Wind energy system for generating power

Abstract

The invention relates to an airborne wind energy system with a substantial, integrated safety and security architecture which, in emergency situations (crash scenario), controls the wind energy system as a whole or the installed individual components and safely brings same directly back to the ground station, which takes into consideration a controllable kite construction for high wind layers in order to synergistically and substantially increase the lift force, which is normally generated solely by the gas-filled airship (climbing balloon or zeppelin), in order to maximize the generation of power with the aid of the wind converter while simultaneously ensuring the necessary stability of the entire system in the air.

Description

[0001] Wind turbine for energy generation

[0002] The present invention relates to a wind turbine for generating electrical energy.

[0003] Introduction

[0004] The purpose or rationale of the present invention is to implement a wind turbine (WTG) driven by high-altitude winds (>500 m to 15,000 m) with an energy generation capacity of at least >0.5 megawatts. In particular, the design underlying the invention is intended to integrate a substantial safety and security architecture as preventive measures against fall risks, accident risks, and damage minimization measures in the event of an unexpected, yet entirely possible or latent fall scenario, thereby obtaining official approval for primary project implementation on land (= inshore).A significant increase in lift force through synergistic partial solutions in order to achieve a substantially higher, more efficient, more uniform and permanent energy generation using wind power and, as a result, a significantly better stabilisation of the overall system, even under extremely demanding and sometimes chaotic weather conditions.

[0005] It is striking that 4-dimensional wind turbines (=WTGs) known from the state of the art, which are not attached directly to the ground (=inshore) or on or above floating pontoons (=offshore), which use wind power to generate energy while flying or hovering, generally represent solutions or embodiments that fundamentally focus on design solutions or inventions whose main emphasis is on embodiments of various wind harvesting systems (e.g. Darrieus / Savonius rotors or similar designs), without taking the above-mentioned aspects into account. In particular, the fact is ignored that, depending on the design of the flying vehicle, WTGs can be massively pushed sideways by wind force and, theoretically, could be pushed to ground level in very strong winds; similar to a water buoy that is pushed downwards by the current and waves of the water.Even aircraft designed like airplanes or blimps are deflected by wind force and, at low altitudes, create inherent problems during the hovering phase, as uncontrollable whirlwinds can prevail, particularly if the wind converter with generator is located on or directly next to the aircraft and in the air. The prevailing dynamics (e.g., different air resistance [=cW]) result in different differences in gravity, and achieving a kind of homeostasis or compensating for the resulting differences would be a technical masterpiece. Fundamentally, however, the question remains whether such a structure would even possess any meaningful climb performance, since the climb capability of purely gas-filled wind turbines is extremely modest in relation to the energy generation.

[0006] Lifting forces from gas-filled aircraft only allow for small wind power generation plants, since with increasing wind strength the force acting on the rotor blades increases disproportionately and consequently would result in the vertical deflection of the entire structure (=GK) into less windy air layers.

[0007] Furthermore, there is a physical and economic conflict of interest between the structurally induced buoyancy force (gas buoyancy vs.

[0008] The ratio between the total weight of a large wind turbine driven by high-altitude winds and the maximum desired energy generation (i.e. the larger the corresponding rotor area, the heavier the overall structure becomes), necessitating additional stabilizing structures that increase weight. This is why the relatively low lift force of flying or hovering HWKs (HWK system inventions that are state of the art and are exclusively equipped with a flying craft) is fundamentally the limiting factor. This obvious and inherent fundamental problem could, of course, be elegantly circumvented by attaching the H-GWKA to a fossil fuel-powered helicopter (limiting factor: oxygen content in the air) in order to benefit from the high-altitude winds; however, the energy yield would likely be lower than the energy used by the helicopter or one or more oversized drones.Likewise, a construction from the ground using a kind of "lantern pole" - from which the energy generation device hangs - would also not be effective, since the resulting construction height and the associated technical effort would contradict the original intention.

[0009] The present invention provides a wind turbine. The wind turbine comprises a ground station, a tether, a wind converter, and an airship. The airship is connected to a base plate of a ground station via the tether. The wind converter has a rotor and a generator connected to the rotor. The airship has a flight initiation device. The wind converter is arranged on the tether in the region between the base plate and the airship, preferably underneath the airship. The wind turbine according to the invention further comprises a safety and security device integrated in the region extending from the base plate to the airship.

[0010] The wind turbine (WTG) according to the invention comprises exclusively flight-capable tandem systems comprising an airship and a flight initiation device, which ensure that the H-GWTG can develop maximum lift and thus dimension the energy generation device (wind turbine) in such a way that its performance potential is more than competitive with existing WTGs, which traditionally use the wind force acting on the ground or from the sea surface to generate energy (= harvesting). Interestingly, an extremely inconspicuous and significantly underestimated and hidden factor, which counteracts the lift force in four-dimensional WTGs, is usually ignored: namely, the stable holding cable, which can easily weigh 1 kg or more per linear meter. At a desired flight altitude of, for example, 10,000 m, the holding cable alone would weigh 10.000 kg and more and with such a weight, a construction with a holding rope attached to the top of a zeppelin-like airship would automatically pull the top significantly downwards and thus move the integrated wind converter from the optimal flight position (LUV).This could of course be avoided by attaching another cable to such a structure, ideally one of the same weight, in order to successfully counteract any prevailing imbalance in the overall system; however, if the second or even more cables (the system's buoyancy decreases with each additional holding cable) are only attached to the ground, there is a potential risk that the cables could become twisted, particularly in unstable weather conditions, and thus endanger the entire system, or the cables could be stretched so far apart that the area consumed would increase massively and would therefore be contrary to the implementation of a wind turbine approved by the authorities on land.

[0011] For a realistic, officially approved commissioning, especially as a competitive alternative to existing wind turbines constructed traditionally on the ground (inshore) or on a floating pontoon (offshore), it is essential that the wind turbine design incorporates preventive measures against emergency situations; true to the motto: "what goes up, must come down." It is fundamentally impossible to construct a mechanistic, flying or floating wind turbine in such a way that its probability of absolute integrity is 100% (complete exclusion of any residual risk). Therefore, the fundamental invention is intended to contribute to ensuring that a latent residual risk of an emergency situation (e.g., a crash scenario) remains risk-free to life and limb.

[0012] Furthermore, it is obvious that suspended or flying inshore wind turbines always require regulatory approval, and especially when assessing the latent residual risk to life and limb, approval without a convincing safety concept is unthinkable. In contrast, the underlying idea will be much easier to obtain approval for offshore operations that can be implemented at any time. The underlying idea should, in particular, optimize the coupling of energy generation versus direct energy use (e.g., hydrogen production directly at industrial facilities, energy supply directly to cities without long power lines).

[0013] During our research, we noticed that this important point has not been taken into account to date, and especially in connection with the extremely costly and massive environmental damage caused by the expansion of power grids and pipeline routes through developed or planned offshore wind farms, the underlying invention is intended to represent a future-oriented solution.

[0014] Additionally, the underlying invention was intended to enhance the inherent lift force of the airship for realistic deployment in strong wind regions far from the ground, by utilizing a flight initiation device, preferably in the form of a towing kite, preferably flying directly on the airship. It is obvious that some ideas aimed at using wind converters capable of generating large amounts of power also envision the use of a kite to substantially increase the essential lift force of the entire system. However, the deployment of a kite is always viewed as an automatic, easily implemented activation with self-regulating flight readiness, and therefore, viable solutions are generally not offered that realistically enable the deployment of a towing kite at higher altitudes.Optimal control of a towing kite, especially in descending winds or onset of wind turbulence, jeopardizes the operation of the entire system. The fact is that the airship is launched and positioned first, and only then should a towing kite be initiated. This difficult passage should be achieved exclusively with smart control, knowing that towing kite designs tend to have an unstable sail area.

[0015] The underlying concept therefore favors a tandem solution – a preferred initiation device (e.g., a kite, drone, or hang-glider) and a parachute. After initiating a kite, for example, the parachute is pulled upwards until the tensioning device integrated into the parachute has fully tensioned the parachute, thus ensuring its suitability for gliding. It is important that the towing parachute remains in a controlled position near the airship, performing its work, in order to ensure that the regulation – deployment and retraction – of the towing parachute can be controlled and monitored at all times.The underlying concept is to ensure absolute control and alignment of the entire system, first bringing all the equipment into the appropriate, optimal hovering position. Then, the parachute is positioned. Once the lift force has been synergistically maximized, the preferably adjustable rotor blades are ideally positioned into the wind (= LUV) to initiate and maximize the desired power generation. It is essential that the safety of the commissioning and continuous operation of the entire system is guaranteed.In a worst-case scenario, the maximum damage should be limited exclusively to the system's equipment. Should the entire system crash, each component will be safely lowered to the ground in such an emergency scenario, using the on-site navigation and software-supporting components and drogue parachutes located on each component. These safety concepts control the individual components and slowly guide them into a safe area using the software and sensor-supported control system. The remaining critical components are secured and retracted with minimal risk using the safety structure established in the ground station.

[0016] In principle, it can be stated that the structure of a suspended wind turbine (=WTG) is largely identical. They consist of a ground station and a hovering aircraft connected to the ground station, which propels at least one rotor and a generator connected to the rudder, including a gearbox. To avoid the need for a costly tower in a wind turbine, it is known to connect a ground station to a wire rope, to which a rotor for generating electrical power is attached.

[0017] State of the art

[0018] An example of wind turbines with a gas-filled airship (here a climbing balloon) is the PCT application "PCT / EP2012 / 000021 Magnetically Legged Vertical Axis Wind Turbine for High Altitudes". In this idea, due to the relatively low lift force, which results exclusively from the lift force of the gas fed into the climbing balloon in relation to the selected volume of the climbing balloon and the weight of the heavy wind converter-generator unit, the proportions are realistically reproduced and thus the structurally limited size of the wind converter is predetermined. Furthermore, it can be stated that the larger the airship in relation to the wind converter, the more vulnerable and uncontrollable the overall structure is in strong winds.

[0019] Also evident is the statistically significant and neglected problem of crashes of suspended wind turbines, as the commissioning of suspended wind turbines inherently entails the potential risk of an uncontrolled and therefore serious emergency situation if they crash for whatever reason (design flaw, material fatigue, extreme climatic conditions, third-party negligence).

[0020] Furthermore, our research revealed that relevant inventions or designs by third parties have only taken the problems described above into account in a rudimentary manner and, if at all, only in CHP plants with low energy generation < 0.5 megawatts.

[0021] Any attempts to solve this problem using integrated parachute structures for total weights > 5 t would be completely unrealistic, and thus such HWKs would not receive an operating permit over populated regions. The fact is, the higher the flight position of a HWK, the greater the fall radius and corresponding crash risks, i.e., if the tether were to break at a point in the upper third, the HWK would be massively blown away by the wind.

[0022] In order to solve the problems outlined above, the underlying invention is designed in such a way that the individual assemblies and their primarily intended and integrated safety architecture are separated from one another in an emergency situation (e.g. the risk of falling is "smartly" decoupled in order to bring the latent risk of falling in such challenging, 4-dimensionally acting constructions to zero percent [0%]) in order to get the respective fall weight for each assembly as low as possible, so that the likewise integrated fall safety precautions for each assembly can achieve maximum effect in order to make a latent risk of accident, in particular for life and limb, completely manageable.

[0023] The underlying invention was designed based on a fictitious crash scenario in such a way that, in contrast to the prior art, a latent risk of falling is eliminated with an integrated safety architecture and safety precautions, thereby eliminating any residual risk to life and limb. In particular, in such a case or event, situation-dependent and immediately counteracting and completely autonomous measures are initiated, based on the described safety structure located on the ground station, as well as the sensor- and computer-assisted, algorithm-based, "smart" control and monitoring unit and safety systems installed on the respective individual components (= assemblies).

[0024] The base plate may comprise a turntable which is mounted rotatably relative to the base plate, wherein a plant safety chamber is located on the turntable, in which a safety cell is integrated which is equipped with a spring-damper device.

[0025] The ground station may further comprise at least one controllable airbag device, wherein the airbag device is preferably arranged in the region of an upper end of the safety cell.

[0026] The plant safety chamber can further comprise a large cable drum driven by at least one high-speed motor, which is preferably located on the right and / or left side of the large cable drum. The at least one high-speed motor is designed to wind the holding cable onto the large cable drum at a high rotational speed. Of course, the high-speed motor can also be used to unwind the holding cable and particularly preferably has a freewheel and a brake with a spring-damper unit. The holding cable can comprise an integrated electrical conductor, via which, for example, the electrical energy generated by the generator can be conducted to the ground station and there to the energy infrastructure.Likewise, the integrated electrical conductor can be used to exchange signals and data between the electrical units of the ground station and the wind converter and / or the airship. The electrical conductor can be multi-core and have different cross-sections.

[0027] The plant safety chamber can be mounted so that it can pivot relative to the turntable. For this purpose, the plant safety chamber is preferably suspended at its lower end in a movable swing construction and, particularly preferably, to support the alignment, is additionally movably connected to a pivoting device of the plant safety chamber via a support bracket of the turntable.

[0028] Additionally, pivoting telescopic arms can be arranged on the turntable, which are preferably 180 degrees to each other and positioned to the left and right of the plant safety chamber, to each of which a position holding rope is connected via a high-performance cable drum, which is attached directly to an external structure of the rotor.

[0029] The heavy-duty cable drums are not responsible for the vertical movement of the wind converter, but are designed to provide an additional braking function for the wind converter in a fall scenario.

[0030] The base plate can be designed to be movable, using vertically movable independent wheel suspensions installed on the base plate and steerable wheels attached to the independent wheel suspension.

[0031] Several, preferably four, anchoring piles can be arranged on the base plate, which are designed to anchor the base plate in the subsoil. The anchoring piles are preferably each provided with a thread and drill head. The wind converter can comprise a vertical (e.g., Savonius / Daerrius rotor) or a horizontal rotor designed as a wind turbine, which is suspended from a structure of the wind converter. The structure of the wind converter is preferably composed of an outer and inner construction, with the rotor suspended in the center of the rotor gimbal between the outer and inner structures.

[0032] At the lower end of the inner structure, the holding rope can be connected to the wind converter in a load-bearing manner via compressed air-filled detonators or an electromagnetic coupling, with an anchor weight and / or a braking parachute preferably being arranged at the lower end of the inner structure.

[0033] The supporting kite(s) or parachute ("spinnaker") can be attached not to the airship / balloon unit, but directly to the outer ring of the converter unit in order to relieve the load on the airship in strong winds.

[0034] A reduced balloon unit can be provided, which is only intended to carry the tether(s) (between ground station and airship / balloon) and the "airship / balloon" assembly upwards.

[0035] An air-assisted or software-controlled hoisting device can be provided, which can pull the converter unit from the ground station to the optimized energy harvesting altitude position. This process is only possible if the pulling force due to the activation of the airbag ("spinnaker") and / or kite increases sufficiently to support the additional weight of the converter unit being hoisted and its commissioning, i.e., its upwind orientation.

[0036] The wind converter can include:

[0037] - Air-assisted or software-controlled braking (braking and / or steering parachute(s), electromagnetic and / or electro-pneumatic and / or electromagnetic detonation / detachment units) and detachment unit to enable the entire assembly to be elegantly separated from the overall system in an emergency and to drop it in a controlled, controllable and safe manner to the ground station

[0038] - For safety reasons, air-assisted or software-controlled external hook devices should be installed on the outer ring of the assembly, which can be activated ultra-quickly in an emergency using a cable-based or radio-controlled trigger unit.

[0039] - Installation of a direct or indirect safety net on the ground (with or without a center hole; consisting of 4 x ground pillars, each equipped with a spring / damper unit at the end of the pillar), which can decelerate the falling assembly in a controlled manner and catch it without damage in the event of an emergency.

[0040] Telescopic arms can preferably be arranged between the outer structure and the inner structure.

[0041] Preferably, compressed air-filled detonators or the electromagnetic clutch and / or a braking parachute can be arranged at the lower end of the inner structure, positioned on an outer side.

[0042] The airship may comprise a gas-filled balloon, preferably a climbing balloon, to which a parachute is directly attached, which will float close to the balloon in flight mode.

[0043] The airship and / or balloon unit may preferably have the following features:

[0044] - Gas outlet devices or release valves in the balloon outer skin to ensure a controlled, AI-assisted or software-controlled descent of the balloon,

[0045] - and / or gas release cutouts within the balloon outer skin to ensure a faster, abrupt gas release,

[0046] - Air-assisted or software-controlled decoupling and separation maneuver in an emergency situation to quickly separate the module from the overall system, - Air-assisted or software-controlled braking parachute and / or steering parachute to allow the airship to float to the ground in a controlled and safe manner (to ensure reusability).

[0047] The parachute can be pulled upwards by a self-flying, small flight initiation device, for example a kite, a drone or a hang glider, and during the launch phase the orientation of the parachute can be controlled by smart cable winches which are arranged on the gas-filled balloon and wherein the parachute is connected to the cable winches via cables and wherein the flight initiation device is connected to the parachute via a cable.

[0048] An exoskeleton can be arranged inside the parachute, which unfolds and opens the parachute after the launch phase and through an integrated control unit.

[0049] The flight initiation device may comprise a braking parachute, which is preferably triggered before the separation of the flight initiation device, by means of a separation device arranged on the cable, wherein the braking parachute is arranged at a top dead center of the flight parachute.

[0050] A compressed air-filled detonator or an electromagnetic clutch can be arranged at the top dead center of the parachute as a separating device.

[0051] Inside the airship, durable safety hoses can be installed, which in turn comprise several gas chambers and each have inlet and outlet valves as well as pressure sensors, which are supplied by the gas supply network installed on board, which runs between the safety hoses and which are protected and separated from the environment by the robust, preferably sharkskin-like structured outer skin of the airship.

[0052] A holding box can be mounted on the airship in the slipstream, with an integrated safety cell, which preferably contains a liquid gas tank with an included gasification unit and a gas line that is directly connected to the gas supply network, so that the gas can be supplied to the safety hoses and / or their individual gas chambers.

[0053] Alternatively, an electrolyzer for producing hydrogen, a water tank, a water pump and a gas pressure distribution unit for the produced hydrogen can be arranged in the safety cell.

[0054] As a further alternative, an integrated accumulator, preferably a lithium-ion battery, can be arranged in the safety cell.

[0055] The safety cell can be attached to the holding box by at least one safety belt and at least one closure and can additionally comprise at least one compressed air-filled detonator and / or an electromagnetic clutch and a braking parachute on the at least one closure.

[0056] All surface materials (outer skin) intended for the subject matter of the invention and its flight-capable variants should preferably be provided with a wind flow-optimizing, streamline-promoting microstructured skin, similar to shark skin, and at the same time provide preventive protection against any contamination (lotus effect) from the atmosphere or possibly animals.

[0057] All flying vessels (gas-filled round balloons or Beluga-type balloons as well as zeppelins) or their described variants are filled with different gases (e.g. helium and / or hydrogen).

[0058] Every wind converter design is generally connected to a generator for power generation and preferably also to an intermediate gearbox to allow for "smart" regulation (increasing or decelerating) of the speed generated on the generator axis. Furthermore, all rotor blade designs should preferably be movable and connected to a "smart" control unit so that the angle of incidence (windward or leeward) of the wind on the rotor blade can be controlled.

[0059] All gas balloons shall preferably be equipped with electric, 360° rotatable, software and sensor-supported, autonomous or automatic and / or remotely controlled (in case of emergency) X-turbopropellers and electric, software and sensor-supported, autonomous or automatic and / or remotely controlled (in case of emergency) adjustable elevators and / or rudder for stabilisation and positioning purposes.

[0060] In addition, all turbo propellers should preferably be adjustable to rotate clockwise or counterclockwise and preferably run counter to the rotation of the wind turbines.

[0061] In an acute emergency (crash scenario), the separation of individual assemblies or parts from the control system should preferably be carried out according to a smart, integrated step-by-step plan ("evacuation"), and the smart control system is designed so that the decision as to whether and which assembly should be separated from the control system, how, and which braking systems should be activated at what time, should be made smartly and completely independently, depending on the prevailing weather conditions; always strictly oriented towards the scenario with the least damage to life and limb as well as the material used.

[0062] Preferably, the kite and / or hang glider envelopes should be made of a very durable and resilient sail material or similar material, in particular the areas that are located within the gaps in vertical wind converter designs (e.g. Darrieus or Savonius wind converters). These sail areas should be rolled up inside the frame and / or gathered like a blind. Only in the wind harvesting zone should the sail area be pulled out and firmly fixed using an electro-mechanical and / or electro-hydraulic and / or electro-pneumatic or purely electric sail tensioning device, which is powered directly by the power supply from the ground station or indirectly by the power generated on board, using the cables stretched between the frames.

[0063] The underlying invention and its described embodiments are preferably equipped with a computer-assisted ground control system, navigation (GPS and / or inertial navigation system for positioning), radar, infrared, sonar systems, high-frequency systems, turbofans (sideprops), or computer-assisted software that implements a predictive analysis and worst-case scenario optimization algorithm, digital matrix control logic, collision protection, and warning systems for the entire system and its operation. As simple, preventive protective measures, audiovisual warning systems should also be implemented on the critical components or assemblies.

[0064] The outer skin of the gas-filled balloons and / or kite / dragon designs should preferably be made of flexible, robust solar modules, provided they meet the same material requirements as high-performance materials.

[0065] Preferably, all design variants or assemblies should also be equipped with effective lightning protection, de-icing and defrosting devices (e.g., sheathed heating wires) and substantially protective airbag designs, preferably with integrated, "smart" air release valves, which should develop a damping effect through controllable, slowly escaping air outlet up to a maximum reasonable air volume in the event of repeated ground contact.

[0066] The "sailcloth material" could also consist of flexible solar modules if they have the same usage properties as high-performance sail materials

[0067] An additional single or double tail unit can be attached to the gas-filled ascending balloon at the middle of the side of the airship, which is preferably also attached with additional gas-filled chambers alongside and below the tail unit and is equipped at each end with two rudders and an elevator or with a horizontal propeller unit.

[0068] An additional folded towing kite can be arranged in the slipstream of the gas-filled ascending balloon. This kite is attached to an upwardly movable towing kite carrier and is pulled upwards using a smart cable winch, a towing cable towing kite and an additional pulley.

[0069] The towing kite can be placed on the tail unit with the movable towing kite luggage rack, preferably in the middle.

[0070] On the airship, a folded towing kite can be arranged on a movable trigon sight (sled).

[0071] The movable trigon sight can move centrally in a central rail, which fixes the maximum freedom of movement by position stoppers.

[0072] The towing kite can be attached to the top of the kite, which functions as a kind of climbing aid for the towing kite.

[0073] To counteract excessive drifting of the converter unit and / or the airship or balloon in strong winds, lateral propeller units or "sideprops" can be installed to stabilize and fix / secure the position of the entire unit.

[0074] In the following, embodiments of the underlying invention are explained in more detail with reference to the attached drawings, in which:

[0075] Fig. 1 shows an embodiment of the wind turbine according to the invention, primarily its safety and security architecture, as an overall construction in a longitudinal section

[0076] Fig. 2 shows a schematic view of the ground station including the safety chamber Fig. 3 shows a cross-section of the carriage device

[0077] Fig. 4 shows an example of the base plate with pivoting telescopic arms

[0078] Fig. 5 shows a cross-sectional schematic view of a vertically oriented wind converter example in an oblique, wind-induced oblique orientation of the external structure

[0079] Fig. 6a to c show schematic views of a wind converter example - a vertically suspended Darrieus rotor or horizontally suspended rotor blade converter - with gimbal suspension

[0080] Fig. 7 shows another example of a wind converter – here a horizontally suspended, rotor-driven wind turbine – with oversized rotors in relation to the outer structure

[0081] Fig. 8 shows a horizontally aligned, rotor-driven wind converter example, in a tilted position of the overall system caused by the wind power

[0082] Fig. 9 shows another embodiment of a vertically suspended Darrieus wind turbine, in a rectangular constructed outer structure

[0083] Fig. 10a shows a schematic view of a horizontally suspended, rotor-driven wind turbine with a connected tail unit with elevator and rudder

[0084] Fig. 10b shows a horizontally driven propeller unit instead of an elevator

[0085] Fig. 11 further shows a horizontally suspended TWIN rotor-driven wind turbine. Fig. 12 schematically shows a horizontally suspended rotor-driven wind turbine, with attached positioning cables on its outer structure using distance-securing telescopic arms located on the ground station.

[0086] Fig. 13 shows an example of a Darrieus wind converter unit with "Smart" controllable rudders

[0087] Fig. 14 shows schematically an initiation kite unit

[0088] Fig. 15 shows a cross-section of a climbing balloon with a tandem flight unit consisting of an initiation kite unit and an uninflated parachute

[0089] Fig. 16 shows an alternative initiation unit, a drone with four side-mounted fan units (= sideprobs)

[0090] Fig. 17 shows a schematic view in the first step of an air parachute tightly attached to the ascending balloon without one of the previously described flight initiation units (kite or drone)

[0091] Fig. 18 shows in a second step a parachute inactive from the ascending balloon and not tensioned by an exoskeleton

[0092] Fig. 19 shows in a final step a fully unfolded, flightworthy parachute

[0093] Fig. 20 shows the schematic view of a towing kite initiation design with a luggage carrier positioned directly on the gas-filled ascending balloon or on a possibly integrated tail unit

[0094] Fig. 21 shows as an alternative a luggage carrier on a realized double tail unit with the same towing kite initiation design

[0095] Fig. 22 shows a bird's eye view of the luggage carrier positioned on a single tail unit Fig. 23 shows a hang glider luggage carrier construction on a movable and adjustable trigon sight

[0096] ALTERNATIVE DRAWINGS

[0097] Fig. 20A shows the schematic view of a towing kite initiation design with a luggage carrier positioned directly on the riser or on a possibly integrated tail unit equipped with an airbag

[0098] Fig. 21A shows a climbing balloon design with alternatively positioned elevator and rudder

[0099] Fig. 22A shows a bird's eye view of an alternative luggage carrier on a realized double tail unit with the same towing kite initiation design

[0100] Fig. 23A also shows a bird’s eye view of the luggage carrier positioned on a single tail unit

[0101] Fig. 24 shows an example of the movable kite carrier construction in the action phase

[0102] Fig. 25 shows a cross-section of an installed tail unit, which additionally has a gas chamber positioned below and between the ascending balloon and the tail unit

[0103] Fig. 26 shows schematically the central guide rail of the movable trigon sight.

[0104] Fig. 27 shows in cross section the safety hose chambers of the flight unit

[0105] Fig. 28 shows a bird's-eye view of the safety tube chambers without the protective ascending balloon outer skin. Fig. 29 schematically shows a safety capsule 77 attached to the gas-filled airship, with an integrated liquid gas tank and various additional devices designed to refill the gas cells in the airship with gas in the event of a pressure drop.

[0106] Fig. 30 shows an alternative, self-sufficient gas filling using an electrolyzer, which produces hydrogen in the safety capsule 77 and thus supplies the gas chambers with hydrogen if there is a pressure drop there

[0107] Fig. 31 shows another variant of the gas supply, using a liquid gas tank, which is, however, connected to the ground station and which feeds the liquid gas via a gas pressure line directly to the aircraft and in advance into the gasification device in order to be able to fill deficient gas chambers with gas.

[0108] Fig. 31 An alternative is to equip the safety capsule 77 with

[0109] Fig. 1 Overall construction shows a cross-sectional view of an embodiment, in particular the comprehensive safety and security architecture, of the underlying invention as an overall construction (=GK). It should be emphasized that not all detailed solutions have been taken into account in the illustration. The GK consists of the base plate assembly 10, which consists of an internal, ball-bearing turntable 11 and an outer, fixed part, which is connected to several, preferably four, anchoring posts 14, which have a software-supported motor and control unit as well as existing threads and drill heads, which mill themselves into the ground independently at the push of a button. Furthermore, steerable wheels 12 are located at the outer corners of the base plate, each of which has a height-adjustable, software- and sensor-supported,motor-driven independent wheel suspensions 13, which act reciprocally to the anchoring piles. To accommodate the deflection of the GK expected due to wind force, a type of swing structure 16 is located on the turntable, in which the pivoting system safety chamber / maintenance box 17 can easily align itself to the angle of inclination of the GK. The purpose of this swing structure is, among other things, the controlled retrieval (elevator principle) of the wind converter (=WK) and / or airship (=LE; gas-filled ascending balloon or a Zeppelin [keel-type / inflation airship]) in order to efficiently carry out any maintenance work (= normal operation) and, in particular, to transport the GK or the wind converter assembly ultra-quickly into the safety cell 22, which forms the heart of the system safety chamber 17 and features an integrated, extremely resilient airbag structure 22a.which is located at the upper end of the safety cell 22 and whose angle of inclination can be changed using a sensor and software-supported control unit in order to achieve the impact speed of the wind converter unit, which can be caught up faster than its fall speed, which is significantly slowed down by various safety precautions installed (e.g. autorotation of the wind turbine, brake parachutes and parachute, etc.), so that the wind converter unit is forced by the system, like a plumb line, to fall perpendicular to the safety cell 22 in a controlled manner or to fall drastically by the acting and activated brake systems in order to prevent destruction of the wind converter unit. For this purpose, the holding cable 24, which preferably consists of an inner sheath (= integrated, electrical conductor cable; alternatively: holding cable and parallel, separate conductor cable 45b and / or separate gas line 83) and an outer sheath,Its function, in addition to the actual holding function of the wind converter, is to direct the current flow from the generator 31, which is flanged to the wind converter and preferably has an additional integrated gearbox, to the ground station. Furthermore, there are several, preferably two, pivoting and motor-controlled pivot arms 25 on the turntable 11, which additionally secure the wind converter with safety cables 25, in particular to counteract any drifting of the wind converter in strong winds. The next assembly visible is the wind converter.which in turn consists of an outer structure 27 (round or elliptical circle or rectangle) and an inner structure 28 (round or elliptical circle or rectangle) and a rotor blade suspended inside the inner structure (here a Darrieus rotor 30a; alternatively, a Savonius rotor and / or hybrid structures would also be conceivable), at the upper and / or lower end of which a generator and preferably an upstream gear unit 31 is positioned, which is mounted by means of a gimbal (pivotable or pendulum-capable) suspension, which always positions the rotor blade at 90 degrees perpendicular to the wind direction. For further alignment support, a controllable rudder 44 should preferably be located on the left and right side of the rotor blade and / or be provided with an entire, laterally mounted tail unit 42 with a horizontally rotating propeller unit 45, for example, visible here at the rear; furthermore, the vertical position of the rotor blade should be controlled by means of,Each of these has sensor- and computer-assisted, electro-pneumatic or electro-hydraulic telescopic arms 34 positioned at the lower section between the outer and inner structures, as well as preferably an additional, aerodynamically shaped anchor weight 32 attached to the lower end of the inner structure. The next assembly, the airship (= LU), consists, among other things, of a gas-filled (helium and / or hydrogen) ascending balloon or zeppelin 46 with an exemplary tail unit 42 with elevator 43 and rudder 44 located at the rear, which should also contribute to the GK as a whole always turning into the wind (= LUV) and remaining there completely even during power generation. Furthermore, the flight parachute 49, which is unfolded here, has an integrated exoskeleton 49, which is controlled by the sensor- and computer-assisted cable winches 47 located on the airship.which are supplied by the secondary circuit of the generator and are attached to corresponding holding cables 48, and which is pulled into position with the aid of the flight initiation apparatus (here a kite 54) located at the end of the GK so that it can be deployed immediately after the detachment from the gas-filled ascending balloon 46, which is controlled at all times by the sensor- and computer-assisted electrically operated cable winches, and subsequent activation of the exoskeleton mechanism (analogous to a mechanical skeleton of a sun or umbrella) to unfold the parachute 49 and the resulting and intended gliding function, in order to synergistically increase the lift forces of the gas-filled ascending balloon / zeppelin 46.

[0110] The tethers can incorporate an air-assisted or software-controlled braking unit (e.g., drop pockets installed on the tether(s) that open in the event of a sudden fall and, like small parachutes, significantly increase the frictional resistance of the tether). This allows the tether(s) to be wound up in a controlled and damage-free manner using the high-speed cable drum attached to the ground station in the event of an emergency (e.g., if the tether(s) break), using the high-speed cable drum attached to the ground station. One of the key advantages of the underlying concept over the state of the art is that in the event of an emergency situation (e.g., a fall scenario caused by external influences, material fatigue or excessive stress, weather or climate-related factors, etc.), the tether(s) can be wound up in a controlled and damage-free manner.) arising, regardless of where it occurs, if the holding cable 24 or 48 is severed or torn or if one of the modules is torn off, the safety and security architecture is designed in such a way that, in combination with the integrated "smart (= sensor and software supported, algorithm-based control units)" control units and safety equipment (e.g. parachute) and early warning systems (audio-visually triggered, clearly perceptible alarm signals), the GK and / or individual modules are guided to the ground or descend with maximum security in order to proactively and preventively completely rule out any latent risk to life and limb and to significantly minimize any material damage to the GK and / or its individual components.

[0111] Fig. 2 shows the base plate assembly 10, which consists of an internal, ball-bearing turntable 11 and an outer, fixed part. Furthermore, there are several, preferably four, anchoring posts 14, which are equipped with a "smart" motor and control unit as well as a thread and drill head 15, which independently drill into the ground at the push of a button to guarantee the necessary anchoring of the GK. Furthermore, there are steerable wheels 12 at the outer corners of the base plate, each of which has a height-adjustable, software- and sensor-supported, motor-driven independent wheel suspension 13, which correspond reciprocally with the anchoring posts. To accommodate the deflection of the GK expected due to wind force, a type of swing structure 16 is located on the turntable, in which the pivoting safety chamber 17 can move.is attached to robust support beams 18 and a pivoting device 19; inside the safety chamber 17, a large cable drum is centrally suspended, with sensor- and computer-assisted high-speed winding motors 21 located on the left and right sides, as well as a safety cell 22 located above, which has a spring-damping unit 23 inside, the purpose of which, among other things, ensures the controlled, non-critical and, thanks to the integrated spring-damping unit 23, effectively and efficiently decelerated retrieval (elevator principle) of the wind converter (=WK) and / or airship (=LE; gas-filled ascending balloon or a Zeppelin [keel- / inflation airship]), in order to be able to carry out any maintenance work and, in particular, in an emergency situation (risk of crash), to move the GK ultra-fast into a safety cell 22, which is designed so that the WK assembly and / or the airship assembly can be ideally maintained by the fitters.to be retrieved; for this purpose, the holding cable 24, which preferably consists of an inner sheath (= electrical conductor cable) and an outer sheath, is used. Its primary function, in addition to the actual holding and retrieval function of the GK, is to conduct the current flow from the generator 31 to the ground station 10. Above the safety chamber 17, there is a stable and durable airbag unit 22a, which is equipped with several integrated, smart air release valves (damping function), which optimally decelerates the cost-intensive WK in a gentle manner. Furthermore, there are several, preferably two, pivoting and motor-controlled pivot arms on the turntable 11, arranged 180 degrees apart and secured with support devices 25, which additionally secure the WK with the spacer safety cables 25.In particular, this is intended to counteract any potential drifting of the wind converter in strong winds, and the preferred installation on the turntable 11 prevents twisting of the tensioned cables. The distance safety cables are also wound on high-speed cable drums, and before the wind converter assembly can be secured in the safety cell, the telescopic swivel arms, which are 180 degrees apart, are positioned lengthwise so that the tip remains significantly higher. In an emergency situation (e.g., a crash scenario), the wind converter can be decelerated in a controlled manner via its tether connection via the smart control unit (= negative gravitational acceleration) before the wind converter impacts the airbag system 22a located on the safety cell 22, thus progressively preventing significant fall damage.

[0112] Fig. 3 shows a schematic side view of the swing construction in which the safety chamber 17 can pivot back and forth on ball bearings depending on the wind strength and the correlating deflection of the GK. Fig. 4a again shows the base plate assembly 10 with the additional sensor and computer-assisted, electrodynamically and / or electro-pneumatically controlled, preferably 180-degree pivot arms 25 located on the turntable 11, which are additionally held in position by telescopic supports 90, as well as the cable deflection pulleys 60 positioned at the upper end and the high-performance cable drums / cable winches 91 located on the ground, driven by a smart and electrically operated control unit, with the respective position holding cables 26; these high-performance cable drums / cable winches are intended to, in an emergency situation (risk of falling), prevent the various braking units (e.g.

[0113] Braking parachutes) or in particular the wind converter assembly faster to the ground group orto the safety cell vertically, like a plumb line, pulled downwards, as if they were to fall downwards due to gravity, in order to completely rule out any risk to life and limb, and by braking the wind converter assembly with the help of the safety cell 27 integrated in the system safety chamber 17, on the angle-controllable airbag unit / s 22a located at the upper end, as well as the spring-damping unit 23 installed inside, plus in interaction with the pivoting telescopic arms 25, which in a fall scenario should be spread out at an angle in which they should still be positioned significantly higher than the edge of the system safety chamber in order to be able to brake the wind converter assembly in a controlled manner using the taut position holding cables 26, so that in the sum of the described and installed braking systems, the fall damage for the entire system or for the wind converter assembly can be minimized.

[0114] As an additional braking system and to further increase the desired overall braking force (negative acceleration), the rotor unit of a horizontal wind converter 38 should preferably be activated in such a way that the braking effect is additionally achieved through the autorotation of the rotor. In such an emergency situation (= crash scenario), such an emergency maneuver should be carried out automatically using the smart control unit. The sequence of activities to be carried out must be strictly observed as follows:

[0115] 1. the anchor weight 32, if installed, must be separated from the internal structure 28 by means of the compressed air-filled detonators and / or electromagnetic clutch 78,

[0116] 2. The telescopic arms 34, which are used to fix the inner structure in order to bring the rotor unit ideally into the wind (= LUV), should then be separated from the fastening point of the inner structure by the attached, compressed air-filled detonators and / or electromagnetic clutch 78, so that the inner structure becomes freely movable,

[0117] 3. In parallel, the controllable or movable rotor blades are turned out of the wind,

[0118] 4. the brake parachute 82 installed at the bottom dead center of the inner structure 28 is activated first and when the rotor unit together with the inner structure 28 is to be in the desired horizontal position

[0119] 5. the brake parachute, which is also located on the inside of the internal structure but at the top dead center, is activated by the smart control unit in order to keep the rotor unit in the optimal, horizontal position so that the autorotation is triggered and its maximum braking effect and the two brake parachutes 82 located and acting on the sides achieve a synergistic braking effect.

[0120] Fig. 4b shows, in addition to Fig. 4a, a mobile version provided with vertically adjustable independent wheel suspension 13 and steerable wheels 13, in which the base plate 10 with the integrated turntable 11 is anchored to a type of lifting platform, which is preferably anchored by 4 support pillars and with the help of which the base plate together with the installed system safety / maintenance chamber and the preferably electro-pneumatic and / or hydraulically extending to the ground through the running channel 94 located in the support pillars as well as the countersunk nose 93 anchored in the base plate can be lowered, thus making it much easier to reach the maintenance-intensive wind converter assembly as well as the airship assembly, which can be pulled down as needed using the holding cable 24 on a cable winch attached to the base plate.

[0121] Fig. 5 shows the schematic view of the BG wind converter consisting of an outer structure 27 (round or elliptical circle or rectangle) and an inner structure 28 (round or elliptical circle or rectangle) and a vertical wind turbine suspended inside the inner structure (here a Darrieus rotor 30a; could just as well be a Savonius rotor and / or similar rotors), at the upper and / or lower end of which a generator and preferably upstream gear unit 31 is positioned, which is pivotable orpendulum-capable) suspension 33, which always positions the wind converter at 90 degrees perpendicular to the wind direction; furthermore, the vertical position of the wind converter should be maintained by means of sensor- and computer-assisted, electro-pneumatic or electro-hydraulic telescopic arms 34, each positioned at the lower area between the outer and inner construction, and preferably an additional, aerodynamically shaped anchor weight 32 attached to the lower end of the inner construction, which can be released in an emergency situation by means of the preferably compressed air-filled detonators or electromagnetic clutches 78 and preferably a brake parachute 82, in order to be safely separated from the GK and / or wind converter assembly and to glide to the ground.

[0122] Fig. 6a also shows the BG wind converters. In addition to Fig. 5, for further support of alignment into the wind, a controllable rudder 44 is preferably located on the left and right sides of the wind converter, as well as the previously described position-holding cables 26, which can preferably be released ultra-quickly in an emergency situation by means of mounted, compressed air-filled detonators or electromagnetic clutches 78. In the center of the vertical wind converter (Darrieus rotor 30a), a tensioning device 95 (individual, thin tension cables) running from one rotor blade to the other rotor blade should preferably be tensioned. One of the rotor blades should preferably contain the tear-resistant, durable sail material, which is pulled and tensioned by the opposing rotor blade through the internal tension system, thus creating a high braking resistance.In order to be able to additionally decelerate the BG in an emergency situation (crash scenario); additionally and preferably, there should be compressed air-filled detonators or electromagnetic couplings 78, preferably positioned on the outside, at the upper and lower ends of the inner structure 28, as well as a braking parachute each, so that in an emergency situation (crash scenario), by individual, situation-dependent detachment of the wind converter assembly, it can be brought into the horizontal position and, above all, held in place to support the Darrieus rotor 30a by the staggered pulling of the braking parachutes 82 positioned at the bottom and top, so that the preferably integrated sail material located between the two rotors can provide its optimal additional braking effect.

[0123] Fig. 6b shows, in contrast to Fig. 6a, a horizontal rotor blade converter 30b and, for illustration, an embodiment of the mounting of an electrical conductor 45b starting from the generator unit 31.

[0124] Fig. 6c shows, in addition to Figs. 6a and 6b, the positioning of compressed air-filled detonators or electromagnetic couplings 78 including the included brake parachutes 82; the detonators are intended to separate the fixed telescopic arms 34 from the inner structure 28.

[0125] Fig. 6d illustrates the final position of the BG Wind Converter or that of the wind turbine (here a rotor blade converter 30b) in an emergency situation (crash scenario) with the aid of the two included, smartly controllable (important: time-delayed) brake parachutes 82, which are intended to bring the inner structure 28 including the wind converter into the horizontal plane and hold it in place in order to bring the rotor of the wind converter into "autorotation" so that the fall speed of the BG Wind Converter in interaction with the brake parachutes is maximized and a low-risk securing of the BG Wind Converter including additional equipment can be guaranteed.

[0126] Fig. 7 also shows schematically the BG wind converter, but with a horizontal WK with an oversized, db with fixed rotor blades 39 or by electro-pneumatically and / or electro-dynamically variable, telescopic rotor blades in size, length and area variable, whose area and dimension is larger than the outer construction 27, so that when activated, i.e. the rotor blades 39 in the wind

[0127] (= LUV), the rotation of which would damage the outer structure and the rotor blades, and in the expected high wind speeds, even completely destroy them. To solve this problem, the outer structure 27 is to be constructed in only half, with additional, stable outer arms 41 on the left and right sides, which in turn stabilize the entire assembly with a stable lower connecting element 37 and corresponding stable holding cables 48 or rods. The also attached outer positioning cables 26, which run to the ground station 10, are attached directly to the outermost end of the side arms.

[0128] Fig. 8 also shows a BG wind converter with a horizontal WK, which has a laterally mounted tail unit 42 with an elevator 44 and rudder 43 located at the rear.

[0129] Fig. 9 shows the schematic view of a BG wind converter with a vertical wind turbine (here a Darrieus rotor 30a), which is located within a rectangular outer and gimbal-mounted 33 inner structure 28; furthermore, the wind turbine is provided with a generator 31 mounted below and / or above, preferably with an upstream gearbox, so that the generated current can flow directly into a primary circuit via the conductor integrated in the holding cable 24 directly to the ground station and indirectly into a demand-optimised secondary circuit, which, among other things, supplies the cable winches 47 of the holding cables 48 in the individual assemblies (ground station, wind converter / wind turbine, airship with linked flight parachute) as well as for the operation of a flight initiation device (55 or 56 or 57) with power for their propulsion.

[0130] Fig. 10 a shows a wind converter with horizontal WK 38 and integrated rotor unit with at least one or more, preferably 3 rotor blades 39 and a tail unit 42 with elevator 43 and rudder 42 located at the rear. Fig. 10 b shows a wind converter with horizontal WK 38 and integrated rotor unit with at least one or more, preferably 3 rotor blades 39 and a tail unit 42 with a horizontal propeller unit 45 located at the rear and supplied electrically via the secondary power circuit.

[0131] Fig. 11 shows a schematic view of a TWIN rotor unit 40, the front and rear of which are equipped with a rotor unit with one or more, preferably three, rotor blades, which are mutually driven by the wind to successfully counteract occurring torque forces; the rotor blades of the front rotor unit are preferably smaller than those of the downstream rotor unit.

[0132] Fig. 12 shows, in addition to Fig. 5, a connected tail unit 42 to additionally supplement the turning into the wind (= LUV).

[0133] Fig. 13 also shows the BG wind converters and, in addition to Fig. 5, a "smart", controllable rudder 44 is preferably located on the left and right side of the WK to further support alignment into the wind.

[0134] Fig. 14 shows an example of a flight initiation apparatus of the corresponding parachute 49, namely a preferred kite 54; kites are basically light aircraft and fly independently even in light winds and are easily controllable and manageable flying objects thanks to a smart control system.

[0135] Fig. 15 shows a schematic view of the last assembly, the airship (= LU), which consists of a gas-filled (helium and / or hydrogen) ascending balloon or zeppelin 46 (keel or inflated airship), various sensor- and computer-controlled, electrically driven cable winches 47 and corresponding holding cables 46, an air canopy 49 (a type of spinnaker on a sailing ship, only stiffened with an additional exo-skeleton 50) which is attached directly to the ascending balloon in the deactivated state and which is stretched tightly around the ascending balloon like a second, but max. half-sized ascending balloon skin, which is brought into the wind with the aid of a light, independently flying kite or dragon which is attached to the air canopy and is wound up and unwound with the aid of the cable winches, so that the kite then takes over the function of a kite in order to maximize the ascending power of the GK.

[0136] The schematic representation in the upper part shows a suspended parachute 49, with the exoskeleton 50 shown here, the associated control unit 51 located in a cylinder, inside which is a spring / damper unit 52 and a piston 53 as a de- and activation control unit, which is regulated by electro-pneumatic and / or electro-hydraulic, sensor and computer-assisted, whose power source is the secondary circuit, as well as the flight initiation apparatus (here a kite 54) located at the end of the GK is pulled into position so that it can be pulled into position immediately after the de-coupling from the gas-filled ascending balloon 46, which is controlled at any time by the sensor and computer-assisted electric cable winches, and subsequent activation of the exoskeleton mechanism and thus the desired tensioning of the parachute 49 and the resulting gliding function,in order to synergistically increase the buoyancy forces of the gas-filled ascending balloon / Zeppelin 46.

[0137] The parachute can also act as an additional braking parachute for the assembly in an existing emergency situation (crash scenario).

[0138] Fig. 16 shows an embodiment, also with a tandem flight, which, instead of the kite or hang glider mentioned in Fig. 14 / 15, which is required for the necessary initiation and ascent of the parachute, is replaced by a software- and sensor-supported drone equipped with several turbofans (= sideprops), preferably four, to provide the necessary "assistance in delivery." The drone is to be powered either by the on-board electrical secondary circuit (preferred) and electrical connection cable, or alternatively by carrying a small, lightweight engine powered by fossil fuels and a small fuel tank.

[0139] After successful work and successfully flying the parachute 49, the kite / dragon or drone should preferably detach itself from the parachute using the tether separation device (integrated separating disc) located on the parachute 49 and float independently to the ground or, ideally, directly to the ground station using the attached, preferably steerable, brake parachute 82 and be re-mounted on the parachute during the next maintenance work on the GK in order to be able to resume its function the next time the GK is launched.

[0140] Fig. 17 - 19 schematically shows the advance of an activated air umbrella 49, in particular the release mechanism, whose control unit is located in a safety cylinder 51 inside the air umbrella and within the recess in the central axis of the airship 46 to prevent any flying sparks and the associated risk to the gas-filled airship. Inside the cylinder is an electro-pneumatic or electro-hydraulically driven tensioning device, which, with the help of the secondary circuit of the generator and / or emergency power (if installed), is maintained by an on-board accumulator, which consists of an activatable piston 53 and a spring / damper element 52 for counter-regulation, as well as a smart control unit for carrying out the tensioning / relaxing process of the integrated exoskeleton 50 and the associated flight capability of the air umbrella.

[0141] Fig. 20 demonstrates an alternative embodiment in that instead of the preferred tandem variant consisting of, for example, an initiation kite and an optimally controllable parachute, a kite construction is used, wherein the folded towing kite 59 is located on a kite luggage carrier 58, which is positioned directly on the ascending balloon in its slipstream and which is connected by means of a sensor and computer controlled cable winch 47 fed by the secondary circuit, a directly connected deflection pulley 60 and a second deflection pulley 60 positioned somewhat to the side, higher than the first deflection pulley, as well as the kite luggage carrier directly connected by towing cables 62 and indirectly to the towing kite.The launching process of the towing kite is initiated in such a way that, in the first step, the movable kite carrier 58, which is optimally located in the slipstream, is first pulled into an inclined position (like a launching ramp) by the towing cables in order to give the towing kite an ideal launching position, and then take off with a strong pull on the holding cables.

[0142] Fig. 21 shows, in addition to Fig. 20, the placement of the kite luggage carrier 58 including the folded towing kite 59, which is positioned on an installed double tail unit 61, preferably in the slipstream area of ​​the aircraft and in front of the deflection pulley 60

[0143] Fig. 22 shows, in addition, a bird's eye view of the positioning of the folded towing kite 59 and the kite luggage carrier 58 as well as the lower pulley 60 on an installed, simple tail unit 42.

[0144] Fig. 23 shows a schematic representation of an alternative, inactive towing kite mount, including the folded towing kite 59, mounted on a movable trigon sight 64, which is mobile by means of a center rail 67 located on the airship and the axial guide rails 68 positioned on the right and left sides of the airship. The movable trigon sight can only move between the fixed position stoppers 69, with the path being oriented towards the maximum deflection of the towing kite. Furthermore, a kite is attached to the towing kite, which together with the towing kite forms a flight tandem, particularly during the flight initiation phase.

[0145] Fig. 24 shows, in addition to Fig. 23, a schematic representation of an activated flight tandem, ie the quite efficient, self-flying kite first brings the trigon visor 64 optimally into the wind so that secondly it pulls the towing kite into the optimal ascent position and then the kite is independently separated from the towing kite as already described and flies or falls slowly back to the ground station or on the ground with the help of the brake parachute 82 attached to the kite and then activated.

[0146] Fig. 25 schematically shows a single tail unit 42 as well as a double tail unit 61, which additionally have a gas-filled chamber in the middle section in order not to reduce the generated lift force available to the GK as a whole, because each component is naturally pulled downwards by gravity and is diametrically opposed to the lift force.

[0147] Fig. 26 shows, in addition to Fig. 23, the central middle rail 67, which is necessary for guiding the movable trigon sight.

[0148] Fig. 27 shows a schematic cross-section of the stable safety hoses 70 located in the flight unit. These hoses, in order to prevent a latent emergency risk, preferably also have separate gas chambers (segments) 71, preferably constructed according to a "honey comb" structure. Furthermore, each gas chamber has an inlet / outlet valve for gas pressure regulation, a pressure sensor for comparing the desired and actual pressure, and a gas supply network that fills the individual gas chambers via a liquid gas tank. The individual safety hoses 70 are arranged centrally around the central axis 74 of the flight unit and are mutually secured. The robust outer shell of the flight vessel is tensioned to protect them.

[0149] Ideally, any airship design should have a lightweight and very stable tubular frame construction to prevent deformation caused by strong winds. The safety tubes are protected from the prevailing weather conditions by the airship's robust, preferably sharkskin-like outer skin.

[0150] Fig. 28 shows, in addition, the safety hoses 70 stacked on top of each other, which are arranged around the central axis 74 of the aircraft from a bird's eye view.

[0151] Fig. 29 shows a schematic view of the gas-filled airship with a holding box 76 installed in the lee and an integrated safety capsule 77, in which the resistant and stable liquid gas tank 80, which can be filled from the outside at any time, as well as the gas evaporation unit 81 preferably located within the safety cell and a gas line 83 running to the gas supply network 75 of the airship, as well as the very robust holding belts with integrated safety holding lock 79 running outside the safety cell and preferably the compressed air-filled detonators and / or electromagnetic clutch 78 mounted directly on the holding lock, in order to separate the safety cell including the dangerous liquid gas tank from the airship in an emergency situation (crash scenario) and to use the integrated brake parachute 82 and the / the several sensor and computer-controlled,at least one airbag(s) 88, which preferably inflates around the entire safety cell using the compressed air-filled propellant charge carried on board, as well as with a preferably battery-operated control unit or purely mechanically triggered gas release valves located in the outer shell of the airbag(s), which will thus bring the safety cell undamaged and safely to the ground, and the valves create an additional damping effect in case the safety cell bounces on the ground due to the impact.

[0152] Fig. 30 shows an alternative gas supply by taking along a water-filled safety tank 87, a water pump 84 and an electrolyzer 86, a gas pressure pump which feeds the hydrogen produced by the electrolyzer, which receives its power from the power line located in the holding cable 88 and is directly connected to the secondary power circuit of the generator, which is fed through the gas line 83 directly into the gas supply network 75 installed in the aircraft.

[0153] Fig. 31 shows an additional alternative for gas supply using a liquid gas tank, gas line and high-pressure gas pump located on the ground station, so that the line cross-section can be kept very small and thus the latent risk potential is reduced to a minimum, since in an emergency situation and an unintentional disconnection of the gas line the gas supply is stopped immediately and if there is gas in the line at that moment, the amount of gas would not pose a great danger to the overall structure; it is intended that the gas line only opens to fill any gas chambers when the control unit installed in the GK detects a gas loss and automatically starts the filling process, and for the majority of the rest of the time the gas line remains unfilled and with a high-pressure gas pump installed this requirement is achievable and desirable.The gasification unit on board the airship is designed to safely convert the liquefied gas from a liquid to a gaseous state as needed for filling the gas chambers. Gas filling during maintenance work is carried out alternatively and thus directly via the gas filling nozzle for refueling Airship 89, which is located directly on the airship.

[0154] As an additional design alternative, the safety capsule 77 can also contain a conductive accumulator 86b, which is permanently charged by the secondary circuit in order to be able to safely supply the entire system or its components with power in any situation in an emergency situation (e.g. crash situation and total failure of the secondary circuit) and the resulting failure (residual risk) of the on-board safety architecture (e.g. various control devices, brake parachutes, etc.). If the generated direct current should cause problems with regard to compatibility with the consumers to be supplied, a transformer should transform the direct current generated by the generator into alternating current.

[0155] List of reference symbols

[0156] GK overall construction

[0157] W Wind

[0158] H-GWKA high-altitude wind turbine

[0159] WKA wind turbine

[0160] WK wind converter / wheel

[0161] LU airship

[0162] BG assembly

[0163] RI rotor rotation axis left

[0164] Rr Rotor rotation axis right

[0165] Smart sensor- and software-supported, algorithm-based, current-dependent control unit

[0166] I Ground station

[0167] 10 Base plate

[0168] II Turntable

[0169] 12 steerable wheels

[0170] 13 Height-adjustable independent suspension

[0171] 14 anchoring piles

[0172] 15 thread and drill head

[0173] 16 Swing construction

[0174] 17 Plant safety chamber / maintenance box

[0175] 18 Support bracket safety chamber

[0176] 19 Swivel device

[0177] 20 large cable drums

[0178] 21 high-speed winding motors Safety cell, with an angle-adjustable airbag construction at the upper end

[0179] 23 Spring-damper unit

[0180] 24 Holding rope, preferably with integrated electrical conductor

[0181] 25 pivoting telescopic arms

[0182] 26 position holding ropes

[0183] 11 Wind converter / wind turbine unit

[0184] 27 Exterior construction 28 Interior construction

[0185] 29 Rudder

[0186] 30a Darrieus Rotor

[0187] 30b rotor blade converter

[0188] 31 Generator and transmission unit

[0189] 32 anchor weight

[0190] 33 gimbal suspension

[0191] 34 telescopic arms

[0192] 35 Rudder control unit

[0193] 36 connecting struts

[0194] 37 connecting segment

[0195] 38 horizontal wind converter

[0196] 39 Rotor unit with rotor blade(s)

[0197] 40 TWIN rotor unit

[0198] 41 structural side arms

[0199] 42 Single tail unit

[0200] 43 Elevator

[0201] 44 Rudder

[0202] 45a horizontal propeller unit

[0203] 45b conductor cable

[0204] III Airship gas-filled ascending balloon / Zeppelin (keel airship / inflation airship) with integrated tubular frame

[0205] 47 cable winches

[0206] 48 holding ropes

[0207] 49 Parachute

[0208] 50 Exoskeleton

[0209] 51 cylinder control unit

[0210] 52 Spring / damper element

[0211] 53 stamps

[0212] 54 Flight Initiation Kite

[0213] 55 Flight Initiation Kites

[0214] 56 Flight Initiation Drone

[0215] 57 Sideprobs (fan units) IV Primary towing kite

[0216] 58 towing kite luggage carriers

[0217] 59 Folded towing kite

[0218] 60 pulley

[0219] 61 twin tail

[0220] 62 towing ropes for towing kites

[0221] 63 Gas-filled chamber

[0222] 64 Movable trigon sight

[0223] 65 towing kites

[0224] 66 kites

[0225] 67 center rail

[0226] 68 Axial guide rail

[0227] 69 Position stopper

[0228] V Integrated airship safety hose elements

[0229] 70 safety hose

[0230] 71 gas chambers

[0231] 72 intake and exhaust valves

[0232] 73 pressure sensors

[0233] 74 Central axis

[0234] 75 Gas supply network

[0235] VI Gas supply unit

[0236] 76 Holding box

[0237] 77 Safety Capsule

[0238] 78 Compressed air-filled detonators and / or electromagnetic clutches

[0239] 79 Safety belts and fasteners

[0240] 80 LPG tank

[0241] 81 Gasification device

[0242] 82 brake parachute

[0243] 83 Gas pipeline

[0244] 84 water pipe

[0245] 85a water pump

[0246] 85b Gas pressure distribution unit a Electrolyzer b Accumulator (preferably lithium-ion)

[0247] water tank

[0248] Holding rope with power cable for the secondary power circuit

[0249] Gas filling nozzle for refueling the aircraft

[0250] Telescopic supports

[0251] High-performance cable drums or winches

[0252] Support pillars

[0253] countersunk nose

[0254] Running channel

[0255] clamping device

[0256] Separator holding rope robust, sharkskin-like structured outer skin

Claims

Patent claims 1. A wind turbine (WKA), comprising: a ground station (1), a holding cable (24), a wind converter (WK), and an airship (LU); wherein the airship (LU) is connected to a base plate (10) of the ground station (1) via the holding cable (24); wherein the wind converter (WK) has a rotor (30) and a generator (31) connected to the rotor (30); wherein the airship (LU) has a flight initiation device, and wherein the wind converter (WK) is arranged on the holding cable (24) in the region between the base plate (10) and the airship (LU), preferably underneath the airship (LU), characterized in that the wind turbine (WKA) further comprises a safety and security device which is integrated in the region extending from the base plate (10) to the airship (LU). 2 Wind turbine (WKA) according to claim 1, characterized in that the base plate (10) comprises a turntable (11) which is rotatably mounted relative to the base plate (10), wherein on the turntable (11) there is a plant safety chamber (17) in which a safety cell (22) is integrated, which is equipped with a spring-damper device (23). 3 Wind turbine (WKA) according to claim 1 or 2, wherein the ground station (1) further comprises at least one controllable airbag device (22a), wherein the airbag device (22a) is preferably arranged in the region of an upper end of the safety cell (22). 4 Wind power plant (WKA) according to claim 2 or 3, characterized in that the plant safety chamber (17) further comprises a large cable drum (20) which is driven by at least one high-speed motor (19), which is preferably located on the right and / or left side of the Large cable drum (20), wherein the at least one high-speed motor (19) is designed to wind the holding cable (24) onto the large cable drum (20) at a high rotational speed.

5. Wind turbine (WKA) according to one of the preceding claims, characterized in that the holding cable (24) comprises an integrated electrical conductor (24a). 6 Wind turbine (WKA) according to one of claims 2 to 5, characterized in that the system safety chamber (17) is pivotally mounted relative to the turntable (10), for this purpose the system safety chamber (17) is preferably suspended at the lower end in a movable swing construction and, particularly preferably, to support the alignability, is additionally movably connected to a pivoting device (19) of the system safety chamber (17) via a support bracket (18) of the turntable (11). 7 Wind power plant (WKA) according to one of claims 2 to 6, characterized in that additional pivotable telescopic arms (25) are arranged on the turntable (11), which are preferably 180 degrees to each other and are positioned to the left and right of the plant safety chamber (17), to which a position holding cable (26) is connected via a respective high-performance cable drum (90), which are fastened directly to an outer structure (27) of the rotor (30). 8 Wind turbine (WKA) according to claim 7, characterized in that the high-performance cable drums (90) are not responsible for the vertical movement of the wind converter (WK), but are designed to provide an additional braking function for the wind converter (WK) in a crash scenario. 9 Wind turbine (WKA) according to one of the preceding claims, characterized in that the base plate (10) is designed to be movable by means of vertically movable independent wheel suspensions (13) installed on the base plate (10) and steerable wheels (12) fastened to the independent wheel suspension (13).

10. Wind power plant (WKA) according to one of the preceding claims, characterized in that several, preferably four, automatically acting anchoring piles (14) are arranged on the base plate (10), which are designed to anchor the base plate (10) in the ground, wherein the anchoring piles (14) are preferably each provided with a thread and drill head (15) and are fastened to the base plate 10 11. Wind power plant (WKA) according to one of the preceding claims, characterized in that the wind converter (WK) comprises a vertical (e.g. Darrieus rotor 30a) or a horizontal rotor (30) designed as a wind wheel, which is suspended from a structure of the wind converter (WK), wherein the structure of the wind converter (WK) is preferably constructed from an outer (27) and inner construction (28) and in the middle of which the rotor (30) is suspended gimbal-mounted between the outer and inner constructions (27, 28).

12. Wind power plant (WKA) according to claim 11, characterized in that at the lower end of the inner structure (27) the holding cable (24) is connected to the wind converter (WK) in a load-bearing manner via compressed air-filled detonators or an electromagnetic coupling (78), wherein an anchor weight (32) and / or a brake parachute (82) is preferably arranged at the lower end of the inner structure (27).

13. Wind turbine (WKA) according to claim 11 or 12, characterized in that preferably telescopic arms (34) are arranged between the outer structure (27) and the inner structure (28).

14. Wind power plant (WKA) according to one of claims 11 to 13, characterized in that compressed air-filled detonators or an electromagnetic clutch (78) and / or a braking parachute are preferably located both at the lower end and at the upper end of the inner structure (28), positioned on the outside thereof.

15. Wind power plant (WKA) according to one of the preceding claims, characterized in that the airship (LU) is a gas-filled balloon, preferably comprises a climbing balloon (46) on which a flight parachute (49) is located, which in flight mode will fly close to the gas-filled airship (46).

16. Wind turbine according to claim 15, characterized in that the parachute (49) is pulled upwards by a self-flying, small flight initiation device, for example by a kite (54), a drone (56) or a kite (55), and in the take-off phase, the orientation of the parachute (49) is controlled by smart cable winches (47) which are arranged on the gas-filled balloon and wherein the parachute (49) is connected to the cable winches (47) via cables and wherein the flight initiation device is connected to the parachute (49) via a cable (48).

17. Wind turbine according to claim 15 or 16, characterized in that an exoskeleton (50) is arranged within the flight umbrella (49), which inflates and deflates the flight umbrella (49) after the starting phase with the integrated control unit (51).

18. Wind turbine according to one of claims 15 to 17, characterized in that the flight initiation device comprises a braking parachute (82) which is preferably triggered before the separation of the flight initiation device, by means of a separation device (96) arranged on the cable (48), wherein the braking parachute (82) is arranged at a top dead center of the flight parachute (49).

19. Wind turbine according to claim 18, characterized in that a compressed air-filled detonator or an electromagnetic clutch (78) is arranged as a separating device (96) at the top dead center of the parachute (49).

20. Wind turbine according to one of the preceding claims, characterized in that durable safety hoses (70) are installed inside the airship (LU), which in turn comprise several gas chambers (71) and each have inlet and outlet valves (72) and pressure sensors, which are supplied by the gas supply network (75) installed on board, which runs between the safety hoses (70). and which are protected from the outside by the robust, preferably sharkskin-like structured, outer skin (97) of the airship (LU).

21. Wind turbine according to claim 20, characterized in that a holding box (76) is mounted on the airship (LU) in the lee, with an integrated safety cell (77), in which there is preferably a liquid gas tank (80) with an included gasification unit (81) and a gas line (83) which is directly connected to the gas supply network (75), so that the gas supply to the safety hoses (70) and / or its individual gas chambers (71) can thereby take place.

22. Wind turbine according to claim 21, characterized in that alternatively in the safety cell (77) there is an electrolyzer (86a) for generating hydrogen, a water tank (87), a water pump and a gas pressure distribution unit for the generated hydrogen 23. Wind turbine according to claim 21, characterized in that an integrated accumulator (86b), preferably a lithium-ion battery, is arranged in the safety cell (77).

24. Wind turbine according to claim 21, characterized in that the safety cell (77) is fastened to the holding box (76) by at least one safety belt and at least one closure (79) and in addition at least one compressed air-filled detonator and / or an electromagnetic clutch (78) and a braking parachute (82) are preferably arranged on the at least one closure.

Images