, which accommodates the lightweight construction. So it is z. B. possible to surround spars with a simple 3D braid, or such einulaminieren in the bending sections, which contains a number of transverse fibers / weft threads in the space. By an appropriate number and suitable arrangement of the connecting elements also undesirable local deformation, a so-called "buckling" or in extreme cases, the breakage of the pressure rod prevented and the power flow can be directed within the structure so that shear forces are avoided, the bending rod in his Inside is loaded only on pressure and, accordingly, can be kept slim, which in addition to the lightweight construction also benefits the structural elasticity.

Furthermore, according to a further embodiment of the flexible impact vane, the latter can advantageously have a flexible outer casing in which the at least one bending element and at least one shaping element connected to the bending element and defining the flow profile of the bending impact vane are arranged.

Alternatively, a plurality of spaced-apart profile bodies may be provided, which are arranged substantially along a bending section. In this way, the profile body arranged on the bending section form the skeleton, which defines the flow profile of the bending impact vane.

Particularly advantageously, the profile body can simultaneously represent the shape stabilizers of the drive device. In this way, the profile body not only define the flow profile of the bending blade, but at the same time ensure that the distance between bending sections is limited.

In this context, it should be explicitly stated that the wing or profile body according to the invention or parts thereof can be constructed in different ways and with different materials, for example in an open skeleton construction with partial, one-sided or double-sided skin or outer covering, as a hollow body or solid body, which, for example, consist of a rubber-like material, elastomer, of an elastic foam, etc., or may be structured in its interior in a suitable manner. In this direction, the prior art continuously provides new possibilities. In this context, z. As the 3D weaving, knitting, gluing and joining techniques, gradient and composite materials, laminates and composite materials, multi-component injection molding process, etc. mentioned, which allow a wealth of different design variants, the example only with a few examples / embodiments can be addressed.

In a generally preferred skeleton construction in the art, three-dimensional deformation is facilitated if the wings are constructed so that all the structural elements are movable and elastically interconnected in the joints. For this purpose, the profile ribs may also be wholly or partially embedded in an elastomer or consist of such.

A preferred arrangement that allows a great flexibility at the same time good shape retention consists z. Example, in that the carrier element, a torsion-elastic profile element or a series of tread ribs are mounted laterally tiltable in a predetermined angular range, which are preferably aligned in the flow direction and preferably fixed on both sides movable to the spars. In this case, fastening of the profile ribs on the carrier element may also have two or more degrees of freedom, so that the profile ribs, e.g. tilted laterally and are also rotatably mounted about the central axis of the support element over a predetermined angular range. This facilitates a twisting of the wing or reduces the torsional stress of the spars. It is also advantageous that the movably suspended ribs can be fan-shaped spread without force or merged with their free ends, and so the virtually no resistance is opposed to the longitudinal changes associated with the 3D deformation of the wing surface, especially in the area of the wing trailing edge skeleton side.

Of course, it is advantageous, in particular in the case of a skeleton construction, if the construction is partially or completely over-stretched or stretched over by an elastically stretchable outer shell, for example a covering with a kind of mesh, a membrane or generally skin, which connects the parts in a planar manner and elastically couples , so that virtually no further bracing elements are needed. An elastic skin effectively provides for a "coordinated" behavior of the moving parts, and with changing geometries for constantly flowing contour transitions. Of course, it also fulfills a flow-dynamic function and not least a decorative with a variety of design options as a sensor or other functional surface, advertising media, etc.

It should also be noted that the sensors corresponding in each movement chain and possibly also a control unit may be provided as a whole.

Similarly, the wing area of a tailed blade located in the tail area may also be altered by active or passive spreading or folding, which may be advantageous for example for trim or control. This degree of freedom can also be further expanded by the fact that the profile elements are freely pivotally suspended on the bending sections in the wing plane in the lateral direction, so that the wing surface can possibly also be completely or partially jalousie or bottle ship-like folded in the direction of the bar. By unlocking the shoulder joint or a corresponding storage of wing wing or an additional joint z. B. in the root area of the spars, it is possible, if necessary, to apply the wing to the hull, for example, to facilitate transport, push the construction through a narrow pressure lock or "launch" in the arrow, and then unfold the wings. Further advantageous folding, folding and rolling mechanisms will be explained later with reference to the figures.

Thus, the various individual elements interact optimally with their different degrees of freedom, they can, for. B. be held together by springs or rubber-like elastomers, the latter may be formed, for example, as a circulating belt. This can also serve to set the desired Pflampepfeilung or change it.

A resilient coupling of the structural elements can be achieved in the simplest way by forming a suitable skin structure or coating with an elastic network or an elastically extensible membrane.

The profile ribs can in turn be designed differently according to the respective application requirements. The palette ranges from solid to thin clasps from full to hollow. You can z. B. inflatable, as a balloon, buoyancy, tank or otherwise payload carriers may be formed and possibly also offer for attachment or integration of sensors or other functional elements. For example, profile-forming surface elements can also be designed as electronic circuit boards, thus being used in a multifunctional manner. Also, the profile elements may themselves be designed according to the type of drive device according to the invention, whereby their profile can be actively varied and adjusted.

The ability to fill profile chambers or otherwise suitably designed voids in the wing construction with different media, gases, liquids, foams or solid particles (lead o. Ä.), Etc., which differ in their density, compressibility and other properties in addition to the mentioned trimming the weight or static up or down and the balancing of the structure for setting or active control of mechanical properties, stiffness, elasticity, restoring forces, etc. are used. It is also advantageous that the chambers can also be subjected to variable pressure individually or in suitable composite systems, for which purpose suitable system components (filler neck, valves, hoses, etc.) can be integrated in a simple manner. Through the use of pressurized chambers or membrane structures massive structural elements can be saved and a high strength can be achieved with low weight. In addition, z. B. in underwater wings by emptying ballast chambers and the transport weight in air can be reduced.

A further advantageous embodiment includes that the bending sections of the bending element can be filled with a medium and stiffened by variable internal pressure or adapted in a simple manner for different power conditions and / or application requirements. Due to the pressure conditions in the interior of a bending section, its bending behavior, ie its rigidity, can thus be influenced. By influencing the rigidity of the bent portions or portions of a bending portion in the area which bends, the bent shape of this bending portion can be manipulated specifically. In this way, even complex bends with different radii of curvature can be achieved. The rigidity of the bending section can be achieved both passively by design measures, such as thickness distribution, profiling, gradients or sections with material gradations. Furthermore, one can change the stiffness actively, in sections or over the entire length of the bending section, and control by changing physical parameters affecting the stiffness, such as pressure or temperature. Thus, a plurality of pressure chambers can be arranged along the longitudinal axes in the interior of a bending section, which can be acted upon individually or coupled with a variable pressure.

For completeness, it should be mentioned again that the spaces between the structural elements in the wings used differently (payload, etc.) and / or pressure variable with a special fluid or simply filled with the surrounding medium, which in addition to the other aspects mentioned u. a. also the optical or acoustic transparency further improved.

In a further advantageous embodiment variant, it is provided that wing parts or the structure are configured as a whole like a membrane and are designed so that they are inflated by the back pressure (air, water, etc.).

Another alternative is to make wing parts or the structure as a whole of elastomers, wherein z. B. different material thicknesses and / or material combinations with different properties: density, tensile and bending properties, moduli, Shore hardness, etc. can be used to build and differentiate the structures of the invention and the desired features. Such a basic structure with integrated Duck- and bending elements, tendons and "collagen" fibers, film hinges, cavities, filling elements and differentiated skin structures can be in large parts or in whole z. B. are produced in multi-component injection molding, it is conceivable to make the wing structure in a broader sense, also structured matrix body in which other mechanical elements, prefabricated components or other functional groups such. B. certain electronic modules, sensors, etc. embedded, for example, with encapsulated or can be added later. The o. G. Options for pressure-variable chamber filling with different media as well as payload recording are of course retained in this integrated or embedded design.

In another embodiment form variable ribs are provided as a profile element whose profile curvature can be adjusted in the direction of flow by means of an actuator. These can - to give just one example - similar to those described above Double wing on one side be equipped with a continuous spar or clasp element that connects lying in the flow direction in front of the wing spar profile nose with the underlying profile end, and by Aktuierung, ie axial displacement of corresponding sub-elements on the opposite side profile relative to each other in the desired manner up or to be bent down. By means of the variable profile curvature, the buoyancy or propulsion effects of the wing can be selectively influenced or control functions can be realized. In addition, there are also many other implementation options, which equally affects the matching adjustment.

In a preferred embodiment of the watercraft according to the invention, at least two bending impact wings can be arranged opposite one another on a hull. Alternatively, the opposing Bielaglagflügel also, with the omission of the trunk, are directly connected to their wing roots. In this way, you get a watercraft, which is complex maneuverable by appropriate control of the impact of the individual bending blades in the water.

In a further advantageous embodiment of the watercraft, at least one bending section of the one bending impact vane can be connected with the bending section of the other bending impact vane with each other in a motion-transmitting manner. This can be with respect to the fixation of a spar for attachment to a separate carrier or fuselage segment in an embodiment with z. B. two opposing flapping wings and a spar of the one wing connected to the counterpart of the opposite wing, for example, be formed as a continuous flexible spar, the two other spars of the opposite sides, for example, by a common adjusting symmetric or by means of separate adjusting possibly asymmetrical can be moved in their longitudinal direction. In this case, the hull segment in size, shape and structure can be freely designed or completely eliminated, resulting in different design options u. a. also result for flying wings.

Finally, in a further advantageous embodiment of the watercraft according to the invention, at least one bending section of the one bending impact vane and at least one bending section of the other bending impact vane can be connected to the same drive. In this way, the path length of the longitudinal adjustment and the associated unilateral stretching or compression of the contour, a skin or an internal material is reduced and distributed evenly on both sides and the symmetry of the movement can be improved. For this purpose, both spars of a wing are slidably mounted in the base region and preferably moved mechanically coupled by a common actuator.

This can be in an embodiment of the invention z. B. be realized in such a way that the support member is held with a drawstring on the fuselage, which is connected at both ends or as a circulating drawstring with a motorized element for longitudinal displacement and in the base region of the support member forms a tangent to the fuselage segment tangentially loop around the Runs fuselage and - there is preferably guided in a slideway, a wheel or a roller bearing to minimize friction - the two bars of the support element on opposite sides of the loop - are fixed so that the train of the band in one or other direction, the two spars are moved in opposite directions tangentially along the outer contour of the support structure.

By guiding the drawstring around the hull - especially in the form of an annularly closed loop and the saddle-like support surface results in a high tensile and pressure stability and robustness against shocks and other mechanical shocks. In addition, the assembly and disassembly of the wing is facilitated. Alternatively, the leadership of the spars and actuators can of course also be done on the inside of the outer contour or an inner skeleton.

The drive devices according to the invention can also be used for a variety of other applications. It can be used in actively driven or passively flowed flow bodies, for example in flow dynamic resistance bodies, flow bodies, Strömungsleitkörpern, transverse or drive body, as a stabilizer, wings, sails, kites, etc., the aforementioned applications can be used to from to energy to extract a flow.

In the following, the invention will be explained by way of example with reference to the accompanying drawings. The different features can be combined independently or omitted, as already explained above in the individual advantageous embodiments.

Fig. 1 a bis e

das Grundprinzip der erfindungsgemäßen Antriebsvorrichtung mit einer ersten Aus- führungsform eines Biegeelementes;

Fig. 2

eine weitere Ausführungsform der erfindungsgemäßen Antriebsvorrichtung; sofern in dieser Anmeldung vom Verbindungselement gesprochen wird, ist damit er Bie- geabschnitt gemeint, in welchem vom Antrieb eine Kraft in das Biegeelement ein- gebracht wird;

Fig. 3 a,b,c

einen Schnitt durch einen elastischen Flügel- bzw. Profilkörper mit Führungsta- schen 6 sowie zwei Beispiele für unterschiedliche Ausführungen der Materialvertei- lung mit Kammern 5b zur Gewichtseinsparung und Formmaterial 5a zur Erzielung bestimmter mechanischer, strömungsdynamischer etc. Eigenschaften, als Möglich- keit zur druckvariablen Befüllung mit unterschiedlichen Medien, als Nutzraum etc;

Fig. 4

eine Frontansicht: Doppelflügel von vorn in verschiedenen Flügelauslenkungen/ Schlagphasen

• a) einzeln dargestellt
• b) ortsfest - zeigt zwischen den Strukturelementen bestehenden Freiraum 7, der als Designraum z. B, für die Gestaltung eines Rumpfsegmentes zur Verfügung steht;

Fig. 5

eine Ausbildung einer wellenförmigen Flügelkontur unter äußerer Krafteinwirkung 10 bei nach oben ausgelenktem Flügel (z. B. am Ende eines Aufschlages) -

• a) "anatomisch"
• b) schematisch;

Fig. 6

Ausführungsbeispiele für verschiedene vorteilhafte Befestigungsmöglichkeiten ei- nes erfindungsgemäßen Biegeschlagflügels an einem konvexen - vorzugsweise el- liptischem Rumpfquerschnitt mittels einer geschlossenen Zugbandschlaufe 14;

Fig 7

ein Ausführungsbeispiel für Nurflügler mit zwei Biegeschlagflügeln (Typ "Adler- Rochen") in zwei Ansichten: Biegeelement 1 dorsal (rückenseitig) durchgehend, ventral (bauchseitig) zweigeteilt und aktuiert, Rumpf ist als breiteres Profilelement ausgebildet, Die Schwanzaufnahme 18 kann ggf. auch als Düse für einen Jetan- trieb ausgelegt sein, welche vorzugsweise schwenkbar gelagert ist - für Schubvek- torsteuerung, die Profilelemente 16 sind in diesem Fall vorzugsweise als gräten- ähnliche Profilspangen ausgebildet, können vorteilhafterweise gemäß Anspruch 17 und 18 verstellbar sein - beispielsweise in Anlehnung an das in Anspruch 6 be- schriebenen Prinzip - natürlich entsprechend adaptiert;

Fig. 8

eine Frontal- und Dorsalansicht einer anderen Ausführungsform mit eingezeichne- ten Aktuatoren 20 und Antriebsrädern 15 und einem beweglichen Heckflügel/ Schwanz 21;

Fig. 9 a-e

ein Beispiel für einen Nurflügler mit elliptischem Rumpfquerschnitt 17 und drei biegsamen Flächenelementen 21, 4 in horizontaler Anordnung, der hervorragende Manövriereigenschaften insbesondere auch in der vertikalen Ebene hat - Loopings etc auf engstem Raum, Manta-ähnliche Anmutung im Habitus und kinematischen Verhalten;

Fig. 10

eine schematische Veranschaulichung der in Querrichtung divergierenden Bewe- gungstendenzen mit dem Grundprinzip: Kraftansatz am äußeren Ende 8 des Flü- gelholmes und das Buckeln vom Biegeelement 4 und dem aus seiner Ursprungsla- ge verschobenen Zugseils 3, welches durch eine Überlast entstehen kann wenn keine Profilrippen 16 vorhanden sind;

Fig. 11

eine Variante einer Flügelaufhängung mittels einer Zugschlaufe als Kraftübertra- gungselement 14. Das Antriebsrad 15 spannt über die Gegenlager 23 die Zug- schlaufe 14 und liegt innerhalb des Biegeelementes bzw. Trägerverbundes 1;

Fig. 12

eine weitere Variante einer Flügelaufhängung mittels einer Zugschlaufe 14, bei der das Antriebsrad 15 von einem Ausleger gehalten wird, der um einen proximalen Lagerpunkt aktiv oder passiv schwenkbar ist;

Fig. 13

eine weitere Variante einer Flügelaufhängung mittels einer Zugschlaufe 14, bei welcher die Antriebsvorrichtung seitlich ausfahrbar gestaltet ist, d. h. in seiner Spannweitenrichtung gegenüber einem Körper 17 verschoben und auch wieder eingefahren werden kann. Dabei spannt das Antriebsrad 15 über die Gegenlager 23 die Zugschlaufe 14 und wird über den Aktuator 20 gemeinsam mit den anderen Elementen der Antriebsvorrichtung 30 verschoben, wobei zugleich eine hier nicht dargestellte Längenkompensation der Zugbänder 14 durchgeführt wird;

Fig. 14

ein Beispiel für eine Ausführungsform bei welcher das Biegeelement von einer zug- festen Struktur 3, beispielsweise einem 3D Gewirk, umhüllt ist, welche quer zur Hauptachse verlaufende Faserelemente aufweist, welche ein Auseinanderweichen der die Holme verhindern und zugleich zur Befestigung von Profilrippen 16 dienen. Dabei sind die Biegeabschnitte 4 in spezielle Führungstaschen der zugfesten Struktur eingeschoben;

Fig. 15

ein Beispiel für einen Klappmechanismus mit Drehpunkten 24 im Holm, um die der äußere Flügelabschnitt quer zur Flügelfläche geklappt werden kann, und Verbin- dungsmitteln 26 welche ein Arretierung in der Arbeitsstellung ermöglichen;

Fig. 16

ein Beispiel für eine zusammenklappbare Flügelkonstruktion, die auch eine Verän- derung der Flügelpfeilung gestattet. Drehpunkt 24 im Holm um den Flügel klappen zu können und Drehpunkt 25 in den Profilen um diese klappen zu können und der Drehpunkt A 1 der Profile gegenüber dem Holm (siehe auch Fig. 19);

Fig. 17

ein Beispiel für einen Biegeschlagflügel mit einem Vogelflügel-ähnlichen Armskelett welches Gelenke aufweist und einen Faltmechanismus verkörpert, mit dem eine Längenveränderung des Flügel in Spannweitenrichtung bei gleichzeitiger Variation der Flügelfläche erreicht bzw. der Flügel auch zusammengefaltet werden kann. Drehpunkte 24 im Holm um den Flügel klappbar bzw. aktiv oder passiv veränderbar zu gestalten und somit eine Flächenänderung;

Fig. 18

einrollbare Flügel;

Fig. 19

ein an der Wurzel um die Achse A2 tordierbares Biegeelement 1 mit Profilelemen- ten 5 in unterschiedlichen Ausführungsformen beispielhaft als Hohlkörpern 5b, wel- che gegebenenfalls mit unterschiedlichen Medien druckvariabel befüllt werden können, zusätzlichen Versteifungsrippen 16 und Formmaterial 5a;

Fig. 20

eine Skizze eines Biegeelementes 1 mit Profilelementen 5 welche in den Achsen A2 und A1 gegenüber dem Trägerverbund 29 drehbar gelagert sind und so eine 3D Verformung des Flügel erleichtern bzw. ermöglichen;

Fig. 21

eine serielle Anordnung von mehreren Flügelpaaren 40, 40' an einem gemeinsa- men Rumpf 17, welche gemeinsam z. B. eine undulatorische Bewegung ausführen können, dabei in energiesparender Weise jeweils das Nachstromfeld des Vorläu- ferpaares nutzen können;

Fig. 22

einseitig befestigte Biegeschlagflügel 40, welche z. B. ein Objekt antreiben oder stabilisieren bzw. ein Medium bewegen (Propulsor) oder leiten können, oder auch von der Strömung bewegt werden können, z.B. zur Energiegewinnung;

Fig. 23

ein Flügelelement 40, welches mittels Aktuatoren 20 bezüglich einer anderen Kon- struktionseinheit bzw. Struktur ein- und ausgefahren werden kann, beispielsweise bei einem Schiff als Stabilisator eingesetzt werden kann;

Fig. 24

ein Beispiel für eine sternförmige Anordnung von mehreren Flügeln (2x3) um einen Rumpf 17 welche hin und her schlagen oder in zwei hintereinander gestaffelten Ebenen an Naben befestigt sind und als Rotoren gegenläufig gedreht werden;

Fig. 25

ein Beispiel für eine einseitig angeströmte Doppelflügelkonstruktion: Kite, Strö- mungsanker etc. mit dem Biegeabschnitt 4 und dem zugseitig angreifenden Biege- abschnitt 3, Profilrippen 16 und einer Sehnenscheide 27;

Fig. 26

eine weitere Ausführungsform eines Biegeelementes und

Fig. 27

eine weitere Ausführungsform eines Biegeelementes, mit welchem Biege- und Tor- sionsbewegungen erzeugbar sind.

Show it:

Fig. 1 a to e

the basic principle of the drive device according to the invention with a first embodiment of a bending element;

Fig. 2

a further embodiment of the drive device according to the invention; If in this application the connection element is used, then it is meant to mean the bending section in which the drive introduces a force into the bending element;

Fig. 3 a, b, c

a section through an elastic wing or profile body with guide pockets 6 and two examples of different embodiments of the material distribution with chambers 5b for weight saving and mold material 5a to achieve certain mechanical, fluid dynamic etc. properties, as a possibility for pressure variable filling with different media, as usable space etc;

Fig. 4

a front view: double wing from the front in different Flügelauslenkungen / beat phases

• a) shown individually
• b) stationary - shows between the structural elements existing space 7, the design space z. B, is available for the design of a fuselage segment;

Fig. 5

a formation of a wave-shaped wing contour under the external action of force 10 with the wing deflected upwards (eg at the end of an impact) -

• a) "anatomical"
• b) schematically;

Fig. 6

Exemplary embodiments of various advantageous fastening possibilities of a bending impact wing according to the invention on a convex-preferably elliptical fuselage cross-section by means of a closed drawstring loop 14;

Fig. 7

an embodiment for flying wings with two Biegeschlagflügeln (type "eagle rays") in two views: bending element 1 dorsal (back) continuous, ventral (abdomen) divided into two parts and actuated, fuselage is designed as a wider profile element, the tail receptacle 18 may also as For nozzle control, the profile elements 16 are preferably formed in this case as a bone-like profile clips, advantageously according to claim 17 and 18 may be adjustable - for example, based on the described in claim 6 principle - of course adapted accordingly;

Fig. 8

a frontal and dorsal view of another embodiment with subscribed actuators 20 and drive wheels 15 and a movable rear wing / tail 21;

Fig. 9 ae

an example of a flying wing with elliptical fuselage cross-section 17 and three flexible surface elements 21, 4 in a horizontal arrangement, which has excellent maneuverability, especially in the vertical plane - loops etc in a confined space, manta-like appearance in habitus and kinematic behavior;

Fig. 10

a schematic illustration of the transversely diverging movement tendencies with the basic principle: force approach to the outer end 8 of the wing Holmes and buckling of the bending element 4 and the displaced from its original position pull rope 3, which can be caused by overload if no profile ribs 16th available;

Fig. 11

a variant of a wing suspension by means of a pull loop as a force transmission element 14. The drive wheel 15 spans the drawstring 14 via the abutment 23 and lies within the bending element or carrier assembly 1;

Fig. 12

a further variant of a wing suspension by means of a pull loop 14, in which the drive wheel 15 is held by a cantilever which is active or passive pivotable about a proximal bearing point;

Fig. 13

a further variant of a wing suspension by means of a pull loop 14, wherein the drive device is designed to be laterally extendable, ie moved in its spanwise direction relative to a body 17 and can be retracted again. In this case, the drive wheel 15 spans the tension loop 14 via the abutment 23 and is displaced via the actuator 20 together with the other elements of the drive device 30, at the same time a length compensation of the tension straps 14, not shown here, being performed;

Fig. 14

an example of an embodiment in which the bending element of a tensile structure 3, for example, a 3D knitted fabric is wrapped, which has transversely to the main axis extending fiber elements which prevent divergence of the spars and at the same time serve to secure profile ribs 16. The bending sections 4 are inserted into special guide pockets of the tensile structure;

Fig. 15

an example of a folding mechanism with pivot points 24 in the spar around which the outer wing portion can be folded transversely to the wing surface, and connecting means 26 which allow a locking in the working position;

Fig. 16

an example of a collapsible wing construction, which also allows a change of Flügelpfeilung. Fulcrum 24 in the spar around the wing to be able to fold and pivot 25 in the profiles to this can fold and the pivot point A 1 of the profiles relative to the spar (see also Fig. 19 );

Fig. 17

an example of a bending blade with a bird's wing-like arm skeleton which has joints and a folding mechanism, with which a change in length of the wings in the spanwise direction with simultaneous variation the wing area reached or the wing can also be folded. Pivot points 24 in the spar around the wing hinged or actively or passively changeable to make and thus a change in area;

Fig. 18

roll-up wings;

Fig. 19

a bending element 1 with profiled elements 5 that can be twisted at the root about the axis A2 in different embodiments by way of example as hollow bodies 5b, which can optionally be filled with variable pressure media, additional reinforcing ribs 16 and molding material 5a;

Fig. 20

a sketch of a bending element 1 with profile elements 5 which are rotatably mounted in the axes A2 and A1 relative to the carrier assembly 29 and thus facilitate or enable 3D deformation of the wing;

Fig. 21

a serial arrangement of a plurality of wing pairs 40, 40 'on a common hull 17, which together for. B. can perform an undulatorische movement, while in an energy-saving manner each can use the Nachstromfeld the Vorläu- ferpaares;

Fig. 22

one-sided fixed bending blade 40, which z. B. drive or stabilize an object or move a medium (Propulsor) or can conduct, or can be moved by the flow, for example, to generate energy;

Fig. 23

a wing element 40, which can be extended and retracted by means of actuators 20 with respect to another construction unit or structure, for example, can be used as a stabilizer in a ship;

Fig. 24

an example of a star-shaped arrangement of several wings (2x3) around a fuselage 17 which swing back and forth or are mounted on hubs in two successive staggered planes and are rotated in opposite directions as rotors;

Fig. 25

an example of a double-wing construction flowed in on one side: kite, flow anchor, etc. with the bending section 4 and the bending section 3 acting on the tension side, profile ribs 16 and a tendon sheath 27;

Fig. 26

a further embodiment of a bending element and

Fig. 27

a further embodiment of a bending element, with which bending and Torsions movements can be generated.

In FIG. 1 is the basic principle of the drive device 30 according to the invention for a bending blade 40 shown. The drive device 30 is configured on one side, the drive side I with a drive 15 connectable.

The drive device 30 comprises a substantially formed in the form of a wedge bending element 1 with two bending sections 3, 4, the drive side by a distance d are spaced from each other. On the drive side, the distance is defined by bearing elements 2, which may be, for example, a receptacle, guide, a sliding bearing or a sleeve. The distance α of the bending sections 3, 4 from each other decreases in the direction away from the drive, ie in the direction of the longitudinal axis L of the wedge, which extends from its base in the direction of the tip. In the region of the end facing away from the drive II of the bending element 1, in FIG. 1 the wedge tip 8, the bending sections 3, 4 are coupled force-transmitting. For example, we can the bending sections 3, 4 positively, positively and / or materially connected to each other. However, they can also be coupled in a force-transmitting manner via intermediate elements, as long as the wedge shape is given with the flanks of the bending sections 3, 4 tapering away in the direction away from the drive.

According to the invention, the bending sections 3, 4 are held so as to be movable relative to one another on the drive side essentially along the longitudinal axis L of the wedge. The bending element 1 is capable of being transferred to a different curvature in the thickness direction of the bending impact wing, depending on the relative position of the bending sections on the side of the drive. In FIG. 1 corresponds to the thickness direction of the bending blade of the straight line, which runs through the two bearings 2.

In FIG. 1 the bearings 2 are shown as non-tilt bearings, although a rotation of the bending elements 3, 4 about its longitudinal axis and an axial displacement of the bending sections 3, 4 may allow, but prevents tilting of the bending sections 3, 4 relative to the bearing 2. In this way, it is ensured that a pressure acting on the tip 8 of the wedge is reacted with a force component transverse to the longitudinal axis of a bending section 3, 4 into a curvature of the corresponding bending section 3, 4.

In the FIGS. 1a to 1d is the bending section 4, which numbers a tensile and compressive forces transmitted bending element, such as a push rod or spar, fixed in its storage 2. D. h., The bending section 4 is held firmly and immovably in the storage 2. The bending section 3, which forms the wedge-shaped bending element 1 together with the bending section 4, is in FIG. 1 shown as purely tensile element, such as a pull rope or a tension belt. In the following, reference numeral 3 denotes a purely tensile forces transmitting part and reference numeral 4 a tensile and compressive forces transmitting part.

If you like, in FIG. 1b is shown, the bending sections 3, 4 moves on the side of the drive 15 relative to each other substantially along the longitudinal axis L of the wedge, the bending element 1 according to the invention performs a curvature. The curvature takes place in the plane which span the longitudinal axis of the bending sections 3 and 4 and takes place in the direction in which forces, in Fig. 1b the tensile forces of the bending section 3 act on the bending section 4. In this case, the deflection of the bending section 4, based on the in Fig. 1a shown starting position, the greater the further the bending portion 4 extends away from the drive side. In FIG. 1b the relative movement is achieved by pulling on the tensile bending section 3 by the drive 15 (in FIG FIG. 1b schematically represented by an arrow). In this way, by the bending section 3 tensile forces at the top 8 of the bending element 1 on the in FIG. 1b rod-shaped bending section 4 shown transmitted. The tensile forces act on the tip of the bending section 4 with a force component transverse to the longitudinal axis of the bending section 4, whereby the wedge tip 8 of the bending element 1 is deflected in the bending plane and the bending element 1 in the in FIG. 1b shown curvature is transferred.

The transition from the FIG. 1a to FIG. 1b in relative movement of the drive-side bending sections 3, 4 is shown schematically in the Figure 1d summarized. The bending sections 3, 4 shown as solid lines show the initial state of the FIG. 1 a. The dashed lines shown bending sections 3 ', 4' show the curved state of FIG. 1b after relative movement by drive-side displacement of the tensile bending section 3 on the drive side substantially along the longitudinal axis L of the wedge.

Alternatively, as in Figure 1e shown, the tensile bending section 3 may be fixed in its bearing 2. In Figure 1e is the tension and compression resistant bending section 4 along its longitudinal axis held in the storage 2 axially displaceable, as indicated by an arrow. In Figure 1e the non-tilting bearing 2 is a sleeve whose inner cross-section substantially corresponds to the outer cross-section of the held bending section 4. In this way, an axial relative displacement of sleeve 2 and bending section 4 is ensured without the bending section 4 can be tilted relative to the bearing sleeve 2. The pushing out of the bending section 4 away from the drive side results in tensile forces being applied to the wedge tip 8 in an analogous manner via the tensile bending section 3, which is fixed in its bearing 2 FIG. 1b be exercised and one with Fig. 13 Comparable curvature of the bending element 1 can be achieved.

Of course it is also possible, the movements of Figures 1b and 1e to combine and drive side simultaneously pull the tensile bending section 3 and exert pressure forces on the pressure-resistant bending section 4 by axial displacement in the direction away from the drive.

An alternative embodiment is in Figure 1c shown. In this, the bending element 1 substantially corresponds to the bending element of FIG. 1a , but additionally has a further tensile bending section 3. The drive-side bending sections 3, 4 are spaced from each other and according to the embodiment of the Figure 1c essentially on a line. In this way, when the tensile bending sections 3 are moved on the drive side by the drive 15 substantially along the longitudinal axis L of the wedge relative to the pressure-resistant bending section 4, a bilateral curvature of the bending element can be achieved. For example, if you pull on the in Figure 1c shown left bending section 3, one of the FIG. 1b carried out corresponding bending, wherein the right bending portion 3 entrained and pulled axially in its storage away from the drive. Would you mind, what in Figure 1c is not shown, drive side pull on the right bending portion 3, the bending element 1 would bend in the opposite direction, which the mirror image of Figure 1c would correspond. In this way it is possible to bend the bending element back and forth on both sides in one plane.

In FIG. 2 an alternative embodiment of the drive device 30 according to the invention for a bending blade 40 is shown. As well as in all subsequent descriptions of the figures is used for parts or elements which correspond to one of the preceding figures, the same reference numerals.

The embodiment of the FIG. 2 corresponds substantially to the embodiment of the FIG. 1a However, wherein the tensile bending section 3 in FIG. 2 is replaced by a tensile and compression resistant bending section 4. The two movable pressure rods as bending sections 4 clamp the bending element 1, which is essentially in the form of a wedge. In their bearings 2 on the drive side both bending sections 4 are held tilt-proof. Optionally, one or both may be moved relative to each other by a drive substantially along the longitudinal axis L of the wedge.

If, as in FIG. 2 is shown on the right bending portion 4 from the drive 15 compressive forces are transmitted so that it is pushed out in the bearing 2 axially away from the drive, while the left bending portion 4 is fixed in its bearing 2, the bending element 1 bends, as in FIG. 2 is shown.

If, on the other hand, tensile forces were transferred to the right bending section 4, so that this bending section would be pulled axially substantially in the direction of the drive on the drive side, while once again the left bending section was firmly clamped, the direction of curvature would be reversed, ie. H. the bending tip 8 is deflected clockwise.

In this way can be in the in FIG. 2 illustrated embodiment with a bending element 1, which has only two tensile and compression-resistant bending sections 4, a visible on two sides bending of the bending element 1 reach.

In this case, one bending section 4 can be fixed on the drive side, while the other bending section is held axially displaceable in its bearing 2, ie that it can be displaced in and counter to the direction substantially corresponding to the longitudinal axis L of the wedge. Alternatively, both bending sections 4 may be held on the drive side in tilt-proof bearings 2. In this case, the bending movement is achieved in that the two drive-side bending sections are either alternately tensile or compressive or simultaneously, but oppositely, ie, the one bending section 4 is tension loaded and the other bending section 4 is pressure-loaded simultaneously. The simultaneous, but opposite power transmission has the advantage that larger forces can be transmitted to the top 8 of the flexure 1.

An embodiment in which both bending sections 4 on the drive side is axially displaceably held in non-tiltable bearings 2, allows the bending element 1 to be displaced in the direction of the end facing away from the drive, ie extended, without the bending element 1 bending. By a rectified and simultaneous displacement of the bending elements 4 of Fig. 2 Thus, the bending element 1 can be displaced relative to the drive or the base on which the drive device is arranged.

It is also possible to generate a relative movement by means of a bending section 4 fixed in a bearing 2. This can be achieved by changing the length of the bending section from its support to the point at which the bending section is force-transmittingly coupled to another bending section. For example, the length of a tensile and compression-resistant bending section 4, which is constructed telescopically, can be changed. Also, the length of a tensile bending section 3 are changed, for example, if you build the bending section contractile in the manner of a muscle.

In FIG. 3 an exemplary embodiment of a bending blade according to the invention 40 is shown, which comprises a drive device according to the in FIG. 2 has shown embodiment. For the sake of clarity, is in FIG. 3 the drive 15 is not shown. In FIG. 3a is the bending blade 40 shown in perspective. The bending blade 40 has a span direction S, a chord direction B and a height H. The drive-side ends I of the bending sections 4 are arranged in the region of the wing root. The extending from the drive side I bending sections 4 of the bending element 1 extend in the in the FIG. 3 shown embodiment substantially along the spanwise direction S of the bending impact wing 40th

The wing itself has a wing body 5, which consists of a plastic material. Thus, the wing body 5 defines in the FIG. 3 the flow profile of the bending blade 40, wherein the shaped body is the shaping element 5 of the bending blade 40.

As in the FIGS. 3b and 3c is shown, the wing body 5 may for example consist of a molding material 5a, such as foam or an elastomer, which Has cavities 5b. The bending sections 4 of the bending element 1 are connected to the outer shell of the molding 5 in FIG. 3 connected, in which in the region of the outer shell of the molded body 5 pockets 6 are provided, in which the bending sections 4 can be arranged.

The bending movement of the drive device 30, d. H. the curvature of the bending sections 4 in the region of the wedge-shaped bending element 1 from the drive-side bending sections 4 to the tip 8 can be transmitted to the elastic shaped body. In this way, a bending impact can realistically be adjusted with structurally simple means by the bending movement of the bending element 1 flowing, the bending movement following contour transitions of the shaping element 5 triggers.

As in Figure 3c is shown, the molded body 5 may have a downstream elastic trailing edge 22, which optimizes the flow dynamic behavior and reduces turbulence in the region of the downstream trailing edge. In FIG. 3 the flow direction is indicated by arrows. When in cross-section substantially elliptical shaped shaped body 5 is the inflow-side edge of the blunt, round end and the downstream edge of the end with an acute angle.

FIG. 4 shows a particular embodiment of a watercraft according to the invention, in which a bending blade 40 according to the invention is used as drive and / or control members. The watercraft of the FIG. 4 comprises two bending blades according to the invention 40a and 40b, which are arranged opposite to each other and directly connected to each other at their wing roots. At the watercraft the FIG. 4 is the bending portion 4 'of a bending blade 40a with the bending portion 4' of the other bending blade 40b movably connected. In the in FIG. 4 In the embodiment shown, a continuous bending section 4 'forms in each case a bending section of the one bending impact wing 40 a and the bending impact wing 40 b. Otherwise, the drive device essentially corresponds to the in FIG. 2 illustrated embodiment. The other bending sections 4 of the flexible blades 40a and 40b are connected at their drive-side ends to transmit motion, each with a drive 15. By the drive, during the operation of the watercraft, a drive component oriented substantially in the direction of the longitudinal axis of the wedge-shaped bending element 1 can be introduced into the bending section. That is, the driving side ends of the bending sections 4 are connected to the respective drive 15 substantially in the direction of the longitudinal axis of the wedge back and forth movable. The movements of the two drives 15 are synchronized so that the bending sections 4 at the same time both outwardly expressed (upper sketch of FIG. 4a ) or contracted inwards (lower sketch of FIG. 4a ) become. In this way, a symmetrical bending of the two bending elements 1 can be achieved and the watercraft 50 of the FIG. 4 operate as a flying wing.

Alternatively, the drive-side sections of the bending sections 4, instead of being coupled in each case with its own drive, can also be connected to a common drive.

In Fig. 5 the arm region 13 is shown bent with an inventive longitudinal curvature actively bent upward. The base is fixed between the supports 9 with the corresponding sliding guide 2. The position of the connection point 8 of the two spars is determined by the ratio of the effective, ie from the support 9 free length of push rod 1 and tension belt 3, acts against the forces acting from outside 10 as another fixed point or virtual support. "The lateral action the outer forces 10 can only reinforce the bulge in the arm region 13. The soft flexible tip 11, on the other hand, has no second fixed point The wing tip 11 is bent downward by the lateral force 10 over the entire hand region 12 compared to the relaxed state 11 ' ,

This results in a wave-shaped bending impact movement, which can be realized with the invention according to the distal force approach, axial guidance of the beam base (claim 1) and a simple additional measure, an elastically trailing hand in a simple manner, the flow behavior and for an "organic" appearance in the motion kinematics provides.

Fig. 6 shows exemplary embodiments of various advantageous fastening possibilities of a bending impact wing according to the invention on a convex-preferably elliptical fuselage cross section by means of a closed drawstring loop 14. Fig. 6a shows a one-sided attachment, ie only on a spar and Fig. 6b shows a two-sided attachment, ie on both spars. The advantage here is: a simple, robust, reliable attachment with tangential / axial, so optimal force into the structure, a good dimensional stability in all motion situations and load cases, a large-scale edition - no thin axles, which is crash-proof, shock-resistant and always form-fitting.

The spars are guided over the attachment point of the band. At the end extended in the proximal direction, an abutment is provided for support against the hull contour, which ensures a secure guidance with lateral force on a wing. Fig. 6 c shows an advantageous wheel drive. By entanglement of the loop 14 by an adjustment 15 - in the detail drawings simple or double - for traction improvement - shown - actuator is decoupled in a simple way of large external forces. The latter are picked up by the large loop, can not compress the wheel, engage there tangentially in - almost - one point, ie approximately in the same axis position, the wheel can not tilt, whereby the axle load on the adjusting is minimized. Fig. 6 d shows equally advantageous alternatives with a perforated belt with good lateral guidance, in the z. B. can engage a gear. Fig. 6e and 6f show that the drawstring loop 14 may be at least partially formed as a toothed belt, on which a matching gear 15 or more - preferably coupled - coupling not shown - attack adjusting wheels 15. The variant e) requires less space, leaves more space in the fuselage, and allows the distribution of forces lower axle loads and stress of individual teeth or timing belt sections.

In a further advantageous embodiment, the in Fig. 25 is shown schematically, the bending element 1 can also be designed to be on only one side against flow, ie it is brought opposite a flowing medium in an angle. In this case, the bending portion 4 may be with the skin contour 19 on the pressure-receiving side of the construction and the bending portion 3 on the tension-receiving side. In the case of a kite-like structure, in the case of a part of the kite, the bending section 4 and the balance (the holding network) would be the bending section 3. This bending section 3 would then extend from the point of attack 8 and / or the trailing edge of the wing over structural elements into the middle one Be led area where necessary and enter into the mentioned below sheath 27. Such a structure would be able to be held by a return, a rope and be actuated by other ropes. A one-sided train in the sense of a steering kite thus leads to a start on one side and a drop on the other and thus to a rotation. To change the buoyancy, the link can also be used to adjust the trailing edge. The tension elements can run in an advantageous embodiment obliquely over the wing, so that they additionally cause a Vertwistung the wing at a change in length. Due to the new design, the control cables are close to each other and could, to minimize resistance, be partially guided together in profile-shaped tendon sheaths 27 and fanned out at the lower end for control function again. This would also lead to a better control, since the changed flow of the ropes, which is dependent on the different voltage is thus reduced

Such a device can be used, for example, as an anchor, shaving board, surf kite or kite.

In Fig. 26 a further advantageous embodiment of a drive device 30 according to the invention for a bending blade 40 is shown. In this case, the bending element 1 is designed substantially in the form of a pyramid-shaped wedge with a square, here square base. For this purpose, the bending element 1 has four bending sections 4a to 4d which are spaced apart on the drive side and whose distance from one another in the direction of the drive (in FIG Fig. 26 not shown) away.

The bending sections 4a to 4d represent the edges of the pyramidal wedge, which extends from the pyramid base on the drive side to the pyramid tip 8 in the region of the end facing away from the drive of the bending element 1, the pyramid tip 8.

The drive-side ends of the bending sections 4a to 4d can by a drive 15 (in Fig. 26 not shown) pressure or tensile load. The advantage of this embodiment is that in each case two bending sections form a bending element 1, as shown in FIG Fig. 2 is shown. D. h., By corresponding relative movement of the drive-side bending sections, for example, the bending sections 4 a and 4 c, the bending element 1 in the plane, which is spanned by the longitudinal axes of the bending sections 4 a and 4 c, are curved. Characterized in that further bending sections 4b and 4d are provided, which can transmit a force to the tip 8 of the bending element 1, which has a pressure component perpendicular to this plane, it is with the bending element 1 of in Fig. 26 shown embodiment also possible to herauszukrümmen the bending element 1 from the bending plane defined by the bending sections 4a and 4c. In this way, the bending element of the Fig. 26 in principle, be curved in all the bending planes, which through the longitudinal axes of two of the bending sections 4a to 4d are defined, in which the corresponding bending sections are displaced on the drive side relative to each other. Thus, the tip 8 of the bending element 1 can be reciprocated in multiple directions and revolve in mixing movements or describe a total of a concave curved surface.

The control of the drive-side sections of the bending sections 4a to 4d is preferably carried out so that the respective diagonally opposite sections 4a and 4c or 4b and 4d are controlled as V-carrier or actuators coupled. In this way one achieves the greatest possible base distance of the side of the drive spaced apart bending sections, whereby the greatest possible force can be applied, since the wedge tip 8 of the respective V-carrier forms the largest possible angle.

Even if this is in Fig. 26 is not shown, it is not necessary to form the individual bending sections 4a to 4d the same length. Also, the base area of the pyramid defined by the drive-side portions of the bending portions 4a to 4d need not be square, but may take any quadrangular shape. It is possible in principle to use any number of bending sections and to connect to a pyramid-shaped wedge.

Furthermore, it is also possible that in Fig. 26 two diagonally opposite bending sections arranged, for example, the sections 4a and 4c or the sections 4b and 4d, as purely tensile bending sections, such as traction cables are formed. The possible bending of the bending beam 1 are not affected.

Fig. 27 shows a further embodiment of the bending element 1, which from the basic principle of the embodiment of Fig. 26 equivalent. Deviating from the Fig. 26 has the bending element 1 of Fig. 27 However, three drive side spaced-apart bending sections 4a to 4c, which are formed as pressure rods. Even with this configuration of three bending portions 4a to 4c forming a substantially tetrahedral wedge, it is possible to make the tip 8 of the bending element 1 like the tip 8 of the bending element 1 of the embodiment of FIGS Fig. 26 to move.

Furthermore, the bending element 1 differs from the Fig. 27 from the bending element of Fig. 26 in that the bending sections are substantially helical from the drive-side end of the bending element to the end remote from the drive of the bending element extend. By this helical configuration, it is possible that combined bending and torsional movements can be achieved. Of course, it is also possible to design helical only one or only selected bending sections of a bending element in order to achieve targeted movement patterns of a bending movement superimposed by a torsional movement.

Another embodiment is to arrange any number of drive devices in any spatial orientation to each other. Several drive devices may be arranged for example in a plane about a common center axis, whereby z. B. a bell-shaped movement is possible. Also, a plurality of drive device may be radially arranged in space around a common center. This could imitate the shape of a sea urchin.

The drive device or the wing can be rigidly attached to a base element, for. B. held a hull. However, it is also possible to keep the Antriebsvorichtung movable, for example by attachment to a rotating, pivoting, hinged or other movable base element. In this way, the drive device can be adjusted independently of its operation relative to the body to which it is attached.

Incidentally, the pyramidal wedge may be formed by any number of bending portions.

Legend of the reference numbers with synonyms

1

Carrier element, spar, bending element, bending rod, push rod

2

Pickup, storage, guide, plain bearings

3

Tension-resistant connecting element, pull rope, tension belt, tensioning element

4

Connecting element, which is tension and compression resistant, carrier element, spar, Biegeele- ment, bending rod, push rod

5

Profile body, wing body,

5a

Molding material (elastomer, foam, etc.)

5b

Chambers, cavities, utility room

6

Bag, sleeve, slide bearing, guide etc.

7

Free space, design space

8th

Connection point, point of application, transmission point, point

9

In stock

9 '

virtual support

10

external force

11

soft / flexible / elastic / pliable seats, elastic winglet

11 '

= 11 in the relaxed state

12

"Hand area"

13

"Arm portion"

14

Tieback, loop, power transmission element, drive component

15

Drive wheel, adjusting wheel, if necessary gear, drive

16

Tread ribs, profile clips, shape stabilizer

17

Hull, fuselage segment, carrier unit

18

Tail receiver, if necessary nozzle for thrust vector control

19

elastic contour band or skin contour, shape stabilizer

20

actuator

21

Rear wing, tail

22

elastic trailing edge

23

thrust bearing

24

Axle in the spar

25

Axis in profile

26

Holm connecting element

27

tendon sheath

28

boom

29

Carrier composite or carrier element with two bars

30

driving device

40, 40a, 40b

Flexible impact blade

50

Watercraft or aircraft

A1

Axis in the vertical direction on the wing surface

A2

Axis in the spanwise direction / expansion direction of the carrier composite

I

drive-side end of the bending element

II

remote from the drive end of the bending element

L

Longitudinal axis of the wedge-shaped bending element

d

Distance between bending sections

1. 1. Biegeschlagflügel, der als Trägerelement einen von der Flügelbasis zur Flügelspitze verlaufenden flexiblen Holm besitzt, welcher an seiner Basis kipp- und drehfest gelagert ist und im Übrigen als Biegeelement fungiert, und mittels eines schräg am Außenbereich des Biegeelmentes angreifendem Verbindungsgliedes, das am anderen Ende mit einem Aktuator verbunden ist, quer zur Flügelfläche gekrümmt werden kann, so dass ein Flügelausschlag in Form einer Biegeschwingung mit stetigen Konturverlauf realisiert wird.
2. 2. Biegeschlagflügel nach Punkt 1, bei dem der Flügel elastisch verwunden werden können.
3. 3. Biegeschlagflügel nach einem der Punkte 1 bis 2, bei dem der Holm torsionselastisch gestaltet ist.
4. 4. Biegeschlagflügel nach einem der Punkte 1 bis 3, bei dem das Verbindungsglied gleichermaßen als Biegeelement ausgebildet und an seiner Basis kipp- und drehfest in axialer Richtung verschiebbar gelagert ist.
5. 5. Biegeschlagflügel nach Punkt 4, der mit einem anderen Biegeschlagflügel verbunden ist, wobei ein Holm des einen Flügels mit dem Pendant des gegenüberliegenden Flügels als ein durchgehender flexibler Holm ausgebildet ist und die zwei anderen Holme der gegenüberliegenden Seiten durch ein gemeinsames Verstellglied symmetrisch oder mittels separater Verstellglieder ggf. auch asymmetrisch in ihrer Längsrichtung verschoben werden können.
6. 6. Biegeschlagflügel nach einem der Punkte 1 bis 5, bei welchem beide Holme als Verstellglied ausgebildet sind und an der Basis mechanisch gekoppelt vom Aktuator gegenläufig verstellt werden.
7. 7. Biegeschlagflügel nach einem oder mehreren der vorherigen Punkte, bei welchem das Trägerelemente nach dem Angriffspunkt des Verbindungselementes eine weiche, biegsame Spitze besitzt, die eine vom Arm abweichende Bewegung ausführen kann, z. B. bei äußerer Krafteinwirkung nachgiebig verformt werden kann, so dass bei einem Flügelschlag ein wellenförmiger Verlauf der Flügelkontur / S-Schlag / erzielt werden kann, bei Auftriebserzeugung auch als elastisches Winglet wirkt und zur Reduktion des Rand-Wirbelwiderstandes beiträgt.
8. 8. Biegeschlagflügel nach einem oder mehreren der vorherigen Punkte, dessen Körper aus einem Elastomer besteht, in welchem ggf. spezielle Taschen für Holm und/oder Verbindungselement vorgesehen sein können.
9. 9. Biegeschlagflügel nach einem oder mehreren der vorherigen Punkte, bei welchem der Flügelkörper in Skelettbauweise mit Profilrippen aufgebaut ist, die in Strömungsrichtung ausgerichtet sind.
10. 10. Biegeschlagflügel nach einem oder mehreren der vorherigen Punkte, welcher einen steuerbaren Aktuator zur Dämpfung, Verstärkung bzw. aktiven Herbeiführung einer Verwindung der Flügel aufweist.
11. 11. Biegeschlagflügel nach Punkt 10, bei dem der Aktuator zur aktiven Verwindung der Flügel über Zugelemente am Flügel angreift, welche zumindest in einem Abschnitt spiralförmig im oder um das Trägerelement verlaufen.
12. 12. Biegeschlagflügel nach Punkt 10, bei dem in einer vorbestimmten Distanz vom Trägerelement Zugelemente angeordnet sind, die zumindest zwei voneinander beabstandete Profile in Bezug auf deren Profilhöhe diagonal verspannen und bei Zugeinwirkung den Diagonalabstand verkürzen, so dass die Profilelemente relativ zueinander um die Längsachse des Trägerelementes verdreht und die von den Profilelementen aufgespannte Fläche entsprechend verwunden wird.
13. 13. Biegeschlagflügel nach Punkt 10, bei welchem zur Übertragung einer Torsionskraft eine flexible Welle vorhanden ist.
14. 14. Biegeschlagflügel nach einem der Punkte 1 bis 10, bei welchem pro Flügel zumindest zwei Trägerelemente vorhanden sind, die voneinander beabstandet sind und in Bezug auf ihre Auslenkung individuell angesteuert werden können, so dass die Flügelfläche auf unterschiedliche Weise vertwistet werden kann.
15. 15. Biegeschlagflügel nach einem der Punkte 1 bis 14, bei dem Profilelemente mit einer flexiblen Hinterkante ausgestattet sind.
16. 16. Biegeschlagflügel nach einem der Punkte 1 bis 15, bei welchem die Profilelemente in einem Flügelbereich verformbar gestaltet sind.
17. 17. Biegeschlagflügel nach einem der Punkte 1 bis 16, welcher zumindest ein steuerbares Aktuatorelement zur Formänderung von Profilelementen aufweist.
18. 18. Biegeschlagflügel nach einem oder mehreren der vorherigen Punkte, bei welchem das Rumpfsegment in zumindest einer Projektion einen in etwa elliptischen Querschnitt aufweist, in welchen die Holme des Trägerelements jeweils tangential einmünden bzw. diesem formschlüssig aufliegen, so dass sich im Formübergang von Stützstruktur und formvariablem Flächenelement ein stetiger Verlauf der Außenkontur ergibt.
19. 19. Biegeschlagflügel nach einem oder mehreren der vorherigen Punkte, bei einem der Holme des Trägerelementes ein schlaufenförmiges Zugband befestigt ist, das an beiden Enden oder als umlaufende Schlaufe mit einem motorischen Element zur Längsverschiebung des Holmes verbunden ist und im Basisbereich des Trägerelementes um die Rumpfkontur geführt ist - vorzugsweise in einer Gleitbahn, über ein Rad oder ein mehrgliedriges Rollenlager -, so dass beim Zug des schlaufenförmigen Zugbandes in die eine oder andere Richtung der Befestigungspunkt des Holmes tangential entlang der Außenkontur der Stützstruktur verschoben wird.
20. 20. Biegeschlagflügel nach einem oder mehreren der vorherigen Punkte, zumindest ein Trägerelement mit einem Zugband am Rumpf gehalten wird, welches an beiden Enden oder als umlaufendes Zugband mit einem motorischen Element zur Längsverschiebung verbunden ist und im Basisbereich des Trägerelementes eine dem Rumpfsegment beidseitig tangential anliegende Schlaufe bildet, die um den Rumpf verläuft und - dort vorzugsweise in einer Gleitbahn, über ein Rad oder ein Rollenlager geführt ist - wobei die beiden Holme des Trägerelementes an gegenüberliegenden Seiten der Schlaufe befestigt sind, so dass beim Zug des Bandes in die eine oder andere Richtung die beiden Holme in zueinander gegenläufiger Richtung tangential entlang der Außenkontur der Stützstruktur verschoben werden.
21. 21. Biegeschlagflügel nach einem oder mehreren der vorherigen Punkte, bei welchem eine motorische Einheit bzw. ein Verstellglied mehrere Verstellfunktionen gleichzeitig bedient.
22. 22. Biegeschlagflügel nach einem oder mehreren der vorherigen Punkte, welcher drei Flügel besitzet, von denen einer als rückwärtiges Schwanzsegment ausgebildet ist, sowie einer geeigneten Anzahl von Aktuatoren, die vorzugsweise im Rumpf angeordnet sind.
23. 23. Biegeschlagflügel nach einem oder mehreren der vorherigen Punkte, bei welchem zumindest die Flügel und das Schwanzsegment von einer elastisch dehnbaren Außenhaut umschlossen sind.
24. 24. Biegeschlagflügel nach einem oder mehreren der vorherigen Punkte, welcher einen Mittel zur Änderung seines aero- bzw. hydrostatischen Auftriebes aufweist.

Other embodiments of the present invention may be:

1. 1. Bending blade, which has a carrier element extending from the wing base to the wing tip flexible beam which is tilt-mounted and non-rotatably mounted on its base and acting otherwise as a bending element, and by means of an obliquely attacking on the outer region of the Biegeelmentes connecting member at the other end connected to an actuator, can be curved transversely to the wing surface, so that a sash in the form of a bending vibration is realized with a continuous contour.
2. 2. Bending blades according to item 1, in which the wings can be wound elastically.
3. 3. bending blade according to one of the items 1 to 2, in which the spar is designed torsionally elastic.
4. 4. Bending blade according to one of the items 1 to 3, in which the connecting member is equally formed as a bending element and tilt-mounted at its base and rotatably mounted in the axial direction slidably.
5. 5. Bending blade according to item 4, which is connected to another bending blade, wherein a spar of one wing with the counterpart of the opposite wing is formed as a continuous flexible spar and the two other spars of the opposite sides by a common adjusting symmetric or by means of separate Adjustment may possibly also be moved asymmetrically in their longitudinal direction.
6. 6. Bending blade according to one of the items 1 to 5, in which both bars are designed as adjusting and mechanically coupled to the base are adjusted in opposite directions by the actuator.
7. 7. bending blade according to one or more of the preceding points, in which the carrier elements after the point of the connecting element has a soft, flexible tip, which can perform a different movement from the arm, z. B. can be deformed yielding in external force, so that when a wing beat a wave-shaped course of the wing contour / S-beat / can be achieved in lift generation also acts as an elastic winglet and contributes to the reduction of the edge vortex resistance.
8. 8. Bending blade according to one or more of the preceding points, whose body consists of an elastomer, in which possibly special pockets for spar and / or connecting element can be provided.
9. 9. Bending blade according to one or more of the preceding points, wherein the wing body is constructed in skeleton construction with profile ribs, which are aligned in the flow direction.
10. 10. Bending blade according to one or more of the preceding points, which has a controllable actuator for damping, amplification or actively causing a twisting of the wings.
11. 11. Bending blade according to item 10, in which the actuator for active twisting of the wings engages via tension elements on the wing, which extend spirally in or around the carrier element at least in one section.
12. 12. Bending blades according to item 10, in which are arranged at a predetermined distance from the support element tension elements, the diagonally brace at least two spaced apart profiles with respect to their profile height and shortening the diagonal distance when pulling, so that the profile elements relative to each other about the longitudinal axis of the support element twisted and the surface spanned by the profile elements is correspondingly wound.
13. 13. bending blade according to item 10, wherein for transmitting a torsional force, a flexible shaft is present.
14. 14. Bending blade according to any one of items 1 to 10, wherein at least two carrier elements are present per wing, which are spaced apart and can be controlled individually with respect to their deflection, so that the wing surface can be vertwistet in different ways.
15. 15. Bending blades according to any one of items 1 to 14, are provided in the profile elements with a flexible trailing edge.
16. 16. Bending blade according to one of the items 1 to 15, wherein the profile elements are designed deformable in a wing area.
17. 17. Bending blade according to one of the items 1 to 16, which has at least one controllable actuator element for changing the shape of profile elements.
18. 18. Bending blade according to one or more of the preceding points, in which the fuselage segment in at least one projection has an approximately elliptical cross-section, in which the spars of the carrier element respectively open tangentially this form-fitting rest, so that there is a steady course of the outer contour in the shape transition of support structure and form-variable surface element.
19. 19. Bending blade according to one or more of the preceding points, in one of the spars of the support element a loop-shaped tension band is attached, which is connected at both ends or as a circumferential loop with a motor element for longitudinal displacement of the spar and guided in the base region of the support element to the fuselage contour is - preferably in a slideway, a wheel or a multi-membered roller bearing - so that the pull of the loop-shaped drawstring in one or the other direction of the attachment point of the spar is moved tangentially along the outer contour of the support structure.
20. 20. Bending blade according to one or more of the preceding points, at least one support element is held with a drawstring on the fuselage, which is connected at both ends or as a revolving drawstring with a motor element for longitudinal displacement and in the base region of the support member a tangent to the fuselage segment tangentially fitting loop forms, which runs around the hull and - there preferably in a slideway, is guided over a wheel or a roller bearing - wherein the two bars of the support element are secured to opposite sides of the loop, so that the train of the band in one or the other direction the two spars are displaced tangentially in mutually opposite directions along the outer contour of the support structure.
21. 21. Bending blade according to one or more of the previous points, in which a motor unit or an adjusting member serves several adjustment functions simultaneously.
22. 22. Bending blade according to one or more of the previous points, which has three wings, one of which is designed as a rear tail segment, and a suitable number of actuators, which are preferably arranged in the hull.
23. 23. Bending blade according to one or more of the preceding points, wherein at least the wings and the tail segment are enclosed by an elastically stretchable outer skin.
24. 24. Bending blade according to one or more of the preceding points, which has a means for changing its aero- or hydrostatic buoyancy.

Claims (17)

1. Drive device (30), in particular for a flexible impact blade (40), one side of which is designed so that it can be connected to a drive (15), with a flexible element (1) essentially in the shape of a wedge comprising at least two flexible portions (3, 4) extending away from the drive and spaced at a distance apart from one another on the side of the drive, their distance from one another becoming shorter in the direction remote from the drive, and which are coupled in a force transmitting arrangement in the region of the end of the flexible element (1) facing away from the drive, characterised in that the flexible portions (3, 4) are retained on the side of the drive so that they are able to move relative to one another essentially along the longitudinal axis of the wedge and the flexible element (1) is designed so that it can be transferred to a different curvature pointing in the thickness direction of the flexible impact blade as a function of the relative position of the flexible portions (3, 4) on the side of the drive.
2. Drive device (30) as claimed in claim 1, characterised in that a section of at least one flexible portion (3, 4) is retained on the drive-side end in a bearing (2) which is prevented prevents from tilting of the retained section.
3. Drive device (30) as claimed in claim 1 or 2, characterised in that the flexible element (1) is designed essentially in the form of a pyramid-shaped wedge and comprises at least three flexible portions (3, 4) spaced at a distance apart from one another on the drive side, their distance from one another becoming shorter in the direction remote from the drive.
4. Drive device (30) as claimed in one of the preceding claims, characterised in that the end of the flexible element (1) facing away from the drive (15) is extended in the direction remote from the drive in the form of a flexible extension (11).
5. Drive device (30) as claimed in one of the preceding claims, characterised in that at least one flexible portion (3, 4) extends from the drive-side end of the flexible element (1) to the end of the flexible element (1) facing away from the drive in an essentially helical shape in at least certain sections.
6. Drive device (30) as claimed in one of the preceding claims, characterised in that a drive (15) is provided which can be connected to the drive-side end of at least one flexible portion (3, 4) in a motion transmitting arrangement, by means of which a driving component directed
   towards the end of the flexible element facing away from the drive can be transmitted to the flexible portion (3, 4) during operation.
7. Drive device (30) as claimed in one of the preceding claims, characterised in that the drive (15) has at least one reversible force transmitting element (14, 16) which connects at least two flexible portions (3, 4) to one another on the drive side.
8. Drive device (30) as claimed in one of the preceding claims, characterised in that at least one shape stabiliser (16) is provided, which restricts the maximum distance of two flexible portions (3, 4) on at least one point of the flexible element (1).
9. Drive device (30) as claimed in one of the preceding claims, characterised in that connecting means (31) are provided, which respectively hold two points of the flexible portions (3, 4) at the same distance from one another irrespective of the deformation of the flexible element (1).
10. Flexible impact blade (40), characterised by at least one drive device (30) as claimed in one of claims 1 to 9 for changing the external contour of the flexible impact blade (40), and wherein the drive-side ends of the flexible portions (3, 4) are disposed in the region of the blade root.
11. Flexible impact blade (40) as claimed in claim 10, characterised in that the flexible impact blade (40) has a flexible outer skin in which the at least one flexible element (1) as well as at least one shape-imparting element (5) connected to the flexible element (1) and defining the flow profile of the flexible impact blade (40) are disposed.
12. Flexible impact blade (40) as claimed in claim 10 or 11, characterised in that a plurality of profiled bodies (16) spaced at a distance apart from one another are provided, which are disposed essentially along a flexible portion (3, 4).
13. Flexible impact blade (40) as claimed in claim 12, characterised in that the profiled bodies (16) simultaneously act as the shape stabilisers of the drive device (30).
14. Watercraft (50) with a drive and/or control element, characterised in that the drive and/or control element is a flexible impact blade (40) as claimed in one of claims 10 to 13.
15. Watercraft (50) as claimed in claim 14, characterised in that at least two flexible impact blades (40) as claimed in claims 10 to 13 are disposed lying opposite one another or on a hull (17).
16. Watercraft (50) as claimed in claim 15, characterised in that at least one flexible portion (3, 4) of one flexible impact blade (40) is connected to the flexible portion (3, 4) of the other flexible impact blade (40) in a mutual motion transmitting arrangement.
17. Watercraft (50) as claimed in claim 15 or 16, characterised in that at least one flexible portion (3, 4) of one flexible impact blade (40) and at least one flexible portion (3, 4) of the other flexible impact blade (40) are connected to the same drive (15).

Images