DE2142429A1 - Buoyancy system - Google Patents

Description

Buoyancy system

The invention relates to a buoyancy system for Creation of vertical lift.

The system according to the invention is particularly suitable for use with free-flying missiles of the type commonly referred to as "floating missiles", but is not limited to such use. In this context, a distinction must be made between a "hovercraft" and a ground effect or hovercraft, the latter building an air cushion by means of sucked in and downward expelled atmospheric air "on which it floats * Accordingly ^; Opposite are "Schv / ebeflugkörper", for which the best known

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SaÄsr.tan; H. AvlfiSusor, MBnshan 173 -S3 · Ώύυΐίά.ι Bon!:, ÄtänoSon) <5 / 250J3 · iojlschadAonlo Mu.jA-w 44312

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Example of the helicopter is, not how. the hovercraft, limited to operation within a meter or a little more over an area, but produce an independent one in a manner similar to a fixed-wing aircraft Boost.

Known operational "hovercraft" are characterized by a rotating float or propeller., by means of which the necessary lift forces on conventional V / can be generated. The intricate structure of such rotary wing assemblies, especially for helicopters, is at which the angle of attack of the rotary blades is constantly changing) is generally known and "does not need to be discussed here. In addition to such missiles using a rotating wing arrangement rotating predominantly in a horizontal plane various independent lift-generating missiles proposed, in which approximately from the center of the missile Air in all directions via a rigid arrangement of the floats is blown out to create a vertical lift. According to such proposals, the air should along both the top and the bottom of the buoyancy bodies are blown out, with a buoyancy according to the known aerodynamic principles arise. .

The proposed lift systems with rigid arrangement for the float but were / escape disgusted not v pus because of the obvious shortcomings of this construction. In practice, because of their design-related properties, such systems would deliver only an extremely low level of lift and consequently only allow little or no payload at all. Even more serious is the fact that no applicable method has yet been found for the control or guidance of such missiles. The poor maneuverability also characterizes the known missiles with rotating propellers, with the exception of the 'relatively complex helicopters and the like. Poor steerability is obviously an ornate thing to do when the missile al a

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^r OrttGlNAL. INSPECTED

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Observation platform for military purposes or, named, to serve for sport purposes. Previous attempts, relative cheap plug bodies equipped with cameras in the field to use, remained unsuccessful, since such missiles only vertically above and connected to a ground station were deployable and thus revealed the position of the ground personnel.

An important object of the invention is to provide such ■ To overcome the difficulties of known devices and an operationally reliable one with simple, economical means To create a system for generating vertical lift, which can be used for a novel, steerable hovercraft.

In a buoyancy system of the type mentioned above erfindungsger.s £ provided that on a missile a number each having a buoyancy surface having buoyancy elements is arranged at a mutual distance and that each of the buoyancy elements a nozzle arrangement is assigned, by means of which a gas flow to the respective buoyancy surfaces. Creation of a suppressed area through detachment and reinvestment the gas flow from and to the buoyancy surface can be fed at supersonic speed.

In the system according to the invention, buoyancy is created by influencing it the detachment and reapplication of a boundary layer by creating pressure differences over a number of curved lines outward and downward upwelling or relaxation areas. The number of equidistant from one another arranged lift surfaces is at least three. In an advantageous embodiment of the invention, four are cross-shaped arranged buoyancy surfaces provided. On the upper sides of the buoyancy surfaces, due to their influx

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flowing arranged convergent- divergent jjüsen with l-ber

ordered convergent- diverg

Sound velocity blown gas streams a negative pressure. This happens because the tibei'schp.llatrömurifj from replaces the drive-off and then lies back to it, where between the: separation point and the application point at the

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"* * _ζ ~ 2142423

At the top of the buoyancy, a negative pressure area emerges. ^{Atmospheric Di 1} UCk acting on the underside of the lift surfaces causes the required pressure difference. The lift forces resulting from this pressure difference and the vertical component of the inertial forces of the supersonic gas flow together produce the vertical lift.

According to an advantageous embodiment of the invention Buoyancy system are inlets for the controlled supply of Ambient air is provided in the negative pressure areas on the buoyancy surfaces. By supplying the ambient air is the "supersonic flow from the top of the lift surface deflected and thereby destroys the negative pressure area. This results in an imbalance of the forces by means of which the position and direction control of the missile can be brought about is. As long as the horizontal components of the forces acting on the lift surfaces are balanced, the Flugköioer in the stationary state of suspension, while a through Pressure equalization brought about imbalance of forces causes a predetermined position or direction control. The position and direction control can also be done by changing the volume and / or pressure of one or more buoyancy sf cause laughing flowing supersonic gas stream.

In an advantageous embodiment of the invention the top of the lift surfaces is formed so that the gas flow separates at least twice and wiederanlegt, ⁱ whereby zv / ei negative pressure regions are created and the total available lift forces are considerably increased.

In a modified embodiment of the invention, a missile at its top has a hood into which a fluid from a drive source is introduced under pressure will. A vertically installed gas turbine, the outlet nozzle of which faces the interior, is particularly suitable as the drive source facing the hood. The hood is preferably arranged on a conical body in such a way that it is opposite

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this is tiltable. In this embodiment, the Hood and the conical body share the nozzle for the Exiting of the oversized flow, the steering wheel takes place. of the missile by tilting the hood, by> '3.εε the flow throttled confused on one side of the conical body). According to another training, the steering takes place deonrch, that part of the gas flow bus the hood in a stau & nni ^ r is directed, which is a horizontal. Etcuer-oo-c Has outlet nozzle.

Further features, details and advantages of the Erfincnmp: result from the following description; of execution? - examples based on the drawing. In this shows:

Fig. 1 is an isometric view of a first embodiment ^ -

form of a missile with the lift according to the invention system,

Fig. 2 is a sectional view of a second embodiment a missile with the lift system according to the invention,

Figure 5 is an enlarged sectional view of a detail of Figure 5 Embodiments according to FIGS. 1 and. 2,

Fig. 4 is an isometric view of a further development of the Missile with the lift system according to the invention,

FIG. 5 shows a plan view of the missile according to FIG. H , FIG. 6 shows a schematic representation of the missile, and FIG

7 shows a schematic representation of an optimally designed Lift area.

The embodiment of a missile shown in Fig. Λ with the lift system according to the invention has an essentially conical shape. The upper surface of the payload part of the missile is formed by a conical wall 10 made of metal and has an opening at the upper, tapered end. Through this open

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ηαης becomes air cn ti ana: the axis of the missile perpendicular cufv.'Hj? ti; blown out under pressure.

A hood 12 is located over the tapered end of the wall 10

arranged on the missile. As can be seen in particular from FIG. 5, the hood 12 is hollow and has a cap part 14, into which a fluid "from a drive source takes." Pressure is blown in. Along the lower edge, the cap part 14 runs an outwardly protruding flange 16, An annular, convergent divergent nozzle 18 is formed between the underside of the flange 16 and the upper End.e of the conical wall 10, through which a pressurized into the Hood 12 injected fluid can escape. Due to the pressure and shape prevailing in the hood 12 the nozzle, the fluid or gas exiting through the nozzle moves at supersonic speeds along the surface the wall 10 blown out ..

As can be seen from the sectional view in FIG. 2, the missile has a payload area 20 ₅ which is delimited by the inner surface of the wall 10 and a base plate 22. In a typical practical embodiment as an unmanned, remote-controlled observation platform, electronic devices such as steering and control systems, controllable television cameras and receiving and transmitting devices can be accommodated in the payload compartment 20 of the missile. Additional payload space can be provided on top of the hood 12 and cameras or the like can be arranged in or on it.

A drive shaft 24 is installed in the missile coaxially with the conical wall 10. This is for example a vertically installed gas turbine, the outlet nozzle 26 of which faces the hood 12. Those emerging from the nozzle 26 under pressure Combustion gases flow into the hood 12 and out of the nozzle 18 in the manner shown in FIG out.

In the embodiment of FIG. 1, the hood 12 has a

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rotatable shell JO, which the steering and control: client. The upper part 50 forms a storage chamber in its interior, between which and the lower part of the hood 12 a flow connection can be established by means of a valve arrangement. The storage chamber has an outlet nozzle ⁷ 'which can be rotated in different directions when the upper part 30 is rotated by means of devices (not shown). By establishing a flow connection between the storage chamber and the lower part of the hood 12, a control thrust can thus be generated in that part of the combustion gases exits through the "outlet nozzle" which is rotated in the desired direction.

In addition to the above-described rotatable arrangement of part of the hood or in its place, the steering and control device according to Fig..2 use. The hood 12 is therein by means of a number of double-articulated linkages held on the wall 10. This allows the hood 12 to be at any angle to the vertical axis of the missile tilt, whereby an imbalance position of the horizontal components of the inertia forces exiting from the nozzle 18 Gases enter. With regard to the clarity of the representation, the operating devices for the Linkage 36 is omitted in the drawing.

The mode of operation of the buoyancy system can be seen from FIG. 3. In the sectional view of the outlet nozzle 18 shown therein, PS designates a pressurized one in the hood 12 Gas before it exits through the convergent-divergent annular nozzle 18. The underside that together forms the nozzle 18 of the flange 16 and the outer surface at the upper end of the wall are designed so that on the outlet side of the nozzle 18 an asymmetrical propagation of the supersonic nozzle jet emerging from the nozzle occurs along a line A-A '. The flat annular flange 16 arranged on the convergent-divergent nozzle 18 supports the turbulent mixing between the detaching boundary layer of the nozzle jet and the surrounding atmosphere, which is initially located on the wall 10, creating a negative pressure zone. The output from the nozzle 18

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emerging gas flows at supersonic speed over the surface of the wall 1O ₅ whereby the flow in a known V / cis © at point A separates from the wall and - at some distance from point A at point B - rests on it again »Between the Points A and B of the wall 10 initially located ambient atmosphere is "entrained by mixing with the supersonic flow, so that a vacuum is created on the surface of the wall between points A and B. The combined effect of the negative pressure zone formed on the top of the wall 10 and 22 of the missile present on the underside of the bottom plate atmospheric pressure producing a lift forces, together with the vertical component of the inertia forces of the gases exiting the nozzle 18 causes this lifting force sufficient for the vertical ascent of the flying object buoyancy _o

In the embodiment according to FIG. 2, the conical wall 10 is provided with a vertically displaceable outer edge part 40. A downward displacement of the edge part 40 from the extension of the wall 10 increases the distance between points A and B and thus moves the point , on which the supersonic flow is applied again ₃ downstream ο The lengthening of this vortex path thus causes the underpressure zone formed on the upper side of the wall 10 to widen and, as a result, increased buoyancy.

It has been determined in tests that the angle θ formed in the divergent part of the nozzle 18 should be in the range between 30 and 50 °. This condition can also be fulfilled if the angle Oi is up to 90 ° _o At an angle oi of 90 ° the annular flange 16 runs outwards and upwards, with no ssnkrselrb © Koinpenesrba of inertia forces, the gas flow, then in addition to the buoyancy forces generated by al © Dr-iäskuntorschiede

ΒθΙ that in Figo ^l '· M ß ? shown lieiter-developed the invention has the-Flugköi-pex? HO sin imtor-e © part in the form of a s 112 nnä GiD oöG5? Gs part in the form of Gin © r hood 114 on _o

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Per jacket 112 is an essentially ring-shaped part with a rotationally symmetrical, roughly hemispherical or even corsaired outer surface. Similarly, the shell 112 may also consist of a number of flat segments each _s be composed with a tapering outline of connected "The hood 114 is substantially cylindrical. Starting from the cylindrical hood 114 four floating elements are arranged 116a to 116 d in the same ¹ spaced apart in such a way on the jacket 112, ClAu ϊ \ β the shape of a cross form (Figure "5)" The individual Auftrieboelemente 116 each have two side walls 118, 120 having an extending therebetween lifting surface 122, an upper housing and 124 having formed therein with your W interior of the hood 114 is flow-connected nozzle 126. the nozzles 126 are convergent-divergent in a plane and extend in each case between the relevant Seiter; - walls 118, 120 of the buoyancy elements 116

The buoyancy system according to the invention is driven by means of a bypass jet engine ₄ which is arranged in the hood 114 and generates a supersonic gas flow that flows along the buoyancy surfaces 122 of the buoyancy elements and creates buoyancy forces by detaching and reapplying them. The parts of the outer surface of the jacket 112 lying between adjacent buoyancy elements can be used to generate additional buoyancy forces in that a supersonic or subsonic gas flow is blown over them. The air sucked in by the gas turbine enters the hood 114 in the direction of the arrows 127 and the supersonic gas stream flows in the direction of the arrows IJO and 132 over the buoyancy _{surfaces 122 ösw c} d: ls outer surface of the Hanteis 112 “The over the Area of the Plante!;? 112 a-aröia Gas passes over Du sen segments Ίψκ miw, asr H subs 'Ί'Ά mi3:. Zw sohßß. Jeueils awei Aufi "3? I @ l> s & l. AIPGjVUCuI 116 ist- e: L "_i III ⁵ .33iis3g

IlGnο

S ssigt; a scheffisibisiGrto I'fc.rst6ili; ^. g iS3 ea buoyancy; / sta! u3o to Hpoitslccroe ^ Gastui ^

sB familiar structure, with

ine

m fore = and nau

2 θ S 0! 1 2 / ö ϊ 5 i "

set 1365 of a combustor assembly 133, and a turbine 1 ^Zl O, From 'the compressor 136 is branched off compressed air and the lronverp; erjt ~ divergent nozzle "passed 126 via the lift surfaces 122 This is a separation with subsequent reapplication of the supersonic flow at the lift surfaces 122 instead of _%, which creates local negative pressure areas on them »The pressure differences between the negative pressure areas and areas of atmospheric pressure at corresponding points on the underside of the missile result in a vertical lift ,, thus contribute to the generation of lift ο If the flow of the turbine exhaust gases is to run over the jacket segments in the subsonic area, which creates a slight negative pressure and a corresponding lift on the upper side of the jacket 112, the nozzle segments 134 must be convergent In contrast, if the turbine exhaust gas flows over the jacket segments in the supersonic range, the nozzle segments 134 must be convergent-divergent, with an increased negative pressure for generating lift on the upper side of the jacket 112 due to the detachment and reapplication of the flow.

7 shows an enlarged cross-section through a nozzle 126 with the associated buoyancy surface 122 '. The pressure of the gas flow I30 exiting through the nozzle 126 is in the supercritical range, ie the ratio of the branched compressor pressure P _Q above the constriction of the nozzle 126 to the atmospheric Pressure P _& is greater than 3? preferably about 10. After passing through the nozzle 126, which is convergent-divergent in one plane, the gas can relax freely and strives to detach itself from the walls of the passage. "The upper divergent wall of the nozzle 126 is limited to a length, which corresponds to the distance to the free separation point S ^ of the immediate boundary layer or is slightly less = at this point there is a negative pressure «,

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due to which a transverse end cc pressure gradient acts on the outer boundary layer of the nozzle sti * ahls, f: o that this is deflected along the lift surface 122. _; The outer boundary of the flow runs along the line 136. By deflecting the jet stream along the surface 122, a curved shock wave 157 arises, which spreads from the free separation point S _x to a point R 1

I I

of surface 122 extends.

The same factors which flow the detachment of the supersonic effect from the upper wall of the nozzle 125, ^act. Iuch · to the running along the surface 122 a flow, which results in a separation of the flow at a point Sp.

The separation of the flow creates a local suction or sub-pressure area with extremely low pressure. The negative pressure area 138 on the surface 122 in deu. Pressure is considerably less than ambient atmospheric pressure. This negative pressure zone helps to keep the flow on the lift surface 122 and creates a considerable vertical pressure difference in relation to the ambient pressure present on the underside of the missile, which creates a vertical lift. The supersonic flow detached from the surface 122 at the point S ₂ rests on it again at a point Rχι, a local negative pressure area being created between these two points, the pressure of which comes up to a vacuum, whereby due to the pressure lower ™

* The difference between the negative pressure on the surface 122 and the ambient pressure acting downwards compared to the surface 122 results in a vertical imbalance of forces and thus a vertical lift. The profile shapes shown in Fig. 7 each extend over the entire width of the buoyancy elements 116, so that the separation point Sg and the reattachment point R ^ are in reality lines that extend over the width of the buoyancy elements, and the pressure differences over the entire Width between the walls 118 and 120 of the buoyancy elements are present.

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\ ^{7 from} α ex · .. mouth 140 of the IKise 126 to sum re-installation point K ,, the lift surface 122 runs in a straight line. If the surface were to continue in this straight line or plane beyond this point, the flow would continue to run against it and no further lift would arise guided, wherein the angle enclosed between the first section 122a and the second section 122b of the surface is less than 180 °. This profile shape causes a second relaxation and / or a second separation of the gas flow Sm point R /. and reappearance of the same at a point Kp. This creates a second negative pressure area 142 and a secondary or reflected shock wave 144. The extremely low pressure on the surface of the lift surface 122 in the second negative pressure area 142 produces a pressure difference to the ambient pressure on the underside of the missile due to the pressure difference corresponding upward force and thus contributes significantly to vertical lift.

The attitude and direction control of the missile with the inventive The buoyancy system is carried out effortlessly by means of pneumatic control devices .. On each of the buoyancy elements 116 is one which opens into the negative pressure area 138 and not one actuated state by a valve 148 closed passage opening present. A connection leads via the valve 148 to the free environment, so that the ambient atmosphere, the pressure of which is considerably higher than that in the negative pressure zone 1J8, when the valve 148 is open, flows into the negative pressure zone and fills its negative pressure, whereby the flow then breaks off from surface 122. By filling the vacuum zone 158 and cutting off the flow from the surface 122 the buoyancy ceases at the relevant surface. This obviously arises towards the the remaining three buoyancy elements create an imbalance of forces and thus a change in position or direction of the missile. By Closing the valve 148, the inflow of the ambient atmosphere is Sphere interrupted, so that the overflow is underneath

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renewed formation of the negative pressure zone 138 again to the Area 122 creates. The valves 148 can be in any desired Sequence and combination open or closed c-s & n werdon, the correct position and direction control of the plug body to accomplish.

A payload space, be it for dead load or passage, is U preferably for the arrangement under a coat 112 vor-gesti ·· -, · .. and, depending on the intended use of the missile, can be used for: have a good shape (Fig. 6). The simplicity, n:> it ö.cr according to the invention Buoyancy system for position and direction control accomplish by means of programmable ventilation valves allows the training to be extremely compact Missile without the use of the main rotor systems required in conventional hovercraft and auxiliary rotor. The missile is accordingly light to hide when it is not in use and can be easily transported on the floor. Since, moreover, the Most, if not all, of the compressor air and the turbine exhaust is directed outward rather than straight down towards the ground, there are ground erosion effects as well In the case of conventional hovercraft, the sucking in of heavily contaminated air into the engine is almost the same completely switched off. Accordingly, a missile with the buoyancy system according to the invention can be used without Schv / ie-

use from unprepared places, which its usability is additionally expanded.

Although in the preferred embodiment described above Implementation of the invention four buoyancy elements 116 in a cruciform Arrangement are present, with a preferably uniform arrangement along the circumference of the missile any number from .at least three upwards provided be.

All of the features and advantages of the invention that emerge from the claims, the description and the drawing, including constructive one-working, spatial arrangements and precautions, can be drawn both for themselves and for themselves Ln taelier * rer i'.oiübi.iiüM jn örrüiduni:; ci _; >i3; j: -t: Lieh ε, ϊίη * 2 0 * i 0 I 2 / U jh 4

ORIGlNAL BATHROOM

Claims (1)

2U2429 Va t ent so r u e: Buoyancy system for generating vertical buoyancy, iurcli marked that on a missile (112,114) a number, because a lift surface (122) having buoyancy elements (116a. To d) in mutual Distance is arigeor-dnet and that, ie that of the impulses a nozzle assembly; (126) is assigned, by means of which A Cias flow (IJO) surrs to the respective driving forces. Create a negative pressure area (158) by detaching and Reassembly of the gas flow from and to the buoyancy surface can be fed at supersonic speed » 2. Au ft ri eb s system according to claim '1, thereby geke η η - ζ ei ch η et that the missile has a substantially ring-shaped Qiier cut having Man at (112) and that at least three buoyancy elements (116) are arranged at equal mutual distances around the jacket. 5. On drive ε sy st a according to claim 1 or 2, characterized marked that the nozzle arrangements jcv; hurry a convergent-divergent nozzle (126) on v / iron which opens at one end of the relevant buoyancy element (116). ^L \. Buoyancy ε system according to claim 1 or 3, characterized characterized in that the missile has an im contains substantially annular cross-section having jacket (112) and that four buoyancy elements in the same mutual Intervals and provided in a cross-shaped arrangement on the jacket are. 5. Buoyancy system according to at least one of the claims to 4, characterized in that each buoyancy surface (122) a first section (122a) extending from the nozzle arrangement (126) and a second section extending from the first Part (122b) which includes an angle of less than 180 ° with the first part « 209812/0154 ORIGINAL C. Buoyancy system according to at least one of the claims 1 to 5, thereby ff e k e η η ζ ei c h η e t that pec.ep. the Buoyancy elements (116a to d), a pair of side walls (118, 120) delimiting the buoyancy surface (122) and a housing * (124) for the nozzle arrangement (126) on v / ei st. 7. Buoyancy s syst em according to at least one of claims 1 to 6, thereby g e k en η ze rejects that with j ei a of the buoyancy elements (116a to d) a control device (146, 148) is connected for optional filling of the negative pressure area (138) present on the lift surface. 8. On drive ssy st a according to claim 7? thereby g e k e η η draws, that the control device includes a valve assembly (148) for the supply of gas at a higher than the pressure prevailing in the negative pressure zone (138) on v / eist. 9. Buoyancy system according to claim 7, characterized in that the control device is a valve arrangement (148) for ventilating the negative pressure zone (1-8) with ambient air. 10. Buoyancy system according to at least one of claims 1 to 9, characterized in that devices (136 to 140) for supplying a flow of pressurized gas to the Nozzle arrangements (126) are provided with a pressure ratio that is critical to the ambient pressure. 11. Buoyancy system according to at least one of claims 1 to 10, characterized in that the device for supplying a flow of pressurized gas to the nozzle assemblies (126) is a gas turbine. 12. Buoyancy system according to claim 11, characterized in that the gas turbine is a dumbbell or two-current engine (136 to 140) and that devices for branching off compressed air from the sheath flow and to the nozzles (126) are present are. 2 0 9 8 12/0154 BATH ORIGINAL 1Y. Buoyancy system according to at least one of claims 1 to 12, characterized in that second ^{nozzle arrangements (13 7} O for the exit of exhaust gases from the engine between the buoyancy elements. (116a to d) for further generation of buoyancy along the surface of the Mantle (112) are available. 14. Buoyancy system according to at least one of claims 1 to 13, characterized in that the missile has a Nut 2.1 has a dream " 20981 2/0154 BATH ORIGINAL