DE2313919A1 - PULL-UP BODY, IN PARTICULAR FOR AN IMPACT AIRSHIP - Google Patents

Description

Ing, Hermann Pope March 19, 1973

7742 8-t. Georgen / Black Forest 2313919 001/055-HIfr / Ar

Gas carrier, in particular for an impact airship

The invention relates to a gas support body, in particular for a Bulging airship.

Well-known gas-tight airship bodies are due to the dynamic pressure at the bow tip under overpressure. The one about the movement of the airship resulting back pressure causes a compression of the Lifting gas and a reduction in buoyancy. In the case of such known arrangements, this also leads to greater stress of the walls of the mainly supporting middle part of the envelope wall, whereby the envelope weight and also the effort for the Shell is relatively high. At the same time, this indicates a loss of useful lift, drive power, and construction and operating costs.

The invention is based on the described disadvantages to overcome, and to achieve a pressure relief of the gas space in an advantageous manner.

According to the invention this is achieved in that the airship body at the bow and at the stern in the area of the pressure change circle, which is about a circle of 0.6 times the largest diameter corresponds, through wan. β is subdivided, which absorb axial pressure and show no significant change in shape radially, these walls with the actual supporting gas envelope absorbing thrust are connected.

As a result, an overpressure is created by the dynamic pressure at the tip of the bow upright, gas-tight airship body, in particular made of fabrics with foils, on the bow and also on the stern due to inherent rigidity Walls divided in such a way that the turf provides considerable pressure relief. A high speed of the air

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ships will then no longer lead to compression and a reduction in buoyancy in the Gaavo lumlna due to the dynamic pressure. The stress on the walls of the mainly load-bearing middle part is significantly reduced because the mean lifting gas pressure only needs to be about half of the maximum dynamic pressure. The envelope weight is reduced with the same security. The associated expenditure in terms of load-bearing capacity and construction, as well as drive power and construction operating costs are reduced.

As a result of the subdivision of the airship body by means of the partition walls in the bow and stern, which depend on axial and radial dimensional stiffness to absorb the pressure forces acting from the outside on the bow and stern, the production of such envelopes from several, separately dimensionally stable ring parts and other joining together from the outside possible. In particular, in impact airships, the use of inflatable double walls, which are sufficiently self-contained with the appropriate pressure, is of considerable advantage, since a hall is not necessarily required for this.

In an embodiment of the invention, the gas envelope is preferably provided in its middle with a further subdivision, the clay is partitioned off two bulky, membrane-like walls that can bulge apart and towards each other, the latter extending up to the liiill-Yolumeni between the same) zacke air-free filling approach with a flammable daytime gas.

Hie inventive arrangement is particularly advantageous for rear-wheel drive with Blasstrahldücen because high fan pressure is applicable "Ia under higher impact pressure front section Kings nen expansion tank for the shielding gas for be with ¥ ärmeisolation working impingement iuftschiff with Hing Construction Torge See" Jü "aerodynamic Pora is not disturbed ·

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The carrying case body according to the invention or the shell wall are preferably near the tropic of pressure and suction divided by special partitions, 'wooei these Tragwänae in radial Direction and advantageous hold also stiff in the axial direction are, so α aß ο the form of the trag,, ashülle not distorted will. The partition walls are designed so that they against the center of the airship body directed dynamic pressures at least in the area of the respective horizontal components record and transfer to the outer shell wall, if not the surface area of the bearing pressure is sufficient for this. The mean value of the horizontal components of the pressure on the nose surface within the turning circle diameter is according to the so-called Fuhrmann curve about 0.24, i.e. H. around 1/4 of the peak pressure on the center of the bow, whereby the lower circle diameter corresponds to 0.6 times the outer diameter. The lifting gases The adjacent bow wall can therefore be supported by the supporting turf with about 3 pressure above it. The support pressure aettt from the gas buoyancy and any required static Pressure together. The in haloer height acting ^ mean value.

It can be advantageous to use the bow partition with its intransigent Edge part consisting of a hollow ring or a truss can consist of unyielding supports made of pipes or latticework to connect with the keel. This makes it possible to forego the static counterpressure in the buoyancy gas, because of this shortfall from the steep rings of the -ug- or Sternv: and then balanced by the keel frame between the eye and corner walls can be. Further invention is related to this the bow-over rear wall of a hollow, plate-shaped Lattice framework was d, advantageously white with a tight cover educated. As an alternative to this or in addition, according to a wtifceren Design ο he invention the wall of a hard-inflated, little elastic ring and a curl-shaped are formed on tensile stressed element.

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Ea also act j ie horizontal Scgjcciiponenten on the vault-Len trap askörperteil axiberh ^r ~. _b üe3 the turning circle between pressure and suction. In the case of a Prall-Lul chilf not with protective garb inflated Dopyeiwandriri,: en can the.; e the thrust in the direction of their width on aie Trei.n.vand im - ^! -ug and in the stern easily transferred.

One can make use of the printing division without further use because yes eggs suction on the Ki ΐ.telteil containing the carrier gas, a considerable amount has and can reach up to 40 i "of the maximum dynamic pressure. Here it is, however, favorable that the diameters at these points are smaller than the largest diameter dc3 of the central part, which is also affected by a lower suction vacuum.

Another embodiment vorteilh.u ie aer invention provides that the hugfiäcne and the rear wall are of at least näherungsweiae spherical Wänaen, retildet, wherein the bow or the stern durcn a movable aichte V / and in two gas spaces divided can v / ground, One of them is under blowing pressure as a result of the dynamic pressure that occurs in flight; it is under blood pressure, so that the movable viand with the inner wall of the sleeve converts an otherwise required gas -: - r pressure is set and un ; erdennen pressure and to ^ a. Never pull lu £ t. The. e so-called iugi "rennwand or Heekirennvand are 'Xoer äaa aeic Iragrasiorper connected keel bridges ^' .: arm Tr.it υ in an α er at a distance r.sha

Continue to invent _; s ^ emäß iöt provided "AASS it from the carrier gas inde pendent ^ ugrauffl to be la Fiu £ CIIT iMz't ^out; läat fill it flight bie zwa dynamic pressure automatically, wherein a safety valve can be spread during the descent air at excess pressure. Soliliefllicii is invented, an inflated ring body to absorb ττοη axial forces in the subdivision of a supporting body so auasugeetalton that srlndeotens the back surface on the side ö 3 smaller l ^ aükea through

409S33 / 0136 " ³ "

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a tensioned, gas-tight wall or at least through a diagonal Belts on a ring body absorbs twisting forces through radial tension.

The drawing shows exemplary embodiments and further embodiments of the invention.

Figure 1 shows a gas carrier for airships that has a common Interior has. The distribution of pressure and suction circular lines, which are 0.6 times the diameter, are sing - indicates. The entire pressure distribution curve is determined by the maximum dynamic pressure at the given speed of the iPlug-

body. The support body, which is to be regarded as a boiler, must be there be sized anywhere for this print. In the middle part there is also the suction as a result of the flow around it, because this is exactly it acts like pressure from within in the same direction. In addition, the suction has to be added. The shell must 'therefore Be dimensioned for a greater pressure than for a ram pressure so that the bow is not deformed.

Figure 2 shows the arrangement according to the invention with partitions in the area of the turning zone of the pressure in the bow and stern. The partitions can, for example, be made from a large honeycomb structure exist, which is glued on both sides with panels.

Be at the joint-steep can simultaneously bow and ^ü hatched hurry, and En-en With the connected elteile.

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At the connection point, the bow and stern parts can be used at the same time as well as the ends of the Mittelteila be connected. Dae Ganz is then tied to the keel with a strap over the greater part of the length of the tragic body, which, however, is not shown is. It can be seen that the pressure in the inner part is low greater than about the fourth part of the maximum dynamic pressure to i needs to be. This is usually caused by the buoyancy pressure achieved at a height of half the diameter.

Because the airship body must also be able to assume an incline of up to 30 ° to the horizontal, one will dtn; Maximum internal pressure at the top of the ends of the Traggae middle section \ for a larger Traggae pressure height of T, 8 χ d. This applies to a full filling with hydrogen. With partial filling or ^! For operation only with natural gas or steam, a pressure level of around 1.1 χ d is sufficient.

where Figure 3 shows another arrangement where the ϊβϊϊ Bug ¥ iX a special spherical space that is tightly sealed by inert gas space

having
is divided. The connection may be made with the aid of a more strongly inflated ring of tissue. On this ring eineniehtgezeicinieter can saeharti- gsx vessel wall mounted leg ₅ which can divide the Xugelraum in two gas ". * The front room mtg are under pressure, which corresponds to the maximum dynamic pressure in the middle. The rest of the air is used to take up protective gas, which is drained from the protective gas space to take up the expansion gas and the double wall is again put under full pressure on the descent Outside the gas wall, fans (not shown) are arranged to create the necessary overpressure in the double seed wall. It should be mentioned that when running at a constant height, the fans can be shut off by closing the lines.

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In the stern, a lattice is shown, which the forces in makes the rear bladder independent of the lifting gas.

In the case of the one not shown (because it is dealt with in other patents) Rear-wheel drive can therefore pressure the jet propulsion from the lifting gas interpret completely independently. The pressure can be considerably higher than the peak pressure because the nozzle jet is faster flows out as the feed rate. The arrangement leaves accommodate a relatively large amount of lift gas in the entire airship body.

In Fig. 4 there is a middle division of the gas space shown. A lattice ring or inflation ring fastened to the shell is gas-tight with two membrane-like, bendable Walls connected.

It is suggested to fill this space with a lifting gas, for example hydrogen, which can be supplied with a certain amount of water vapor. With such a gas mixture one can Boiling point of the water in this room to the partial pressure of the water vapor compared to the rest of the gas (according to the law of Dalton). All that is needed is a sealed amount of water and such a supply of heat that just the flowing back Condensate is evaporated again. The device for this is not shown since it is easily understandable. Man the returning water will act on a contact balance. As long as water in the container exerts weight on the scales, i.e. is present, heat is supplied, for example by Conduction of waste heat flows from cooling water or exhaust gases through a radiator. When the water disappears in the contact balance the heat flow is reduced or switched off.

It can also be sufficient that only one downpipe for the condensed water is laid out in such a way that it always fills with water, while the steam rises unaffected by it at another point, for example through a U-tube. Let it be for example only the bottom of this container is provided with heating ribs.

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The heat transfer will then be intense as long as there is water on this floor. When there is no more water is, then only the amount that flows back as condensate can be evaporated. This gives a very simple automatic control of the temperature in the gas space between the two membranes. You are indulgent designed to handle the changing gas volumes at the bottom and to be recorded in height without pressure. The arrangement is therefore in the middle, so that the heating effect on both sides occurs evenly and there is symmetry in the gas space.

In Figure 4 it is also shown that the subdividing the support body Front and rear walls as a lattice framework advantageously also with a lattice framework continuously under the gas envelope can be connected. In addition, this connection takes the possibly missing pressure in the lower part of the gas envelope on.

This arrangement may also serve to facilitate assembly of the system. On the scaffolding, the middle wall is connected to the ring, which can also be a framework ring. From there, you can line up the inflated rings symmetrically and connect them from the outside or, as long as the system is not closed, from the inside. Man can work in this system, since he is not pressed down by the shell but works in the open air. This is important for the production of impact airships of any size. So far, the limit was about βο, οοο m ^ total volume of impact ships with a simple fabric shell, it was also not possible to build airships with an inner support frame as small as desired, otherwise the lattice girders would have had to have too weak wall thicknesses, apart from the complexity .

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ORiGINAL INSPECTED

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The arrangement according to the invention is not limited to a steam lift compensation airship in which Natural gas from the envelope is consumed and replaced by recirculated water vapor in order to keep the buoyancy the same. It is also applicable to airships that Extract natural gas from the envelope to such an extent that the weight of used aviation fuel is balanced. But it is also with airships that work according to other systems to use with success. In addition to the system of subdivision: Approximately in the middle of the gas space, a disc of heated gas is provided, which in turn is steam Heat is supplied. The ones in the disk array Amount of gas located and the supplied water vapor respectively. the total amount of water present in the circuit are included so mutually tunable that the desired temperature of the boiling or. Condensation point is reached; which, for example, 81 ° C at a ratio of 5o% Hydrogen (or another gas) to 5o% steam. According to Dalton, a gas behaves in a mixture with others as if it were there alone. The resulting lowering of the boiling point in this example corresponds to the boiling point of water at a height of 5 km.

But you can set any temperature, for example 50 ° C. The tables for with humidity saturated air show at 5o ° C (e.g. tropical temperature) in one cubic meter of water. A lower operating temperature of the buoyancy gases would be important in order to further reduce the heat loss through the thermally insulated envelope Reduce. In particular, the proportion of heat radiation is then greatly reduced.

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409839/0 136 ORIGINAL INSPECTED

Claims (8)

- ίο - Ing.Hermann Papst 19.3.73 St. Georgen 001/055 / Pe Claims Gas carrier, especially for a Pral1 airship, characterized in that the airship body at the bow and at the stern in the area of the pressure change circle, which corresponds approximately to a circle of 0.6 times the largest diameter, divided by walls is, which absorb axial pressure and show no significant change in shape radially, with dies.e walls connected to the actual gas shell in a thrust-absorbing manner are. 2) airship body according to claim 1, characterized in that the carrier gas envelope preferably has a further subdivision in its center, which is sealed off by two bulky, membrane-like walls that can bulge apart and against each other, the latter extending up to zero volume between the same can approach for the purpose of air-free filling with a flammable lifting gas. 3) gas support body according to claim 1 or 2, characterized in that the bow and stern - walls of fetch, plate-shaped lattice framework walls, preferably with a tight cover, are formed, 4) Support gas body according to claim 1 or Z _5, characterized in that the walls are formed by hard inflated weoig elastic rings and ball scha If ö> isi <| en ₅ elements subjected to tension. 5) gas carrier according to any ¹ of claims 1-4, characterized in that the bow surface and the rear wall are at least roughly spherical, the bow and stern space being divided into two fiasräuae by a movable dense man, one of which is under blowing pressure as a result 403839/0138 3/19/73 of the dynamic pressure occurring in flight (or under blower pressure), so that the movable wall with the inner Kugelwand puts an otherwise required gas under pressure and can expand and contract under pressure. 6) Luftschi ffkörper according to one of the preceding claims, characterized characterized in that the bow partition wall and the stern partition wall via the keel bridge structure connected to the gas support body are kept at a distance from each other. 7) gas support body according to one of the preceding claims, characterized in that that the bow space, which is independent of the lifting gas, is connected to the outside space by inflation can be filled with air from the direction of flight up to the ram pressure, with a safety valve during the descent with air with overpressure can flow out. 8) Inflated ring body, especially for the inclusion of axial forces in the subdivision of a gas carrier, characterized in that at least the annular surface the side of the lower pressure - through a tensioned gas-tight wall or at least through diagonal belts - on the Ring body absorbs twisting forces through radial tensile stresses. 409839/0136