DE202022000839U1 - Load transfer system, redundancy system and functional system for an aerostatic buoyancy device - Google Patents

Abstract

Load transfer system for an aerostatic buoyancy device (1) in the form of a captive balloon, free balloon or airship for lifting or transporting loads in an atmosphere, which has a buoyancy body (2.1) made up of gas-tight or airtight shells (3.1 - 3.n) in the form of foil or membrane-like envelopes (4.1 - 4.n), from which adjustable volumes of the atmospheric medium (5.1 - 5.n) are evacuated by means of an evacuation and supply system (6) and back into them can be admitted, whereby the buoyant body (2.1) are lighter than the surrounding atmosphere and can cause and regulate an aerostatic lift, characterized in that it has a support screen (7), wherein
- The support umbrella (7) consists of a mast (10), suspension cables (11) and a first main anchor (12.1); and
- the mast (10) at one end by means of suspension cables (11) suspended or guyed from the mast (10), which are at an angle greater than 0° and less than 90° to the mast (10), the first main anchor (12.1) carries and thereby passes through the planar plane of the first main anchor (12.1); and
- the first main anchor (12.1) carries at least three shells (3.1 - 3.n) with corresponding at least three shells (4.1 - 4.n) on at least one side of its cross section; and
- The mast (10) is at least partially in the buoyancy body (2.1); and
- the atmospherically or aerostatically caused pressure and tensile forces from the shells (3.1 - 3.n) and corresponding envelopes (4.1 - 4 .n) to the first main anchor (12.1), dated first main anchor (12.1) to the suspension cables (11), and from the suspension cables (11) to the mast (10); and
- a second main anchor (12.2) carries at least three shells (3.1 - 3.n) with corresponding at least three shells (4.1 - 4.n) on at least one side of its cross section; and
- The first main anchor (12.1) is connected to the second main anchor (12.2) by tension cables (14); and
- the buoyant body (2.1) is spatially and structurally delimited, defined or enclosed essentially by the first main anchor (12.1) on the one hand and the second main anchor (12.2) on the other side; and
- in the aerostatic buoyancy device (1) in the embodiment of a tethered balloon or free balloon, the mast (10) at its other end by means of support cables (11) suspended or guyed from the mast (10), which are at an angle greater than 0° and less than 90° to the mast (10), is connected to the second main anchor (12.2); and
- In the aerostatic buoyancy device (1) in the embodiment of an airship, the mast (10) and the second main anchor (12.2) rest on a hull (15) and are attached to it, the hull (15) being subjected to compressive or tensile forces from the buoyant body (2.1) receives, located below or on the lower side of the buoyancy body (2.1), whereby the focus of the aerostatic buoyancy device (1) is lowered or shifted downwards.

Description

TECHNICAL AREA

The technical field of the invention is aerostatics or lighter-than-air technology, which usually includes tethered balloons, free balloons and airships of various types.

BACKGROUND AND PRIOR ART

This invention relates to a further development of the aerostatic lifting device IN 201711018898 , which is mentioned in the preamble of the main claim (claim 1) and the dependent claims. Such an aerostatic buoyancy device is from IN 201711018898 known by the same applicant.

Aerostatic or lighter-than-air buoyancy devices generate aerostatic lift in an atmosphere due to the fact that they are lighter than the bulk of the surrounding atmospheric medium, e.g., atmospheric air, which they displace. For this purpose, the buoyant body of such a buoyancy device, which consists of a shell, is usually filled either with lifting gases that are lighter than air, such as helium or hydrogen, or with hot air, which is also lighter than the ambient air due to the higher temperature (J.K. Bock, B Knauer, "Lighter than air: balloons, airships, platforms", p. This creates either lifting gas-filled balloons and airships (gas balloons and gas airships) or hot-air-filled balloons and airships (hot air balloons and hot airships). However, lifting gas-filled as well as hot air-filled balloons and airships have significant disadvantages.

Balloons and airships filled with lifting gas require large amounts of a lifting gas, mostly helium today, which is expensive to buy. While hydrogen is comparatively inexpensive and offers slightly more buoyancy than helium, it can become highly flammable on contact with air, posing a significant fire hazard. It is therefore generally not used as a lifting gas. In gas-filled balloons and airships, the total mass of lifting gas in an envelope usually remains more or less constant and cannot be regulated significantly, resulting in virtually invariable buoyancy. If the lift is to be reduced in flight, e.g. B. for a descent and a landing, either a certain amount of lifting gas to the atmosphere or entrained ballast must be released as a rule. Since this amount of lifting gas is permanently lost by draining and helium is expensive, draining is largely avoided. However, the carriage of ballast often represents a significant part of the available payload, which therefore cannot be used for other purposes such as the transport of cargo or people. Since most gas-filled balloons and airships cannot generally change lift force significantly, they always remain lighter than air once their envelopes are filled with a lifting gas, necessitating a permanent ground tether for ground handling to prevent them from becoming inflated rise unintentionally or move back and forth in the wind. Because gas-filled balloons and airships are intended to be lighter than air with their payload, they suddenly become much lighter when the payload (e.g., cargo and/or people) is unloaded or disembarked, causing the lifting force on a balloon or airship to suddenly increase increased, as well as the force on the required connection device on the ground. For these purposes, extensive tethering devices and complex ground handling are typically required, making practical balloon or airship operations complicated, time consuming and expensive. There is also considerable natural leakage or diffusion of lifting gas atoms and molecules, such as helium, through the balloon or airship envelope, requiring regular refilling of the lifting gas.

Since the density of hot air is only slightly lower than that of atmospheric air, its lifting capacity is limited and requires large volumes of hot air in an enclosed envelope to produce relatively low lift (J.K. Bock, B. Knauer, "Leichter als Luft : Ballone, Luftschiffe, Platformen”, p. 34f, Verlag Frankenkupplung, 2003, 1st edition). Consequently, the envelope of a hot-air balloon or hot-airship must be large in order to be able to lift or transport a relatively small payload. Hot air balloons and hot airships also require large amounts of thermal energy to heat the air in their envelope. This is usually provided by a burner with a combustible gas such. propane, carried in cylinders in compressed liquid form, consuming a significant portion of the available payload and significantly increasing the overall weight of the hot air balloon or hot airship. Because hot air balloons and hot airships typically require a burner to heat the air in the envelope, with the burner usually placed in or near an opening in the envelope, there is a risk of fire if an envelope catches fire that may be increased by wind.

Because of these limitations, there is the idea of generating aerostatic lift through a vacuum. The evacuation of a buoyancy body filled with atmospheric air can make it lighter than the ambient air it displaces. Using a vacuum to lift a balloon or airship offers several advantages. On the one hand, there is no need for a lifting gas such as helium or hydrogen or for hot air, including the required thermal energy. This means considerable cost savings. There is also no risk of fire like there is with hot air balloons. On the other hand, a vacuum offers more buoyancy per cubic meter than a lifting gas or hot air, since the mass of the lifting gas or hot air is omitted. Thus, either the dimensions of the buoyancy body could be reduced or more payload could be lifted or transported with the same size. A buoyancy regulation can also be implemented in a relatively simple manner in that the air volume in the buoyancy body is regulated. For takeoff and ascent, air can be evacuated from the buoyancy body to make it lighter than air; for landing and descent, air can be let into the buoyancy body to make it heavier than air. This also simplifies ground handling, since a vacuum balloon or airship can be maintained in a heavier-than-air condition for loading and unloading a payload on the ground, so that, for example, unloading the payload does not result in an unintentional ascent of the balloon or airship leads. This also eliminates the need for cumbersome holding devices and their operation by ground personnel.

However, until now it has not been possible to make practical use of vacuum-based aerostatic buoyancy because no material is strong and at the same time light enough to withstand the considerable force of atmospheric air pressure (approx. 101 kPa on the surface of the earth) acting on an evacuated lifting device would to withstand. Thin, sheet-like hull materials, while lightweight, cannot withstand the full range of atmospheric pressure. During an evacuation, they initially bend severely, usually deform plastically and finally tear. Denser hull materials, such as sheet metal, are too heavy for larger gauges and too sensitive to pressure for smaller gauges or not rigid enough to compress and eventually tear or break as well.

The main challenge for utilizing vacuum-based aerostatic lift is therefore a structural and material-technical one, and consists of developing a supporting structure for the lifting body of a vacuum balloon or vacuum airship that can withstand the atmospheric air pressure and is light enough at the same time. Approaches to a solution are known which are limited to a planar arrangement of wall-like buoyancy body limitations and which are rigid and stiff and act as a single layer. Such buoyant body limitations extend along the entire buoyant body surface and form a rigid lattice or frame network. In their entirety, these form a support structure which is intended to absorb the forces caused by the air pressure. The entire atmospheric air pressure is absorbed by a single, wall-like buoyancy body, which is used for pressure-related load transfer and gas-tight room closure. Hollow bodies are known, including composite constructions and multi-layer honeycomb structures, which serve as buoyancy bodies, but where the load-bearing and space-enclosing layer, in view of the air pressure difference between the evacuated hollow body and the ambient atmosphere, is a monolayer, i.e. singular, buoyancy layer with a single envelope, which has to absorb the entire atmospheric air pressure difference between the evacuated hollow body and the surrounding atmosphere as well as the associated compressive and tensile forces.

A planar arrangement of rigid, rigid, wall-like and single-layer buoyancy boundaries covering the entire surface of the buoyancy body leads to a high weight with sufficient resistance to air pressure-related forces, since the buoyancy body boundaries are made of solid materials with high densities and the lattice or frame network forms a close-meshed support structure. In order to absorb the entire air pressure in a single-layer or individual buoyancy device limitation, sufficiently dimensioned elements, material thicknesses and strengths are also required, which also increase the weight.

From the IN 201711018898 a distribution of the forces caused by air pressure over several layers of buoyancy bodies, which are called shells, is known. Controllable volumes of the atmospheric medium, such as ambient air, are evacuated from these airtight or gas-tight shells in the form of foil or membrane-like shells, which lie one inside the other and are separated by distances, and then let back into them, which means that the buoyant body can be lighter or heavier than the surrounding atmosphere and thus causes and regulates an aerostatic lift. At the same time, only a (fractional) part of the total air pressure-related forces acts on one shell, since these are distributed over several shells. This results in a sequence of shells in which the degree of evacuation can be increased stepwise or stepwise from the outermost shell closest to the ambient atmosphere to the innermost shell of the buoyant body furthest away from the ambient atmosphere.

Even if the envelopes themselves are able to absorb the air pressure-related forces, distributed over several envelopes, due to their tensile strength, it is not clear how the supporting frameworks (structural frameworks) absorb these forces, which in their sum correspond to the entire air pressure difference between the buoyancy body and the correspond to the ambient atmosphere, structurally further and finally derive, since no structurally stiffened or anchored support system is described. Thus, although the air pressure-related forces that act on a membrane or film-like shell of a shell can be absorbed with assumed slight deflection and excluded cracking, however, in the IN 201711018898 no complete or structurally realistic force dissipation with reference to the entire buoyancy body is described, ie according to the description there is no absorption of the forces occurring after they act on the envelopes.

IN 201711018898 describes a series of supporting frameworks ("structural frameworks") of a buoyancy body, which are intended to absorb the forces caused by the air pressure from the envelopes, such as a series of rings ("series of rings"), helical supporting elements ("helixes") , Nets ("meshes and nets"), load-bearing surfaces ("load-bearing surfaces"), including at least one additional load-bearing element ("structural element"). However, the naming of these load-bearing frameworks and load-bearing elements does not represent a complete or functioning load-bearing system. No force dissipation or interaction of the named elements in a structurally coherent system is described.

On the one hand, it is unclear how a mere series of rings is supposed to absorb and dissipate the high compressive and tensile forces acting on a shell. No structural bracing, mounting or anchoring is described. With the atmospheric forces involved in an evacuation, even at low evacuation rates, rings connected in a row connected to an envelope would tip to different sides and twist, while the envelope would rupture or become damaged. It is also not described how an additional support element could prevent or exclude this. It is also not mentioned how the support elements interact. The situation is similar with helical load-bearing elements, which would also behave structurally like a series of rings that are not anchored or not braced. The naming of nets and load-bearing surfaces describes neither a complete and structurally self-contained transmission nor a final absorption of the air pressure-related forces, since no bracing, mounting or anchoring is described here either. In structural terms, flexible nets behave in a similar way to the flexible, foil or membrane-like shells and cannot serve as reinforcement, support or anchoring. Bending-resistant or rigid nets can have a certain amount of stiffening, but this requires greater material thicknesses to prevent buckling, which increases the weight considerably, so that such nets should not be applicable for an aerostatic buoyancy device. Structural analysis of load-bearing surfaces is similar to that of rigid or resistant nets. Greater material thicknesses would also be necessary here due to the risk of buckling, but this would increase the weight so much that no usable aerostatic lift would arise.

In addition, the IN 201711018898 a separate supporting framework ("structural framework") for each individual shell ("shell"). According to their description and main claim, each shell consists of an air-tight membrane supported by a supporting framework. Such an arrangement is associated with a considerable weight, since the weight of relevant load-bearing frameworks increases rapidly with a sequence of several shells. This is particularly the case with the load-bearing frameworks described, ie rings, helical supports, webs and load-bearing surfaces, since these require compressive strength and bending stiffness that can only be provided by dense, pressure-resistant or solid materials such as metals or metal alloys. as described in the description and the relevant claims.

Due to the explanations given above, IN 201711018898 does not describe any usable or implementable supporting structures for the aerostatic lifting device described.

Since the primary challenge with vacuum or negative pressure based aerostatic buoyancy devices is to accommodate the significant forces caused by air pressure in a load-bearing yet lightweight structure, their structural design, along with critical structural details, is of paramount importance to ensure functionality and practicality. For this purpose, a load transfer system is required that provides the necessary structural stiffening and strength while being light enough to fully absorb the forces of air pressure and provide useful aerostatic lift.

Another central challenge of vacuum-based balloons and airships is the avoidance and minimization of a loss of lift during flight in cases where the air or gas tightness of the lifting body cannot be guaranteed due to cracks or breaches. Since the air pressure difference between the interior of a buoyant body and the surrounding atmosphere is at most atmospheric pressure, on the earth's surface approx. 101 kPa, a rapid pressure equalization between the buoyant body and the surrounding atmosphere can take place if a buoyant body cracks or breaks through. This is accompanied by a considerable suction effect, ie due to the difference in air pressure, larger quantities of air can be quickly sucked from the surrounding atmosphere into the buoyant body through a crack or opening in the shell of a buoyant body. This can lead to an enlargement of the tear or breach, which can further damage the envelope of a buoyancy device, and to a complete loss of aerostatic buoyancy, as the buoyancy device's vacuum is entirely replaced by atmospheric air and it is now heavier than air to the ground sinks.

In this context, IN 201711018898 exclusively describes a single, i.e. singular, buoyancy body in the sense of a single functional unit. In the event of a hull rupture or breach, the appropriate shell would fill either with ambient atmospheric air or with air from the adjacent shell, depending on its position in the shell sequence. In both cases, this would lead to an imbalance in the air pressure-related force distribution on the shells and supporting structure. The resulting severe hull deflections can damage further hulls and cause a complete loss of aerostatic lift. In the event of a simultaneous breach of all envelopes, the vacuum or negative pressure of the buoyancy body would be completely replaced by atmospheric air, while the shells and the buoyancy body as a whole quickly fill with atmospheric ambient air, becoming heavier than air and sinking to the ground. The described subdivision of a shell into at least two parts by means of a skin layer does not change this, since a single skin layer in shells further inwards would not be able to withstand the increased air pressure resulting from a breach or tear within the shell. This means that a single puncture or tear can result in damage to all of the envelopes and their supporting structure, as well as a complete loss of aerostatic lift. A single buoyancy body thus offers no redundancy in the event of hull tears or breaches and loss of buoyancy.

In addition, from the IN 201711018898 known that a propulsion system for the aerostatic lifting device can optionally be located within a shell. However, it is not clear how the weight of a relatively heavy propulsion system in relation to the shells is to be absorbed. No load transfer for a drive system within a shell is described. The description of the hulls and their supporting framework does not indicate sufficient load-bearing capacity for a propulsion system. The high compressive and tensile forces that occur when installing and operating a drive system require a functional and coherent support structure.

Furthermore, the atmosphere known from IN 201711018898, in which the aerostatic buoyancy device is operated, is exclusively air from the earth's atmosphere. However, an aerostatic lift can also be generated and controlled by the evacuation and supply of another atmospheric medium from or into the shells, since this lift can in principle take place in any atmosphere in which the aerostatic lifting device is lighter overall than the volume displaced by it the surrounding atmosphere. Thus, with an appropriate design of the evacuation and delivery system of the aerostatic lift device, it can also reside in other atmospheric media, i.e. atmospheres, and generate and control aerostatic lift in another planetary atmosphere, such as that of Mars or Venus.

OBJECT OF THE INVENTION

1. (a) ein Lastabtragungssystem bereitzustellen, das ein baustatisch vollständiges, gewichtssparendes und effizientes Tragsystem darstellt; und
2. (b) ein Redundanzsystem bereitzustellen, um einen aerostatischen Auftriebsverlust infolge eines Hüllenrisses oder -durchbruches zu vermeiden, minimieren oder kontrollieren, und die betriebliche Resilienz des aerostatischen Auftriebsgerätes zu verbessern; und
3. (c) ein Funktionssystem bereitzustellen, das die aerodynamischen, aerostatischen und betrieblichen Eigenschaften energie- und gewichtssparender, effizienter und praktikabler gestaltet.

In this prior art, the invention is based on the object of an aerostatic buoyancy device (1) in the form of a captive balloon, free balloon or airship for lifting or transporting loads in an atmosphere, wherein the buoyant body (2.1) of the aerostatic buoyancy device (1) consists of gas or airtight shells (3.1 - 3.n) in the form of foil or membrane-like shells (4.1 - 4.n) that are separated by distances and from which adjustable volumes of the atmospheric medium (5.1 - 5.n ) can be evacuated by means of an evacuation and supply system (6) and let back into it, as a result of which the buoyancy body (2.1) can become lighter than the surrounding atmosphere and can bring about and regulate aerostatic buoyancy,

1. (a) to provide a load transfer system that is a structurally complete, weight-saving and efficient support system; and
2. (b) to provide a redundancy system to account for aerostatic loss of lift due to avoid, minimize or control an envelope rupture or breach, and improve the operational resilience of the aerostatic lifting device; and
3. (c) to provide a functional system that makes the aerodynamic, aerostatic and operational characteristics more energy and weight saving, efficient and practical.

SOLUTION OF THE TASK

The task mentioned under point (a) is achieved in one aspect by the load transfer system of the type mentioned at the beginning with the features of claim 1, in a further aspect by the load transfer system with the features of claim 16, and in an additional aspect by the load transfer system with the Features of claim 17 solved. Advantageous configurations are listed in at least one dependent claim.

The object mentioned under point (b) is solved by the redundancy system with the features of claim 33. Advantageous configurations are listed in at least one dependent claim.

The task mentioned under item (c) is solved in one aspect by the function system with the features of claim 46 and in a further aspect by the function system with the features of claim 47 . Advantageous configurations are listed in at least one dependent claim.

SUMMARY OF THE INVENTION

In a first aspect, the invention relates to a load transfer system in the form of a support parachute (7), which is a structurally complete, weight-saving and efficient support system for an aerostatic buoyancy device (1) in the form of a captive balloon, free balloon or airship, for lifting or transporting loads in an atmosphere, and which has a buoyant body (2.1) made up of gas-tight or airtight shells (3.1 - 3.n) in the form of film-like or membrane-like shells (4.1 - 4.n) that lie one inside the other and are separated by distances, from which adjustable volumes of the atmospheric medium (5.1 - 5.n) can be evacuated by means of an evacuation and supply system (6) and let back into it, as a result of which the buoyant body (2.1) can become lighter than the surrounding atmosphere and can bring about and regulate aerostatic buoyancy, represents.

In a further aspect, the invention relates to a load transfer system in the form of a double-cone-shaped support stand (8), which is a structurally complete, weight-saving and efficient support system for an aerostatic buoyancy device (1) in the form of a captive balloon, free balloon or airship, for lifting or transporting loads in an atmosphere, and which has a buoyant body (2.1) consisting of gas-tight or airtight shells (3.1 - 3.n) in the form of film-like or membrane-like shells (4.1 - 4.n) that lie one inside the other and are separated by distances which controllable volume of the atmospheric medium (5.1 - 5.n) can be evacuated by means of an evacuation and supply system (6) and let back into it, as a result of which the buoyant body (2.1) can become lighter than the surrounding atmosphere and can cause and regulate aerostatic buoyancy , represents.

In an additional aspect, the invention relates to a load transfer system in the form of a hyperboloid support stand (9), which is a structurally complete, weight-saving and efficient support system for an aerostatic buoyancy device (1) in the form of a captive balloon, free balloon or airship, for lifting or transporting loads in an atmosphere, and which has a buoyant body (2.1) consisting of gas-tight or airtight shells (3.1 - 3.n) in the form of film-like or membrane-like shells (4.1 - 4.n) that lie one inside the other and are separated by distances which controllable volume of the atmospheric medium (5.1 - 5.n) can be evacuated by means of an evacuation and supply system (6) and let back into it, as a result of which the buoyant body (2.1) can become lighter than the surrounding atmosphere and can cause and regulate aerostatic buoyancy , represents.

In a further aspect, the invention relates to a redundancy system for an aerostatic buoyancy device (1) in the form of a tethered balloon, free balloon or airship for lifting or transporting loads in an atmosphere, which has a buoyancy body (2.1) made up of one another and separated by distances , Gas or airtight shells (3.1 - 3.n) in the form of foil or membrane-like envelopes (4.1 - 4.n) from which adjustable volume of the atmospheric medium (5.1 - 5.n) by means of an evacuation and supply system (6) can be evacuated and lowered back into it, whereby the buoyant body (2.1) can become lighter than the surrounding atmosphere and can bring about and regulate an aerostatic lift, with the buoyant body (2.1) being replaced by at least one further, redundancy-generating buoyant body (2.2 - 2. n) supplemented to prevent, minimize or control aerostatic lift loss due to envelope rupture or breach and to improve the operational resilience of the aerostatic lifting device (1).

In an additional aspect, the invention relates to a functional system for an aerostatic buoyancy device (1) in the form of a tethered balloon, free balloon or airship for lifting or transporting loads in an atmosphere, which has a buoyancy body (2.1) made up of one another and separated by distances , Gas or airtight shells (3.1 - 3.n) in the form of foil or membrane-like envelopes (4.1 - 4.n) from which adjustable volume of the atmospheric medium (5.1 - 5.n) by means of an evacuation and supply system (6) can be evacuated and lowered back into it, whereby the lifting body (2.1) can become lighter than the surrounding atmosphere and can cause and regulate aerostatic lift in order to make the aerodynamic, aerostatic and operational properties more energy- and weight-saving, more efficient and more practical .

CONSTRUCTIVE DESCRIPTION OF THE INVENTION

The following structural description explains the objects, features and advantages of the invention, with reference to the accompanying drawings.

The load transfer system according to section [0025] comprises a supporting parachute (7) which completely absorbs the pressure and tensile forces arising in the buoyant body (2.1) by evacuating and supplying volumes of the atmospheric medium (5.1-5.n). The support umbrella (7) consists of a mast (10), suspension cables (11) and a first main anchor (12.1). The mast (10) carries the first main anchor (12.1 ), and leads through the flat plane of the first main anchor (12.1); the first main anchor (12.1) carries at least three shells (3.1 - 3.n) with corresponding at least three shells (4.1 - 4.n) on at least one side of its cross section; the mast (10) is located at least in part in the buoyancy body (2.1); The pressure and tensile forces caused by the evacuation and supply of volumes of the atmospheric medium (5.1 - 5.n) in the buoyancy body (2.1) are caused by atmospheric or aerostatic forces and are absorbed by the shells (3.1 - 3.n) and corresponding envelopes (4.1 - 4 .n) to the first main anchor (12.1), from the first main anchor (12.1) to the suspension cables (11), and from the suspension cables (11) to the mast (10); a second main anchor (12.2) carries at least three shells (3.1 - 3.n) with corresponding at least three shells (4.1 - 4.n) on at least one side of its cross section; the first main anchor (12.1) is connected to the second main anchor (12.2) by tension cables (14); the buoyant body (2.1) is spatially and constructively delimited, defined or enclosed essentially by the first main anchor (12.1) on one side and the second main anchor (12.2) on the other side; in the aerostatic buoyancy device (1) in the embodiment of a captive balloon or free balloon, the mast (10) is at its other end, by means of suspension cables (11) suspended or guyed from the mast (10), which are at an angle greater than 0° and smaller than 90° to the mast (10), connected to the second main anchor (12.2) ( 1 ); in the aerostatic buoyancy device (1) in the embodiment of an airship, the mast (10) and the second main anchor (12.2) rest on a hull (15) and are attached to it, with the hull (15) being subjected to compressive or tensile forces from the buoyant body (2.1) receives, and is located below or on the lower side of the buoyancy body (2.1), whereby the center of gravity of the aerostatic buoyancy device lowers or shifts down ( 2 ).

The advantage of this support parachute (7) is that all air pressure-related forces are completely dissipated and absorbed. The load transfer is thus completely defined structurally. The forces caused by the air pressure are transmitted from the shells (4.1 - 4.n) on one side of the load transfer system to the first main anchor (12.1), where they are in turn transmitted to the mast (10) via suspension cables (11). The mast (10) can finally absorb these forces due to appropriate design, bending stiffness, dimensioning, strength and material properties. On the other side of the load transfer system, the forces caused by the air pressure are passed on from the envelopes (4.1 - 4.n), in the embodiment of a tethered balloon or free balloon, to the second main anchor (12.2), which is also connected to the mast (10 ), and is connected to the first main anchor (12.1) by means of tension cables (14), where they are finally taken up by the mast (10). In the embodiment of an airship, the air pressure-related forces are passed on from the envelopes (4.1 - 4.n) to the second main anchor (12.2), the second main anchor (12.2) and the mast (10) resting on a hull (15) and attached to this. The second main anchor (12.2) is also connected to the first main anchor (12.1) by means of tension cables (14). In the former case, all of the air pressure-related forces are completely and finally absorbed by the mast (10). In the latter case, the forces caused by air pressure are absorbed partly by the mast (10) and partly by the hull (15). The hull (15) can finally absorb these forces due to appropriate design, flexural rigidity, dimensioning, strength and material properties as well as a suitable connection to the mast (10) and the second main anchor (12.2).

In addition, the advantage of this supporting umbrella (7) is that not every shell (4.1 - 4.n) requires its own structure or supporting framework. With the appropriate properties and material strength, an envelope (4.1 - 4.n) can absorb the necessary air pressure-related forces without its own rigid and heavy structure or load-bearing framework. The support screen (7) represents a single, ie singular, support structure which carries all the cases (4.1 - 4.n). The first main anchor (12.1) and second main anchor (12.2) each carry at least three cases (4.1 - 4.n). This is made possible on the one hand by the high tensile force of the supporting ropes (11) and by the appropriate design, bending stiffness, dimensioning, strength and material properties of the first main anchor (12.1) and second main anchor (12.2). A weight saving is also achieved in this way.

On the other hand, the advantage of this support parachute (7) is that the forces caused by the air pressure are absorbed by light, flexible tension elements, namely the support cables (11) and tension cables (14), instead of heavier, rigid pressure elements. Ropes are generally lighter per unit length or volume than compression rods or rods and can absorb high tensile forces. This contributes significantly to weight savings.

Another advantage of this supporting umbrella (7) is its preferably symmetrical design. A vacuum or negative pressure within a shell (3.1 - 3.n) is constantly distributed over the surface of the corresponding shell (4.1 - 4.n). The resulting air pressure-related forces are thus also transmitted evenly to the load transfer system. With a laterally symmetrical design of the support umbrella (7), preferably the same tensile force acts on each support cable (11). As a result, bending moments on the mast (10) can be reduced or eliminated, which means that lower material thicknesses for the mast (10) are possible and further weight savings are achieved.

An additional advantage of this supporting umbrella (7) is that the shells (4.1 - 4.n), the first main anchor (12.1), suspension cables (11) and tension cables (14) can be moved along the longitudinal direction of the mast (10). This is possible because there are no rigid or rigid elements along the longitudinal direction of the mast (10). By means of a telescopically retractable and extendable mast (10), these elements, and thus the entire buoyancy body (2.1), can be designed to be retractable and extendible, foldable and foldable or collapsible in order to save space on the aerostatic buoyancy device (1) on the ground park or stow. The first main anchor (12.1) can move orthogonally or almost orthogonally to its two-dimensional plane, while shells (4.1 - 4.n), carrying cables (11) and tensioning cables (14) are designed to be flexible or foldable accordingly.

The load transfer system according to Section [0026] comprises a double-cone-shaped supporting stand (8) which completely absorbs the pressure and tensile forces arising from evacuation and supply of the atmospheric medium (5.1-5.n) in the buoyancy body (2.1). The double-cone-shaped support stand (8) consists of a first main anchor (12.1) and a second main anchor (12.2), which are separated by a distance and lie one above the other, and between which they are not orthogonal, i.e. diagonal, to the surface plane of the first main anchor (12.1) or second main anchor (12.2) are rigid tripod supports (16) which are connected to the first main anchor (12.1) and the second main anchor (12.2) and are located in the buoyancy body (2.1). The stand supports (16) are laid diagonally in such a way that they run transversely, in particular centrally, through the enclosed volume of the buoyant body (2.1), thereby diametrically opposite points, i.e. points offset by 180°, on the first main anchor (12.1 ) and the second main anchor (12.2) intersect along a central straight line orthogonal to the first main anchor (12.1) or second main anchor (12.2), thus forming the outline of two opposite cones that meet at their vertices. The stand supports (16) are held at their crossing point by a holding element (20), in particular a clamp or lacing. The first main anchor (12.1) and the second main anchor (12.2) carry at least three shells (3.1-3.n) with at least three corresponding shells (4.1-4.n) on at least one side of its cross section. A shell (4.1 - 4.n) is connected to the first main anchor (12.1) and the second main anchor (12.2) in a gastight or airtight manner on one side. The buoyant body (2.1) is spatially and structurally delimited, defined or surrounded essentially by the first main anchor (12.1) on the one hand and the second main anchor (12.2) on the other side. The atmospherically or aerostatically caused pressure and tensile forces caused by an evacuation and supply of volume of the atmospheric medium (5.1 - 5.n) in the buoyancy body (2.1) are absorbed by the shells (3.1 - 3.n) and corresponding envelopes (4.1 - 4 .n) forwarded to the first main anchor (12.1), the second main anchor (12.2) and the tripod supports (16) and received by them ( 3 ).

The load transfer system according to section [0027] comprises a hyperboloid support stand (9) which completely absorbs the pressure and tensile forces arising in the buoyant body (2.1) by evacuation and supply of the atmospheric medium (5.1-5.n). The hyperboloid support stand (9) consists consisting of a first main anchor (12.1) and a second main anchor (12.2), which are separated by a distance and lie one above the other, and between which non-orthogonal, i.e. diagonal, to the planar plane of the first main anchor (12.1) or second main anchor (12.2) rigid tripod supports (16) are connected to the first main anchor (12.1) and the second main anchor (12.2) and are located in the buoyant body (2.1). The stand supports (16) are laid diagonally in such a way that they do not run transversely, in particular not centrally, through the enclosed volume of the buoyancy body (2.1), and do not come up with points that are diametrically opposite, ie offset by less than 180° connect the first main anchor (12.1) and the second main anchor (12.2), laid in at least two opposite or opposite laying directions, with corresponding laying angles, thus forming the outline of a hyperboloid or at least two hyperboloids with different curvatures. At least two tripod supports (16) running in opposite directions are held at their crossing point by a holding element (20), in particular a clamp or lacing. The first main anchor (12.1) and the second main anchor (12.2) carry at least three shells (3.1-3.n) with at least three corresponding shells (4.1-4.n) on at least one side of its cross section. A shell (4.1 - 4.n) is connected to the first main anchor (12.1) and the second main anchor (12.2) in a gastight or airtight manner on one side. The buoyant body (2.1) is spatially and structurally delimited, defined or surrounded essentially by the first main anchor (12.1) on the one hand and the second main anchor (12.2) on the other side. The atmospherically or aerostatically caused pressure and tensile forces caused by an evacuation and supply of volume of the atmospheric medium (5.1 - 5.n) in the buoyancy body (2.1) are absorbed by the shells (3.1 - 3.n) and corresponding envelopes (4.1 - 4 .n) forwarded to the first main anchor (12.1), the second main anchor (12.2) and the tripod supports (16) and received by them ( 4 ).

The advantage of the double-cone-shaped support stand (8) and the hyperboloid support stand (9) is that it completely dissipates and absorbs the forces generated by the air pressure. The double-cone-shaped support stand (8) and the hyperboloid support stand (9) each form a structurally stiffened and anchored structure. The compressive and tensile forces arising in the stand supports (16) as well as the bending moments are completely absorbed by the first main anchor (12.1), second main anchor (12.2) and the stand supports (16) through appropriate bending stiffness, dimensioning, strength and material properties, without additional or external bracing or anchoring is required.

In addition, the advantage of the double-cone-shaped support stand (8) and the hyperboloid support stand (9) lies in the fact that not every shell (4.1-4.n) requires its own supporting structure or supporting framework. The double-conical support stand (8) and the hyperboloid support stand (9) each represent a single, i.e. singular, support structure which carries all the cases (4.1 - 4.n). The first main anchor (12.1) and the second main anchor (12.2) each carry at least three cases (4.1 - 4.n). This is made possible by appropriate design, bending stiffness, dimensioning, strength and material properties of the first main anchor (12.1), second main anchor (12.2) and the stand supports (16). A weight saving is also achieved in this way.

On the other hand, the advantage of the double-conical support stand (8) and the hyperboloid support stand (9) is that the designs described represent a particularly weight-saving and at the same time effective use of rod elements in the form of the stand supports (16). This achieves high structural stability with an optionally small number of stand supports (16) or with lower material thicknesses of the stand supports (16).

Another advantage of the double-cone-shaped support stand (8) and the hyperboloid support stand (9) is that the first main anchor (12.1) and the second main anchor (12.2) can have relatively small material thicknesses, and this in turn contributes to a lower weight. The first main anchor (12.1) and the second main anchor (12.2) act structurally like brackets that run around the ends of the tripod supports (16), whereby they mainly absorb bending moments that are caused by the air pressure acting on the envelopes (4.1 - 4.n). forces arise. The first main anchor (12.1) and the second main anchor (12.2) are supported by the tripod supports (16), which are preferably designed at regular intervals or symmetrically around them. The load-bearing function of the tripod supports (16) reduces bending moments in the first main anchor (12.1) and second main anchor (12.2), as a result of which they use lower material thicknesses and can therefore be designed to be lighter.

A further advantage of the double-cone-shaped support stand (8) and the hyperboloid support stand (9) lies in their preferably symmetrical design, which also contributes to weight savings. A vacuum or negative pressure within a shell (3.1 - 3.n) is constantly distributed over the surface of the corresponding shell (4.1 - 4.n). They arise The forces caused by the air pressure are thus also transmitted evenly to the load transfer system. With a laterally symmetrical design of the double-cone-shaped support stand (8) and the hyperboloid support stand (9), preferably the same compressive and tensile forces and bending moments act on the first main anchor (12.1), the second main anchor (12.2) and the stand supports (16) on each side, whereby a constant and even force dissipation can be guaranteed when the air pressure-related forces are passed on, which avoids excessive force concentrations at individual points. This reduces the forces and bending moments that occur in the first main anchor (12.1), second main anchor (12.2) and in the tripod supports (16), as a result of which lower material thicknesses and cross-sections are made possible, which in turn lead to a considerable saving in weight.

The redundancy system according to Section [0028] consists of supplementing the buoyancy body (2.1) with at least one additional buoyancy body (2.2 - 2.n), each additional buoyancy body (2.2 - 2.n) being grouped with the first buoyancy body (2.1) and works or can be operated independently of the first buoyancy body (2.1) and of each other, so that each buoyancy body (2.1 - 2.n) forms a functionally independent section, unit, chamber, section, with each additional buoyancy body (2.2 - 2.n) also consists of nested, gas or airtight shells (3.1 - 3.n) in the form of foil or membrane-like envelopes (4.1 - 4.n), in which different degrees of evacuation, vacuum or negative pressure levels are generated , As a result of which all buoyancy bodies (2.1 - 2.n) are lighter than the surrounding atmosphere and can cause and regulate aerostatic buoyancy.

This serves to ensure functional safety by creating redundancy: If the required vacuum levels cannot be guaranteed within one or more buoyant bodies (2.1 - 2.n) due to the failure of at least one envelope (4.1 - 4.n), for example in As a result of a breakthrough, a perforation, a crack or a leak, the resulting failure of the corresponding buoyancy body(s) (2.1 - 2.n) can be limited to this/these without impairing the functionality of other buoyancy bodies (2.1 - 2 .n) is affected. This avoids, minimizes or controls aerostatic lift loss for the aerostatic lifting device (1) and improves its operational resilience.

In one aspect, the functional system according to section [0029] comprises a drive system for the aerostatic lifting device (1), wherein the drive system, which is optionally located within a shell (3.1 - 3.n), and in particular comprises an engine or a motor, via Supporting elements supported or carried by a hull (15) of the load transfer system according to paragraph [0024], [0025] or [0026], and of the preferred embodiment according to paragraph [0074].

In a further aspect, the functional system according to section [0029] comprises a drive system for the aerostatic lifting device (1), wherein the drive system, which is optionally located within a shell (3.1 - 3.n), and in particular comprises an engine or a motor, is suspended or anchored via tension elements from the first main anchor (12.1), second main anchor (12.2) or from a secondary anchor (13) from the load transfer system according to section [0024], [0025] or [0026].

A propulsion system requires a supporting structure which, on the one hand, allows placement within a shell (3.1 - 3.n) and, on the other hand, offers sufficient strength and anchoring. This is accomplished in one aspect by a hull (15) supporting or carrying the propulsion system and in another aspect by suspension or guying from a first main anchor (12.1), a second main anchor (12.2) or a secondary anchor (13), guaranteed, whereby the resulting pressure and tensile forces are effectively dissipated without impairing the functionality of the shells (3.1 - 3.n).

DESCRIPTION OF PREFERRED EMBODIMENTS

Other objects, features and advantages of the invention will become apparent to those skilled in the art from the following description of the preferred embodiments of the invention, in which reference is made to the accompanying drawings. These preferred embodiments can be found in the dependent claims.

• - dieser hat mindestens eine Durchführungsöffnung (25) für Schlauchleitungen (24);
• - dieser besteht aus mindestens zwei einzelnen Masten (10);
• - dieser hat eine vertikale Ausrichtung;
• - dieser hat eine horizontale Ausrichtung;
• - dieser hat eine geneigte Ausrichtung;
• - dieser wird durch mindestens eine Abstützung, Aussteifung oder Verankerung ergänzt;
• - dieser wird im aerostatischen Auftriebsgerät (1) in der Ausführungsform eines Luftschiffes durch mindestens ein Stagseil (22) oder ein Wantseil (23) ergänzt, das an einem Ende mit dem Mast (10) und am anderen Ende mit dem Rumpf (15) verbunden ist;
• - dieser hat innen freie oder hohle Räume, die Funktionen, Elemente oder Bauteile des aerostatischen Auftriebsgerätes (1), insbesondere Schlauchleitungen (24), aufnehmen können.

In preferred embodiments, the load transfer system according to section [0025] comprises a mast (10) which has one or more of the following features:

• - This has at least one passage opening (25) for hose lines (24);
• - This consists of at least two individual masts (10);
• - this one has a vertical orientation;
• - this one has a horizontal orientation;
• - this one has an inclined orientation;
• - this is supplemented by at least one support, bracing or anchorage;
• - This is supplemented in the aerostatic lifting device (1) in the embodiment of an airship by at least one stay rope (22) or one shroud rope (23) which is connected to the mast (10) at one end and to the fuselage (15) at the other end is;
• - This has free or hollow spaces inside, which can accommodate the functions, elements or components of the aerostatic lifting device (1), in particular hose lines (24).

• - dieses ist über ein Verteilerelement (21), welches am Mast (10) befestigt ist, mit dem Mast (10) verbunden (8);
• - dieses ist über ein Verteilerelement (21), welches mittels weiterer Tragseile (11) vom Mast (10) abgehängt ist, mit dem Mast (10) verbunden (9);
• - dieses ist unterspannt, wobei das Tragseil (11) den Obergurt und ein Zugband (17), welches vor oder hinter dem Tragseil (11) liegt, die Unterspannung bildet, und mindestens ein Pfosten (18) das Tragseil (11) mit dem Zugband (17) verbindet (10).

In preferred embodiments, the load transfer system according to section [0025] comprises a suspension cable (11) which has one or more of the following features:

• - This is connected to the mast (10) via a distributor element (21) which is fastened to the mast (10) ( 8th );
• - This is connected to the mast (10) via a distributor element (21), which is suspended from the mast (10) by means of further suspension cables (11) ( 9 );
• - This is under-tensioned, with the support rope (11) forming the upper chord and a tie (17), which lies in front of or behind the support rope (11), forming the under-tension, and at least one post (18) forming the support rope (11) with the tie (17) connects ( 10 ).

• - dieses bildet eine gas- oder luftdichte Verbindung mit dem Mast (10) und mindestens einer Hülle (4.1 - 4.n);
• - dieses hat mindestens eine Durchführungsöffnung (25) für die Anbringung oder Durchführung einer Leitung, eines Schlauches oder eines Ventils.

In preferred embodiments, the load transfer system according to section [0025] comprises a distributor element (21) which has one or more of the following features:

• - This forms a gas or airtight connection with the mast (10) and at least one shell (4.1 - 4.n);
• - This has at least one feed-through opening (25) for the attachment or implementation of a line, a hose or a valve.

• - dieser hat Druckausgleichsöffnungen in Form von Durchführungsöffnungen (25), Bohrungen, Kanälen, Lochungen oder Perforationen;
• - dieser ist als Hohlrohr oder mit Hohlräumen ausgeführt;
• - dieser trägt mindestens eine aerodynamische Auftriebs- oder Steuerfläche, insbesondere einen Flügel oder ein Leitwerk;
• - dieser wird durch mindestens einen Nebenanker (13) ergänzt, welcher mittels Spannseilen (14) vom ersten Hauptanker (12.1) abgehängt oder abgespannt ist, dabei an mindestens einer Seite seines Querschnittes mindestens drei Schalen (3.1 - 3.n) mit entsprechend mindestens drei Hüllen (4.1 - 4.n) trägt und gas- oder luftdicht mit mindestens drei Hüllen (4.1 - 4.n) verbunden ist (5).

In preferred embodiments, the load transfer system according to section [0025] comprises a first main anchor (12.1) which has one or more of the following features:

• - This has pressure equalization openings in the form of lead-through openings (25), bores, channels, holes or perforations;
• - This is designed as a hollow tube or with cavities;
• - This carries at least one aerodynamic lift or control surface, in particular a wing or tail unit;
• - this is supplemented by at least one secondary anchor (13), which is suspended or guyed from the first main anchor (12.1) by means of tension cables (14), with at least three shells (3.1 - 3.n) with a corresponding minimum of three on at least one side of its cross section covers (4.1 - 4.n) and is gas-tight or airtight with at least three covers (4.1 - 4.n) connected ( 5 ).

• - dieser hat Druckausgleichsöffnungen in Form von Durchführungsöffnungen (25), Bohrungen, Kanälen, Lochungen oder Perforationen;
• - dieser ist als Hohlrohr oder mit Hohlräumen ausgeführt;
• - dieser trägt mindestens eine aerodynamische Auftriebs- oder Steuerfläche, insbesondere einen Flügel oder ein Leitwerk;
• - dieser wird durch mindestens einen Nebenanker (13) ergänzt, welcher mittels Spannseilen (14) vom zweiten Hauptanker (12.2) abgehängt oder abgespannt ist, dabei an mindestens einer Seite seines Querschnittes mindestens drei Schalen (3.1 - 3.n) mit entsprechend mindestens drei Hüllen (4.1 - 4.n) trägt und gas- oder luftdicht mit mindestens drei Hüllen (4.1 - 4.n) verbunden ist (5).

In preferred embodiments, the load transfer system according to section [0025] comprises a second main anchor (12.2) which has one or more of the following features:

• - This has pressure equalization openings in the form of lead-through openings (25), bores, channels, holes or perforations;
• - This is designed as a hollow tube or with cavities;
• - This carries at least one aerodynamic lift or control surface, in particular a wing or tail unit;
• - this is supplemented by at least one secondary anchor (13), which is suspended or braced from the second main anchor (12.2) by means of tension cables (14), with at least three shells (3.1 - 3.n) with a corresponding minimum of three on at least one side of its cross section covers (4.1 - 4.n) and is gas-tight or airtight with at least three covers (4.1 - 4.n) connected ( 5 ).

• - dieser hat Druckausgleichsöffnungen in Form von Durchführungsöffnungen (25), Bohrungen, Kanälen, Lochungen oder Perforationen;
• - dieser ist als Hohlrohr oder mit Hohlräumen ausgeführt;
• - dieser trägt mindestens eine aerodynamische Auftriebs- oder Steuerfläche, insbesondere einen Flügel oder ein Leitwerk.

In preferred embodiments, the load transfer system according to section [0025] comprises a secondary anchor (13) which has one or more of the following features:

• - This has pressure equalization openings in the form of lead-through openings (25), bores, channels, holes or perforations;
• - This is designed as a hollow tube or with cavities;
• - This carries at least one aerodynamic lift or control surface, in particular a wing or tail unit.

• - diese ist an mindestens einer Seite gas- oder luftdicht am ersten Hauptanker (12.1) befestigt;
• - diese ist an mindestens einer Seite gas- oder luftdicht am zweiten Hauptanker (12.2) befestigt;
• - diese ist an mindestens einer Seite gas- oder luftdicht an einem Nebenanker (13) befestigt;
• - diese ist an mindestens einer Seite vom ersten Hauptanker (12.1) mittels Spannseilen (14) abgehängt oder abgespannt;
• - diese ist an mindestens einer Seite vom zweiten Hauptanker (12.2) mittels Spannseilen (14) abgehängt oder abgespannt;
• - diese ist an mindestens einer Seite von einem Nebenanker (13) mittels Spannseilen (14) abgehängt oder abgespannt;
• - diese ist gespannt, vorgespannt, gestrafft oder nicht flatternd am ersten Hauptanker (12.1) oder zweiten Hauptanker (12.2) befestigt;
• - diese ist ungespannt, ungestrafft oder flatternd am ersten Hauptanker (12.1) oder zweiten Hauptanker (12.2) befestigt;
• - diese hat zur nächstgelegenen oder benachbarten Hülle (4.1 - 4.n) einen gleich bleibenden Abstand;
• - diese hat zur nächstgelegenen oder benachbarten Hülle (4.1 - 4.n) einen variierenden Abstand;
• - diese liegt auf einem Tragseil (11) oder Spannseil (14) auf.

In preferred embodiments, the load transfer system according to section [0025] comprises a shell (4.1 - 4.n) which has one or more of the following features:

• - This is attached gas-tight or airtight on at least one side to the first main anchor (12.1);
• - This is attached gas-tight or airtight on at least one side to the second main anchor (12.2);
• - This is gas-tight or air-tight on at least one side attached to a secondary anchor (13);
• - This is suspended or braced on at least one side from the first main anchor (12.1) by means of tension cables (14);
• - This is suspended or braced on at least one side from the second main anchor (12.2) by means of tension cables (14);
• - This is suspended or braced on at least one side from a secondary anchor (13) by means of tension cables (14);
• - This is tensioned, prestressed, tightened or not fluttering attached to the first main anchor (12.1) or second main anchor (12.2);
• - This is loose, not taut or flapping attached to the first main anchor (12.1) or second main anchor (12.2);
• - This has a constant distance to the nearest or neighboring shell (4.1 - 4.n);
• - This has to the nearest or adjacent shell (4.1 - 4.n) a varying distance;
• - This rests on a carrying cable (11) or tensioning cable (14).

In a preferred embodiment, depending on the shape of the aerostatic lifting device (1), the load transfer system according to paragraph [0025] comprises a first main anchor (12.1), a second main anchor (12.2) or a secondary anchor (13) having the same( n) have a diameter, size, cross-section or circumference.

In a preferred embodiment, depending on the shape of the aerostatic lifting device (1), the load transfer system according to paragraph [0025] comprises a first main anchor (12.1), a second main anchor (12.2) or a secondary anchor (13), which one(s) different (n) have a diameter, size, cross-section or circumference.

• - diese liegen nicht orthogonal, d.h. diagonal, zur flächigen Ebene des ersten Hauptankers (12.1), zweiten Hauptankers (12.2) oder eines Nebenankers (13), wobei sie zwei diagonal gegenläufige oder entgegengesetzt laufende Spannrichtungen haben und dabei den Umriss eines Hyperboloids bilden ( 11);
• - diese liegen nicht orthogonal, d.h. diagonal, zur flächigen Ebene des ersten Hauptankers (12.1), zweiten Hauptankers (12.2) oder eines Nebenankers (13), wobei sie mindestens vier diagonal gegenläufige oder entgegengesetzt laufende Spannrichtungen haben und dabei die Umrisse mindestens zweier Hyperboloide mit verschiedenen Krümmungen bilden (12).

In preferred embodiments, the load transfer system according to paragraph [0025] comprises tethers (14) having one or more of the following features:

• - These are not orthogonal, ie diagonally, to the planar plane of the first main anchor (12.1), second main anchor (12.2) or a secondary anchor (13), whereby they have two diagonally opposite or opposite running directions of tension and thereby form the outline of a hyperboloid ( 11 );
• - These are not orthogonal, i.e. diagonally, to the flat plane of the first main anchor (12.1), second main anchor (12.2) or a secondary anchor (13), whereby they have at least four diagonally opposite or oppositely running tensioning directions and the outlines of at least two hyperboloids form different curvatures ( 12 ).

In a preferred embodiment, the load transfer system according to section [0025] comprises a tensioning cable (14), which is tensioned underneath, with the tensioning cable (14) having the upper chord and a tensioning strap (17), which lies in front of or behind the tensioning cable (14), the undertensioning forms, and at least one post (18) connects the tensioning cable (14) to the drawstring (17) ( 13 ).

In a preferred embodiment, the load transfer system according to Section [0025] comprises a tension cable (14) and a tie (17) which are attached at one end to the first main anchor (12.1) or to a secondary anchor (13) and at the other end to the second main anchor (12.2 ) or attached to a secondary anchor (13) ( 13 ).

In a preferred embodiment, the load transfer system according to paragraph [0025] comprises a post (18) connected to at least one shell (4.1 - 4.n), the post (18) passing through the shell (4.1 - 4.n). and thereby forms a gas-tight or air-tight connection with the shell (4.1 - 4.n) ( 14 ).

In a preferred embodiment, the load transfer system according to paragraph [0025] comprises a post (18) connected to at least one sleeve (4.1 - 4.n), the sleeve (4.1 - 4.n) passing through the post (18). , which is divided into at least two parts through the passage of the envelope (4.1 - 4.n), which are connected to corresponding envelope sides ( 15 ).

In a preferred embodiment, the load transfer system according to section [0027] comprises a cover (4.1 - 4.n) which rests on at least one stand support (16).

In a preferred embodiment, the load transfer system according to section [0026] or [0027] comprises tensioning cables (14) which connect the first main anchor (12.1) and the second main anchor (12.2) to one another.

• - diese liegen nicht orthogonal, d.h. diagonal, zur flächigen Ebene des ersten Hauptankers (12.1) oder des zweiten Hauptankers (12.2), wobei sie zwei diagonal gegenläufige oder entgegengesetzt laufende Spannrichtungen haben und dabei den Umriss eines Hyperboloids bilden (16a und 16b);
• - diese liegen nicht orthogonal, d.h. diagonal, zur flächigen Ebene des ersten Hauptankers (12.1) oder des zweiten Hauptankers (12.2), wobei sie mindestens vier diagonal gegenläufige oder entgegengesetzt laufende Spannrichtungen haben und dabei die Umrisse mindestens zweier Hyperboloide mit verschiedenen Krümmungen bilden (17a und 17b).

In preferred embodiments, the load transfer system according to section [0026] or [0027] comprises tension cables (14) which have one or more of the following features:

• - These are not orthogonal, ie diagonally, to the planar plane of the first main anchor (12.1) or the second main anchor (12.2), whereby they have two diagonally opposite or oppositely running clamping directions and thereby form the outline of a hyperboloid ( 16a and 16b );
• - these are not orthogonal, ie diagonally, to the flat plane of the first main anchor (12.1) or the second main anchor (12.2), whereby they have at least four diagonally opposite or opposite directions of tension and thereby form the outlines of at least two hyperboloids with different curvatures ( 17a and 17b ).

In a preferred embodiment, the load transfer system according to section [0026] or [0027] comprises a tensioning cable (14) which is tensioned underneath, the tensioning cable (14) having the upper chord and a tensioning strap (17) which is located in front of or behind the tensioning cable (14). lies, forms the lower tension, and at least one post (18) connects the tensioning cable (14) to the tie (17), the tensioning cable (14) and the tie (17) at one end on the first main anchor (12.1) and at the other end are attached to the second main anchor (12.2) ( 18a and 18b ).

In a preferred embodiment, the load transfer system according to section [0026] or [0027] comprises a post (18) which is connected to at least one shell (4.1 - 4.n), the post (18) extending through the shell (4.1 - 4 .n) and thereby forms a gas-tight or air-tight connection with the shell (4.1 - 4.n) ( 19a and 19b ).

In a preferred embodiment, the load transfer system according to paragraph [0026] or [0027] comprises a post (18) connected to at least one shell (4.1 - 4.n), the shell (4.1 - 4.n) being connected to the post (18), which is divided into at least two parts through the passage of the shell (4.1 - 4.n), which form a connection with one side of the shell each ( 20a and 20b ).

• - dieser hat Druckausgleichsöffnungen in Form von Durchführungsöffnungen (25), Bohrungen, Kanälen, Lochungen oder Perforationen;
• - dieser ist als Hohlrohr oder mit Hohlräumen ausgeführt;
• - dieser trägt mindestens eine aerodynamische Auftriebs- oder Steuerfläche, insbesondere einen Flügel oder ein Leitwerk.

In preferred embodiments, the load transfer system according to section [0026] or [0027] comprises a first main anchor (12.1) which has one or more of the following features:

• - This has pressure equalization openings in the form of lead-through openings (25), bores, channels, holes or perforations;
• - This is designed as a hollow tube or with cavities;
• - This carries at least one aerodynamic lift or control surface, in particular a wing or tail unit.

• - dieser hat Druckausgleichsöffnungen in Form von Durchführungsöffnungen (25), Bohrungen, Kanälen, Lochungen oder Perforationen;
• - dieser ist als Hohlrohr oder mit Hohlräumen ausgeführt;
• - dieser trägt mindestens eine aerodynamische Auftriebs- oder Steuerfläche, insbesondere einen Flügel oder ein Leitwerk.

In preferred embodiments, the load transfer system according to section [0026] or [0027] comprises a second main anchor (12.2) which has one or more of the following features:

• - This has pressure equalization openings in the form of lead-through openings (25), bores, channels, holes or perforations;
• - This is designed as a hollow tube or with cavities;
• - This carries at least one aerodynamic lift or control surface, in particular a wing or tail unit.

In a preferred embodiment, the load transfer system according to section [0026] or [0027] comprises a second main anchor (12.2) which rests on a fuselage (15) and is attached to it, the fuselage (15) being subjected to compressive or tensile forces from the buoyancy body ( 2.1) and is located below or on the lower side of the buoyancy body (2.1), whereby the center of gravity of the aerostatic buoyancy device (1) is lowered or shifted downwards ( 21a and 21b ).

In a preferred embodiment, the load transfer system according to section [0025], [0026] or [0027], depending on the shape of the aerostatic lift device (1), comprises a carrying cable (11), tensioning cable (14), stay cable (22), shroud cable ( 23) or drawstring (17), which consists of a natural fiber, i.e. animal, vegetable or mineral fiber, in particular bamboo, cotton, flax, hemp, jute, silk, including composite materials reinforced with natural fibers.

In a preferred embodiment, the load transfer system according to section [0025], [0026] or [0027], depending on the shape of the aerostatic lift device (1), comprises a carrying cable (11), tensioning cable (14), stay cable (22), shroud cable ( 23) or drawstring (17) made of a synthetic or chemical fiber, i.e. a fiber made of natural polymers, synthetic polymers or inorganic materials, in particular aramid, fibers based on ultra high molecular weight polyethylene, carbon fibers, metals and metal alloys.

In a preferred embodiment, the load transfer system according to section [0025], [0026] or [0027] comprises an outermost shell (3.n) with the corresponding outermost shell (4.n) of a buoyancy body (2.1), a front of outer atmospheric , environmental or weather-related influences forms a protective outer shell with a corresponding outer shell.

• - dieser trägt aerodynamische Auftriebs- oder Steuerflächen, insbesondere mindestens einen Flügel oder ein Leitwerk;
• - dieser ragt oder steht an mindestens einer Seite über den Umriss der äußersten Schale (3.n) und entsprechend der äußersten Hülle (4.n) des Auftriebskörpers (2.1) hervor;
• - dieser bildet an mindestens einer Seite einen aerodynamisch wirksamen oder geometrisch gegenseitig angepassten Übergang mit der äußersten Schale (3.n) und entsprechend mit der äußersten Hülle (4.n) des Auftriebskörpers (2.1);
• - dieser hat mindestens eine synklastische oder antiklastische Krümmung an seiner Oberfläche;
• - dieser variiert in seiner Breite oder Höhe, und hat dabei schmalere und breitere Stellen oder Abschnitte, mit abgerundeten oder fließenden Übergängen zwischen ihnen;
• - dieser liegt zu mindestens einem Teil innerhalb des Auftriebskörpers (2.1);
• - dieser ist als Druckkabine ausgeführt;
• - dieser weist eine Nutzlastkabine auf, welche über eine Hecktür, bevorzugt über eine Heckklappe, be- und entladen wird;
• - dieser weist ein Cockpit auf, welches sich räumlich an eine Nutzlastkabine anschließt, räumlich mit dieser verbunden ist und vor dieser liegt.

In preferred embodiments, the load transfer system according to section [0025], [0026] or [0027] a hull (15) having one or more of the following features:

• - This carries aerodynamic lift or control surfaces, in particular at least one wing or tail unit;
• - This protrudes or protrudes on at least one side beyond the outline of the outermost shell (3.n) and correspondingly the outermost shell (4.n) of the buoyant body (2.1);
• - This forms on at least one side an aerodynamically effective or geometrically mutually adapted transition with the outermost shell (3.n) and accordingly with the outermost shell (4.n) of the buoyancy body (2.1);
• - this has at least one synclastic or anticlastic curvature on its surface;
• - this varies in width or height, having narrower and wider parts or sections, with rounded or smooth transitions between them;
• - This is at least partially within the buoyancy body (2.1);
• - this is designed as a pressurized cabin;
• - This has a payload cabin, which is loaded and unloaded via a rear door, preferably via a tailgate;
• - This has a cockpit, which is spatially connected to a payload cabin, is spatially connected to it and is located in front of it.

• - diese/dieser/dieses besteht aus einer Naturfaser, d.h. tierischen, pflanzlichen oder mineralischen Faser, insbesondere aus Bambus, Holz, Holzwerkstoffen, Papier, Pappe, einschließlich naturfaserverstärkten Verbundwerkstoffen;
• - diese/dieser/dieses besteht aus einer Kunst- oder Chemiefaser, d.h. einer Faser aus natürlichen Polymeren, synthetischen Polymeren oder anorganischen Stoffen, insbesondere aus Aluminium-Lithium-Legierungen, Aramid, Fasern auf der Basis von Polyethylen mit ultrahoher Molekülmasse, Kohlestofffasern sowie Verbundwerkstoffen mit Kohlestofffasern.

In preferred embodiments, the load transfer system according to section [0025], [0026] or [0027] comprises a mast (10), a first main anchor (12.1), a second main anchor (12.2), a secondary anchor (13), a hull (15) , a distributor element (21), a post (18) or an aerodynamic flight control element, in particular a wing, tailplane or control surface, which has one or more of the following features:

• - This / this / this consists of a natural fiber, ie animal, vegetable or mineral fiber, in particular bamboo, wood, wood-based materials, paper, cardboard, including composite materials reinforced with natural fibers;
• - this consists of an artificial or man-made fibre, ie a fiber made from natural polymers, synthetic polymers or inorganic substances, in particular aluminum-lithium alloys, aramid, fibers based on ultra-high molecular weight polyethylene, carbon fibers and composite materials with carbon fibers.

In a preferred embodiment, the redundancy system according to section [0028] comprises at least one shell (4.1 - 4.n) which is connected to the nearest or neighboring shell (4.1 - 4.n ) is connected, wherein the shell transverse surfaces (19) can be oriented horizontally, vertically or diagonally, and are designed so that the space or volume between the adjacent or adjacent shells (4.1 - 4.n) is divided into at least two compartments or compartments and thereby absorb the lateral surfaces (19) of the casing compressive or tensile forces ( 22 ).

In a preferred embodiment, the redundancy system according to Section [0028] comprises a load transfer system according to Section [0025], wherein the load transfer system, in particular the parachute (7), carries more than one buoyancy body (2.1 - 2.n), and each buoyancy body (2.1 - 2.n) is spatially and structurally delimited, defined or surrounded by the first main anchor (12.1), second main anchor (12.2), a secondary anchor (13) or a distributor element (21) ( 5 ).

In a preferred embodiment, the redundancy system according to Section [0028] comprises a load transfer system according to Section [0026], wherein the buoyancy body (2.1) is supplemented by at least one further buoyancy body (2.2 - 2.n), each with a double-cone-shaped support stand (8), and each buoyant body (2.1 - 2.n) is spatially and structurally delimited, defined or surrounded by its first main anchor (12.1) and second main anchor (12.2) ( 6 ).

In a preferred embodiment, the redundancy system according to section [0028] comprises a load transfer system according to section [0027], wherein the buoyancy body (2.1) is supplemented by at least one further buoyancy body (2.2 - 2.n) each with a hyberboloid support stand (9), and each buoyant body (2.1 - 2.n) is spatially and structurally delimited, defined or surrounded by its first main anchor (12.1) and second main anchor (12.2) ( 7 ).

In preferred embodiments, the redundancy system according to paragraph [0028] comprises a load transfer system in a preferred embodiment according to one or more of the previous paragraphs.

In a preferred embodiment, the post-section redundancy system comprises a post-section load transfer system [0025], [0026] or [0027], wherein the first main anchor (12.1), second main anchor (12.2) or a secondary anchor (13) has pressure equalization openings in the form of lead-through openings (25), bores, channels, holes or perforations.

In a preferred embodiment, the redundancy system according to section [0028] comprises a load transfer system according to section [0025], [0026] or [0027], wherein the first main anchor (12.1), second main anchor (12.2) or a secondary anchor (13) has at least one pressure equalization opening has which has a valve for controlling or stopping the flow of atmospheric medium.

In a preferred embodiment, the redundancy system according to section [0028] comprises a load transfer system according to section [0025], wherein at least two grouped and independently functioning or operable buoyancy bodies (2.1 - 2.n) are connected for the purpose of stowage or space-saving on the floor can be drawn in and out, folded in and out or collapsible by the mast (10) being retracted and extended telescopically, whereby the buoyancy bodies (2.1 - 2.n) connected to the mast (10) move together with the first main anchor (12.1) or a secondary anchor (13), corresponding shells (3.1 - 3.n) and their shells (4.1 - 4.n) and with corresponding support cables (11) or tension cables (14) raise and lower, fold in and out or can be raised and retracted, with the casings (4.1 - 4.n), supporting ropes (11) or tensioning ropes (14) being designed to be flexible or foldable accordingly.

In a preferred embodiment, the redundancy system according to section [0028] comprises outermost shells (4.n) of the buoyancy bodies (2.1 - 2.n), which on at least one side, in particular the front side, of the aerostatic buoyancy device (1) are made of a more rigid, thicker, more tear-resistant, stronger, or more durable material than the other sides.

In a preferred embodiment, the redundancy system according to Section [0028] comprises at least one aerodynamic lift or control surface, in particular a wing or tail unit, for lift supplementation and flight control, which is controlled by a first main anchor, a second main anchor, a secondary anchor or a fuselage from the load transfer system according to paragraph [0025], [0026] or [0027] and from the preferred embodiment according to paragraph [0076].

In a preferred embodiment, the redundancy system according to Section [0028] comprises a parachute system as an overall rescue system, which is part of the supporting parachute (7) from the load transfer system according to Section [0025] and is located inside the mast (10), being attached to the mast (10 ) is attached or anchored, whereby when the parachute system is deployed, at least one parachute emerges from an opening at one end of the mast (10) into the surrounding atmosphere and then opens.

Thus, the parachute system can be fastened or anchored in the preferably hollow spaces of the mast (10) in a structurally effective and space-saving manner. Since the mast (10) has a preferred vertical orientation and preferably passes through the center of gravity of the aerostatic lifting device (1), a parachute emerging from the mast (10) unfolds a balanced carrying capacity.

• - dieses wird durch elektrischen Strom betrieben;
• - dieses wird durch einen Brennstoff betrieben;
• - dieses wird durch regenerative Energiequellen betrieben;
• - dieses wird durch elektrischen Strom betrieben, der aus Photovoltaik, d.h. Solarzellen, oder aus Solarthermie gewonnen wird;
• - dieses wird durch elektrischen Strom betrieben, der aus Photovoltaik, d.h. Solarzellen, gewonnen wird, wobei sich die Solarzellen an Bord des aerostatischen Auftriebsgerätes (1) befinden;
• - dieses verwendet für das Einlassen der Volumen des atmosphärischen Mediums (5.1 - 5.n) in die Schalen (3.1 - 3.n) den Ansaugdruck oder Sog eines zuvor in den Schalen (3.1 - 3.n) erzeugten Vakuums oder Unterdrucks.

In preferred embodiments, the redundancy system according to section [0028] comprises an evacuation and supply system (6) which has one or more of the following features:

• - this is powered by electricity;
• - This is powered by a fuel;
• - This is powered by renewable energy sources;
• - This is powered by electricity that is obtained from photovoltaics, ie solar cells, or from solar thermal energy;
• - This is operated by electric current, which is obtained from photovoltaics, ie solar cells, the solar cells being on board the aerostatic lifting device (1);
• - This uses the suction pressure or suction of a vacuum or negative pressure previously created in the shells (3.1 - 3.n) to admit the volumes of atmospheric medium (5.1 - 5.n) into the shells (3.1 - 3.n).

The possible use of different energy sources for the evacuation and supply system (6) as well as the use of the suction pressure or suction of a vacuum or negative pressure previously generated in the shells (3.1 - 3.n), whereby a mechanical medium supply is minimized or unnecessary, increases the operational resilience of the aerostatic lifting device (1).

• - diese erzeugt einen aerodynamischen Auftrieb während des Fluges des aerostatischen Auftriebsgerätes (1);
• - diese hat mindestens eine synklastische oder antiklastische Krümmung an der Oberfläche der äußersten Hüllen (4.n) der Auftriebskörper (2.1 - 2.n);
• - diese hat in der Frontansicht des aerostatischen Auftriebsgerätes (1) einen kreisförmigen, ellipsenförmigen, halbkreisförmigen, halbellipsenförmigen, spitzbogenförmigen, parabelförmigen, tropfenförmigen, eiförmigen, rechteckigen, trapezförmigen, rautenförmigen oder gleichdickförmigen Umriss;
• - diese hat in der Seitenansicht des aerostatischen Auftriebsgerätes (1) einen kreisförmigen, ellipsenförmigen, halbkreisförmigen, halbellipsenförmigen, spitzbogenförmigen, parabelförmigen, tropfenförmigen, eiförmigen, rechteckigen, trapezförmigen, rautenförmigen oder gleichdickförmigen Umriss, wobei eine Symmetrieachse des Umrisses, und damit der Umriss selbst, vertikal ausgerichtet, nach vorne oder nach hinten geneigt ist;
• - diese hat in der Front- oder Seitenansicht des aerostatischen Auftriebsgerätes (1) einen rechteckigen, trapezförmigen, rautenförmigen oder gleichdickförmigen Umriss, welcher an mindestens einer Ecke oder Kante abgerundet ist.

In preferred embodiments, the functional system according to section [0029] includes an external appearance or shape of all buoyancy bodies (2.1-2.n) in their cumulative totality, largely determined by the outermost shells (4.n) of the buoyancy bodies (2.1-2.n). that has one or more of the following characteristics:

• - This generates an aerodynamic lift during flight of the aerostatic lift device (1);
• - This has at least one synclastic or anticlastic curvature on the surface of the outermost shells (4.n) of the buoyancy bodies (2.1 - 2.n);
• - In the front view of the aerostatic buoyancy device (1), this has a circular, elliptical, semi-circular, semi-elliptical, pointed arch, parabolic, drop-shaped, egg-shaped, rectangular, trapezoidal, rhombic or equal-width outline;
• - In the side view of the aerostatic buoyancy device (1), this has a circular, elliptical, semi-circular, semi-elliptical, pointed arch, parabolic, teardrop-shaped, egg-shaped, rectangular, trapezoidal, diamond-shaped or of equal thickness outline, with an axis of symmetry of the outline, and thus the outline itself, vertically aligned, tilted forwards or backwards;
• - In the front or side view of the aerostatic buoyancy device (1), this has a rectangular, trapezoidal, diamond-shaped or constant-thickness outline, which is rounded off at at least one corner or edge.

In a preferred embodiment, the functional system according to section [0029] comprises an atmosphere in which the aerostatic lift device (1) is located, which is the atmosphere of a planet, in particular Earth, Mars and Venus, and that the volumes of the atmospheric Medium (5.1 - 5.n) from the respective atmosphere or the respective atmospheric medium in which the aerostatic buoyancy device (1) is located, exist or are related.

In preferred embodiments, the functional system according to section [0029] comprises a load transfer system according to one or more of the previous sections.

In preferred embodiments, the functional system according to section [0029] comprises a redundancy system according to one or more of the previous sections.

character list

• 1 zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems mit einem Tragschirm (7) für das aerostatische Auftriebsgerät (1) in der Ausführungsform eines rotationssymmetrischen Fesselballons oder Freiballons.
• 2 zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems mit einem Tragschirm (7) für das aerostatische Auftriebsgerät (1) in der Ausführungsform eines rotationssymmetrischen Luftschiffes mit einem Rumpf (15).
• 3 zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems mit einem doppelkegelförmigen Tragstativ (8) für das aerostatische Auftriebsgerät (1) in der Ausführungsform eines rotationssymmetrischen Fesselballons oder Freiballons.
• 4 zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems mit einem hyperboloiden Tragstativ (9) für das aerostatische Auftriebsgerät (1) in der Ausführungsform eines rotationssymmetrischen Fesselballons oder Freiballons.
• 5 zeigt einen Vertikalschnitt des erfindungsgemäßen Redundanzsystems für das aerostatische Auftriebsgerät (1) mit vier gruppierten, redundanzerzeugenden Auftriebskörpern (2.1 - 2.4) und dem erfindungsgemäßen Lastabtragungssystem in Form eines Tragschirms (7), mit einem ersten Hauptanker (12.1), einem zweiten Hauptanker (12.2), einem Nebenanker (13), Spannseilen (14) und Schalen (3.1 - 3.3) mit entsprechenden Hüllen (4.1 - 4.3).
• 6 zeigt einen Vertikalschnitt des erfindungsgemäßen Redundanzsystems für das aerostatische Auftriebsgerät (1) mit sechs gruppierten, redundanzerzeugenden Auftriebskörpern (2.1 - 2.6) und je einem erfindungsgemäßen Lastabtragungssystems mit einem doppelkegelförmigen Tragstativ (8).
• 7 zeigt einen Vertikalschnitt des erfindungsgemäßen Redundanzsystems für das aerostatische Auftriebsgerät (1) mit sechs gruppierten, redundanzerzeugenden Auftriebskörpern (2.1 - 2.6) und je einem erfindungsgemäßen Lastabtragungssystems mit einem hyperboloiden Tragstativ (9).
• 8 zeigt einen Ausschnitt des erfindungsgemäßen Lastabtragungssystems mit einem Tragschirm (7) im Vertikalschnitt, wobei die Tragseile (11) über ein Verteilerelement (21), welches am Mast (10) befestigt ist, mit dem Mast (10) verbunden sind.
• 9 zeigt einen einen Ausschnitt des erfindungsgemäßen Lastabtragungssystems mit einem Tragschirm (7) im Vertikalschnitt, wobei die Tragseile (11) über ein Verteilerelement (21), welches mittels weiterer Tragseile (11) vom Mast (10) abgehängt ist, mit dem Mast (10) verbunden sind.
• 10 zeigt einen Ausschnitt des erfindungsgemäßen Lastabtragungssystems mit einem Tragschirm (7) im Vertikalschnitt und einem unterspannten Tragseil (11).
• 11 zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem Tragschirm (7) und Spannseilen (14), die diagonal zur flächigen Ebene des ersten Hauptankers (12.1) und zweiten Hauptankers (12.2) liegen, wobei die Spannseile (14) zwei diagonal gegenläufige oder entgegengesetzt laufende Spannrichtungen haben und dabei den Umriss eines Hyperboloids bilden.
• 12 zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem Tragschirm (7) und Spannseilen (14), die diagonal zur flächigen Ebene des ersten Hauptankers (12.1) und zweiten Hauptankers (12.2) liegen, wobei die Spannseile (14) vier diagonal gegenläufige oder entgegengesetzt laufende Spannrichtungen haben und dabei die Umrisse zweier Hyperboloide mit verschiedenen Krümmungen bilden.
• 13 zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem Tragschirm (7) und zwei unterspannten Spannseilen (14).
• 14a zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem Tragschirm (7) und zwei unterspannten Spannseilen (14), wobei die Pfosten (18) durch die jeweiligen Hüllen (4.1 - 4.3) hindurchführen und dabei eine gas- oder luftdichte Verbindung mit diesen bilden. Vergrößerte Ausschnitte davon sind in Vertikalschnitten dargestellt.
• 15a zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem Tragschirm (7) und zwei unterspannten Spannseilen (14), wobei die Hüllen (4.1 - 4.3) durch die jeweiligen Pfosten (18) hindurchführen, die sich durch die Durchführung der Hüllen (4.1 - 4.3) in jeweils mindestens vier Teile teilen, die mit entsprechenden Hüllenseiten verbunden sind. Vergrößerte Ausschnitte davon sind in Vertikalschnitten dargestellt.
• 16a zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem doppelkegelförmigen Tragstativ (8) und Spannseilen (14), die diagonal zur flächigen Ebene des ersten Hauptankers (12.1) und zweiten Hauptankers (12.2) liegen, wobei die Spannseile (14) zwei diagonal gegenläufige oder entgegengesetzt laufende Spannrichtungen haben und dabei den Umriss eines Hyperboloids bilden. Eine Einzelteildarstellung davon ist abgebildet.
• 16b zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem hyperboloiden Tragstativ (9) und Spannseilen (14), die diagonal zur flächigen Ebene des ersten Hauptankers (12.1) und zweiten Hauptankers (12.2) liegen, wobei die Spannseile (14) zwei diagonal gegenläufige oder entgegengesetzt laufende Spannrichtungen haben und dabei den Umriss eines Hyperboloids bilden. Eine Einzelteildarstellung davon ist abgebildet.
• 17a zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem doppelkegelförmigen Tragstativ (8) und Spannseilen (14), die diagonal zur flächigen Ebene des ersten Hauptankers (12.1) und zweiten Hauptankers (12.2) liegen, wobei die Spannseile (14) vier diagonal gegenläufige oder entgegengesetzt laufende Spannrichtungen haben und dabei die Umrisse zweier Hyperboloide mit verschiedenen Krümmungen bilden. Eine Einzelteildarstellung davon ist abgebildet.
• 17b zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem hyperboloiden Tragstativ (9) und Spannseilen (14), die diagonal zur flächigen Ebene des ersten Hauptankers (12.1) und zweiten Hauptankers (12.2) liegen, wobei die Spannseile (14) vier diagonal gegenläufige oder entgegengesetzt laufende Spannrichtungen haben und dabei die Umrisse zweier Hyperboloide mit verschiedenen Krümmungen bilden. Eine Einzelteildarstellung davon ist abgebildet.
• 18a zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem doppelkegelförmigen Tragstativ (8) und drei unterspannten Spannseilen (14).
• 18b zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem hyperboloiden Tragstativ (9) und drei unterspannten Spannseilen (14).
• 19a zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem doppelkegelförmigen Tragstativ (8) und drei unterspannten Spannseilen (14), wobei die Pfosten (18) durch die jeweiligen Hüllen (4.1 - 4.3) hindurchführen und dabei eine gas- oder luftdichte Verbindung mit diesen bilden. Vergrößerte Ausschnitte davon sind in Vertikalschnitten dargestellt.
• 19b zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem hyperboloiden Tragstativ (9) und drei unterspannten Spannseilen (14), wobei die Pfosten (18) durch die jeweiligen Hüllen (4.1 - 4.3) hindurchführen und dabei eine gas- oder luftdichte Verbindung mit diesen bilden. Vergrößerte Ausschnitte davon sind in Vertikalschnitten dargestellt.
• 20a zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem doppelkegelförmigen Tragstativ (8) und drei unterspannten Spannseilen (14), wobei die Hüllen (4.1 - 4.3) durch die jeweiligen Pfosten (18) hindurchführen, die sich durch die Durchführung der Hüllen (4.1 - 4.3) in jeweils mindestens vier Teile teilen, die mit entsprechenden Hüllenseiten verbunden sind. Vergrößerte Ausschnitte davon sind in Vertikalschnitten dargestellt.
• 20b zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem hyperboloiden Tragstativ (9) und drei unterspannten Spannseilen (14), wobei die Hüllen (4.1 - 4.3) durch die jeweiligen Pfosten (18) hindurchführen, die sich durch die Durchführung der Hüllen (4.1 - 4.3) in jeweils mindestens vier Teile teilen, die mit entsprechenden Hüllenseiten verbunden sind. Vergrößerte Ausschnitte davon sind in Vertikalschnitten dargestellt.
• 21a zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem doppelkegelförmigen Tragstativ (8), wobei der zweite Hauptanker (12.2) auf einem Rumpf (15) aufliegt und an diesem befestigt ist.
• 21b zeigt einen Vertikalschnitt des erfindungsgemäßen Lastabtragungssystems für das aerostatische Auftriebsgerät (1) mit einem hyperboloiden Tragstativ (9), wobei der zweite Hauptanker (12.2) auf einem Rumpf (15) aufliegt und an diesem befestigt ist.
• 22 zeigt einen Vertikalschnitt des erfindungsgemäßen Redundanzsystems und Lastabtragungssystems in Form eines Tragschirms (7) für das aerostatische Auftriebsgerät (1), wobei eine Hülle (4.1 - 4.3) durch Hüllenquerflächen (19) gas- oder luftdicht mit der nächstgelegenen oder benachbarten Hülle (4.1 - 4.3) verbunden ist.
• 23 zeigt einen Vertikalschnitt des erfindungsgemäßen Redundanzsystems für das aerostatische Auftriebsgerät (1) mit vier gruppierten, redundanzerzeugenden Auftriebskörpern (2.1 - 2.4) und dem erfindungsgemäßen Lastabtragungssystem in Form eines Tragschirms (7), mit den Merkmalen des unten genannten Ausführungsbeispiels.
• 24a zeigt einen Vertikalschnitt des Nebenankers (13) und entsprechender Hüllen (4.1 - 4.3) aus dem in 23 gezeigten Ausführungsbeispiel nach Abschluss eines exemplarischen Evakuierungsvorganges. Über dem Nebenanker (13) befindet sich der Auftriebskörper 2.2, unter dem Nebenanker (13) der Auftriebskörper 2.3. Die Vakuumniveaus zwischen und in den einzelnen Hüllen (4.1 - 4.3) werden in prozentualen Angaben bei den entsprechenden Volumen atmosphärischer Luft (5.1 - 5.3) genannt. Die Kennzeichnung bzw. Nummerierung der zwischen den Auftriebskörpern 2.2 und 2.3 liegenden drei Hüllen (4.1 - 4.3) geht in diesem Beispiel vom Auftriebskörper 2.2 aus.
• 24b zeigt einen Vertikalschnitt des Nebenankers (13) und entsprechender Hüllen (4.1 - 4.3) aus dem in 23 gezeigten Ausführungsbeispiel im Falle von Hüllenrissen bzw. -durchbrüchen im Auftriebskörper 2.2. In dem Fall fallen die Vakuumniveaus der zur Umgebungsatmosphäre gerichteten Hüllen (4.1 - 4.3) im Auftriebskörper 2.2 auf 0 %. Die Vakuumniveaus der zwischen den Auftriebskörpern 2.2 und 2.3 liegenden Hüllen (4.1 - 4.3) werden in dem Fall angepasst.

The invention is explained and described in more detail below with reference to the drawings. The drawings are exemplary and schematic representations.

• 1 shows a vertical section of the load transfer system according to the invention with a supporting screen (7) for the aerostatic lifting device (1) in the embodiment of a rotationally symmetrical captive balloon or free balloon.
• 2 shows a vertical section of the load transfer system according to the invention with a support screen (7) for the aerostatic lifting device (1) in the embodiment of a rotationally symmetrical airship with a fuselage (15).
• 3 shows a vertical section of the load transfer system according to the invention with a double-cone-shaped support stand (8) for the aerostatic lifting device (1) in the embodiment of a rotationally symmetrical captive balloon or free balloon.
• 4 shows a vertical section of the load transfer system according to the invention with a hyperboloid support stand (9) for the aerostatic lifting device (1) in the embodiment of a rotationally symmetrical captive balloon or free balloon.
• 5 shows a vertical section of the redundancy system according to the invention for the aerostatic buoyancy device (1) with four grouped, redundancy-generating buoyancy bodies (2.1 - 2.4) and the load transfer system according to the invention in the form of a supporting umbrella (7), with a first main anchor (12.1), a second main anchor (12.2) , a secondary anchor (13), tensioning cables (14) and shells (3.1 - 3.3) with corresponding cases (4.1 - 4.3).
• 6 shows a vertical section of the redundancy system according to the invention for the aerostatic buoyancy device (1) with six grouped, redundancy-generating buoyancy bodies (2.1 - 2.6) and one load transfer system according to the invention with a double-cone-shaped support stand (8).
• 7 shows a vertical section of the redundancy system according to the invention for the aerostatic lifting device (1) with six grouped, redundancy-generating buoyancy bodies (2.1-2.6) and one load transfer system according to the invention with a hyperboloid support stand (9).
• 8th shows a detail of the load transfer system according to the invention with a support umbrella (7) in vertical section, the support cables (11) being connected to the mast (10) via a distributor element (21) which is fastened to the mast (10).
• 9 shows a section of the load transfer system according to the invention a support umbrella (7) in vertical section, the support cables (11) being connected to the mast (10) via a distribution element (21) which is suspended from the mast (10) by means of further support cables (11).
• 10 shows a detail of the load transfer system according to the invention with a support umbrella (7) in vertical section and a support cable (11) under tension.
• 11 shows a vertical section of the load transfer system according to the invention for the aerostatic device (1) with a supporting parachute (7) and tensioning cables (14) which lie diagonally to the planar plane of the first main anchor (12.1) and second main anchor (12.2), the tensioning cables (14) have two diagonally opposite or opposite directions of span, forming the outline of a hyperboloid.
• 12 shows a vertical section of the load transfer system according to the invention for the aerostatic device (1) with a supporting parachute (7) and tensioning cables (14) which lie diagonally to the planar plane of the first main anchor (12.1) and second main anchor (12.2), the tensioning cables (14) have four diagonally opposite or opposite directions of span, forming the outlines of two hyperboloids with different curvatures.
• 13 shows a vertical section of the load transfer system according to the invention for the aerostatic lifting device (1) with a support screen (7) and two tension cables (14) under tension.
• 14a shows a vertical section of the load transfer system according to the invention for the aerostatic device (1) with a supporting parachute (7) and two tension cables (14) under tension, with the posts (18) leading through the respective envelopes (4.1 - 4.3) and thereby being gas-tight or air-tight form a connection with them. Enlarged sections thereof are shown in vertical sections.
• 15a shows a vertical section of the load transfer system according to the invention for the aerostatic device (1) with a supporting parachute (7) and two tension cables (14) under tension, with the sleeves (4.1 - 4.3) leading through the respective posts (18) which extend through the passage of the Divide casings (4.1 - 4.3) into at least four parts each, which are connected to corresponding casing sides. Enlarged sections thereof are shown in vertical sections.
• 16a shows a vertical section of the load transfer system according to the invention for the aerostatic device (1) with a double-cone-shaped support stand (8) and tensioning cables (14) which lie diagonally to the planar plane of the first main anchor (12.1) and second main anchor (12.2), the tensioning cables (14 ) have two diagonally opposite or opposite directions of span, forming the outline of a hyperboloid. An exploded view of it is shown.
• 16b shows a vertical section of the load transfer system according to the invention for the aerostatic device (1) with a hyperboloid support stand (9) and tensioning cables (14) which lie diagonally to the planar plane of the first main anchor (12.1) and second main anchor (12.2), the tensioning cables (14 ) have two diagonally opposite or opposite directions of span, forming the outline of a hyperboloid. An exploded view of it is shown.
• 17a shows a vertical section of the load transfer system according to the invention for the aerostatic device (1) with a double-cone-shaped support stand (8) and tensioning cables (14) which lie diagonally to the planar plane of the first main anchor (12.1) and second main anchor (12.2), the tensioning cables (14 ) have four diagonally opposite or opposite directions of span, forming the outlines of two hyperboloids with different curvatures. An exploded view of it is shown.
• 17b shows a vertical section of the load transfer system according to the invention for the aerostatic device (1) with a hyperboloid support stand (9) and tensioning cables (14) which lie diagonally to the planar plane of the first main anchor (12.1) and second main anchor (12.2), the tensioning cables (14 ) have four diagonally opposite or opposite directions of span, forming the outlines of two hyperboloids with different curvatures. An exploded view of it is shown.
• 18a shows a vertical section of the load transfer system according to the invention for the aerostatic lifting device (1) with a double-cone-shaped support stand (8) and three tension cables (14) under tension.
• 18b shows a vertical section of the load transfer system according to the invention for the aerostatic lifting device (1) with a hyperboloid support stand (9) and three tension cables (14) under tension.
• 19a shows a vertical section of the load transfer system according to the invention for the aerostatic buoyancy device (1) with a double-cone-shaped support stand (8) and three tension cables (14) under tension, the posts (18) leading through the respective casings (4.1 - 4.3) and thereby forming a gas-tight or air-tight connection with them. Enlarged sections thereof are shown in vertical sections.
• 19b shows a vertical section of the load transfer system according to the invention for the aerostatic lifting device (1) with a hyperboloid support stand (9) and three tension cables (14) under tension, the posts (18) leading through the respective casings (4.1 - 4.3) and thereby creating a gas or form an airtight connection with them. Enlarged sections thereof are shown in vertical sections.
• 20a shows a vertical section of the load transfer system according to the invention for the aerostatic lifting device (1) with a double-cone-shaped support stand (8) and three undertensioned tensioning cables (14), with the sleeves (4.1 - 4.3) leading through the respective posts (18) that pass through the passage divide the casings (4.1 - 4.3) into at least four parts each, which are connected to corresponding casing sides. Enlarged sections thereof are shown in vertical sections.
• 20b shows a vertical section of the load transfer system according to the invention for the aerostatic lifting device (1) with a hyperboloid support stand (9) and three undertensioned tension cables (14), with the sleeves (4.1 - 4.3) leading through the respective posts (18) that pass through the passage divide the casings (4.1 - 4.3) into at least four parts each, which are connected to corresponding casing sides. Enlarged sections thereof are shown in vertical sections.
• 21a shows a vertical section of the load transfer system according to the invention for the aerostatic lifting device (1) with a double-cone-shaped support stand (8), the second main anchor (12.2) resting on a fuselage (15) and being attached to it.
• 21b shows a vertical section of the load transfer system according to the invention for the aerostatic lifting device (1) with a hyperboloid support stand (9), the second main anchor (12.2) resting on a fuselage (15) and being attached to it.
• 22 shows a vertical section of the redundancy system and load transfer system according to the invention in the form of a support screen (7) for the aerostatic lifting device (1), with one shell (4.1 - 4.3) being connected to the nearest or neighboring shell (4.1 - 4.3 ) connected is.
• 23 shows a vertical section of the redundancy system according to the invention for the aerostatic buoyancy device (1) with four grouped, redundancy-generating buoyancy bodies (2.1 - 2.4) and the load transfer system according to the invention in the form of a supporting umbrella (7), with the features of the exemplary embodiment mentioned below.
• 24a shows a vertical section of the secondary anchor (13) and corresponding cases (4.1 - 4.3) from the in 23 shown embodiment after completion of an exemplary evacuation process. Above the secondary anchor (13) is the buoyancy body 2.2, below the secondary anchor (13) of the buoyancy body 2.3. The vacuum levels between and in the individual envelopes (4.1 - 4.3) are given in percentages with the corresponding volumes of atmospheric air (5.1 - 5.3). The identification or numbering of the three cases (4.1-4.3) located between the buoyancy bodies 2.2 and 2.3 is based on the buoyancy body 2.2 in this example.
• 24b shows a vertical section of the secondary anchor (13) and corresponding cases (4.1 - 4.3) from the in 23 shown embodiment in the case of shell cracks or breakthroughs in the buoyancy body 2.2. In that case, the vacuum levels of the envelopes (4.1-4.3) facing the surrounding atmosphere fall to 0% in the buoyant body 2.2. The vacuum levels of the envelopes (4.1-4.3) lying between the buoyancy bodies 2.2 and 2.3 are adjusted in this case.

EXEMPLARY EMBODIMENT

The invention is explained and described in more detail below using an exemplary embodiment ( 23 ).

In this example, the aerostatic buoyancy device (1) is designed as a captive balloon. It has a load transfer system, which has a support parachute (7) of the type mentioned at the outset, and a redundancy system, with the buoyancy body (2.1) being supplemented by three further buoyancy bodies (2.2 - 2.4) that create redundancy. A total of four grouped and independently functioning or operable buoyancy bodies (2.1 - 2.4) are formed.

Each buoyant body (2.1-2.4) has three shells (3.1-3.4) lying one inside the other and separated by distances, with corresponding shells (4.1-4.4) directed towards the surrounding atmosphere are, and three shells (3.1 - 3.3) lying one inside the other and separated by distances, with corresponding covers (4.1 - 4.3), which are directed towards the respectively adjacent buoyancy body (2.1 - 2.4).

The mast (10) carries the first main anchor (12.1) at one end by means of suspension cables (11) suspended from the mast (10), which are at an angle of approximately 45° to the mast (10). The mast (10) leads through the flat plane of the first main anchor (12.1) and through the buoyancy bodies (2.1 - 2.4). At its other end, the mast (10) is connected to a second main anchor (12.2) by means of suspension cables (11) suspended from the mast (10), which are also at an angle of about 45° to the mast (10). The suspension cables (11) are each connected to the mast (10) via a distributor element (21), the distributor elements (21) forming an airtight connection with the mast (10).

The first main anchor (12.1) and second main anchor (12.2) carry three shells (3.1-3.3) each with three covers (4.1-4.3) on three sides of their cross-section.

A secondary anchor (13) is located between the first main anchor (12.1) and the second main anchor (12.2) and is connected to them by means of tension cables (14). The secondary anchor (13) carries three shells (3.1-3.3) each with three covers (4.1-4.3) on three sides of its cross-section.

The shells (3.1 - 3.3) directed towards neighboring buoyancy bodies, with corresponding shells (4.1 - 4.3), are connected to the mast (10) via distributor elements (21), the distributor elements (21) forming an airtight connection with the mast (10). form.

Thus, essentially the first buoyant body (2.1) by a distributor element (21) and the first main anchor (12.1), the second buoyant body (2.2) by the first main anchor and the secondary anchor (13), the third buoyant body (2.3) by the secondary anchor (13) and the second main anchor (12.2) and the fourth buoyant body (2.4) spatially and structurally delimited, defined or enclosed by the second main anchor (12.2) and a distributor element (21).

The envelopes (4.1 - 4.3) are airtightly connected to the first main anchor (12.1), the second main anchor (12.2), the secondary anchor (13) and the distributor elements (21). The shells (3.1 - 3.3), with corresponding shells (4.1 - 4.3), of a buoyancy body (2.1 - 2.4) include different volumes of atmospheric air (5.1 - 5.3). In each case, the innermost shell (3.1), together with the innermost shell (4.1), encompasses the largest volume of atmospheric air (5.1).

The mast (10) has free or hollow spaces inside, which allow the passage of hose lines (24) from the external evacuation and supply system (6) into each buoyancy body (2.1 - 2.4) via corresponding passage openings (25) in the mast (10) and in enable the distribution elements (21). The hose lines (24) are used for pumping out and letting in atmospheric air from or into the buoyancy body(s) (2.1 - 2.4).

The first main anchor (12.1), second main anchor (12.2) and secondary anchor (13) have pressure equalization openings in the form of lead-through openings (25) in order to pass between the same shells (3.1 - 3.3) and correspondingly the same cases (4.1 - 4.3) of all buoyancy bodies ( 2.1 - 2.4), to ensure the same vacuum level, i.e. the same air pressure, or to control or adjust vacuum levels between them. The air flow between two sides of the first main anchor (12.1), second main anchor (12.2) and secondary anchor (13) can be controlled by appropriate valves in the pressure equalization openings (25). The valves can be closed to prevent pressure equalization.

In order to generate an aerostatic lift, the volume of atmospheric air (5.1 - 5.3) in the respective envelopes (4.1 - 4.3) is evacuated stepwise or stepwise in each lifting body (2.1 - 2.4). The evacuation and delivery system (6) allows the creation and maintenance of different vacuum levels between the individual cases (4.1 - 4.3). During an evacuation, a sequence of progressively or gradually increasing vacuum levels is generated, starting from the outermost shell (4.3) to the innermost shell (4.1) of each buoyancy body (2.1 - 2.4), with the highest desired vacuum level in the innermost shell ( 4.1) and the lowest desired vacuum level in the outermost shell (4.3) on the side facing the ambient atmosphere.

Vacuum levels can be specified as a percentage. For example, a vacuum level of 75% means that 75% of the air mass in a shell (3.1 - 3n) and its corresponding envelope (4.1 - 4.n) has been removed from it, i.e. pumped out. The surrounding atmosphere forms a vacuum level of 0% as a reference value.

The evacuation process begins with the evacuation of all volumes of atmospheric air (5.1 - 5.3) in the envelopes (4.1 - 4.3) facing the ambient atmosphere in each buoyancy body (2.1 - 2.4) to a vacuum level of 25%. This is followed by the evacuation of the two innermost Volu men of atmospheric air (5.1 and 5.2) in each buoyancy body (2.1 - 2.4) to a vacuum level of 50%. The evacuation process is now completed with the evacuation of the innermost volume of atmospheric air (5.1) in each buoyancy body (2.1 - 2.4) to a vacuum level of 75% ( 24a ).

At the same time, the volumes of atmospheric air (5.1 - 5.3) between those shells (4.1 - 4.3) that are directed towards an adjacent buoyant body (2.1 - 2.4) are also evacuated in stages or stepwise and here follow the evacuation process of the innermost shell (3.1 ) and corresponding to the innermost shell (4.1) of a buoyant body (2.1 - 2.4). This brings the volumes of atmospheric air (5.1 - 5.3) between these envelopes (4.1 - 4.3) to the same vacuum level as that of the innermost shells (3.1) and corresponding innermost envelopes (4.1) of the buoyancy bodies (2.1 - 2.4) (75%). In this case, there is no air pressure difference between the envelopes (4.1 - 4.3), which are aligned with an adjacent buoyant body (2.1 - 2.4) ( 24a ).

This results in a gradual or stepwise sequence of vacuum levels from the outermost shell (3.3) to the innermost shell (3.1), with the values 25%, 50% and 75%. Since the atmospheric air pressure falls proportionally with the increase in the vacuum level, there is a pressure difference of 25% between the individual shells (3.1 - 3.3) and corresponding envelopes (4.1 - 4.3) with respect to the sides facing the ambient atmosphere. These are thereby exposed to only 25% of the total atmospheric air pressure, instead of e.g. a single shell (3.1 - 3.3), such as the innermost shell (3.1), having to cope with an air pressure difference of 75% between it and the surrounding atmosphere. Thus, the aerostatic pressure and tensile forces acting on a shell (3.1 - 3.3) or shell (4.1 - 4.3) are significantly lower, which minimizes the deflection or curvature of the shells (4.1 - 4.3) and their functionality is guaranteed .

Due to the cumulative evacuation of the atmospheric air volume (5.1 - 5.3) in the shells (3.1 - 3.3) and corresponding envelopes (4.1 - 4.3), the mass of the aerostatic buoyancy device (1) as a whole can be less than that of the displaced air volume of the surrounding atmosphere, resulting in an aerostatic lift.

The lead-through openings (25) and valves also serve to minimize, control or avoid a loss of buoyancy in the event of a functional failure of one or more buoyancy bodies (2.1-2.4), for example due to a hull rupture or breach. For this purpose, corresponding lead-through openings (25) and valves can be opened or closed, as required, in order to make air pressure adjustments and to keep the air pressure difference between two adjacent envelopes (4.1 - 4.3) within the assumed limits, so that the functionality of the remaining, unimpaired float (2.1 - 2.4) can be guaranteed ( 24b ).

The atmospheric or aerostatic pressure and tensile forces caused by the evacuation and supply of volumes of atmospheric air (5.1 - 5.3) in the buoyancy bodies (2.1 - 2.4) are absorbed by the shells (3.1 - 3.3) and corresponding envelopes (4.1 - 4.3). the first main anchor (12.1) and the second main anchor (12.2), from these to the suspension cables (11), and from the suspension cables (11) to the mast (10), where they are completely taken up. The four independently functioning or operable buoyancy bodies (2.1 - 2.4) offer redundancy in aerostatic buoyancy.

Reference List

1

Aerostatisches Auftriebsgerät

2.1

Auftriebskörper

3.1 -3.n

Schalen

3.1

Innerste Schale

3.n

Äußerste Schale

4.1 - 4.n

Hüllen

4.1

Innerste Hülle

4.n

Äußerste Hülle

5.1 - 5.n

Volumen des atmosphärischen Mediums

6

Evakuierungs- und Zufuhrsystem

State of the art:

1

Aerostatic buoyancy device

2.1

buoyancy body

3.1 -3.n

Peel

3.1

innermost shell

3.n

outermost shell

4.1 - 4.n

cases

4.1

innermost shell

4.n

outermost shell

5.1 - 5.n

Volume of the atmospheric medium

6

Evacuation and delivery system

7

Tragschirm

8

Doppelkegelförmiges Tragstativ

9

Hyperboloides Tragstativ

2.2 - 2.n

Redundanzerzeugende Auftriebskörper

10

Mast

11

Tragseil

12.1

Erster Hauptanker

12.2

Zweiter Hauptanker

13

Nebenanker

14

Spannseil

15

Rumpf

16

Stativstütze

17

Zugband

18

Pfosten

19

Hüllenquerfläche

20

Halteelement

21

Verteilerelement

22

Stagseil

23

Wantseil

24

Schlauchleitungen

25

Durchführungsöffnung

Invention:

7

umbrella

8th

Double cone-shaped support stand

9

Hyperboloid support stand

2.2 - 2.n

Redundancy-generating buoyancy bodies

10

mast

11

carrying rope

12.1

First main anchor

12.2

Second main anchor

13

secondary anchor

14

tension rope

15

hull

16

tripod support

17

drawstring

18

post

19

hull transverse surface

20

holding element

21

distribution element

22

stay rope

23

shroud rope

24

hose lines

25

feedthrough opening

2.1

Erster Auftriebskörper

2.2

Zweiter Auftriebskörper

2.3

Dritter Auftriebskörper

2.4

Vierter Auftriebskörper

3.1

Erste Schale (Innerste Schale)

3.2

Zweite Schale

3.3

Dritte Schale (Äußerste Schale)

4.1

Erste Hülle (Innerste Hülle)

4.2

Zweite Hülle

4.3

Dritte Hülle (Äußerste Hülle)

5.1

Volumen atmosphärischer Luft in erster Schale

5.2

Volumen atmosphärischer Luft in zweiter Schale

5.3

Volumen atmosphärischer Luft in dritter Schale

Example:

2.1

First lifting body

2.2

Second buoyancy body

2.3

Third buoyancy body

2.4

Fourth buoyancy body

3.1

First Shell (Innermost Shell)

3.2

Second shell

3.3

Third Shell (Outermost Shell)

4.1

First Shell (Innermost Shell)

4.2

second shell

4.3

Third Sheath (Outermost Sheath)

5.1

Volume of atmospheric air in first shell

5.2

Volume of atmospheric air in second shell

5.3

Volume of atmospheric air in third shell

ACHIEVABLE ADVANTAGES

• - ein Lastabtragungssystem für ein aerostatisches Auftriebsgerät der eingangs genannten Art bereitzustellen, das ein baustatisch vollständiges, gewichtssparendes und effizientes Tragsystem darstellt;
• - ein Redundanzsystem für ein aerostatisches Auftriebsgerät der eingangs genannten Art bereitzustellen, um einen aerostatischen Auftriebsverlust infolge eines Hüllenrisses oder -durchbruches zu vermeiden, minimieren oder kontrollieren;
• - ein Funktionssystem bereitzustellen, das die aerodynamischen, aerostatischen und betrieblichen Eigenschaften eines aerostatischen Auftriebsgerätes der eingangs genannten Art energie- und gewichtssparender, effizienter und praktikabler gestaltet.

The invention offers the following advantages:

• - To provide a load transfer system for an aerostatic buoyancy device of the type mentioned, which represents a structurally complete, weight-saving and efficient support system;
• - Provide a redundancy system for an aerostatic buoyancy device of the type mentioned in order to avoid, minimize or control an aerostatic buoyancy loss as a result of an envelope rupture or breach;
• - Provide a functional system that makes the aerodynamic, aerostatic and operational properties of an aerostatic buoyancy device of the type mentioned more energy- and weight-saving, efficient and practicable.

QUOTES INCLUDED IN DESCRIPTION

This list of documents cited by the applicant was generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Patent Literature Cited

• IN 201711018898 [0002, 0010, 0011, 0014, 0019]

Claims (51)

Load transfer system for an aerostatic buoyancy device (1) in the form of a captive balloon, free balloon or airship for lifting or transporting loads in an atmosphere, which has a buoyancy body (2.1) made up of gas-tight or airtight shells (3.1 - 3.n) in the form of foil or membrane-like envelopes (4.1 - 4.n), from which adjustable volumes of the atmospheric medium (5.1 - 5.n) are evacuated by means of an evacuation and supply system (6) and back into them can be let in, whereby the buoyant body (2.1) becomes lighter than the surrounding atmosphere and can bring about and regulate an aerostatic buoyancy, characterized in that it has a support screen (7), wherein - the support screen (7) consists of a mast (10), Suspension cables (11) and a first main anchor (12.1); and - the mast (10) at one end by means of suspension cables (11) suspended or guyed from the mast (10) and located at an angle greater than 0° and less than 90° to the mast (10), the first main anchor (12.1 ) carries and thereby passes through the planar plane of the first main anchor (12.1); and - the first main anchor (12.1) carries at least three shells (3.1 - 3.n) with corresponding at least three shells (4.1 - 4.n) on at least one side of its cross section; and - the mast (10) is located at least in part in the buoyancy body (2.1); and - the atmospherically or aerostatically caused pressure and tensile forces from the shells (3.1 - 3.n) and corresponding envelopes (4.1 - 4.n) to the first main anchor (12.1), from the first main anchor (12.1) to the suspension cables (11), and from the suspension cables (11) to the mast (10); and - a second main anchor (12.2) carries at least three shells (3.1 - 3.n) with corresponding at least three shells (4.1 - 4.n) on at least one side of its cross section; and - the first main anchor (12.1) is connected to the second main anchor (12.2) by tension cables (14); and - the buoyant body (2.1) is spatially and constructively delimited, defined or enclosed essentially by the first main anchor (12.1) on the one hand and the second main anchor (12.2) on the other side; and - in the aerostatic buoyancy device (1) in the embodiment of a tethered balloon or free balloon, the mast (10) at its other end by means of support cables (11) suspended or guyed from the mast (10), which are at an angle greater than 0° and smaller than 90° to the mast (10), is connected to the second main anchor (12.2); and - in the aerostatic lifting device (1) in the embodiment of an airship, the mast (10) and the second main anchor (12.2) rest on a fuselage (15) and are attached to it, the fuselage (15) being subjected to compressive or tensile forces from Buoyancy body (2.1) receives, located below or on the lower side of the buoyancy body (2.1), whereby the focus of the aerostatic buoyancy device (1) lowers or moves down. load transfer system claim 1 , characterized in that the mast (10) has one or more of the following features: - it has at least one passage opening (25) for hose lines (24); - This consists of at least two individual masts (10); - this one has a vertical orientation; - this one has a horizontal orientation; - this one has an inclined orientation; - this supplemented by at least one support, bracing or anchorage; - This is supplemented in the aerostatic lifting device (1) in the embodiment of an airship by at least one stay rope (22) or one shroud rope (23) which is connected to the mast (10) at one end and to the fuselage (15) at the other end is; - This has free or hollow spaces inside, which can accommodate the functions, elements or components of the aerostatic lifting device (1), in particular hose lines (24). load transfer system claim 1 , characterized in that a carrying cable (11) has one or more of the following features: - this is connected to the mast (10) via a distributor element (21) which is fastened to the mast (10); - This is connected to the mast (10) via a distributor element (21) which is suspended from the mast (10) by means of further support cables (11); - This is under-tensioned, with the support rope (11) forming the upper chord and a tie (17), which lies in front of or behind the support rope (11), forming the under-tension, and at least one post (18) forming the support rope (11) with the tie (17) connects. load transfer system claim 3 , characterized in that a distribution element (21) has one or more of the following features: - this forms a gas-tight or air-tight connection with the mast (10) and at least one shell (4.1 - 4.n); - This has at least one feed-through opening (25) for the attachment or implementation of a line, a hose or a valve. load transfer system claim 1 , characterized in that the first main anchor (12.1) has one or more of the following features: - It has pressure equalization openings in the form of lead-through openings (25), bores, channels, holes or perforations; - This is designed as a hollow tube or with cavities; - This carries at least one aerodynamic lift or control surface, in particular a wing or tail unit; - this is supplemented by at least one secondary anchor (13), which is suspended or guyed from the first main anchor (12.1) by means of tension cables (14), with at least three shells (3.1 - 3.n) with a corresponding minimum of three on at least one side of its cross section Cases (4.1 - 4.n) carries and gas or airtight with at least three cases (4.1 - 4.n) is connected. load transfer system claim 1 , characterized in that the second main anchor (12.2) has one or more of the following features: - This has pressure equalization openings in the form of lead-through openings (25), bores, channels, holes or perforations; - This is designed as a hollow tube or with cavities; - This carries at least one aerodynamic lift or control surface, in particular a wing or tail unit; - this is supplemented by at least one secondary anchor (13), which is suspended or braced from the second main anchor (12.2) by means of tension cables (14), with at least three shells (3.1 - 3.n) with a corresponding minimum of three on at least one side of its cross section Cases (4.1 - 4.n) carries and gas or airtight with at least three cases (4.1 - 4.n) is connected. load transfer system claim 5 or 6 , characterized in that a secondary anchor (13) has one or more of the following features: - This has pressure equalization openings in the form of lead-through openings (25), bores, channels, holes or perforations; - This is designed as a hollow tube or with cavities; - This carries at least one aerodynamic lift or control surface, in particular a wing or tail unit. load transfer system claim 1 , characterized in that a shell (4.1 - 4.n) has one or more of the following features: - this is gas-tight or air-tight on at least one side on the first main anchor (12.1); - This is attached gas-tight or airtight on at least one side to the second main anchor (12.2); - This is gas-tight or air-tight on at least one side attached to a secondary anchor (13); - This is suspended or braced on at least one side from the first main anchor (12.1) by means of tension cables (14); - This is suspended or braced on at least one side from the second main anchor (12.2) by means of tension cables (14); - This is suspended or braced on at least one side from a secondary anchor (13) by means of tension cables (14); - This is tensioned, prestressed, tightened or not fluttering attached to the first main anchor (12.1) or second main anchor (12.2); - This is loose, not taut or flapping attached to the first main anchor (12.1) or second main anchor (12.2); - This has a constant distance to the nearest or neighboring shell (4.1 - 4.n); - This has to the nearest or adjacent shell (4.1 - 4.n) a varying distance; - This rests on a carrying cable (11) or tensioning cable (14). Load transfer system according to one or more of the preceding claims, characterized in that the first main anchor (12.1), the second main anchor (12.2) or a secondary anchor (13) have the same diameter, size, cross section or circumference. Load transfer system according to one or more of the preceding claims, characterized in that the first main anchor (12.1), the second main anchor (12.2) or a secondary anchor (13) have a different diameter, size, cross section or circumference. load transfer system claim 1 , 5 or 6 , characterized in that the tensioning cables (14) have one or more of the following features: - they are not orthogonal, ie diagonally, to the planar plane of the first main anchor (12.1), second main anchor (12.2) or a secondary anchor (13), wherein they have two diagonally opposite or opposite directions of span, forming the outline of a hyperboloid; - These are not orthogonal, ie diagonally, to the planar plane of the first main anchor (12.1), second main anchor (12.2) or a secondary anchor (13), with at least four diagonally opposite directions have parallel or opposite directions of span, forming the contours of at least two hyperboloids with different curvatures. load transfer system claim 1 , 5 , 6 or 11 , characterized in that at least one tensioning cable (14) is tensioned, with the tensioning cable (14) forming the upper chord and a drawstring (17), which lies in front of or behind the tensioning cable (14), and at least one post (18 ) connects the tensioning cable (14) to the drawstring (17). load transfer system claim 12 , characterized in that the tensioning cable (14) and the tie (17) are attached at one end to the first main anchor (12.1) or to a secondary anchor (13) and at the other end to the second main anchor (12.2) or to a secondary anchor (13). are. load transfer system claim 12 , characterized in that a post (18) is connected to at least one shell (4.1 - 4.n), the post (18) passing through the shell (4.1 - 4.n) and thereby having a gas-tight or air-tight connection of the envelope (4.1 - 4.n). load transfer system claim 12 , characterized in that a post (18) is connected to at least one sleeve (4.1 - 4.n), the sleeve (4.1 - 4.n) passing through the post (18) which extends through the passage of the sleeve ( 4.1 - 4.n) is divided into at least two parts, which are connected to corresponding envelope sides. Load transfer system for an aerostatic buoyancy device (1) in the form of a captive balloon, free balloon or airship for lifting or transporting loads in an atmosphere, which has a buoyancy body (2.1) made up of gas-tight or airtight shells (3.1 - 3.n) in the form of foil or membrane-like envelopes (4.1 - 4.n), from which adjustable volumes of the atmospheric medium (5.1 - 5.n) are evacuated by means of an evacuation and supply system (6) and back into them can be embedded, as a result of which the buoyant body (2.1) becomes lighter than the surrounding atmosphere and can bring about and regulate an aerostatic buoyancy, characterized in that it has a double-cone-shaped support stand (8), wherein - the double-cone-shaped support stand (8) consists of a first main anchor ( 12.1) and a second main anchor (12.2), which are separated by a distance and lie one above the other, and between which there are non-rigid tripod supports (16) that are not orthogonal, i.e. diagonally, to the flat plane of the first main anchor (12.1) or second main anchor (12.2). which are connected to the first main anchor (12.1) and the second main anchor (12.2) and are located in the buoyant body (2.1); and - the tripod supports (16) are laid diagonally in such a way that they run transversely, in particular centrally, through the enclosed volume of the buoyant body (2.1), points on the first main anchor ( 12.1) and the second main anchor (12.2), crossing along a central straight line orthogonal to the first main anchor (12.1) or second main anchor (12.2), thus forming the outline of two opposite cones that meet at their vertices ; and - the stand supports (16) are held at their crossing point by a holding element (20), in particular a clamp or lacing; and - the first main anchor (12.1) and the second main anchor (12.2) carry at least three shells (3.1 - 3.n) with corresponding at least three shells (4.1 - 4.n) on at least one side of its cross section; and - a shell (4.1 - 4.n) is connected to the first main anchor (12.1) and the second main anchor (12.2) in a gastight or airtight manner on one side in each case; and - the buoyant body (2.1) is spatially and constructively delimited, defined or enclosed essentially by the first main anchor (12.1) on the one hand and the second main anchor (12.2) on the other side; and - the atmospherically or aerostatically caused pressure and tensile forces from the shells (3.1 - 3.n) and corresponding envelopes (4.1 - 4.n) passed on to the first main anchor (12.1), the second main anchor (12.2) and the tripod supports (16) and received by them. Load transfer system for an aerostatic buoyancy device (1) in the form of a captive balloon, free balloon or airship for lifting or transporting loads in an atmosphere, which has a buoyancy body (2.1) made up of gas-tight or airtight shells (3.1 - 3.n) in the form of foil or membrane-like envelopes (4.1 - 4.n), from which adjustable volumes of the atmospheric medium (5.1 - 5.n) are evacuated by means of an evacuation and supply system (6) and back into them can be embedded, whereby the buoyancy body (2.1) can be lighter than the surrounding atmosphere and cause and regulate an aerostatic buoyancy, characterized in that there is a hyperboloid support stand (9) - the hyperboloid support stand (9) consists of a first main anchor (12.1) and a second main anchor (12.2), which are separated by a distance and lie one above the other, and between which they are not orthogonal, ie diagonally, to the planar plane of the first main anchor (12.1) or the second main anchor (12.2) there are rigid tripod supports (16) which are connected to the first main anchor (12.1) and the second main anchor (12.2) and are located in the buoyant body (2.1); and - the stand supports (16) are laid diagonally so that they do not run transversely, in particular not centrally, through the enclosed volume of the buoyant body (2.1), and not at diametrically opposite points, ie points offset by less than 180° on the first main anchor (12.1) and the second main anchor (12.2), laid in at least two opposite or opposite laying directions, with corresponding laying angles, thus forming the outline of a hyperboloid or at least two hyperboloids with different curvatures; and - at least two counter-rotating or counter-rotating stand supports (16) are held at their crossing point by a holding element (20), in particular a clamp or lacing; and - the first main anchor (12.1) and the second main anchor (12.2) carry at least three shells (3.1 - 3.n) with corresponding at least three shells (4.1 - 4.n) on at least one side of its cross section; and - a shell (4.1 - 4.n) is connected to the first main anchor (12.1) and the second main anchor (12.2) in a gastight or airtight manner on one side in each case; and - the buoyant body (2.1) is spatially and constructively delimited, defined or enclosed essentially by the first main anchor (12.1) on the one hand and the second main anchor (12.2) on the other side; and - the atmospherically or aerostatically caused pressure and tensile forces from the shells (3.1 - 3.n) and corresponding envelopes (4.1 - 4.n) passed on to the first main anchor (12.1), the second main anchor (12.2) and the tripod supports (16) and received by them. load transfer system Claim 17 , characterized in that a cover (4.1 - 4.n) rests on at least one stand support (16). load transfer system Claim 16 or 17 , characterized in that tension cables (14) connect the first main anchor (12.1) and the second main anchor (12.2) to one another. load transfer system claim 19 , characterized in that the tensioning cables (14) are not orthogonal, ie diagonally, to the planar plane of the first main anchor (12.1) or second main anchor (12.2), thereby having two diagonally opposite or opposite tensioning directions and forming the outline of a hyperboloid. load transfer system claim 19 , characterized in that the tensioning cables (14) are not orthogonal, i.e. diagonally, to the flat plane of the first main anchor (12.1) or second main anchor (12.2), have at least four diagonally opposite or opposite tensioning directions and the outlines of at least two hyperboloids form different curvatures. load transfer system claim 19 , 20 or 21 , characterized in that at least one tensioning cable (14) is tensioned, with the tensioning cable (14) forming the upper chord and a drawstring (17), which lies in front of or behind the tensioning cable (14), and at least one post (18 ) connects the tensioning cable (14) to the tie (17), and wherein the tensioning cable (14) and the tie (17) are attached at one end to the first main anchor (12.1) and at the other end to the second main anchor (12.2). load transfer system Claim 22 , characterized in that a post (18) is connected to at least one shell (4.1 - 4.n), the post (18) passing through the shell (4.1 - 4.n) and thereby having a gas-tight or air-tight connection of the envelope (4.1 - 4.n). load transfer system Claim 22 , characterized in that a post (18) is connected to at least one sleeve (4.1 - 4.n), the sleeve (4.1 - 4.n) passing through the post (18) which extends through the passage of the sleeve ( 4.1 - 4.n) divided into at least two parts, which form a connection with one side of the envelope each. load transfer system Claim 16 until 24 , characterized in that the first main anchor (12.1) has one or more of the following features: - It has pressure equalization openings in the form of lead-through openings (25), bores, channels, holes or perforations; - This is designed as a hollow tube or with cavities; - This carries at least one aerodynamic order drive or control surface, in particular a wing or tail unit. load transfer system Claim 16 until 24 , characterized in that the second main anchor (12.2) has one or more of the following features: - This has pressure equalization openings in the form of lead-through openings (25), bores, channels, holes or perforations; - This is designed as a hollow tube or with cavities; - This carries at least one aerodynamic lift or control surface, in particular a wing or tail unit. load transfer system Claim 16 until 26 , characterized in that the second main anchor (12.2) rests on a hull (15) and is attached to it, the hull (15) absorbing compressive or tensile forces from the buoyant body (2.1) and being below or on the lower side of the buoyant body (2.1) is located, whereby the focus of the aerostatic buoyancy device (1) lowers or moves down. Load transfer system according to one or more of the preceding claims, characterized in that a carrying rope (11), tensioning rope (14), stay rope (22), shroud rope (23) or tension strap (17) is made of a natural fiber, ie animal, vegetable or mineral fibre. consists, in particular bamboo, cotton, flax, hemp, jute, silk, including composite materials reinforced with natural fibers. Load transfer system according to one or more of the preceding claims, characterized in that a carrying cable (11), tensioning cable (14), stay cable (22), shroud cable (23) or tie (17) consists of a synthetic or chemical fiber, ie a fiber made of natural polymers, synthetic polymers or inorganic materials, in particular aramid, fibers based on ultra high molecular weight polyethylene, carbon fibers, metals and metal alloys. Load transfer system according to one or more of the preceding claims, characterized in that the outermost shell (3.n), with the corresponding outermost shell (4.n) of a buoyancy body (2.1), has an outer shell which protects against external atmospheric, environmental or weather-related influences corresponding outer shell forms. load transfer system claim 1 or 27 , characterized in that the fuselage (15) has one or more of the following features: - This carries at least one aerodynamic lift or control surface, in particular a wing or tail unit; - This protrudes or protrudes on at least one side beyond the outline of the outermost shell (3.n) and correspondingly the outermost shell (4.n) of the buoyant body (2.1); - This forms on at least one side an aerodynamically effective or geometrically mutually adapted transition with the outermost shell (3.n) and accordingly with the outermost shell (4.n) of the buoyancy body (2.1); - this has at least one synclastic or anticlastic curvature on its surface; - this varies in width or height, having narrower and wider parts or sections, with rounded or smooth transitions between them; - This is at least partially within the buoyancy body (2.1); - this is designed as a pressurized cabin; - This has a payload cabin, which is loaded and unloaded via a rear door, preferably via a tailgate; - This has a cockpit, which is spatially connected to a payload cabin, is spatially connected to it and is located in front of it. Load transfer system according to one or more of the preceding claims, characterized in that a mast (10), the first main anchor (12.1), the second main anchor (12.2), a secondary anchor (13), a hull (15), a distributor element (21) , a post (18), an aerodynamic lifting or control surface, in particular a wing or tail unit, has one or more of the following features: - this consists of a natural fiber, ie animal, vegetable or mineral fiber, in particular of Bamboo, wood, derived timber products, paper, cardboard, including composite materials reinforced with natural fibers; - this consists of an artificial or man-made fibre, ie a fiber made from natural polymers, synthetic polymers or inorganic substances, in particular aluminum-lithium alloys, aramid, fibers based on ultra-high molecular weight polyethylene, carbon fibers and composite materials with carbon fibers. Redundancy system for an aerostatic buoyancy device (1) in the form of a captive balloon, free balloon or airship for lifting or transporting loads in an atmosphere, which has a buoyancy body (2.1) made up of gas-tight or airtight shells (3.1 - 3.n) in the form of foil or membrane-like shells (4.1 - 4.n) from which adjustable volume of the atmospheric Medium (5.1 - 5.n) can be evacuated by means of an evacuation and supply system (6) and let back into it, whereby the buoyant body (2.1) can become lighter than the surrounding atmosphere and can cause and regulate an aerostatic buoyancy, characterized in that - the buoyant body (2.1) is supplemented by at least one further buoyant body (2.2 - 2.n) which creates redundancy; and - each additional, redundancy-generating buoyancy body (2.2 - 2.n) is grouped with the first buoyancy body (2.1) and functions or can be operated independently of the first buoyancy body (2.1) and of each other, so that each buoyancy body (2.1 - 2.n) forms a functionally independent section, unit, chamber, section; and - each additional, redundancy-generating buoyant body (2.2 - 2.n) also consists of nested, gas-tight or airtight shells (3.1 - 3.n) in the form of foil or membrane-like casings (4.1 - 4.n), in which different degrees of evacuation, vacuum or negative pressure levels are generated, whereby all buoyancy bodies (2.1 - 2.n) are lighter than the surrounding atmosphere and can cause and regulate an aerostatic buoyancy. redundancy system Claim 33 , characterized in that at least one shell (4.1 - 4.n) is connected gas-tight or airtight to the nearest or neighboring shell (4.1 - 4.n) by cross-connection-like shell segments, in particular transverse shell surfaces (19), the transverse shell surfaces (19 ) may be oriented horizontally, vertically or diagonally, and are designed so that the space or volume between the adjacent or adjacent shells (4.1 - 4.n) is divided into at least two compartments or compartments, while the transverse surfaces of the shell (19) pressure - or absorb tensile forces. redundancy system Claim 33 or 34 , characterized in that there is a load transfer system claim 1 until 15 has, wherein the load transfer system, in particular the parachute (7), carries more than one buoyancy body (2.1), and each buoyancy body (2.1 - 2.n) through the first main anchor (12.1), second main anchor (12.2), a secondary anchor (13 ) or a distribution element (21) spatially and structurally delimited, defined or enclosed. redundancy system Claim 33 or 34 , characterized in that there is a load transfer system Claim 16 and 19 until 27 the buoyant body (2.1) is supplemented by at least one further buoyant body (2.2 - 2.n), each with a double-cone-shaped support stand (8), and each buoyant body (2.1 - 2.n) by its first main anchor (12.1) and second main anchor (12.2) is spatially and constructively limited, defined or enclosed. redundancy system Claim 33 or 34 , characterized in that there is a load transfer system Claim 17 until 27 the buoyant body (2.1) is supplemented by at least one further buoyant body (2.2 - 2.n) each with a hyberboloid support stand (9), and each buoyant body (2.1 - 2.n) by its first main anchor (12.1) and second main anchor (12.2) is spatially and constructively limited, defined or enclosed. redundancy system Claim 33 or 34 , characterized in that there is a load transfer system claim 28 until 32 has. redundancy system Claim 33 until 38 , characterized in that a first main anchor (12.1), second main anchor (12.2) or secondary anchor (13) has pressure equalization openings in the form of lead-through openings (25), bores, channels, holes or perforations. redundancy system Claim 39 , characterized in that at least one pressure equalization opening has a valve for controlling or preventing the flow of atmospheric medium. redundancy system Claim 33 and 35 , characterized in that at least two grouped and independently functioning or operable buoyancy bodies (2.1 - 2.n), for the purpose of stowage or space-saving on the ground, can be pulled in and out, folded in and out or collapsed together by the mast (10) is retracted and extended telescopically, as a result of which the buoyancy bodies (2.1 - 2.n) connected to the mast (10), together with the first main anchor (12.1) or a secondary anchor (13), corresponding shells (3.1 - 3 .n) and their cases (4.1 - 4.n) as well as with corresponding supporting ropes (11) or tensioning ropes (14) can be raised and lowered, folded in and out or raised and retracted, with the cases (4.1 - 4.n) , Supporting ropes (11) or tensioning ropes (14) are designed to be flexible or foldable. redundancy system Claim 33 until 41 , characterized in that the outermost shells (4.n) of the buoyancy bodies (2.1 - 2.n) on at least one side, in particular the front side, of the aerostatic buoyancy device (1) are made of a more rigid, thicker, more tear-resistant, stronger or more durable material than exist on the other sides. redundancy system Claim 33 until 42 , characterized in that it uses at least one aerodynamic lift or control surface, in particular a wing or tail unit, for lift supplementation and flight control, which is controlled by a first main anchor (12.1), a second main anchor (12.2), a secondary anchor (13) or a Hull (15) from the load transfer system claim 1 , 5 , 6 , 16 , 17 or 27 being carried or supported. redundancy system Claim 33 and 35 , characterized in that it has a parachute system as the overall rescue system, which is part of the supporting parachute (7) and is located inside the mast (10), being attached or anchored to the mast (10), whereby when the parachute system is used, at least a parachute emerges from an opening at one end of the mast (10) into the surrounding atmosphere and then opens. redundancy system Claim 33 until 44 characterized in that the evacuation and delivery system (6) has one or more of the following features: - it is powered by electric power; - This is powered by a fuel; - This is powered by renewable energy sources; - This is powered by electricity that is obtained from photovoltaics, ie solar cells, or from solar thermal energy; - This is operated by electric current, which is obtained from photovoltaics, ie solar cells, the solar cells being on board the aerostatic lifting device (1); - This uses the suction pressure or suction of a vacuum or negative pressure previously created in the shells (3.1 - 3.n) to admit the volumes of atmospheric medium (5.1 - 5.n) into the shells (3.1 - 3.n). Functional system for an aerostatic buoyancy device (1) in the form of a captive balloon, free balloon or airship for lifting or transporting loads in an atmosphere, which has a buoyancy body (2.1) made up of gas-tight or airtight shells (3.1 - 3.n) in the form of foil or membrane-like envelopes (4.1 - 4.n), from which adjustable volumes of the atmospheric medium (5.1 - 5.n) are evacuated by means of an evacuation and supply system (6) and back into them can be embedded, whereby the buoyant body (2.1) becomes lighter than the surrounding atmosphere and can bring about and regulate an aerostatic buoyancy, the aerostatic buoyancy device (1) depending on the embodiment having a drive system which is optionally located within a shell, characterized in that the drive system, in particular an engine or engine, via support elements from a fuselage (15) in a load transfer system claim 1 or 27 supported or carried. Functional system for an aerostatic buoyancy device (1) in the form of a captive balloon, free balloon or airship for lifting or transporting loads in an atmosphere, which has a buoyancy body (2.1) made up of gas-tight or airtight shells (3.1 - 3.n) in the form of foil or membrane-like envelopes (4.1 - 4.n), from which adjustable volumes of the atmospheric medium (5.1 - 5.n) are evacuated by means of an evacuation and supply system (6) and back into them can be embedded, whereby the buoyant body (2.1) becomes lighter than the surrounding atmosphere and can bring about and regulate an aerostatic buoyancy, the aerostatic buoyancy device (1) depending on the embodiment having a drive system which is optionally located within a shell, characterized in that the drive system, in particular an engine or engine, via tension elements from the first main anchor (12.1), second main anchor (12.2) or from a secondary anchor (13) in a load transfer system claim 1 , 5 , 6 , 16 or 17 is suspended or braced. functional system Claim 46 or 47 , characterized in that the external appearance or shape of all buoyancy bodies (2.1 - 2.n) in their cumulative totality, which is largely determined by the outermost shells (4.n) of the buoyancy bodies (2.1 - 2.n), one or more having the following characteristics: - it generates an aerodynamic lift during the flight of the aerostatic lift device (1); - This has at least one synclastic or anticlastic curvature on the surface of the outermost shells (4.n) of the buoyancy bodies (2.1 - 2.n); - In the front view of the aerostatic buoyancy device (1), this has a circular, elliptical, semi-circular, semi-elliptical, pointed arch, parabolic, teardrop-shaped, egg-shaped, rectangular, trapezoidal, rhombic or equal-width outline; - In the side view of the aerostatic buoyancy device (1), this has a circular, elliptical, semi-circular, semi-elliptical, pointed arch, parabolic, teardrop-shaped, egg-shaped, rectangular, trapezoidal, diamond-shaped or of equal thickness outline, with an axis of symmetry of the outline, and thus the outline itself, vertically oriented, tilted forwards or backwards; - In the front or side view of the aerostatic buoyancy device (1), this has a rectangular, trapezoidal, diamond-shaped or constant-thickness outline, which is rounded at at least one corner or edge. functional system Claim 46 until 48 , characterized in that the atmosphere in which the aerostatic lift device (1) is located is the atmosphere of a planet, in particular of Earth, Mars and Venus, and that the volumes of the atmospheric medium (5.1 - 5.n) consist of or be related to the respective atmosphere or the respective atmospheric medium in which the aerostatic lifting device (1) is located. functional system Claim 46 until 49 , characterized in that it has a load transfer system according to one or more of the preceding claims. functional system Claim 46 until 50 , characterized in that it has a redundancy system according to one or more of the preceding claims.

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