EP1939578B1 - Missile for the supersonic range with a porous front piece - Google Patents

Description

TECHNICAL FIELD OF THE INVENTION

The invention relates to a missile for the supersonic range with an aero-spike extending from a front end face of the missile.

STATE OF THE ART

In the case of missiles for the supersonic range, so-called aero spikes are used in the region of the front end face, which are mounted in the form of a mandrel or a rod directly on a nose or a dome of the missile and are aligned against the flow. A separation of the boundary layer on a surface of the aero-spikes by the action of a bow joint is responsible for the fact that the intrinsically intense bow joint is replaced by a combination of significantly weaker oblique compression joints, cf. Fig. 1 , This has the consequence that losses due to the compression shocks are reduced, which means a reduced so-called characteristic impedance. Up to a certain longitudinal extent of the aero-spike in relation to its transverse extent or a diameter of the missile, a detachment takes place directly on a front end face of the aero-spike, so that a simple extension of the aero-spikes can lead to a further reduction of the characteristic impedance , However, it has been found that beyond a certain length of the aero-spike, separation of the boundary layer takes place only behind the front face of the aero-spike. The length of a forming so-called peel bladder stabilizes and behaves practically independent of the length of the aero-spike, cf. Fig. 2 , The reason for this is that the size of a peel-off bubble on the aero-spike is of course limited, this size in particular being dependent on the shape of the front face and the shape of the aero-spike, as well as flow parameters, such as the Condition of the boundary layer on the Aero-Spike, the Flugmachzahl and the like, depends. This may cause the efficiency of a selected aerospace configuration to be dependent on the prevailing flight conditions, so that the flow effect may vary with changing flight conditions.

In particular, when flying near the ground can act very high impact pressures, which may for example lead to a boundary layer on the aero-spike changed from a laminar state to a turbulent state, with the result that a peel off bladder is greatly reduced in terms of their extent , This, in turn, requires a reduction in the effective slenderness of the missile, thereby increasing the bow drag. This effect can not necessarily be eliminated by simply increasing the length of the aero spike, since the length of the peel bladder is largely independent of the length of the aero spike.

As a compromise solution for the aforementioned problem, it is known to arrange a front body in the form of an extension, an impact body or a so-called aero-disk in the region of the front side of the aero-spike, whereby a certain stabilization can take place. In this case, however, the configuration and the choice of the geometry of the forehead body to be interpreted in the expected unfavorable conditions in flight, so that an ultimately achievable profit is suboptimal. The effect of an Aero-Spike, which is equipped with an Aero-Disk, is Fig. 4 refer to. As the length of the aero-spike increases, however, the effect occurs that the detachment bubbles formed in the area of the end face of the missile and in the area of the aero-disk separate, so that a partial area is formed between these two detachment blisters applies the flow to the aero-spike, s. Fig. 5 , Thus, the actually desired effect is eliminated and for such flow conditions is compared to a conventional aero-spike according to Fig. 2 the resulting total resistance is even increased by the additional fraction caused by the Aero-Disk.

• Chang, P.K., "Separation of Flow", Pergamon Press, 1970, 777p .    [1] Fomin V.M., Tretyakov P.K., Taran J.-P. "Flow control using various plasma and aerodynamic approaches (Short review)", Aerospace Science and Technology, 8, 2004, pp, 411-421 .    [2]
• Gnemmi P., Srulijes J., Roussel K., Runne K., "Flowfield Around Spiked-Tipped Bodies for High Attack Angles at Ach 4.5", Journal of Spacecraft and Rockets, Vol. 40, No. 5, pp. 622-631, Sept.-Oct. 2003 .    [3]
• Huebner L.D., Mitchell A.M. and Boudreaux E.J. "Experimental Results on the Feasibility of an Aerospike Hypersonic Missiles," AIAA Paper 95-0737, Jan. 1995 .    [4]
• Boudreaux E.J., Krishnamurty V.S., Mitchell A.M. and Shyy W., "Experiments and Analysis of an Aerospike Flow Environment for Protecting Infrared Missile Dome," RTO-MP-5, Proceedings of the RTO-Meeting "Missile Aerodynamics", Sorrento, Italy, 11-14 May 1998, NATO RTO, 1998 .    [5]
• Reding J.P., Guenther R.A., Jecmen D.M., "Scale Effects on Fluctuating Pressures in Spike-Induced Flow Separation", Journal of Spacecraft and Rockets, Vol.17, No.2, pp.112-118, March-April 1980    [6]

The state of knowledge on the general problem of reducing the characteristic impedance by using aero-spikes on blunt bodies can be found, for example, in the following publications.

• Chang, PK, "Separation of Flow", Pergamon Press, 1970, 777p , [1] Fomin VM, Tretyakov PK, Taran J.-P. "Flow control using various plasma and aerodynamic approaches (Short review)", Aerospace Science and Technology, 8, 2004, pp, 411-421 , [2]
• Gnemmi P., Srulijes J., Roussel K., Runne K., "Flowfield Around Spiked-Tipped Bodies for High Attack Angles at Ach 4.5", Journal of Spacecraft and Rockets, Vol. 5, pp. 622-631, Sept.-Oct. 2003 , [3]
• Huebner LD, Mitchell AM and Boudreaux EJ "Experimental Results on the Feasibility of Aerospike Hypersonic Missiles," AIAA Paper 95-0737, Jan. 1995 , [4]
• Boudreaux EJ, Krishnamurty VS, Mitchell AM and Shyy W., "Experiments and Analysis of an Aerospike Flow Environment for Protecting Infrared Missile Dome," RTO-MP-5, Proceedings of the RTO Meeting "Missile Aerodynamics", Sorrento, Italy 11-14 May 1998, NATO RTO, 1998 , [5]
• Reding JP, Guenther RA, Jecmen DM, "Scale Effects on Fluctuating Pressures in Spike-Induced Flow Separation," Journal of Spacecraft and Rockets, Vol.17, No.2, pp.112-118, March-April 1980 [6]

JP 2001174200 A discloses a missile whose nose carries an aero-spike, at its front end portion designed as a ball end body is arranged.

JP 05254497 A discloses a missile in which an aero-spike with a hemispherical frontal body in the longitudinal direction of the missile from the nose can be extended to the front. The extension takes place depending on the flight condition of the missile via a suitable servomotor.

US 3,713,607 discloses a missile having a tubular aerospike having a plurality of radial bores along its longitudinal axis. In this case, the bores can be distributed in several transverse planes in the circumferential direction and have different diameters such that the diameter of the bores increases with increasing distance from the front end region of the aero-spike. Furthermore, in US 3,713,607 addressed that a fastening while allowing an angle adjustment to the the Face of the missile-forming dome, obviously during assembly of the Aero-Spikes, is possible.

US 3,643,901 discloses a missile with an aero-spike, which has an end body formed with two sections, wherein the lateral surfaces of the sections lie on a conical surface, the tip of which points to the front. The front portion has a central through hole of constant diameter, wherein the front end surface is formed as a sharp peripheral edge. The first and second portions are separated by a gap in which the portions are connected by radially outwardly extending longitudinally extending struts. Air entering the through-bore of the first section is directed radially outwardly from an end face of the second section and exits radially radially outward from the end body of openings formed between the rods. In US 3,643,901 is also addressed that a plurality of openings or passageways may be provided on the end body.

US 6,698,684 B1 discloses a telescoping aero-spike for an aircraft wherein the telescoping of the aero-spike is done in dependence on flight conditions.

The non-prepublished patent application DE 2006 003 638.7-15 Applicant discloses a transverse to a longitudinal axis of the missile pivotable aero-spike. Here, according to a first proposal, the Aero-Spike can be pivoted passively, for example by flow surfaces or lattice turrets, which can align the Aero-Spike even during an oblique approach to the flow. Alternatively, an active pivoting can take place, for example on the basis of a measuring element which detects flight conditions such as the angle of attack and a pivoting of the aerospike by means of a suitable actuator.

From the further not previously published patent application DE 10 2006 025 270.5 The applicant is known to form the aero-spike itself with a porous material, for example a sintered material or a ceramic, whose open pores form flow channels. Here, the aero-spike may be formed as a solid cross-section or as an open-sided longitudinal recess into which air can enter from the front, which can then escape via the flow channels formed by the open pores at least with radial component of the aero-spike. In addition, radial recesses, holes, slots or perforations on the aero-spike. Furthermore, the application proposes to influence the flow conditions to provide the lateral surface of the aero-spike specifically with a roughness in the direction of the longitudinal axis, for example with roughness in the range of more than 100 microns, more than 200 or 300 microns. In addition, grooves, grooves, notches can be introduced into the lateral surface of the aero-spike or coatings of particles of the same or different size can be applied.

Finally, the non-prepublished patent application discloses DE 2006 015 952.7 the applicant, instead of a tubular or rod-shaped central aero spikes provide several rod-like decentralized Aero spikes. In order not to unnecessarily limit a field of view for an information acquisition device such as a seeker head, the decentralized aero spikes are movable transversely to the longitudinal axis of the missile, for example arranged rotatably on a circular path about the longitudinal axis. In this case, a rotation in accordance with an actuator or by passive measures, such as flow area elements in the front end of the aero-spikes done.

Further prior art results from DE 199 53 701 A1 as well as the non-generic US 2003/132 351 A1 ,

OBJECT OF THE INVENTION

The present invention has for its object to propose a missile, for the flow or flight behavior and the resistance, in particular by the flight and environmental conditions and / or at relatively long aero spikes are improved.

SOLUTION

The object of the invention is achieved with the features of independent claim 1. Further embodiments of a missile according to the invention will become apparent according to the dependent claims 2 to 9.

DESCRIPTION OF THE INVENTION

The invention initially starts out from the basic idea DE 2006 025 270.5 This patent application related to a development of a known from [5], there as "Aeroscoop" designated embodiment, in which the aero-spike is formed as a hollow tube. As a result of the back pressure in the area of the front open front side of the Aero-Spikes occurs for one such aeroscoop air into the interior of the tubular aero-spikes. The aero-spike according to [5] has several openings arranged along the aero-spike, through which the air is blown out from inside the aero-spike. The blown out air causes an outside flow and a pressure wave to be pushed away from the aero-spike. While a production of the required plurality of discrete openings for such an aerosol requires a complex manufacturing and weakening of the supporting structure of the aero-spikes beats DE 10 2006 025 270 to form the aero-spike at least in some areas or completely with a porous material. In such a porous material, flow channels can be formed by open pores, through which targeted air can be "blown out" in order to avoid undesirable application of a flow in the region of the lateral surface of the aero-spike. It should be advantageous in this case that the pores are not distributed discretely, as in an aerosol and thus act only locally on the flow around the aero-spike, but rather the flow channels can be more or less finely distributed over the outer surface of the porous material. As a result, an almost continuous flow influencing can take place, with the outflowing air of the aero-spike being able to be surrounded by a cushion of outflowing air. DE 10 2006 025 270 also shows the arrangement of a forehead body in the front end of the aero-spike, which has for communicating with the interior of the hollow aero-spike opening into the interior bore. As already mentioned above, this bore represents a weakening of the structure. Furthermore, the use of a drilled face body restricts the possibilities of designing the flow conditions since, for such an open inner channel, the pressure in the interior of the frontal body and the aero-spike essentially precedes the back pressure corresponds to the frontal body. For a desired to achieve a given effect end face of the end body further means the arrangement of the central bore of the end body according to DE 10 2006 025 270 in that the frontal body has to have a greater extent transverse to the longitudinal axis of the missile.

Based on the above-mentioned findings, the invention proposes to form the end body with a porous material whose open pores form flow channels. By specifying the pore size and pore density can be specified structurally in a simple manner, which share of a flow is passed through the end body and what proportion of this radially outside must flow past. It is possible that the porosity in the transverse direction is constant or variable. The formation of flow channels by means of open pores on the one hand in the region of the entry of the air in the Flow channels depending on the pore size and thus cross-section of the flow channels a kind of throttling effect can be achieved. On the other hand, the outflow conditions of the air from the flow channels on the back of the end body can be specified by the porosity. In this case, the subject matter of the invention comprises both that the front body is adjoined by a closed aerospike, and that a closed aero-spike is provided or such that the flow channels are provided, for example in the form of (longitudinal and / or transverse). ) Holes, recesses or also has pores into which the flow channels can open as a result of the pores of the frontal body.

• Vorgabe von Partikelgrößen eines zu dem porösen Material umzuwandelnden Rohmaterials,
• die Gestaltung von Druckverhältnissen bei einem Verpressen derartiger Partikel,
• die Auswahl geeigneter Zusatzpartikel,
• einen Einsatz und eine Dosierung eines Treibmittels oder Porenbildners und/oder
• die Gestaltung der Temperaturverhältnisse und anderer Fertigungsparameter.
  Erfindungsgemäß kann ausgenutzt werden, dass in einem porösen Material unter Umständen nicht lediglich Poren gleicher Strömungsquerschnitte gebildet sind, sondern sich beispielsweise ein stochastische Verteilung von Porengrößen ergeben kann, so dass unter Umständen die Strömungsverhältnisse in den einzelnen Poren unterschiedlich gestaltet werden können. Damit können auch die Druckverhältnisse bei Eintritt und Austritt der Luft aus dem Stirnkörper stochastisch verteilt werden, wodurch sich eine verbesserte Einwirkung auf die Umströmung ergeben kann. Beispielsweise sind die Porengrößen um einen Mittelwert stochastisch oder mit einer Normalverteilung verteilt. Auch ist eine beliebige gleiche oder unterschiedliche, u. U. geschlungene Orientierung der Poren möglich.
  Andererseits kann für den Fall, dass ein verhältnismäßig großer Anteil einer von Austrittsöffnungen überdeckten Austrittsfläche für Luft im Bereich der Mantelfläche des Stirnkörpers oder Rückseite des Stirnkörpers gegenüber geschlossenen Teilbereichen derselben Flächen gewünscht ist, die diskrete Anordnung von Öffnungen, beispielsweise in Form axialer Bohrungen, nachteilig sein, da hierdurch der Stirnkörper geschwächt werden könnte. Für eine Bildung der Ein- und Austrittsöffnungen und der Strömungskanäle mit einem porösen Material kann der Anteil der Ein- und Austrittsfläche gegenüber geschlossenen Teilbereichen der Fläche unter Umständen bis zu einem Verhältnis von 1:1 vorgegeben werden, wobei gleichzeitig eine große mechanische Beanspruchbarkeit gewährleistet werden kann.
  Ein mögliches poröses Material, mit dem zumindest Teilbereiche des Aero-Spikes gebildet sein können, kann ein Sintermaterial oder Sintermetall sein. Bei einem derartigen Sintern werden beispielsweise Hohlraummassen vorgeformt, so dass sich ein maximaler Zusammenhalt der Pulverpartikel ergibt. Ein derartiges Zwischenprodukt wird einer Wärmebehandlung unterhalb der Schmelztemperatur des Werkstoffes ausgesetzt mit einer Verdichtung und Aushärtung. Die Herstellung des Zwischenproduktes kann hierbei durch ein Verpressen der Pulvermassen und/oder durch Formung und anschließendes Trocknen erfolgen. Unter ein derartiges erfindungsgemäßes Sintern fällt auch eine Pulvermetallurgie oder der Einsatz plastikartiger gesinterter Kunststoffe. Ebenfalls möglich ist der Einsatz eines Keramikwerkstoffes, der sich durch eine besondere Versteifsfestigkeit, Härte, Druckfestigkeit, Hochtemperaturbeständigkeit, gute Wäremeleitfähigkeit und/oder elektrische Isolation auszeichnet.
  Während der Stirnkörper grundsätzlich einen beliebigen Längs- und Querschnitt besitzen kann, beispielsweise eine kugelförmige Geometrie, eine kegelförmige Geometrie oder eine beliebig gekrümmte Geometrie, ist der Stirnkörper gemäß einem weiteren Vorschlag der Erfindung als Aero-Disk ausgebildet, also scheibenförmig mit Erstreckung quer zur Längsachse des Flugkörpers. Die Dicke eines derartigen scheibenartigen Stirnkörpers wird beispielsweise ausreichend bemessen, damit dieser auch bei Einsatz des Flugkörpers im Überschallbereich eine hinreichende Festigkeit besitzt. Mittels eines scheibenartigen Stirnkörpers kann eine große Stirnfläche des Stirnkörpers, u. U. mit einer Vielzahl von Strömungskanälen im Bereich der offenen Poren, bereitgestellt werden. Andererseits ist für einen scheibenartigen Stirnkörper ermöglicht, dass "gedrosselte" Luft auf der Rückseite des Stirnkörpers über einen größeren Bereich unterschiedlicher Radien austreten kann, um beispielsweise das Anlegen einer Strömung an einen nachgeschalteten Aero-Spike zu vermeiden.
  Während gemäß US 3,643,901 grundsätzlich eine Stirnfläche vermieden wird, aber in einen Strömungskanal eintretende Luft in radialer Richtung umgelenkt werden soll, um die Umströmung und die Ausbildung einer Grenzschicht zu beeinflussen, nimmt eine weitere Ausgestaltung der Erfindung gezielt in Kauf, dass der Stirnkörper eine quer zur Längsachse des Flugkörpers orientierte Stirnfläche aufweist. Hierbei ist es möglich, dass der Stirnkörper in Strömungsrichtung durchlässig ist, so dass Luft weitestgehend in Strömungsrichtung und in Richtung der Längsachse des Flugkörpers mit einem möglichst hohen Impulsverlust in Folge der Drosselwirkung durch die Strömungskanäle und Poren durch den Stirnkörper hindurchtritt.
  Während beliebige Tragstrukturen zwischen vorderer Stirnfläche des Flugkörpers und Stirnkörper möglich sind, ist für eine besonders einfache Ausgestaltung der Erfindung der Aero-Spike mit einer Stange gebildet, die den Stirnkörper trägt. Hierbei ist es durchaus möglich, dass der stangenförmige Aero-Spike entsprechend einer der in DE 10 2006 025 270.5 dargelegten Ausführungsformen ausgestaltet ist mit einem porösen, Strömungskanäle bildenden Material.
  Vorteilhafte Weiterbildungen der Erfindung ergeben sich aus den Patentansprüchen, der Beschreibung und den Zeichnungen. Die in der Beschreibungseinleitung genannten Vorteile von Merkmalen und von Kombinationen mehrerer Merkmale sind lediglich beispielhaft und können alternativ oder kumulativ zur Wirkung kommen, ohne dass die Vorteile zwingend von erfindungsgemäßen Ausführungsformen erzielt werden müssen. Weitere Merkmale sind den Zeichnungen - insbesondere den dargestellten Geometrien und den relativen Abmessungen mehrerer Bauteile zueinander sowie deren relativer Anordnung und Wirkverbindung - zu entnehmen. Die Kombination von Merkmalen unterschiedlicher Ausführungsformen der Erfindung oder von Merkmalen unterschiedlicher Patentansprüche ist ebenfalls abweichend von den gewählten Rückbeziehungen der Patentansprüche möglich und wird hiermit angeregt. Dies betrifft auch solche Merkmale, die in separaten Zeichnungen dargestellt sind oder bei deren Beschreibung genannt werden. Diese Merkmale können auch mit Merkmalen unterschiedlicher Patentansprüche kombiniert werden. Ebenso können in den Patentansprüchen aufgeführte Merkmale für weitere Ausführungsformen der Erfindung entfallen.

A design of the geometry of the flow channels formed with the open pores, during manufacture of the end body of the porous material, u. U. together with the porous aero-spike, are easily specified, for example by

• Specification of particle sizes of a raw material to be converted to the porous material,
• the design of pressure ratios when pressing such particles,
• the selection of suitable additional particles,
• an insert and a dosage of a propellant or pore-forming agent and / or
• the design of the temperature conditions and other manufacturing parameters.
  According to the invention can be exploited that in some circumstances not only pores of the same flow cross-sections are formed in a porous material, but, for example, may result in a stochastic distribution of pore sizes, so that under certain circumstances, the flow conditions in the individual pores can be designed differently. Thus, the pressure conditions at the inlet and outlet of the air can be stochastically distributed from the front body, which may result in an improved effect on the flow around. For example, the pore sizes are distributed around an average stochastic or with a normal distribution. Also, any same or different, u. U. looped orientation of the pores possible.
  On the other hand, in the event that a relatively large proportion of an exit surface covered by outlet openings for air in the region of the lateral surface of the end body or back of the end body relative to closed portions the same surfaces is desired, the discrete arrangement of openings, for example in the form of axial bores, be disadvantageous, since this could weaken the forehead body. For a formation of the inlet and outlet openings and the flow channels with a porous material, the proportion of inlet and outlet surface against closed portions of the surface may be given up to a ratio of 1: 1, at the same time a large mechanical strength can be ensured ,
  A possible porous material, with which at least partial regions of the aero-spike can be formed, can be a sintered material or sintered metal. In such sintering, for example, cavities are preformed, so that a maximum cohesion of the powder particles results. Such an intermediate product is subjected to a heat treatment below the melting temperature of the material with compaction and curing. The preparation of the intermediate product can be carried out by compressing the powder compositions and / or by shaping and subsequent drying. Such a sintering according to the invention also includes powder metallurgy or the use of plastic-like sintered plastics. Also possible is the use of a ceramic material, which is characterized by a special stiffening strength, hardness, compressive strength, high temperature resistance, good heat conductivity and / or electrical insulation.
  While the end body in principle may have any longitudinal and cross-section, for example, a spherical geometry, a conical geometry or an arbitrarily curved geometry, the end body is formed according to a further proposal of the invention as an aero-disk, ie disc-shaped with extension transverse to the longitudinal axis of the missile. The thickness of such a disk-like end body is for example sufficiently dimensioned so that it has a sufficient strength even when using the missile in the supersonic range. By means of a disk-like end body, a large end face of the front body, u. U. be provided with a plurality of flow channels in the region of the open pores. On the other hand, it is possible for a disk-like front body that "throttled" air can escape on the back of the front body over a larger range of different radii, for example, to avoid the application of a flow to a downstream aero-spike.
  While according to US 3,643,901 In principle, an end face is avoided, but in a flow channel entering air is to be deflected in the radial direction to influence the flow and the formation of a boundary layer, takes a further embodiment of the invention specifically in purchasing that the front body oriented transversely to the longitudinal axis of the missile Having face. In this case, it is possible for the end body to be permeable in the direction of flow, so that air passes as far as possible in the flow direction and in the direction of the longitudinal axis of the missile with the highest possible momentum loss as a result of the throttling action through the flow channels and pores through the front body.
  While any supporting structures between the front end face of the missile and the forehead body are possible, for a particularly simple embodiment of the invention, the aero-spike is formed with a rod which carries the forehead body. It is quite possible that the rod-shaped aero-spike according to one of the in DE 10 2006 025 270.5 set forth embodiments is configured with a porous, flow channel forming material.
  Advantageous developments of the invention will become apparent from the claims, the description and the drawings. The advantages of features and of combinations of several features mentioned in the introduction to the description are merely exemplary and can come into effect alternatively or cumulatively, without the advantages having to be achieved by embodiments according to the invention. Further features are the drawings - in particular the illustrated geometries and the relative dimensions of several components to each other and their relative arrangement and operative connection - refer. The combination of features of different embodiments of the invention or of features of different claims is also possible deviating from the chosen relationships of the claims and is hereby stimulated. This also applies to those features which are shown in separate drawings or are mentioned in their description. These features can also be combined with features of different claims. Likewise, in the claims listed features for further embodiments of the invention can be omitted.

BRIEF DESCRIPTION OF THE FIGURES

Fig. 1

zeigt einen schematisch dargestellten Flugkörper entsprechend dem Stand der Technik in Seitenansicht mit einem verhältnismäßig kurzen Aero-Spike in umströmtem Zustand.

Fig. 2

zeigt einen schematisch dargestellten Flugkörper entsprechend dem Stand der Technik in Seitenansicht mit einem verhältnismäßig langen Aero-Spike in umströmtem Zustand.

Fig. 3

zeigt aus dem Stand der Technik bekannte Konfigurationen eines Flugkörpers mit Aero-Spike und unterschiedlichen Endbereichen des Aero-Spikes und Stirnkörpern in Seitenansicht.

Fig. 4

zeigt einen schematisch dargestellten Flugkörper entsprechend dem Stand der Technik in Seitenansicht mit einem eine Aero-Disk aufweisenden, verhältnismäßig kurzen Aero-Spike bei Anströmung in einem Auslegungsbereich.

Fig. 5

zeigt einen schematisch dargestellten Flugkörper entsprechend dem Stand der Technik in Seitenansicht mit einem eine Aero-Disk aufweisenden, verhältnismäßig langen Aero-Spike.

Fig. 6

zeigt einen Flugkörper gemäß DE 10 2006 025 270.5 in schematischer Seitenansicht mit der sich ergebenden verbesserten Umströmung.

Fig. 7

zeigt einen Aero-Spike mit einem Stirnkörper gemäß DE 10 2006 025 270.5 mit einer stirnseitig offenen Längsausnehmung für einen Einsatz in einem erfindungsgemäßen Flugkörper in einem Teillängsschnitt.

Fig. 8

zeigt die Druckverhältnisse über die Längserstreckung eines Aero-Spikes mit einem Stirnkörper gemäß DE 10 2006 025 270.5 für eine Umströmung eines Flugkörpers entsprechend Fig. 5.

Fig. 9

zeigt einen erfindungsgemäßen Flugkörper im Längsschnitt mit einem von einem Aero-Spike getragenen porösen, scheibenförmigen Stirnkörper mit den sich ergebenden Strömungsbedingungen.

Fig. 10

zeigt ein Detail des Aero-Spikes und des Stirnkörpers gemäß Fig. 9 in einer Seitenansicht.

Fig. 11

zeigt den Stirnkörper gemäß Fig. 9 und 10 in einer Vorderansicht.

Fig. 12

zeigt einen Stirnkörper mit einer Vielzahl von Längsbohrungen in einer Seitenansicht.

Fig. 13

zeigt den Stirnkörper gemäß Fig. 12 in einer Vorderansicht.

Fig. 14

zeigt ein Detail einer Seitenansicht eines erfindungsgemäßen Flugkörpers, bei dem durch einen porösen Stirnkörper hindurchgeleitete Luft im Übergangsbereich zum Aero-Spike umgelenkt wird.

Fig. 15

zeigt einen Stirnkörper mit sich stromabwärts trichterförmig erweiterter zentrischer Durchgangsbohrung mit der zugeordneten Umströmung des nachgeschalteten Aero-Spikes in einer Seitenansicht.

Fig. 16

zeigt den Stirnkörper gemäß Fig. 15 in einer Vorderansicht.

Fig. 17

zeigt ein Detail eines erfindungsgemäßen Flugkörpers in Seitenansicht mit einem porösen, scheibenartigen Stirnkörper, dem ein sich stromabwärts erweiternder kegelförmiger vorderer Endbereich des Aero-Spikes nachgeschaltet ist.

Fig. 18

zeigt die Befestigung des Stirnkörpers über einen an sich bekannten Aero-Spike an der vordern Stirnfläche des Flugkörpers in einer Seitenansicht.

Fig. 19

zeigt eine alternative Ausführungsform einer Befestigung des Stirnkörpers an der vorderen Stirnfläche des Flugkörpers in einer Seitenansicht.

Fig. 20

zeigt eine im Wesentlichen Fig. 19 entsprechende Ausführungsform, bei der allerdings sowohl Stirnkörper als auch Aero-Spike mit einem porösen Material gebildet sind.

Fig. 21

zeigt einen Flugkörper in einer Seitenansicht, bei der der Stirnkörper über außermittig angeordnete Streben mit der vorderen Stirnfläche des Flugkörpers verbunden ist.

Fig. 22

zeigt eine weitere Ausführungsform eines Flugkörpers in Seitenansicht, bei der der Stirnkörper durch eine einzige, außermittige und gekrümmte Strebe von dem Flugkörper gehalten ist.

In the following the invention will be further explained and described with reference to preferred embodiments shown in the figures.

Fig. 1

shows a schematically illustrated missile according to the prior art in side view with a relatively short aero-spike in a flow around state.

Fig. 2

shows a schematically illustrated missile according to the prior art in side view with a relatively long aero-spike in a flow around state.

Fig. 3

shows known from the prior art configurations of a missile with aero-spike and different end portions of the aero-spikes and frontal bodies in side view.

Fig. 4

shows a schematically illustrated missile according to the prior art in side view with an aero-disk having, relatively short aero-spike on air flow in a design range.

Fig. 5

shows a schematically illustrated missile according to the prior art in side view with an aero-disk having a relatively long aero-spike.

Fig. 6

shows a missile according to DE 10 2006 025 270.5 in a schematic side view with the resulting improved flow around.

Fig. 7

shows an aero-spike with a frontal body according to DE 10 2006 025 270.5 with a frontally open longitudinal recess for use in a missile according to the invention in a partial longitudinal section.

Fig. 8

shows the pressure conditions over the longitudinal extent of an aero-spikes with a front body according to DE 10 2006 025 270.5 for a flow around a missile accordingly Fig. 5 ,

Fig. 9

shows a missile according to the invention in longitudinal section with a supported by an aero spike porous disc-shaped end body with the resulting flow conditions.

Fig. 10

shows a detail of the aero spike and the forehead body according to Fig. 9 in a side view.

Fig. 11

shows the front body according to Fig. 9 and 10 in a front view.

Fig. 12

shows a front body with a plurality of longitudinal bores in a side view.

Fig. 13

shows the front body according to Fig. 12 in a front view.

Fig. 14

shows a detail of a side view of a missile according to the invention, in which guided through a porous end body air is deflected in the transition region to the aero-spike.

Fig. 15

shows a front body with itself downstream funnel-shaped enlarged central through-hole with the associated flow around the downstream aero-spikes in a side view.

Fig. 16

shows the front body according to Fig. 15 in a front view.

Fig. 17

shows a detail of a missile according to the invention in side view with a porous disc-like end body, which is followed by a downstream widening conical front end portion of the Aero-Spikes.

Fig. 18

shows the attachment of the front body over a known aero-spike on the front end face of the missile in a side view.

Fig. 19

shows an alternative embodiment of a fastening of the front body on the front end surface of the missile in a side view.

Fig. 20

essentially shows one Fig. 19 corresponding embodiment in which, however, both frontal body and aero-spike are formed with a porous material.

Fig. 21

shows a missile in a side view, in which the end body is connected via eccentrically arranged struts with the front end face of the missile.

Fig. 22

shows a further embodiment of a missile in side view, in which the end body is held by a single, eccentric and curved strut of the missile.

DESCRIPTION OF THE FIGURES

• eine in erster, grober Näherung zylindrische Form besitzen,
• eine stumpfe Nase oder Stirnfläche besitzen,
• sich zumindest teilweise mit Überschallgeschwindigkeit bewegen und
• mit einem Aero-Spike ausgestattet sind,

insbesondere Außentanks, Abwurfmunition, Pylone, Antennen an Flügeln. Fig. 1 In particular, such a missile is a rocket, drone, or projectile, or missile that is self-propelled by at least a portion of its trajectory, for example, by a jet engine, which transmits both fuel and fuel carries an oxidizing agent for it. This may be after launch launched or unguided missile, which move only in the air or at least partially in the water. The missile moves at least partially in the air at supersonic speed. Likewise, the missile may be an aircraft, aircraft or fighter aircraft, or its attachments

• have a first, rough approximation cylindrical shape,
• have a dull nose or face,
• move at least partially at supersonic speed and
• equipped with an Aero-Spike,

especially outer tanks, discharge ammunition, pylons, antennas on wings.

The missile 1 is shown for simplicity in flow in an axial flow direction 2. An aero-spike 4 upstream upstream of an end face 3, a dome or a nose, wherein the aero-spike 4 extends coaxially to the longitudinal axis of the missile 1.

Furthermore, in Fig. 1 the flow around the missile 1: In the area of a front end surface 5 of the aero-spike 4 forms a detached boundary layer 6 at a peel angle 7, with the result that (instead of an intense bow thrust for a missile 1 without Aero-Spike 4) the boundary layer 6 in the region of the end face 3 strikes the end face 3 of the missile with a considerably weaker, oblique compression shock, which leads to a reduction of the characteristic impedance. Within the detached boundary layer 6 extending below the separation angle 7, a bow-side detachment bladder 8 is formed, in which air can also circulate against the flow direction 2.

While according to Fig. 1 the longitudinal extent of the Aero-Spikes 4 corresponds to the diameter of the missile 1 or is smaller than this, is in Fig. 2 a missile 1 shown with an aero-spike 4, whose longitudinal extent is greater than the diameter of the cross section of the missile 1 or its maximum frontal transverse extent, in particular approximately twice as large. In such a case, it comes only behind a region 9 in which the flow is applied to the lateral surface of the aero-spike 4, under the peel angle 7 to a detached boundary layer 6. Within the running under the peel angle 7 detached boundary layer 6 forms a bow-side detachment bladder 8, in the air can also circulate against the flow direction 2.

• Fig. 3a einen Aero-Spike mit konstantem Querschnitt, der beispielsweise zylinderförmig ausgebildet ist,
• Fig. 3b einen Aero-Spike mit dreieckförmigem Längsschnitt oder kegelförmiger Konfiguration,
• Fig. 3c einen Aero-Spike mit einem durch eine sphärische Verdickung gebildeten Stirnkörper an dem distalen Ende,
• Fig. 3d einen Aero-Spike mit einem angespritzten oder kegelförmigen Endbereich und einem mittigen Teilbereich konstanten Querschnitts,
• Fig. 3e einen Aero-Spike mit einer durch eine Verdickung des distalen Endes gebildeten Stirnkörper, die im Längsschnitt ungefähr dreieckförmig mit in Flugrichtung orientierter Spitze ausgebildet ist,
• Fig. 3f einen Aero-Spike mit einem im distalen Endbereich angeordneten Stirnkörper in Form einer Scheibe.

Fig. 3 shows by way of example different embodiments for basic basic configurations of an aero-spikes 4 on an end face 3 of a missile 1, namely:

• Fig. 3a an aero-spike with a constant cross-section, which is for example cylindrically shaped,
• Fig. 3b an aero-spike with triangular longitudinal section or conical configuration,
• Fig. 3c an aero-spike having a forehead body formed by a spherical thickening at the distal end,
• Fig. 3d an aerospike having a molded or conical end region and a central subregion of constant cross section,
• Fig. 3e an aerospike having an end body formed by a thickening of the distal end, which is approximately triangular in longitudinal section with a tip oriented in the direction of flight,
• Fig. 3f an aero-spike with an end body arranged in the distal end body in the form of a disc.

It is also possible to use an aero-spike with a so-called "jet-spike" or a "beam-spike", for which a localized optical, electrical or electromagnetic heating of the air takes place in front of the bow joint in the region of a frontal body.

Fig. 4 shows the flow around a missile 1, which has a equipped with an Aero-Disk 10 Aero-Spike 4. In such a case, it does not happen approximately in the region of the longitudinal axis 11-11 in the region of the end face 5 of the aero-spike accordingly Fig. 1 for flow separation, but rather in the radial edge region of the aero-disk 10, so that the detached boundary layer 6 is displaced radially further outwards. When using an aero-disk 10 naturally forms a "rear-side" peel-off bubble 12 behind the aero-disk, for the according to Fig. 4 conditions shown together with the bow-side detachment bladder 8, which is the front face 3 of the missile 1 immediately upstream, connected to a common longer detachment bladder. By the union of the release bubbles 8, 12, a common peel-off bubble can be achieved with a shallower detachment angle 7, resulting in a reduction of the bow resistance result.

Fig. 5 , shows a missile 1 in changed flight conditions, especially with one opposite Fig. 4 extended aero-spike 4. For such conditions, the bow-side detachment bladder 8 is separated from the rear-side detachment bladder 12 behind the aero-disk 10 over an area 9 of applied flow. The aim of the present invention is to avoid such an area 9 of applied flow. so that the release bubbles 8, 12 merge into one another to form a single release base, as in FIG Fig. 6 is shown.

• einen Schlitz, insbesondere einen Längsschlitz oder Querschlitz,
• eine Bohrung,
• eine Perforation,
• beliebige Ausnehmungen

handeln. Gemäß einem besonderen erfindungsgemäßen Vorschlag ist der Aero-Spike 4 zumindest teilweise mit einem porösen Material gebildet, wobei in diesem Fall die Strömungskanäle 15 zumindest teilweise von Poren des porösen Materiales gebildet sein.This is achieved according to the invention by virtue of the fact that 4 air emerges in outlet directions 14 from a lateral surface 13 of the aero-spike, which surrounds the lateral surface 13 in a pillow-like manner and pushes the detached boundary layer 6 away from the aero-spike 4. These are in the Aero-Spike Flow channels 15 are provided which open into the lateral surface 13, for example in the radial orientation. In such a flow channel may, for example. To

• a slot, in particular a longitudinal slot or transverse slot,
• a hole,
• a perforation,
• any recesses

act. According to a particular inventive proposal, the aero-spike 4 is at least partially formed with a porous material, in which case the flow channels 15 may be at least partially formed by pores of the porous material.

According to Fig. 7 The Aero-Spike 4 has an end body 24, which is designed here as an Aero-Disk 10 and has a front end face 25 and a rear end face 26. From the front end surface 5 is an oriented in the direction of the longitudinal axis 11-11 longitudinal recess 16, which is formed for example as a blind hole and partially extends in the aero-spike 4. Behind the aero-disk 10, the longitudinal recess 16 is formed with a hollow cylindrical porous portion 17 in which pores form the flow channels 15 and connect the longitudinal recess 16 with the lateral surface 13 flow-permeable. When moving missile 1 a dynamic pressure 18 acts in the longitudinal recess 16, so that it due to the pressure gradient between the ram pressure 18 in the longitudinal recess 16 on the one hand and in the region of the lateral surface 13 on the other hand to a transport of air from the longitudinal recess 16 to the environment of the lateral surface thirteenth Aero Spikes 4 is coming. The porous subregion 17 is preferably connected in a materially bonded manner to an end-side subregion 19 and to a subregion 20 facing the end surface 3. The end-side portion 19 may be formed in one or more pieces with the aero-disk 10.

Fig. 8 schematically shows a substantially Fig. 5 It has been inventively found that prevails in the region of the peel bladder 12, a pressure 21 which is smaller than the pressure 22 in the area 9 applied flow, wherein the Pressure 22 substantially p _∞ corresponds. The pressure 22 in the region 9 of the applied flow is again smaller than the pressure 23 in the region of the bow-side detachment bladder 8.

Fig. 9 shows an inventive embodiment of the missile 1, in which the end body 24 and an Aero-disk 10 is formed with a porous material. As a result of the flow in the flow direction 2, a back pressure develops in the region of the front end face 25, which causes air (preferably in the direction of the longitudinal axis 11-11) to pass through flow channels formed with the pores and from the rear end face 26 under high momentum loss exits again. This air leads to a flow 27 at low speed adjacent to the end body and in the region of the front lateral surface of the aero-spike, which causes behind the end body 24 in the vicinity of the aero-spike 4 forms a kind of air cushion, which is a rear-side peel-off 12 can extend and thus applying the flow to the Aero-Spike 5 according to Fig. 5 counteracts (see a. Fig. 10 ).

In 10, 11 are individual particles 28 of the porous material of the end body 24 to recognize with formed between adjacent particles 28 flow channels 29. As a result of the irregular, stochastic arrangement of the particles 28, the longitudinal axis of the flow channels 29 is wound in a curve around the particles 28. The cross-section of the flow channels 29 may vary over the course of the same. It is understood that the flow channels 29 are not necessarily closed in itself, but rather can be connected to adjacent (partial) flow channels, so that they branch. Preferably, a flow through the end body 24 is preferably approximately parallel to the longitudinal axis 11-11, which may be predetermined by the formation of the flow channels 29 and the manufacturing method used for the porous material and / or by the pressure conditions, namely a strong pressure difference in the region of the front end face 25 on the one hand and the rear end face 26 on the other hand may be favored.

Fig. 12, 13 show an alternative embodiment in which the end body 24 instead of the flow channels in consequence of the porosity or in addition to these holes 30 has, which are oriented parallel to the longitudinal axis 11-11. The holes 30 may be evenly distributed in both the radial direction and in the circumferential direction or, as seen Fig. 13 it can be seen to be distributed irregularly.

Fig. 14 shows an embodiment of the invention, in which the end body 24 substantially corresponding to that in the 10, 11 formed end body is formed. Between an end face 5 of the aero-spike and the rear end face 26 of the end body 24, a gap 31 is formed into which air from the flow channels 29 enters in the region of the rear end face 26. About the end face 5 of the aero-spike 4, this air is deflected radially outward so far that they can flow around the outer surface of the Aero-Spikes 4 (at low speed) and here, as already explained above, can form an "air cushion". In Fig. 12 a required fastener between the aero-spike 4 and the end body 24 is not shown, which may be arbitrarily formed, for example, straight or curved as extending between the two space-limiting elements extending strut, several such struts or the like, wherein such a Fastening element additionally a flow calming and / or a deflection of the flow can take place. It is also possible that such a fastener is also porous.

In principle Fig. 14 corresponding embodiment with a gap 31 between the aero-spike 4 and end body 24 has according to Fig. 15 the porous or non-porous end body 24 has a central through-bore 32, which is oriented coaxially to the longitudinal axis 11-11. The through hole 32 has in the region of the front end face 25 has a diameter which is smaller than the diameter of the end face 5 of the aero-spike 4. The diameter of the through hole 32 increases in the direction of the aero-spikes 4 continuously to such an extent that the Diameter of the through hole 32 in the region of the rear end face 26 is greater than that of the end face 5 of the aero-spike 4. In a semi-longitudinal section, the through hole is arbitrarily curved, for example, semicircular or parabolic. For such a configuration, therefore, the flow 27 can already receive a radially oriented component in the through-bore 32, while furthermore the end face 5 of the aero-spike may be required for deflecting the air radially outward in the intermediate space 31.

For the in Fig. 17 illustrated embodiment, the air occurs primarily parallel to the longitudinal axis 11-11 through the porous end body 24 therethrough. In the end region 33 which is adjacent to the end body 24, the aero-spike 4 is conically shaped, with the result that in that the flow 27 is provided with a radial component in accordance with the opening angle of the conical end region 33, and the flow 27 can be applied at low speed to the further circumferential surface of the aero-spike 4 to form an "air cushion".

Fig. 18 shows the attachment of the end body 24 via a rod-shaped aero-spike 4 on an end face 3 of the missile 1, wherein the aero-spike 4 may be formed with a constant diameter with a solid profile or hollow profile of closed or porous material. Aero-spike 4 and end body 24 are arranged coaxially to the longitudinal axis 11-11.

For the in Fig. 19 illustrated embodiment, the aero-spike 4 does not extend completely to the end face 3 of the missile 1. Rather, the length of the aero-spike 4 is only about 2/3 of the distance of the front body 24 of the end face 3. The Aero-Spike is held in this case via an additional holding element 34 which is connected in an end region on the end face 3 and in the other end region on which the end face 3 facing end portion of the shortened aero spikes 4 is connected. The retaining element 4 may be, for example, a plurality of struts distributed over the circumference. Preferably, the holding element 34 is formed as a conical body with circumferentially continuous shell surface.

Fig. 20 essentially shows one Fig. 19 corresponding embodiment, although here both the front body 24 and the aero-spike 4 are formed with or made of a porous material. For the in Fig. 20 illustrated embodiment, the aero-spike has a coaxial with the longitudinal axis 11-11 oriented longitudinal recess 16, which extends as a bore open on one side from an interior of the holding member 34 to the end body 24.

For the in Fig. 21 illustrated embodiment, the aero-spike 4 is completely eliminated, in which case the holding member 34 extends from the end face 3 of the missile 1 to the end body 24.

Finally shows Fig. 22 the formation of the retaining element 24 as a strut 35. The strut is approximately flush with the lateral surface of the missile initially parallel to the orientation Longitudinal axis 11-11. Since for the illustrated embodiment, the end body 24 has a smaller diameter than the end face 3 of the missile 1, the strut 35 is formed in the end body 24 facing the end portion in the direction of the longitudinal axis 11-11 and curved in the in Fig. 22 lower edge region connected to the end body 24.

Unlike the in the Fig. 9 to 22nd illustrated disc-shaped configuration of the end body 24 may have any geometry, for example, as a porous sphere, hemisphere, cone, as a rotationally symmetrical body, as a solid material or hollow inside or formed as a material with a porous outer shell.

In Fig. 15 forms the end face 5, in Fig. 17 the lateral surface of the end portion 33, in Fig. 14 the end face 5 a deflection device 36, which guides a basically 27 oriented parallel to the longitudinal axis 11-11 flow 27 to the aero-spike 4 to produce at least one radially oriented component of the flow 27th

In the figures, the particles for the formation of the pores are shown schematically and enlarged. For example, the pores for the use of a sintered metal may have a pore size of about 10 microns to about 0.3 mm.

LIST OF REFERENCE NUMBERS

1

missile

2

flow direction

3

Face missile

4

Aero-Spike

5

Face Aero-Spike

6

detached boundary layer

7

peel angle

8th

bow-sided detachment bladder

9

Range of applied flow

10

Aero-Disk

11

longitudinal axis

12

rear detachment bladder

13

lateral surface

14

exit direction

15

flow channel

16

longitudinal recess

17

porous part

18

backpressure

19

end portion

20

nose-side portion

21

print

22

print

23

print

24

end bodies

25

front face

26

rear face

27

flow

28

particle

29

flow channel

30

drilling

31

gap

32

Through Hole

33

end

34

retaining element

35

strut

36

deflecting

Claims (9)

1. Missile or flying object for the supersonic range with an aero-spike (4) extending from a front surface (3), said aero-spike (4) comprising a front body (24), characterised by the front body (24) being built with a porous material wherein open pores build flow channels (29).
2. Missile or flying object according to claim 1, characterised by the front body (24) being built with a sintered material.
3. Missile or flying object according to claim 1 or 2, characterised by the front body (24) being built with ceramic material.
4. Missile or flying object according to one of the preceding claims, characterised by the front body (24) being an aero-disk (10).
5. Missile or flying object according to one of the preceding claims, characterised by the front body (24) comprising a front surface (25) having an orientation transverse to the longitudinal axis (11-11) of the missile or flying object (1).
6. Missile or flying object according to one of the preceding claims, characterised by a directing device (36) located downstream of the flow channels (29) of the front body (24), wherein the directing device directs air streaming through the flow channels (29) in radial outward direction.
7. Missile or flying object according to one of the preceding claims, characterised by the aero-spike (4) built with a rod, said rod holding the front body (24) and being supported by a supporting body, holding element (34) or at least one strut (35) at the front surface (3).
8. Missile or flying object according to one of the preceding claims, characterised by the front body (24) and the or a rod or strut (35) supporting or holding the front body (24) being built with a porous material.
9. Missile or flying object according to one of the preceding claims 1 to 6, characterised by the front body (24) being supported by a strut (35) at the front surface (3), wherein said strut (35) extends offset from the longitudinal axis (11-11) of the missile or flying object (1).

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