WO2018050145A1 - Flying or sliding element having a power supply unit - Google Patents

Abstract

The invention relates to a flying or sliding element (10) with an outer skin (12), comprising a front element (14, 190) and at least one sail (24, 50, 50', 199, 212, 214, 216, 236, 238), said front element (14, 190) and/or one or more additional elements (16, 18, 20, 22, 42, 194, 196, 197, 198) which is or are arranged transversely and/or longitudinally and/or at an incline, and/or a rear element (58) and/or at least one air chamber (60, 60a, 96, 98, 138, 142, 144, 182, 184, 186, 188, 192, 202, 204, 206, 208, 210, 218, 220, 222, 224, 230, 232), being formed completely by said outer skin (12) as an outer boundary, wherein the outer skin (12) is made to be self-sealed, and the device is designed to be usable for generating power.

Description

 Flying or sliding element with energy supply unit

description

The invention relates to a flying or sliding element, in particular a kite screen, as well as a power feed unit.

State of the art

Kitesurfing, also kiteboarding or stunt kite sailing, is a relatively young sport. When kitesurfing, the athlete stands on a board, which resembles a small surfboard or wakeboard, and is pulled over the water by a stunt kite - also called a windscreen or umbrella. The forward movement is thus comparable to surfing with wind propulsion. Worldwide, there are currently estimated by experts and industry about 500,000 people who operate this sport regularly. The number of kite surfers has increased rapidly in recent years. Compared to windsurfing, the equipment is cheaper and more compact. Apart from that, no other water sport allows such a wide variety of jumps and jumps

Tricks.

Kites are available in different designs, which also differ in attack surface and angle of the wind. Leashes can be used to steer the stunt kite so that the forces exerted on the athlete vary in direction and strength. The size of the screen is also dependent on the wind strength. The kites or kites are about linen or the like. Connected with the athlete and are controlled by this over the lines. The softkites or ram-air kites or mats look like paragliders and are especially suitable for use on land, for example when snowkiting. But there are also closed cell soft kites that can be used to surf the water. Their stability is achieved by the fact that the air can penetrate the leading edge when flying through air inlet valves, where it remains "stored" between two layers of cloth and can no longer escape, ie it has an inflated shape with the help of dynamic pressure Air through the profile openings in the interior of the structure, which has a top sail, a bottom sail and tread ribs.The disadvantage is that when hitting a water surface, the ingress of water can not be prevented long.

Tubekites have different than softkites several outer tubes with therein inflatable inner tubes (Tubes): a front tube (front tube), which gives the screen the shape and one or more cross tubes (struts), which are connected approximately at a 90 ° angle to the front tube and Tubekites can be used on the water A C-kite gets its name thanks to its C-shaped, so very curved shield shape, resulting in a smaller surface that can "catch" correspondingly less wind. He is one of the Tubekites and his front tube is square at both ends.

Bow kites are very similar to the C-kites in construction, however, the profile is much flatter and the front tube is not linear, but is curved towards the two ends, which led to the naming. In addition, the bow shield has "kite cords" with several points of attachment to the kite.The hybrid kites are a mix of C-kites and bow kites, which are like bow kites, where the front tube is stabilized by means of lashing lines at several attachment points. Shape kites are a further development of the bow kites, they are flown with 4-5 lines.

Known is a "sports steering kite" (DE 101 16 109 AI), which proposes a self-stable and weight-reduced construction, which has a carrier transverse to the direction of flight of a plastic batt, and that the carrier in or around a pressure point of a buoyant surface of fabric or foil between the front luff At the lateral ends of the lifting surface, at least two side members in the direction of flight are fastened from an aerodynamically shaped fabric or a foil profile. A disadvantage of the known flight or sliding elements is that the inner tubes often lose air and thus become unstable. The inner tubes are sensitive and unstable, a repair is complex and time-consuming. Soft kites run the risk of losing so much air when landing on the water, especially in waves, that a water start is no longer possible. In an emergency, these can no longer serve the kitesurfer as a liferaft.

Known are kite-like missiles, especially ites, from a ground-level

Base station or controlled by a vehicle. The kites are over

Ropes connected to the base station or the vehicle. Such kite systems are used, for example, for alternative energy production by wind power.

The document WO 2007/12265 A1 describes a wind energy system used for energy generation, which comprises at least one kite which can be controlled from the ground.

This kite is connected via two control cables to a base platform from which the kite is controlled. On the base platform there are also two winches on each of which one of the two control cables is wound over pulleys. The winches are each coupled to an electric motor which, on the one hand, operates the winches to extend or shorten the control cables for steering the kite. On the other hand, the wind energy, which is absorbed by the kite, on the control cables on the

Transmit winds, which in turn drive the electric motors, which then

Energy is gained.

DE 10 2004 018 835 AI discloses a watercraft with wind propulsion, in which at least one free-flying kite-like wind engagement element with an airfoil profile of exclusive, auxiliary or as an emergency drive is connected only via a pull cable to the vehicle body, wherein control means are provided, the a Windingriffselement having a wing profile with a substantially transverse to

Air flow of the wind directed velocity vector dynamically on a closed view of the vessel, but with respect to the air flow substantially vertically directed helical or sinusoidal trajectory lead, the different trajectories or a static flight condition by the control means depending on course, wind direction, Wind speed, gustiness and / or sea state are variable selectable. A disadvantage of the known energy supply units is that the kites of the respective vehicles must in each case set themselves into the correct position for wind attack by consuming control methods in order to obtain energy.

The object of the invention is therefore to provide a flying or sliding element which does not require any additional inner chambers located inside an outer skin and nevertheless allows sufficient stability for exercising the sport and makes available an energy supply unit, for example the use a kite in a simple way to generate energy.

Disclosure of the invention

A flying or sliding element, in particular a kite screen, is disclosed which has a self-sealing outer skin. The kite screen is inflated. The introduced air or a gas like helium flows directly into the outer skin. The outer skin forms one or more air chambers, which are formed entirely from the self-sealing outer skin. This training allows dimensional stability over a longer period. Depending on the positioning, the air chambers can have different sizes and also form very small structures. The outer skin has a sealing property, which is ensured in particular by a suitable material that allows the seal. In particular, this includes gumming, coatings, film-layer composites, structuring, chemical and / or heat treatment, formation and pretreatment of the fibers of fabrics, liners; Post-treatment, in particular by blowing or applying protective layers or sealing material, and the like. The sail surfaces may be formed from the material of the outer skin. The outer skin may be formed kinking, folding and rollable like flat pressure hoses. They have a low weight, are airtight and water-repellent, tear-resistant, UV-resistant, antifouling and saltwater resistant.

The air chambers may be formed as indentations or bulges. There may be only one air chamber or a plurality of separate air chambers may be formed. The outer skin may have an air pressure indicator and possibly a pressure relief valve. The air chambers can be inflated or inflated by means of a pump or be self-inflating. The air chambers can be filled with air, especially when starting and when flying. This is done by filling the dense skin over one or more valves that automatically open and close mechanically or electrically. The valves can be operated for example via a magnetic switch.

The flight or sliding element may be formed in a modular manner and be composed of several components as needed. This allows flexible size and shape design. For example, one or more segments or air chambers can be arranged on a base element. This creates a larger sliding surface. The arrangement and thus the size and design of the aircraft or gliding Elements can thereby by mounting or dismounting, exchange, extension and retraction, flaps, rollers or the like. to be changed. The modules each comprise at least one transverse body and / or a partial front body, and / or a sail. The segments, which can be attached to the basic elements, can be connectable, for example, with connecting elements such as quick couplings. These fasteners for air chambers, air chambers with segments or the like. or connectors for connecting air chambers such as hoses can be designed as quick-acting closures or valves and interchangeable. It is also possible to use quick couplings, plug-in terminals or push-in terminals. It can be used closure elements, which are also used as caps or plugs for hoses or air chambers. If they are designed as valves, they have access to the interior of the air chamber, for example the front body and / or the transverse body, which can serve for repair and cleaning purposes. For closing openings and leaks, a glue gun or the like. be used. The hoses may have a round or conical or elliptical cross section.

The self-sealing outer skin can be sewn and / or glued, welded, vulcanized, gummed or the like. be and have reinforcing or sealing elements. The material used for forming the outer skin or the material structure for the air chambers and the sail area as well as for areas of air chambers and sail surfaces can be designed differently. The self-sealing also takes place through the use of valves and the structure of the outer skin forming material in combination with each other, in particular rubberized or suitably coated hoses. It can be used materials comparable to pneumatic hoses, which are formed with valves and caps closable. They may be connected with connectors. The tubular fabric can be molded or sold by the meter.

The flight or sliding element may additionally inflatable structures such as rods formed of sealed material, slats or the like. or solid rods or slats, which are rigid or formed as telescopic structures. These structures can be pressed apart by inflation, in particular by aerating during takeoff and / or flying, and thus span and stabilize the surface of the flying and sliding element. When the air is released, the telescopic structures merge again or lie folded like a fold on each other. These inflatable structures can be hoses that can be made comparable to bicycle hoses. They can be fabric hoses and / or rubberized. These hoses can directly form the self-sealing outer skin and be associated with sail (s) or it can be connected to these the outer skin, so that it has the self-sealing effect. The hoses for the air chambers can be formed by plastic welding or sewing. They are inserted into the blank of the outer skin and are then in particular welded. The outer skin can also be produced in particular by weaving from threads provided with a sealant and then sealed in particular by vulcanization. Any necessary repair is done, for example, by patching. The hoses may be formed as a molding or pressure hoses or be designed according to a fire hose. If the hoses are available by the meter, sealing caps can be used. Various suitable materials can be combined to form a composite material which then forms the outer skin. Also suitable are nonwovens made of polyethylene, in particular PE-HD, wherein the nonwoven fabric is formed from fibrillated, very close to each other networks fine filaments. Area-bonded sheet-like nonwoven fabrics with a stiffer character or point-bonded products with a textile, softer character can be used. The self-sealing outer skin can be formed independently and then or the like with the sail or sails by sewing, gluing, welding, straps and pockets, hanging, clips, insertion into a Keever or the like. be connected or incorporated into the one or more sails, so that the sail is taut. The flying or sliding element may have devices similar to a bellows, which act by inflation as the above-mentioned inflatable structures.

In the air body of the flying or sliding element sealing means can be introduced, which can then be discharged again. As a result, the outer skin can be sealed off or, if necessary, repaired. The sealing means may also be disposed inactive on the outer skin within the air bodies and be activated by suitable measures, in particular mechanically, electrically or by air pressure. Another type of sealing can be done in particular by a stopper, which can be pressed if necessary in the resulting hole. The good seal can be achieved by heating, vulcanization, gluing, vapor deposition or chemical reactions. For the formation of the outer skin with fibers specially adapted thereto sealant can be used. As a material for the outer skin bionically formed fabrics and fabrics or influenced by the bionics panels can be used. The outer skin may have contours, such as, for example, small protrusions or hedgehogs, which are in particular round-shaped, or have honeycomb-like configurations, or have structures patterned after a spider's web, which increases one Effect strength. The outer shape of the flying or sliding element may be polygonal and have rounded corners.

The outer skin may be formed as a functional fabric, the like on a base material such as a fabric such as natural silk, rayon, viscose or the like. based. This distinguishes the formation of the invention from the prior art base materials used as film laminates or the like. are formed. The skin formed according to the invention can additionally be treated, so that the existing conditions with regard to the use for the flying and sliding element are optimized. The treatment can also be done after assembly in addition or subsequently. The coating of the outer skin may be in particular a glued rubber film. Certain fibers, such as polyester yarns, can be coated before weaving and then processed. These fibers can by special measures such as heating or the like. ensure the tightness. These functions can be activated in particular by these measures after production. The outer skin may be formed, for example rubberized on its inner surface. It can be done inflating the mold. The outer skin may also be a treated Gewebestoff. The impregnated or coated side of the inflatable outer skin and an inner surface may in particular be connected to the outer skin by heating. The tightness can alternatively be generated by gluing. The inner surface thus acts as a sealing component for the air chambers. The tube diameter of the air chambers formed from the outer skin can vary as needed in coordination of the aerodynamics and the intended or required air pressure and the stiffness for the flying or sliding element. Due to the design according to the invention, even the smallest diameters, e.g. 5 mm or larger diameter ausfuhrbar. The sails and the segments may be connected to the air chambers through connecting devices such as connectors, quick couplings, clippers, clips, tabs and pockets, suspension devices, insertion into a welt, closures, hooks, clips, hook-and-loop fasteners or other suitable connection means.

The use of such materials is also suitable for energy production for vehicles, aircraft, ships and the like. Either the said means of locomotion itself have such a surface acting as solar cells or the surface comprises flexible solar cells or the kite connected with such vehicles serves the additional energy production. The use can also take place on buildings, in particular on roofs, walls, etc. connected therewith, in particular also sun protection devices such as awnings, tents, canopies, truck roofs, etc. Subsequent sealing, for example, of leaks, but also seams and the like. or for repair can occur by inflation and introduction of sealant which flows through the air flow to and into the leaks and settles there, so that a connection of carrier material and sealant is formed and thereby sealing takes place. It can also be used repair pins. Furthermore, when repairing the repair site, additional processing such as heating may occur. Repair means may also comprise reinforcing fibers and similar to one

Putty be applied. Minor damage can also be caused by the

Gluing on a repair patch to be repaired. The seal can also be done with tools such as a glue gun.

For the flight and sliding element different valves, even in combination, can be arranged. It can valves are arranged, which are also used for repair purposes and can be removed and installed. The valves may also be as closure elements of air chambers and form an access to the interior of the air chambers, ie front and / or cross body. A first valve A may be formed as an inlet and outlet valve. A second valve B is an internal or internal valve that opens during filling and closes when pressure drops. The valves A and B may be designed as pressure relief valves and / or comprise pressure displays. The valves A and B thus replace the freely external connecting hoses of air chambers of the prior art. The valves may have caps and lids or quick-release closures. The lid can be unscrewed similar to a bottle screw cap with a thread formed. The covers of the valves and / or the valves may be designed to be removable and removable for cleaning and repair purposes of the air chambers. All attachments as well as the valves and caps can be interchangeable arranged. It can also be fixedly arranged support components, where then attachments can be attached. The abovementioned sealing means or repair means can also be introduced via further accesses, such as, for example, the valve openings and closure caps or valve seats. The valves in the air chambers in the formation of bulkheads in

Longitudinal or transverse alignment are arranged so that the air chamber parts are inflatable or the air from the valves can be discharged again.

In a transversely arranged in the flight or sliding air chamber, for example, a valve C is arranged. This valve C is designed as a pressure relief valve or possibly allows access into the air chamber and thus also serves cleaning or repair purposes. It may be adjacent or in addition to an on or inside valve D be ordered, which is automatically and / or operable from the outside. Valve D opens when filling and closes when the pressure drops. The valve D can also be designed as a pressure relief valve or pressure-dependent opening and closing and also allow access to the inside, for example for cleaning or repair purposes, or serve as an inlet or outlet valve. The valve can also be operated from the outside. The valves A, B, C and / or D are automatically or mechanically operated. They can also be operated electrically or electronically. The operation can be done from the outside. The valves can also be remotely controlled. The valves are suitable for use as connection couplings of the individual air chambers, for fastening and air outlets for quick connection and disconnection of the air outlets. The valves may be reversible designed for the passage of the air in the desired direction and / or closing or opening of passages. The valves can by plug connectors, bayonet, quick couplings or the like. be used for the connections of air and / or rods. The valves can be operated by turning, pushing or pulling and also fulfill the function of discharging or blowing out the air.

In the continuous outer skin transverse or longitudinal bulkhead may be incorporated in one embodiment of the invention, so that in case of air loss in one part of the flight or sliding element, the other parts are sufficiently sealed and not lose much stability. The bulkheads are made of lightweight fabric panels and can constrict the outer skin to which they are attached in order to achieve certain desired shape designs, but also serve as a dense partition. At or between the air chambers or the reinforcing elements sail surfaces are formed. The sail surfaces may be formed above a plurality of air chambers, so that above no back pressure arises, but also be performed by the air chambers and thus be designed as a bulkhead, through which the air chambers are divided into halves or half shells. Each half-shell or each part of the air chambers can be inflated or the air contained can be discharged. The targeted bulkheads also serve to deform an inflated round body. This can assume an oval shape by the introduction of a bulkhead, since it can be made flatter, in particular in the constriction than in the more remote area. This can result in aerodynamically different and better properties. In this case, kites and parachutes, and / or paragliders, and / or floats, and / or dinghies for military or recreational sports can be combined. Furthermore, a power generation in particular by air, or also by the incorporation of textiles, by application of foils as well as coatings, which act like solar cells, take place. This can provide the energy to inflate the air chambers and / or actuate the valves as well as to generate energy for other kite-related devices. When carrying a kite, for example, on ships, the air flow and the solar cell effect can provide energy. Operations such as the opening and closing of valves can on leashes, possibly live leashes, via magnetic switch or the like. or via a radio control. Controls can also be remotely controlled with a controller. In this case, a kite-screen or a similar kite-like gliding or flying object is disclosed, which can not win the energy alone by the wind power, but also by the formation of its outer skin by photovoltaic. The air chambers and the sail surfaces of the kite are formed from an outer skin, which have a solar cell effect. This solar cell effect results, for example, from the selection of a material which comprises solar cells or the application of films or coatings, lacquers or the like which act in a similar manner to solar cells or comprise solar cells.

When carrying and using such a trained kite, for example, on a ship thus not only the air flow of the wind, but also the solar line effect of energy can be used. Air or sliding body with air chambers can with air, compressed air, gas such as helium or the like. be filled. The outer skin of the kite-screen or the like can be through the training, in particular as a composite material or the application of paints, films, coatings, fumes or the like. have a solar cell effect of the surface, which formations may contain incorporated solar cells. In particular, solar cells in a very thin, flexible design can be formed, which are arranged areally on the outer skin of the kite. In particular, fiberglass compounds are suitable for this purpose, which are connected, for example, with graphite and sewn into a polymer matrix. It is also possible to use materials or composite materials with organic solar cells, so-called plastic solar cells. These solar cells are made of hydrocarbon compounds, ie plastics. Such compounds have electrically semiconductive properties. Here is a list of the advantages of the mentioned plastic solar cells:

• Low manufacturing costs due to cheap production technologies

• High current yields through thin film large area technologies for plastics • Higher flexibility, transparency and easy handling due to the mechanical properties of plastics

 • High environmental impact, as the plastics are carbon-based

• Adaptation to the solar spectrum through targeted polymer synthesis

The material for this type of solar cell is based on organic hydrocarbon compounds with a specific structure that gives the relevant materials the essential properties of semiconductors. Typical representatives of organic semiconductors are conjugated polymers and molecules, whereby also specially synthesized hybrid structures are used. The production takes place via Abdampfprozesse and then form multi-layer systems. The organic photovoltaic is suitable for use in the production of the energy supply unit according to the invention. The use of such trained substances is also suitable for energy production for vehicles, aircraft, ships and the like. Either the said means of locomotion themselves have such a surface acting as solar cells, or the surface comprises flexible solar cells, or the kite connected with such vehicles serves to generate additional energy. The use can also take place on buildings, in particular on roofs, walls and the like connected therewith, in particular also sun protection devices such as awnings; Tents, canopies, truck roofs, etc. The energy obtained is suitable for driving engines or aggregates, for operating control elements, for lighting, for generating electricity for a second electric circuit, or the like.

The energy gained is led via separate power lines to the respective consumers or a memory. It can be used so-called hybrid lines, which include both the function of the kite-lines as well as the functions of power management and other functions. The hybrid lines include the lines commonly used for kites and, in addition to their function as pull, hold and control lines, have additional units, such as, in particular, power, hydraulic, pneumatic lines; Antennas, lightning rods, etc. A hybrid line can thus have one or more additional functions. The structure and arrangement of the hybrid lines is variable and can be adapted to the respective requirements. The properties of the hybrid lines can complement each other and optimize each other's properties. The hybrid lines can be arranged in parallel or, for example, be formed spirally, so that they are stretchable according to the wind strength and direction. The hybrid leads can include all the required components, so no disturbing additional function carrier such as electricity, hydraulic, pneumatic lines or antennas, lightning rods and the like. must be arranged independently and installed. Thus, the handling of these hybrid lines and the controllability during extension and retraction of the kite is made possible in a simple manner.

The flight or sliding element according to the invention has the advantage that the special shape and stability can be maintained and maintained over the long term by the design without bladder and the resulting freedom of design and arrangement of the air chambers. For repair and assembly, no assembly work, such as retrieving individual air chambers from an envelope construction as in the current state of the art is more necessary. Due to the effect of the self-sealing outer skin and the elimination of additional inner chambers, the design of the air chambers and thus the structure of the flight and sliding element taking into account the aeronautical requirements such as aerodynamics, weight, etc. in various configurations is possible. The individual components of the sliding and flight element can be designed as a kit with sail surfaces and air chambers. The "air bags" or "bladder" used within the outer skin have been eliminated. The energy supply unit has the further advantage that not only a natural energy source can be used by a flight element such as a kite, namely the wind power, but also by the formation of the outer skin or surface of the kite solar energy. Therefore, the control of the correct position of the kite to the wind also no longer needs to be controlled and adjusted complicated, since a non-optimal use of wind power is not only compensated by the additional solar energy won, but is supplemented or additionally available.

Further advantages and advantageous embodiments of the invention can be taken in the following description of the figures, the drawings and the claims.

An exemplary embodiment of the solution according to the invention will be explained in more detail below with reference to the attached schematic drawings. It shows:

1 shows an oblique view of the flying or sliding element in an oblique view from below,

2 shows the flying or sliding element in a plan view, FIG. 3 shows schematically the starting material for the outer skin,

4 shows a section Bl of FIG. 2,

5 shows a section B2 a front and a transverse tube,

6 shows a section B3 through a flight or sliding element with a valve,

7 shows a section B4 through a flight or sliding element with another valve,

8 shows a section B5 with a sail,

9 shows a section B6 with air chamber and sail, FIG. 10 shows a section B7 through the outer skin,

1 1 shows a section B8 through the outer skin,

12 shows a sealing element,

13 shows a further sealing element,

14 shows a further sealing element, FIG. 15 shows a sealing element with a mandrel,

16 shows another sealing element with a mandrel, Fig. 17 shows a pad for sealing,

Fig. 18 illustrates a bulkhead in an air chamber,

19a shows a view of the flying or sliding element with a side element, FIG. 19b shows a projection of a sail area, FIG.

20a to 20r show embodiments of sails and air chambers and support elements,

21a to 21d illustrate embodiments of air chambers,

FIGS. 22a to 22e illustrate exemplary embodiments of an air inlet and outlet valve A.

 22a is an exploded view, FIGS. 22b and 22c show the valve in a sectional plane X and FIGS. 22d and e show a sectional plane Y,

Figs. 23a to 23i illustrate embodiments of a built-in valve B, Figs.

 23a shows an oblique view with the sectional planes XI and ZI, 23c shows a section through the sectional plane ZI, 23d shows a section through the sectional plane XI, FIG. 23e shows a section through the sectional plane ZI, FIG. 23f shows a section through the sectional plane 23g shows an oblique view with the sectional planes X2 and Z2, FIG. 23h shows a section through the sectional plane Z2, FIG. 23 shows a section through the sectional plane X2,

FIGS. 24a to 24e illustrate a simple open-close valve B. FIG. 24a shows an oblique view in the sectional planes X3 and Z3. 24b shows a section through the sectional plane X3, FIG. 24c shows a section through the sectional plane Z3, FIG. 24d according to FIG. 24b the opened valve B and FIG. 24 e the opened valve B according to FIG. 24c, FIG.

25 shows a connector or a quick coupling in a side view,

FIGS. 26a and 26b respectively show two air chambers in different positions in section from the side, FIGS. 27a to 27d show further details and exemplary embodiments of FIG. 1 in a plan view, FIG. 28 shows a plan view of a variable sail structure,

Figs. 29a to 29d show arrangements of air chambers and sail surfaces and

FIGS. 30a to 30c show different air chamber connection elements in an exploded view,

31 shows a cross section through a hybrid line,

Fig. 32 illustrates additional elements to a leash,

Fig. 33 illustrates a hybrid cable with additional media and

Fig. 34 shows a different configuration of the hybrid line.

1 shows a flying or sliding element 10. The flying or sliding element has an outer skin 12 which does not comprise any additional so-called "bladders" but is directly inflated or filled with air or compressed air by means of a single-pumping system is formed self-sealing, wherein the flying or sliding element 10 includes one or more

Front body 14, one or more parts formed, and one or more transverse body 18, 20, 22, 42. The transverse body 18, 20, 22, 42 serve as stiffening elements of a sail 24. The front body 14 may bulkhead 26, 28, 29 , 30, 32, whose seams on the outer skin 12 are visible in this representation. The transverse bodies 16, 18, 20, 22 each have connection tubes 34, 36, 38, 40, 42 to the front body 14. The connecting tubes 34, 38, 40, 44 are tight. The transverse bodies 18, 20, 22, 42 can be inflated during the flight, for example by opening or closing a rotary switch.

Fig. 2 shows the flight or sliding element 10 of FIG. 1 in a plan view. In this case, the fifth transverse body 42 is visible, which is connected via the fifth connecting hose 44 with the front body 14. In the figure, the sectional plane Bl is indicated, in which the Fig. 4 ff. Are shown. A first transverse body 16 is arranged on the first connecting hose 34. 16 draws the hidden in Fig. 1 cross body. The transverse body 16 has a self-sealing outer skin 12. The front 14 and the cross body 16 are each filled with air. This also applies to the other transverse body. FIG. 3 schematically illustrates the starting material 46 for the outer skin 12. The starting material 46 is air-tight and watertight.

Fig. 4 shows a section Bl of Fig. 2, in which the front body 14 is shown with the self-sealing outer skin 12. The front body 14 has a first valve 48 through which air can be introduced and discharged. The valve 48 is designed so that it prevents unwanted air leakage. It is an inlet or outlet valve 48, which may additionally be designed as a pressure relief valve and / or pressure gauge or may include a pressure relief valve. In this illustration, a sail 50 on the front body 14 and the cross member 20 is arranged. This sail can also be the sail 50 ', 24, 24', including individual sail segments.

5 shows a section B2 of a front 14 and a transverse body, each having a self-sealing outer skin 12. On the front body 14, a second valve 52 and the cross member, a third valve 54 is arranged. The second valve 52 is formed inside the front body 14 and opens automatically when filling the front body 14 with air and closes at pressure loss. The third valve 54 in the transverse body may be formed as a pressure relief valve, access to the inside for cleaning or repair purposes or as an inlet and outlet valve. Fig. 6 shows a section B3 through an air or sliding element 10 with a valve 48. In this case, the front body 14 and the transverse body are integrally formed and can serve as a base element and / or segment for the flight or sliding element 10, wherein valves , Transitions and accesses between the individual segments can lie or can be grown on the individual segment.

Fig. 7 shows a section B4 by a flight or sliding element 10 with another valve 56, which is formed on the inside and can be operated automatically and / or from the outside, opens during filling and closes at pressure loss within the system, and as Total pressure relief valve or access to the inside for cleaning and repair purposes or as an inlet and outlet valve is formed. Fig. 8 shows a section B5 with a sail 50, wherein the outer skin 12 is formed self-sealing. In this arrangement, the front body 14 is connected via the sail 50 with a rear body 58 and thus together form a nearly or completely closed contour. The sail 50 stretches when inflating the front body 14 and the rear body 58. The flight or sliding element 10 may be constructed from one or more material webs and have one or more air chambers, which are formed from the outer skin 12. Reinforcement elements such as rods, slats or the like, in particular inflatable elements, can be arranged for reinforcement. It can also be arranged telescopic parts that move apart by the inflation of the front 14 and the rear body 58 and stabilize the sail 50.

Fig. 9 shows a section B6 with front body 14, rear body 58 and sail 50, in the front 14 and rear body 58 form a nearly or completely closed outer contour. The sail 50 spans when inflating the body 14 and 58. The flight or sliding element 10 may be constructed from one or more material webs and having one or more air chambers, which are formed from the outer skin 12. Furthermore, this embodiment can have transverse bodies and / or air chambers 60. The air chambers 60 may have a round or elliptical or flattened conical cross section. Fig. 10 shows a section B7 through the outer skin 12, which is formed self-sealing. The front body 14 is inflated as much as possible in order to locate a possibly existing leak. Into the leak is pierced with a piercing tool 62 and it is introduced a sealant. Due to the internal pressure and the leakage behavior at the leak, the sealant is pressed against the leak area and through the leak. In the process, the sealant (bonded or by vulcanization) bonds to the outer skin 12 at the leak and closes it.

The sealant may comprise fibers or similar stabilizing constituents. It can be colored or neutral. A repair can also be made using or similar to a hot melt application. Fig. 1 1 illustrates a section B8 through the outer skin 12, wherein the leak 64 in this illustration is already sealed by the sealing means as described in Fig. 10. The repair can also be done by means of a PIN or by hot glue.

12 shows a sealing element 66 (PIN) with a visible tear-off edge 68. After inflating and locating the leak, the sealing element 66 is introduced into the leak. In this case, the sealing means may be formed as an adhesive and be applied in advance on the sealing member 66 or during insertion or removal of the sealing member 66th to wet this from the outside. It can also be arranged storage chambers, which provided by bursting the sealing member 66 with the adhesive. By completely inflating the front body 14, the sealing member 66 is completely brought into position, while the sealant connects to the sealing member 66 and the outer skin 12 at the leak and closes this.

Fig. 13 shows another sealing element 70 (PIN) in another embodiment

FIG. 14 illustrates another sealing element 72 (PIN) which also has a tear-off edge 68.

Fig. 15 shows a sealing member 74 (ΡΓΝ) with a mandrel 76 having an inner tear-off edge 78. The sealing element 74 has a tear-off edge 68. The sealing element 74 is pressed by means of a tool comparable to a blind rivet in the leak. The sealant combines with the outer skin and closes the leak.

FIG. 16 illustrates another sealing element 80 (PIN) with a mandrel 82 and an inner trailing edge 84.

Fig. 17 shows a pad 86 for sealing. The leak is glued to the pedestal 86. It can be designed in various shapes and sizes as well as colors.

FIG. 18 shows an embodiment with a bulkhead 247 which is arranged in the transverse body 20. The bulkhead 247 divides the transverse body 20 into an upper side as a half shell 248 and a lower side as a half shell 249. The upper side of the transverse body 20 is open through a connection opening 14 to the front body 12 and is thereby simultaneously ventilated. The bottom of the cross member 20 forms through the bulkhead 247 and the on or inside valve B with the connecting element for the air guide 148 via the front body 12 through the valve B externally controllable ventilation a separate air chamber.

19a illustrates a flying or sliding element 10 with transverse bodies 18, 20, 22 and a sail 50. The transverse bodies 18, 20, 22 can penetrate or intersect the sail 50 as required or be part of the sail 50 or from below of the sail 50 to above the sail 50 change. The sail 50 may also be a part of the transverse body 18, 20, 22 and longitudinal body. The flying or sliding element 10 may have at its outer ends in each case an angled side member 88, which serves for stability and allows a quieter flight. FIG. 19b shows the flying or gliding element 10 with an outer region W. Also in the outer region W, the air chamber 60 can penetrate or overhang the sail surface contour profile. The air chambers 60 that meet the requirements, may be part of the surface of the sail 50, 50 'and the inflow surface.

FIGS. 20a to 20r show embodiments of sails 50 and air chambers 60 which form a base element 92, wherein the air chambers 60 can have an amplification function. The gain function is carried out in particular by attachable air chambers, z. As shown in FIG. 20h, supporting elements such as slats or rods.

Figs. 20a to 20r show embodiments of sails, air chambers and support members, Fig. 20i showing an example of the sails and the air chamber, and Fig. 20j showing an example of sails and support members. A combination is also possible.

Fig. 20a shows a central part or basic element 92 of a flight and sliding element 10 with an air chamber 60 and with a sail 50, wherein both the sail 50 and the air chamber 60 can have a reinforcing function. FIG. 20b shows a segment 90 which can be attached to the middle part on the left. FIG. 20c shows an attachable segment 90 on the right, which is shown in mirror image to the illustration in FIG. 20b. FIG. 20 d shows a deviating embodiment of a segment 90 which can be attached to the left, with an edge 94, FIG. 20 e shows a segment 90 which can be attached to the right, which is formed in mirror image to FIG. 20 d. The left mountable segment 90 of FIG. 20f can be replaced by extension and retraction, flaps, rollers or the like. to be changed. Fig. 20g is another mountable segment 90 in mirror image to the representation of Fig. 20f. FIG. 20h shows an attachable segment 90, which is designed as an air chamber 60, which can also serve as a reinforcing element. The air chamber 60 has the shape of an elongated round body. In Fig. 20i an attachable segment 90 with a sail area 50 and a variable number of air chambers 60 is shown. FIG. 20j shows an attachable segment 90 for the trailing edge of the flight and gliding element 10. FIG. 20k shows a base element 92, which is able to fly on its own. For example, to the base member 92 of FIG. 20k, the mountable segment 90 may be disposed and include a sail surface 50 formed with and without support members. The support elements can reinforcements, slats, tubes or the like. be and be rigidly or mechanically, electrically or air-controlled retractable and retractable. As part of a basic element 92, the mountable segment 90 according to the Fig. 20j by extension and retraction, rolls, flaps or the like. be annoyed. FIG. 201 represents an independently flightable basic element 92 with an ner edge 94, to which the attachable segments 90 can be arranged from the figures 20f and 20g. FIG. 20m illustrates a basic element 92 according to FIG. 20a to which the attachable segments 90 from FIGS. 20b and 20c are arranged. It is also possible to arrange the mountable segment 90 from FIG. 20i, see FIG. Labels in parentheses. In addition, the segment 90 can still be arranged from the Fig. 20h.

Fig. 20k illustrates the base member 92 of Figs. 20n, 20o, 20p in combination with the segment 90 of Fig. 20i. Fig. 20o illustrates the base member 92 of Fig. 201 with the air chamber 60 of Fig. 20g and Figs. 20f combined. FIG. 20p illustrates a base member 92 having a front air chamber 96 and three transverse air chambers 60. FIG. 20q illustrates a base member 92 having air chambers 60 of FIG. 20h.

Fig. 20r shows a base member 92 with a sail 24, which is independently capable of flight. The base member 92 has a circumferential air chamber 98 of front 14 and rear body 58. There may be more segments and reinforcing elements can be arranged. It can be arranged cross body, which can form separate air chambers, in this illustration, no cross body are shown.

FIG. 21 a shows an air chamber 60 with an air inlet and outlet 100. A connection can be achieved with an aerodynamically formed extension 102. The air chamber 60 may be formed as a stiffening element or rigid element. The air chamber 60 may have support or partition walls or bulkheads, which may be elastic and allow for retraction or contraction and the formation of the shape and the Einfaiten.

21b shows a telescopic design of the air chamber 60 with the air inlet and outlet 100 and the connection 102. The telescopic function can take place in one or more stages. For this purpose, an extendable and retractable air chamber or a rod 104 is used.

Fig. 21c illustrates a retractable component. Shown is a sail surface 50 which is stretched between a foldable member 106 and a tie member 108. The connection element 108 may be a quick connection, clips, tabs or be designed as a guide and have the action of support elements. Support elements can reinforcements, slats, tubes or the like. be. The two elements 106 and 108 are by a rotation axis 1 10 against each other and folded out. 21d illustrates two air chambers 60, 60a. These air chambers 60, 60a have a support or partition wall 12, which may be elastic and thereby facilitate retrieval or contraction. The partitions 1 12 may have Verbindungsöffhungen 1 14 and / or valves. The basic shape tending toward the circle can be deliberately deformed by the use of one or more bulkheads and assume an oval shape. This is flatter in the constriction than in the more distant area.

FIGS. 22a to 22e show an inlet and outlet valve A. FIG. 22a shows the valve A in an exploded view. The valve A has a viewing window 16, an overpressure valve 118, a closure lid 120, a connection to an air chamber 122, a ball 124 resting against the stop, an air passage (inlet or outlet) 126 (also when using the ball 124 resting against the stop), a pressure indicator 128 and an air feed 134 for the pressure indicator and pressure relief valve. Fig. 22b illustrates the valve A in a sectional plane X. The pressure gauge 128 indicates the pressure, the pressure relief valve 1 18 is closed. The valve A further comprises a housing 130. The pressure gauge 128 includes pistons 132. An air supply 134 is formed for the pressure gauge 128 and the pressure relief valve 118. It is also conceivable arrangement, wherein the pressure gauge 128 and the pressure relief valve 1 18 are arranged in an air chamber and overpressure a flow channel is released or via the pressure gauge 128, a pressure relief valve 118 opens or that the pressure gauge 128 releases an outflow at overpressure.

FIG. 22c illustrates the valve A through the sectional plane X. The valve A has a spring element 136 or spring elements. Shown are the pistons for pressure indicator 132, the housing 130, the ball 126 to the closure, wherein the ball 126 may also be formed as a cone or piston, further The air supply 134 for the pressure gauge and pressure relief valve and the air passage 126, wherein and outlet 126 is shown closed, an air chamber 138 and an open pressure relief valve 1 18th

FIG. 22d, in addition to the components described for FIG. 22c, also represents a ball stop 140 with the inlet and outlet 126 closed.

22 e of FIG. 22 d represents the ball stop 140 with the inlet valve open,

Fig. 23a shows an open-close valve B with a pressure equalization. The valve B has a housing 150 and a mounting ring 152, a closure element 154, as a ball, piston or cone is formed on, furthermore, an adjusting cap 158, an air passage 162 in / from an inner air chamber, and an air passage 164 in / from another outer air chamber in Fig. 23b, an embodiment of the valve B is shown in section. The valve B is installed and operable from the outside, for example by turning, pushing or pulling. The connection of the air chambers 142, 144 takes place within these air chambers 142, 144, but can also be used outside. The valve B is shown closed. There is a connecting element 146 is arranged. Furthermore, a connecting element for an air guide 148 is formed.

FIG. 23 c represents the valve B in a sectional plane Z 1 in the closed state. The individual parts are illustrated as indicated in FIG. 23 b. Furthermore, a circumferential sealing region 166 is shown.

In Fig. 23d, the valve B is shown in a sectional plane XI in the closed state.

FIG. 23e according to FIG. 23c shows an automatically opened valve B for pressure equalization. The air passage 164 is shown as indicated.

In Fig. 23f of Fig. 23d an automatically opened valve B is shown for pressure equalization.

Fig. 23g shows a valve B opened by turning the adjusting cap 158 with pressure compensation.

Fig. 23h shows the valve B open in the cutting plane Z2, the cover 158 is moved mechanically or with a magnetic switch outwardly to open the valve B.

In FIG. 23i, the valve B is shown open in the sectional plane X2. The lid 156 and / or the adjusting cap 158 is moved outwardly mechanically or with a magnetic switch as shown in Fig. 23e to open the valve B.

Fig. 24a shows an open-close valve B. It shows a seal and connection 170. This is connected to an air chamber. In Fig. 24b, the valve B is shown in the closed state with an indicated air chamber. FIG. 24c shows a closed valve B with the air chambers 142, 144 and a connection of the air chambers. FIG. opened valve B and Fig. 24e an open valve B with the air chambers 142, 144 and their connection 174 and a closure device 171st

In Fig. 25, a quick coupling 176 is shown with a plug 178 and a sleeve or a receiving element 180. This quick coupling 176 may be used to connect junctions e.g. of bars and air chambers of the flying and sliding element, e.g. of the primitive with other segments.

Fig. 26a illustrates a combination of two air chambers, which have different sizes and are arranged adjacent to each other. Fig. 26b illustrates two air chambers, which are spaced from each other and also have different sizes.

In Fig. 27a an embodiment of air chambers 186, 188 is shown in a juxtaposed position to form a "double air chamber." The double air chamber has an arcuate course This arrangement may be transverse or longitudinal and arcuate or straight.

Fig. 27b shows a variation of the illustration in Fig. 1 with a front body 190 and transverse bodies 194, 196 and 198 and a longitudinal body 197. The front body 190 may, as described in Fig. 27a, be formed of a "double-air chamber". The air chambers 194 to 198 are arcuate and, together with the sail surface 199, shape them three-dimensionally in one or more directions and tighten the sail surface 199 to the flying and gliding element The course of the air chambers 194 to 198 may also be oriented in the other direction The air chambers 194 to 198 may be connected to other air chambers, terminate at the end of a sail or terminate in the middle of the sail.

In Fig. 27c, a further embodiment of FIG. 1 is shown, in which an air chamber is arranged as a reinforcing element 202. The course of transverse air chambers 202 is shown in an arc shape. The course can also be curved in the other direction. The outlet angle to the front body 190 may be formed deviating from 90 °.

FIG. 27 d shows a variant with air chambers 204, 206, 208, 210. FIG. 28 shows a variable sail structure of three sail surfaces 212, 214, 216 as well as two air chambers 218, 220. In this case, the air chamber 220 is designed to be binding-friendly due to the formation of the outer edge. It can also be combined two sail areas. FIG. 29 a shows an arrangement in which air chambers 222 and 224 are designed with folding aids 226, 228. The folding aids 226, 228 are bulkheads with the function of folding aids. Furthermore, a connection hole 234 is formed between air chambers 230, 232. The air chambers 222, 224, 230, 232 and possibly further can be connected to each other so that they can form a sail area.

Fig. 29b shows two air chambers 182, 184 in an assembly with a sail 236, which is in each case arranged centrally on the air chambers 182, 184. This figure shows the embedding of these air chambers in the sail material structure. The sail surface 236 can also be used as a bulkhead and thus the air chamber 182 or 184 or both are divided into upper and lower sides as half shells, which are connected to the sail 236 and together form a roundish shape by uniform pressure distribution. The sail 236 may also be a component of adjacent air chambers.

FIG. 29c shows the sail 236, this sail 236 engaging an upper side of the air chamber 182 and the second air chamber 184 resting on the sail 236, thereby forming a further point of engagement for the arrangement of the sail 238. The attack of the sail 236 can also be done centrally of the air chamber 184. When approaching the air from the front thus a paragraph is present, the air pulls the flight element up. A back pressure is avoided. FIG. 29d shows a further exemplary embodiment of the arrangement of two air chambers 184, 192 with a sail 236 arranged in each case on the upper side of the said air chambers.

Fig. 30a illustrates air chamber connectors 240 in an exploded view, exemplified in T- or cross-shaped. These serve to connect air chambers 204, 206 to the air chambers 208, 210. The air chamber 206 has a closure cap 244 in this exemplary embodiment. The air chambers can be made of one meter (hose). These can also be pressure hoses, flexible hoses, expanding / contracting hoses. A connector 242 may also serve for repair.

In addition to the use of the air chamber connecting elements 240 is used for the air chambers 204 to 210 meter goods. This results in addition to the cost savings further re benefits from the consistent shape and dimensions of the meter for processing and repair. In addition to the repairs, a defective section can be better removed, replaced, reconnected or repaired. The use of consistent parts can apply to all fasteners. The connecting elements 240 may include valves, pressure indicators and / or pressure relief valves. Mechanisms can be used to press off lines to separate the air chambers.

FIG. 30b shows receiving devices 246 for receiving air chambers. 30c shows the receiving devices 246 with the air chambers 204, 206 arranged therein and the air chamber connecting elements 240, the connecting piece 242 and the closure cap 244 and the sail 236. Air chambers 204, 206 can, like the sail surfaces 236, connect elements such as lugs, lips, rails, Clamps, bags or the like. exhibit. The receiving devices 246 may be formed similar to a piping and serve to connect the air chambers to sail surfaces.

FIG. 31 shows, by way of example, a hybrid line 250 for an energy feed which can be generated on the surface of the flying and gliding element which comprises a linen casing 251 and a linen core 252. Within the linen casing 251, an additional element 253, which may be formed as a pneumatic or hydraulic line, is arranged in this exemplary embodiment. Furthermore, a further additional element 254, in this exemplary embodiment a current conductor 254, is arranged within the linen casing 251.

FIG. 32 illustrates a construction of a hybrid line 250 that includes a line 255 and ancillary elements 253 and 254. Other additional elements may be antennas, lightning rods, etc.

FIG. 33 shows a hybrid line 250, which shows the linen jacket 251 and an additional element 254, wherein an internal medium carrier 256 is formed. This medium carrier or the medium line 256 is designed to guide media 257 such as gases or liquids. The gas 257 may in particular be compressed air or helium.

In Fig. 34, the hybrid line 250 is shown with the linen core 252, wherein the hybrid line 250 includes the additional elements 253 and 254. FIGS. 31 to 34 show that all the components required for the energy transmission can be combined in one or more hybrid lines 250. These are in particular power lines 254, pneumatic or hydraulic lines 253 or also media lines 256. These additional elements must therefore not be installed independently, but may as well as antenna, lightning rod or the like. to get integrated. The additional elements can be arranged in parallel or in a spiral or can be arranged inside or outside in conjunction with the line 255 and thus form the hybrid line 250. The hybrid leads 250 can also serve as control elements. This simplifies the arrangement and handling as well as the controllability when extending and retracting the hybrid lines 250.

The air chambers can be arranged on the tear-off edge (trailing edge) circumferentially or almost circumferentially. The air chambers and the sail surface or -n can be connected to connecting elements or directly connected or connected by embedding, or also sewn, glued, welded or connected by other suitable means. The air chambers can be arranged side by side or one above the other and independently be formed individually or contiguously. All features described in the description, the following claims and the drawings can be essential to the invention both individually and in any desired combination.

Numeral 1 iste

10 flying or sliding element

12 outer skin

 14 front body

 16 first transverse body

 18 second transverse body

 20 third cross body

 22 fourth transverse body

 24 sails

 24 'sail module

 26 bulkheads

 28 bulkheads

 29 bulkheads

 30 bulkheads

 32 bulkheads

 34 first connecting hose

36 second connecting hose

38 third connection hose

40 fourth connection hose

42 fifth transverse body

 44 fifth connection hose

46 starting material

 48 first valve

 50 sails

50 ^' sail module

 52 second valve

 54 third valve

 56 fourth valve

 58 rear body

 60 air chamber

 60a air chamber

 62 plunge tool

 64 leak

66 first sealing element 68 visible tear-off edge

70 second sealing element

72 third sealing element

74 fourth sealing element

76 first thorn

 78 inner trailing edge mandrel 76

80 fifth sealing element

82 second thorn

 84 inner tear edge mandrel 82

86 sealing pad

 88 side element

 90 cultivable segment

92 basic element

 94 edge

 96 front air chamber

 98 circulating air chamber

100 air inlet and outlet

102 extension

 104 staff

 106 fold-out element

108 connection / support element

1 10 axis of rotation

 1 12 supporting or dividing wall

1 14 connection openings

1 16 viewing window

 1 18 pressure relief valve

 120 closure lid

 122 connection to air chamber

124 ball

 126 air passage

 128 pressure display

 130 housing

 132 pistons of pressure gauge

134 air supply

 136 spring element

 138 air chamber inside

140 ball stop 142 air chamber

 144 air chamber

 146 connecting element

 148 Air duct connection element

 150 housing

 152 fixing ring

 154 Closure element piston, ball, cone, diaphragm

156 spring element

 158 adjustment cap

 160 sealing element

 162 air passage

 164 air passage

 166 circumferential sealing area

 168 Housing and connecting element for air guidance

170 connection

 171 locking device

 172 open / close element

 174 connection air chambers

 176 quick coupling

 178 plugs

 180 sleeve

 182 air chamber

 184 air chamber

 186 air chamber

 188 air chamber

 190 front body

 192 air chamber

 194 cross body

 196 cross body

 197 longitudinal body

 198 cross body

 199 sail area

 200 connection points

 202 air chamber

 204 air chamber

 206 air chamber

208 air chamber 210 air chamber

 212 sail area

 214 sail area

 216 sail area

218 air chamber

 220 air chamber

 222 air chamber

 224 air chamber

 226 Folding aid

228 Folding aid

 230 air chamber

 232 air chamber

 234 connection hole

 236 sail area

238 sail area

 240 air chamber connector

 242 connector

 244 cap

 246 receiving device

247 Schott

 248 top half shell

 249 Bottom half shell

 250 hybrid line

 251 linen coat

252 linen kernels

 253 Additional element hydraulic / pneumatic line

254 Additional element, conductor

 255 lines

 256 medium line

257 medium

A inlet and outlet valve

 B on or inside valve

 W range

X first cutting plane

 XI first cutting plane

X2 first cutting plane X3 first cutting plane

X4 first cutting plane

Y second cutting plane

ZI third cutting plane

Z2 third section plane

Z3 third section plane

Claims

MARTIN. Harry: 71229 Leonberg claims Flight or sliding element (10) with an outer skin (12), comprising a front body (14, 190) and at least one sail (24, 50, 50 ^' , 199, 212, 214, 216, 236, 238), wherein the front body (14, 190) and / or one or more additional bodies (16, 18, 20, 22, 42, 194, 196, 197, 198) arranged transversely and / or longitudinally and / or obliquely, and; or a rear body (58) and / or at least one air chamber (60, 60a, 96, 98, 138, 142, 144, 182, 184, 186, 188, 192, 202, 204, 206, 208, 210, 218, 220, 222, 224, 230, 232) are completely formed by the outer skin (12) as an outer boundary, wherein the outer skin (12) is self-sealed, wherein the sail or sails (24, 50, 50 ', 199, 212 , 214, 216, 236, 238) is or are formed from the outer skin (12) and the outer skin (12) is self-sealed in that it is formed from air- and waterproof materials, characterized in that within the front body (14 ) un d) or the additional bodies (16, 18, 20, 22, 42, 194, 196, 197, 198) and / or the rear body (58) one or more bulkheads (26, 28, 30, 32, 247) are arranged and wherein segments (90) are formed, which are attachable to basic elements (92). Flying or sliding element (10) according to claim 1, characterized in that the front body (14, 190) and one or more additional body (16, 18, 20, 22, 42, 194, 196, 197, 198) and / or the Rear body (58) and Luftkammem (60, 60a, 96, 98, 138, 142, 144, 182, 184, 186, 188, 192, 202, 204, 206, 208, 210, 218, 220, 222, 224, 230th , 232) can be connected to one another by at least one connecting hose (34, 36, 38, 40, 44) and / or air chamber connecting elements (240) and / or connecting elements (242) and / or by a valve. Flying or sliding element (10) according to any one of claims 1 or 2, characterized in that the front body (14) and / or air chambers, which are formed as a transverse body (16, 18, 20, 22, 42), and / or the Rear body (58) at least one valve (48, 52, 54, 56, A, B). 4. flight or sliding element (10) according to claim 3, characterized in that the valve (48, 52, 54, 56, A, B) comprises at least one inlet and outlet valve, pressure relief valve or pressure gauge alone or in combination. 5. flight or sliding element (10) according to any one of claims 3 or 4, characterized in that the valve (48, 52, 54, 56 A, B) outside, on or at least partially formed on the inside. 6. flight or sliding element (10) according to one of claims 2 to 5, characterized in that the valve (48, 52, 54, 56, A, B) is automatically formed electrically or mechanically operable and / or remotely controllable and / or the functions are switchable. 7. flight or sliding element (10) according to one of claims 3 to 6, characterized in that the valve (48, 52, 54, 56, A, B) has access to the interior of the front body (14) and / or the transverse body (16, 18, 20, 22, 42), which is used for repair or cleaning purposes. 8. flight or sliding element (10) according to any one of the preceding claims, characterized in that in the air chambers sealing elements (66, 70, 72, 74, 80) for sealing a leak (64) are introduced. 9. flight or sliding element (10) according to claim 8, characterized in that the sealing element (66) has a mandrel (76), wherein the mandrel (76) has a tear-off edge (76) or that the sealing element (80) has a mandrel (82) comprising a tear-off edge (82). 10. flight or sliding element (10) according to any one of the preceding claims, characterized in that a Abdichtpad (86) for sealing a leak (64) is used. 1 1. flight or sliding element (10) according to one of claims 8 to 10, characterized in that the sealing element (66, 70, 72, 74, 80) has a sealing means. 12. flight or sliding element (10) according to any one of the preceding claims, characterized in that the flight or sliding element (10) consists of several other modules, each comprising at least one additional body (16, 18, 20, 22, 42) and / or a partial front body (12 '), and / or a sail (24', 50 ^' ) is composed. 13. flight or sliding element (10) according to any one of the preceding claims, characterized in that the outer skin (12) has contours or structures and / or reinforcing structures and / or coated and / or has a film layer. 14. flight or sliding element according to one of the preceding claims, characterized in that the outer skin (12) for connection to sails (24, 50, 50 ^' , 199, 212, 214, 216, 236, 238) sewn and / or welded and / or glued and / or reinforcing, sealing or sealing elements or a rubber coating. 15. flight or sliding element (10) according to any one of the preceding claims, characterized in that the outer skin (12) of composite material, fabric fabrics, film, natural silk, rayon, nylon, PVZ, other plastics or viscose and / or is designed as a tubular fabric and is treated or untreated and / or has a protective surface. 16 flight or sliding element (10) according to any one of the preceding claims, characterized in that the flight and sliding element (10) has rigid (106, 108) or inflatable structures which are formed unfolded or foldable or telescopically (60, 108) are formed apart and together driving. 17. flight or sliding element (10) according to any one of the preceding claims, characterized in that the front body (14, 190) from at least two air chambers (60, 60a, 96, 98, 138, 142, 182, 184, 186, 188 , 192, 202, 204, 206, 208, 210, 218, 220, 222, 224, 230, 232). 18. flight or sliding element (10) according to any one of the preceding claims, characterized in that an energy recovery by solar cell effects over the entire flight or sliding element (10), wherein the outer skin (12) and the sails (24, 50, 50 ', 199, 212, 214, 216, 236, 238) are coated with films or coatings with solar cell action. 19. flight or sliding element (10) according to any one of the preceding claims, characterized in that air and / or connecting lines are arranged on the flight or sliding element (10), which serve to transmit the control in different directions and power transmission and / or additional lines are designed for power transmission. 20. flight or sliding element (10) according to claim 19, characterized in that the flight and / or connecting lines and / or additional lines are designed as hybrid lines (250) and a linen sheath (251) and / or a linen core (252) and / or a hydraulic or pneumatic line (253) and / or a current conductor (254) and / or a medium line (256) and / or a medium (257).