EP1813907A1 - Missile for the supersonic range - Google Patents

Abstract

In a supersonic flying body (1) with an aero-spike (12) extending upstream from the front surface (4) of the body, the aero-spike is tiltable transverse to the longitudinal axis (10 - 10) of the body during flight.

Description

TECHNICAL FIELD OF THE INVENTION

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

STATE OF THE ART

An arrangement of a flow guide element in the form of a spike, a so-called "spike" or "aerospike" for reducing pressure and / or temperature on a front face of a missile at supersonic speed has been known for over 50 years, cf.
Chang, PK, "Separation of Flow," Pergamon Press, 1970 , [1]

Further information on the general problem of reducing the resistance of blunt bodies as well as on the application of aero-spikes can be found in the following references: Bertin J., "Hypersonic Aerothermodynamics", AIAA Education Series, 1994 [[2]
Formin VM, Tretyakov PK, Taran J.-P. "Flow Control Using Various Plasma And Aerodynamic Approaches (Short Review)", Aerospace Science and Technology, 8, 2004, pages 411-421 [3]
Kremeyer K., "Lines of Pulsed Energy for Supersonic / Hypersonic Drag Reduction; Generation and Implementation", AIAA-2004-0984, AIAA, 2004 (See: Kremeyer, K., USPTO,
Patent No. US 6,527,221 B1, May 2000 [[4]
Gnemmi P., Srulijes J., Roussel K., Runne K., Flowfield Around Spiked-Tipped Bodies for High Attack Angles at Mach 4.5, Journal of Spacecraft and Rockets, Vol. 40, No. 5, pp. 622-631 , Sept.-Oct. 2003 [[5]

A well-known example of using an aero spike for a missile is the Lockheed Martin TRITDENT long-range missile. Aero spikes are attached directly to, for example, a semi-spherical nose or a seeker head of the missile and are aligned along a longitudinal axis of the missile. In straight flight, the aero-spike can be significantly reduced by an induced flow separation in the area of the distal end of the aero-spike, which results from the interaction of the bow thrust with the boundary layer at the aero-spike, in [1 ] is estimated at up to 80%.

In DE 199 53 701 C2 It has already been recognized that for a flow of the missile, which does not take place exactly in the direction of the longitudinal axis of the missile, the flow detached at the distal end of the aero-spike is almost entirely displaced to a side designated as the lee side or downwind side In the area of a windward side or start-up side, for the most part, the full outside flow hits the end face of the missile. Despite the use of the Aero spikes occur for such Anströmbedingungen undesirable temperature and pressure increases. As a remedy, the document proposes not to form the aero-spike as a mandrel with a constant cross-section and with a tip or a plate at the distal end, but rather to provide a spherical, ellipsoidal or teardrop-shaped attachment at the distal end. This has the result that a compression shock occurs in the region of the distal end of the aero-spike, which is immediately attenuated by a dilution fan. Behind the dilution fan occurs at the essay a replacement. The detached flow mixes with the flow behind the dilution fan and occurs both on the windward side and on the leeward side, where it is then pushed off as well. The detached ones Flow impinges on the entire front face of the missile so that the face is exposed almost entirely to a reduction in pressure and hence resistance and temperature. The example, spherical essay should therefore cause the flow around the front end surface of the missile from the angle of attack can be made largely independent.

Out US 3,713,607 is a hollow cylindrical aerospike for a supersonic missile known, the lateral surface of the aero-spike is perforated. The attachment of the aero-spikes on the front end of the missile is such that with the production of the missile or before a start of the missile, an adjustment of the angle of the aero-spike against the longitudinal axis of the missile is possible.

Further prior art is from AIAA 95-0737, DE 36 12 175 C1 and US 6,527,221 B1 known.

OBJECT OF THE INVENTION

The invention has for its object to provide a missile with an Aero-Spike, in which with alternative or cumulative to the aforementioned measures proposed design features negative effects of flow to the missile at an angle to the longitudinal axis of the missile are at least reduced.

SOLUTION

The object of the invention is achieved with the features of independent claim 1. Further embodiments of the invention can be found in the dependent claims 2 to 12.

DESCRIPTION OF THE INVENTION

The present invention is based on the idea to adapt the missile with the Aero-Spike (exclusively) measures taken by a-priori measures or measures taken before the launch of the missile to different flight conditions. Rather, it is suggested that the Aero-Spike, taking into account the respective flight conditions of the missile is pivotable. In the event that with the pivoting of the aero-spike primarily changed angle of attack in a plane passing through the longitudinal axis of the missile plane is taken into account, this may, for example. The aero-spike be pivotable about an axis perpendicular to the longitudinal axis and the previously mentioned. Alternatively, a spatial pivoting of the aero-spikes can take place about a pivot point arranged in the region of the front end face. By such a degree of freedom of the aero-spike can be taken in particular to ensure that the longitudinal axis of the aero-spikes coincides with the flow or occupies an orientation between the flow and the longitudinal axis of the missile. As a result, the influence of the angle of attack on the flow around the face or nose of the missile can be reduced or eliminated as needed.

In the sense of the invention, an "aero-spike" is understood to mean, in particular, a flow-guiding element which increases the effective degree of slimming of the aircraft by means of a local current reduced in the direction of flight and reduces the nose resistance. The generation of such a local stream at the bow of the missile is carried out, for example, directly by means of so-called "jet spikes" (often referred to as "counterflow-jet", cf., eg [3]), or directly by a manipulation of the total pressure distribution in the atmosphere, which, in interaction with this bow thrust, leads to the formation of a recirculation bubble. Apart from conventional rod-shaped spike elements at the bow, the last type also includes applications with optical, electrical and electromagnetic flow heating by means of "beam-spikes" (also known as "energy deposition control" or the like, see also [3], [4 ]).

• für Flugkörper für lange Distanzen,
• Flugkörper, die über lange Zeitdauern gelagert werden, oder
• Flugkörper, deren Gesamtgewicht eine kritische Größe darstellt.

According to a development of the missile according to the invention, the Aero-Spike is passive pivotable. In this context, "passive" is understood in particular to mean that an adjustment takes place without energy sources deviating from the flow and / or without logic, such as, for example, control electronics. Such passive pivoting thus does not provide additional power requirements or control or regulation requirements, which could be particularly problematic

• for missiles for long distances,
• Missiles stored for long periods, or
• Missiles whose total weight is a critical size.

Furthermore, with passive design, the variability of the aero spikes can result in a simplified structural design, which is error-resistant even under harsh operating conditions.

For a further embodiment of the invention, at least one alignment element is provided. According to an influence of the flow on this alignment element of the Aero-Spike is automatically and passively swiveled. The alignment elements may be rigid elements in accordance with the principle of a wind vane, which are arranged downstream of the bearing point or a bearing axis of the Aero-Spikes and their alignment with the flow, the orientation of the Aero-Spikes pulls. The alignment element may be a flat or curved surface. Alternatively, the alignment element may be formed as a lattice. In this case, the well-known excellent stability behavior of a grating surface wind vane can be used for the invention.

In addition to the aforementioned passive pivoting of the Aero-Spikes, the pivoting can also be done by active measures. In this context, "active" is understood to mean a pivoting using an energy supply of the missile and / or a control or regulation unit with a suitable actuator. Such active pivoting may account for anticipated flight and flow conditions or actual or detected flow or flight conditions.

• fahnenartige Messelemente, die ein elektrisches Signal je nach Winkelstellung der als Festkörper ausgebildeten "Fahne" erzeugen,
• Messorgane zur Erfassung eines Drucks oder einer Materialbeanspruchung in einem Bereich des Flugkörpers, dessen Druckbeaufschlagung oder Materialbeanspruchung von der Anströmrichtung abhängig ist.

For a possible embodiment of such active pivoting, a measuring device is provided for detecting the flight conditions. For example, a measuring device can measure or approximate the actual existing angle of incidence. Taking into account a measuring signal of this measuring element, the Aero-Spike can then be actively swiveled, whereby the actual conditions can be taken into account with high precision. Possible measuring organs are in particular

• flag-like measuring elements which generate an electrical signal depending on the angular position of the "flag" formed as a solid,
• Measuring organs for detecting a pressure or a material stress in a region of the missile whose pressurization or material stress is dependent on the direction of flow.

It is also possible that the missile has a memory unit in which an a priori defined course of a desired influence of the aero-spikes during a flight phase can be stored. During flight operation of the missile then the aero-spike can be actively pivoted taking into account the stored history. In the simplest case, for example, different flight phases such as a climb, a flight phase with cruising altitude and a Zielanflugphase are stored with the associated expected time periods, so that the respective requirements can be taken into account by changing the position of the aero-spikes in the respective phases of flight. Of course, any other different flight phases are to be considered a priori in the memory unit.

If the cause is due to a steering action of the missile, a particularly simple suitable pivoting of the aero-spike can take place in that it depends on a steering action of the missile. For this purpose, for example, in an appropriate storage unit and control unit, an optimal pivoting angle of the aero-spike be stored depending on the steering action of the missile, so that in flight for a request for a suitable steering action optimum pivoting of the aero-spike is known. Such a dependency can be stored in the form of maps or functional dependencies. In the simplest case, the pivoting of the aero-spike with a steering element of the missile is electrically, mechanically or hydraulically coupled.

In a further embodiment of the invention, the aero-spike is pivotable together with the front end face of the missile. As a result, the pivoting enabling grooves, guides, bearings u. Ä. Be avoided in the area of the flow conditions of great importance playing face. Instead, there are increased design possibilities for the transition region from the front end face to the aero-spike. In the event that the front end face is not formed part-spherical in the area of the aero-spike, can continue to be ensured by a joint pivoting of the aero-spike and the front face, that in addition to the adaptation of Aero spikes at the angle of attack also a dependence of the orientation of the front end face against the direction of flow is at least reduced.

Of additional advantage may be such a configuration, when the front end face is formed with a pivotable Zielsuchkopfdom. In this case, a homing head is arranged in the missile, which searches a target, for example, with IR or radar wave transmission. Using a homing dome to cover the homing head may cause u. For example, the aerodynamic requirements may lag behind the desired seeker head functionalities, so the missile may be equipped with a semi-spherical nose which, while capable of high bow drag, improves the seeker head functionality, which is beneficial, for example, for high agile aircraft is. Inside such a homing head dome, all necessary radar antennas or IR sensors can be optimally positioned. The entire "field of view" of the homing head dome can be made of radiation-transmissive materials. Such a concept allows active and flight direction independent target tracking by a corresponding separate movement of the homing head. Due to the requirement for the target seeker dome to be made of a transmissive material, it may be necessary to use a material which places increased demands on the maximum temperatures and pressures acting in the area of the target seeker dome.

In a further missile according to the invention are from the document DE 199 53 701 C2 known design features and the resulting advantages integrated into the present invention. Accordingly, the pivotable aero-spike has a thickening at its distal end. For example, such a thickening is a disk, a sphere, a cone, a drop shape or an ellipsoid.

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 features of different claims is also different from the chosen relationships of the claims possible 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 in einer Seitenansicht einen erfindungsgemäßen Flugkörper mit einem verschwenkbaren Zielsuchkopfdom, der mit diesem verschwenkbar einen Aero-Spike trägt.

Fig. 2

zeigt in einer Seitenansicht einen alternativen erfindungsgemäßen Flugkörper, bei dem eine Verschwenkung des Aero-Spikes über passive Ausrichtelemente erfolgt.

Fig. 3

zeigt ein Strömungsbild für einen Anströmwinkel ≠ 0 bei nicht verschwenkbarem Aero-Spike gemäß dem Stand der Technik.

Fig. 4

zeigt ein Strömungsbild für einen Anströmwinkel # 0 bei verschwenkbarem Aero-Spike gemäß der vorliegenden Erfindung.

Fig. 5

zeigt ein schematisches Blockschaltbild für eine Steuerungs- oder Regelungseinrichtung zur aktiven Verschwenkung eines Aero-Spikes eines Flugkörpers.

Fig. 6

zeigt unter den Ziffern a) bis h) unterschiedliche Ausgestaltungsformen für die Geometrie eines Aero-Spikes in einer Seitenansicht.

Fig. 7

zeigt eine Ausführungsform einer Realisierung einer verschwenkbaren Lagerung eines Zielsuchkopfdoms mit hieran befestigtem Aero-Spike im Teillängsschnitt.

Fig. 8

zeigt eine weitere Ausführungsform einer Realisierung einer verschwenkbaren Lagerung eines Zielsuchkopfdoms mit hieran befestigtem Aero-Spike im Teillängsschnitt.

Fig. 9

zeigt eine weitere Ausgestaltung einer verschwenkbaren Befestigung eines Aero-Spikes an einer Stirnfläche eines Flugkörpers im Teillängsschnitt.

Fig. 10

zeigt einen weiteren erfindungsgemäßen Flugkörper, bei dem eine Verschwenkung des Aero-Spikes um eine flugkörperfeste Achse über passive Ausrichtelemente erfolgt, in Seitenansicht.

Fig. 11

zeigt den Flugkörper gemäß Fig. 10 in Vorderansicht.

Fig. 12

zeigt den Flugkörper gemäß Figuren 10 und 11 in einem Querschnitt XII-XII.

Fig. 13

zeigt einen weiteren erfindungsgemäßen Flugkörper, bei dem eine Verschwenkung des Aero-Spikes um eine flugkörperfeste Achse über passive Ausrichtelemente erfolgt, in Seitenansicht.

Fig. 14

zeigt den Flugkörper gemäß Fig. 13 in Vorderansicht.

Fig. 15

zeigt den Flugkörper gemäß Fig. 13 und 14 in einem Querschnitt XV-XV.

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

Fig.1

shows a side view of a missile according to the invention with a pivotable Zielsuchkopfdom, which carries with this pivotally an aero spike.

Fig. 2

shows in a side view an alternative missile according to the invention, in which a pivoting of the aero-spike takes place via passive alignment elements.

Fig. 3

shows a flow pattern for an angle of attack ≠ 0 with non-pivoting aero-spike according to the prior art.

Fig. 4

shows a flow pattern for an angle of attack # 0 with pivotable Aero-Spike according to the present invention.

Fig. 5

shows a schematic block diagram of a control or regulating device for actively pivoting an aerospike spike of a missile.

Fig. 6

shows under the numbers a) to h) different embodiments of the geometry of an aero-spike in a side view.

Fig. 7

shows an embodiment of a realization of a pivotable mounting a Zielsuchkopfdoms with attached thereto Aero-Spike in partial longitudinal section.

Fig. 8

shows a further embodiment of a realization of a pivotable mounting a Zielsuchkopfdoms with attached thereto Aero-Spike in partial longitudinal section.

Fig. 9

shows a further embodiment of a pivotable attachment of an aerospike on an end face of a missile in partial longitudinal section.

Fig. 10

shows a further missile according to the invention, in which a pivoting of the aero-spikes about a missile-fixed axis via passive alignment elements, in side view.

Fig. 11

shows the missile of FIG. 10 in front view.

Fig. 12

shows the missile according to Figures 10 and 11 in a cross section XII-XII.

Fig. 13

shows a further missile according to the invention, in which a pivoting of the aero-spikes about a missile-fixed axis via passive alignment elements, in side view.

Fig. 14

shows the missile of FIG. 13 in front view.

Fig. 15

shows the missile of FIG. 13 and 14 in a cross-section XV-XV.

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.In particular, such a missile is a missile, drone, or projectile or missile that is self-propelled by a propulsion system, at least over part of its trajectory, for example, by a jet engine having both the Fuel as well as an oxidizing agent for it carries. 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 illustrated in the figures is intended, after covering a trajectory, to hit a moving or stationary target object on land, water or in the air, according to FIG. 1, an opposing missile 3. The missile 1 has in the region of a front end face 4 a homing seeker 5, via which the position of the target object relative to the missile can be detected and influenced via a control device steering elements such that the trajectory 2 of the missile 1 hits the target object. The front end face 4 is formed with a substantially part-spherical Zielsuchkopfdom 6, which is mounted with a pivot axis or a ball joint 7 pivotable about the pivot axis or spatially movable relative to the ball joint relative to the housing of the missile 1. The Zielsuchkopfdom 6 is independent of the pivoting under sealing and under favorable aerodynamic design in a tubular outer surface 8 of the missile 1 over. 1, the flow 9 of the medium in which the missile 1 moves is indicated by an arrow. Opposite a longitudinal axis 10-10 results in an angle of attack 11, which is for the flight state shown in Fig. 1 # 0.

For a neutral position that correlates with an angle of attack of 0 for which the flow 9 is directed in the direction of the longitudinal axis 10-10, an aero-spike 12 carried by the target seeker dome 6 is aligned with the longitudinal axis 10-10 and the flow direction. The aero-spike 12 is designed for the illustrated embodiment as a mandrel with a cylindrical lateral surface whose longitudinal extent is a multiple of the diameter. At the proximal end of the aero-spike 12 is fixedly connected to the Zielsuchkopfdom 6. The distal end 12 has a taper or conical tip for the illustrated embodiment, in which case also out DE 199 53 701 C2 known deviating geometries and essays can be used.

To adapt to a different from 0 approach angle 11 as shown in FIG. 1, the Zielsuchkopfdom 6 is pivoted about the previously described neutral position about an axis oriented vertically to the plane, so that a pivot angle 13 of the Aero-Spikes 12 relative to the longitudinal axis 10-10 results. For the embodiment shown in Fig. 1 corresponds to the pivot angle 13 the angle of attack 11, wherein for another design is also possible that the pivot angle 13 deviates from the angle of attack 11, in particular smaller than this. Since the Zielsuchkopfdom 6 is pivotally mounted in its interior, the attachment point of the Aero-Spikes 12 moves to the Zielsuchkopfdom 6 on a circular path around the pivot axis 7 with the radius of the distance of the attachment point of the pivot axis, so that with increasing pivoting the distance of the attachment point is increased from the longitudinal axis 10-10.

2 shows a passive embodiment for enabling a pivoting of the aero spike 12. For this embodiment of the invention, the Zielsuchkopfdom 6 carries alignment elements 14. The alignment elements 14 are to be referred to as L-shaped in a first approximation, wherein the free end portion of the short leg of the L is rigidly secured to the Zielsuchkopfdom 6 and the long leg of the L in the neutral position approximately parallel to the longitudinal axis 10-10 and slightly spaced from the lateral surface 8 of the missile 1 extends. The end of the alignment elements facing away from the Zielsuchkopfdom 6 carries surfaces 15 or a Gitterleitwerk. The surface 15 or the lattice are arranged in the direction of the longitudinal axis 10-10 behind the pivot axis 7 of Aero-Spike 12, Kugelsuchkopfdom 6 and the alignment elements 14 so that forces due to the flow, which act on the surfaces 15 and are greater than on the aero-spike 12 forces exerted by the flow, cause the Aero-Spike 12 aligns exactly to the flow 9. The distance of the alignment elements 14 from the lateral surface 8 of the missile 1 is selected such that the required pivoting about a pivot angle 13 during an expected flight operation is possible.

3 and 4 show a sketch of the resulting flow structures, on the one hand for a prior art rigid aero-spike 12 and on the other hand for a pivotable aero-spike according to the present invention in an oblique flow. While, according to FIG. 3, the front end face 4 and the homing seeker dome 6 in the region 16 are acted upon by the flow detached from the aero-spike 12, such a stress is the front end face 4 and the Zielsuchkopfdoms 6 for the pivoting of the Aero spikes 12 as shown in FIG. 4 largely avoided.

5 shows a schematic block diagram for actively influencing the swivel angle 13 of the aero-spike 12 with respect to the longitudinal axis 10-10 of the missile. A measuring element 17 supplies a signal 18 which at least correlates with the angle of attack 11. The signal 18 is fed to a control device 19. The control device 19 determines an application signal 20 for an actuator 21 which, in particular via a force, a moment, a travel or an angle 22, acts on the aero-spike 12 for adjusting the swivel angle 13. The control device 19 may be provided separately for driving the Aero-Spikes 12 or, as indicated in Fig. 5, take over other functions, such as generate steering signals 23 to influence the trajectory 2 of the missile 1 or process signals of the homing 5. The control device 19 is connected via a signal connection 24 in conjunction with a memory device 25 in which, for example, a priori determined gradients for the pivot angle 13 of the Aero-Spikes 12 are stored and / or dependencies of the Beaufschlagungssignals 20 of a signal 18 and / or steering signals 23 in Form of functional parameters or maps are stored.

• Fig. 6a einen Aero-Spike mit konstantem Querschnitt, der beispielsweise zylinderförmig ausgebildet ist,
• Fig. 6b einen Aero-Spike mit dreieckförmigem Längsschnitt oder kegelförmiger Konfiguration,
• Fig. 6c einen Aero-Spike mit einer sphärischen Verdickung an dem distalen Ende,
• Fig. 6d einen Aero-Spike mit einem angespritzten oder kegelförmigen Endbereich und einem mittigen Teilbereich konstanten Querschnitts,
• Fig. 6e einen Aero-Spike mit einer Verdickung des distalen Endes, die im Längsschnitt ungefähr dreieckförmig mit in Flugrichtung orientierter Spitze ausgebildet ist,
• Fig. 6f einen Aero-Spike mit einer Verdickung im distalen Endbereich in Form einer Scheibe,
• Fig. 6g einen Aero-Spike mit einem "Jet-Spike", bei dem mittels Pfeilen an dem distalen Ende des Aero-Spikes das Austreten eines in Flugrichtung gerichteten Gas- und/oder Flüssigkeitsstrahles angedeutet ist und
• Fig. 6h einen Aero-Spike mit einem "Beam-Spike", für den eine lokalisierte optische, elektrische oder elektromagnetische Erhitzung der Luft vor dem Bugstoß erfolgt.

Possible types of Aero spikes 12 blunt or pointed spikes, Aero spikes with discs, balls or cones or with its combinations on the nose, as well as emerging in the direction of plasma, liquid or gas jets are used, this in conjunction with a swivel target seeker dome or on mobile separate scaffolding or sled. 6 shows, by way of example, different embodiments of basic basic configurations of an aero-spike on a nose of a missile, namely:

• 6a shows an aero-spike with a constant cross-section, which is for example cylindrically shaped,
• FIG. 6b shows an aero-spike with a triangular longitudinal section or conical configuration, FIG.
• 6c shows an aero-spike with a spherical thickening at the distal end,
• FIG. 6 d shows an aero-spike with a molded-on or conical end region and a central subregion of constant cross-section, FIG.
• 6e shows an aero-spike with a thickening of the distal end, which is approximately triangular in longitudinal section with a tip oriented in the direction of flight, FIG.
• 6f an aerospike with a thickening in the distal end region in the form of a disc,
• 6g shows an aero-spike with a "jet spike" in which the escape of a gas and / or liquid jet directed in the direction of flight is indicated by means of arrows at the distal end of the aero-spike, and
• 6h shows an aero-spike with a "beam spike", for which a localized optical, electrical or electromagnetic heating of the air takes place in front of the bow thrust.

For the embodiment shown in Fig. 7 , the missile 1 in the front end region has an extension 26 which carries a spherical end portion 27. Fixedly connected to the Zielsuchkopfdom 6 are inwardly extending support 28 which carry a ball sleeve 29. The spherical end portion 27 and the ball sleeve 29 form a joint 30, via which the Zielsuchkopfdom 6 with the attached thereto Aero-spike 12 is spatially, for example in the direction 31 relative to the missile 1 is pivotable.

For the embodiment shown in Fig. 8 , the Zielsuchkopfdom 6 is approximately spherical and received in a ball seat 32 of the missile 1, whereby in this case, the joint 30 is formed. If such a training in the Zielsuchkopfdom 6 to arrange a homing head, so this is to be formed as an independent unit. Alternatively, a transmission of electrical signals between the missile 1 and the Zielsuchkopfdom 6 done, for example by means of sliding contacts, moving wires or a transmission of radio signals.

For the embodiment shown in Fig. 9 , the Aero-Spike 12 has a spherical or cylindrical end portion 33, with which this is pivotally mounted in the spatial direction or pivotally mounted in the plane in a cylindrical or spherical receptacle 34, whereby in this case the joint 30th is formed.

• Die Schwerkraft erzeugt ein Moment auf die Hülse 36, welches darauf abzielt, dass der Schwerpunkt der Hülse 36 mit Anbauteilen exakt unterhalb der Längsachse angeordnet ist, was bedeutet, dass für einen Geradeausflug ohne Querbeschleunigungen eine Querachse 38-38 quer zur Vertikalen orientiert ist. Unabhängig von einer Rollbewegung des Flugkörpers 1 um die Längsachse 10-10 ist damit die Hülse 36 gegenüber dem Gravitationsfeld ausgerichtet.
• Für den Fall einer auf den Flugkörper 1, bspw. infolge einer Lenkbewegung, wirkenden Querbeschleunigung führt die exzentrische Anordnung des Schwerpunkts der Hülse 36 mit Anbauteilen ebenfalls zu einer in Richtung einer Verdrehung der Hülse 36 gegenüber dem Fortsatz 35 gerichteten Verstellmoment, mit dem eine Ausrichtung der Querachse 38-38 entsprechend der Querbeschleunigung, einer Lenkbewegung und/oder einer Veränderung der Anströmrichtung automatisiert Rechnung erfolgen kann.

10 to 12 show a further embodiment of the invention with passive alignment of the aero-spike 12. Compared to a front cylindrical extension 35 is a hollow cylindrical sleeve 36 by means of a sliding bearing pivotally mounted about the longitudinal axis 10-10 of the missile 1. The focus of the sleeve 36 with the attachments u. U. arranged eccentrically to the longitudinal axis 10-10, for example due to a material region 37 with increased density. The eccentric arrangement of the center of gravity of the sleeve 36 with attachments has the following effects:

• Gravity creates a moment on the sleeve 36 which aims to locate the center of gravity of the sleeve 36 with attachments exactly below the longitudinal axis, which means that for transverse flight without lateral accelerations a transverse axis 38-38 is oriented transverse to the vertical. Regardless of a rolling movement of the missile 1 about the longitudinal axis 10-10 so that the sleeve 36 is aligned with respect to the gravitational field.
• In the event of a transverse acceleration acting on the missile 1, for example as a result of a steering movement, the eccentric arrangement of the center of gravity of the sleeve 36 with attachments also leads to an adjusting moment directed in the direction of a rotation of the sleeve 36 relative to the extension 35, with which an alignment of the Transverse axis 38-38 can be done automatically according to the lateral acceleration, a steering movement and / or a change in the direction of flow invoice.

The sleeve 36 carries on both sides in the direction of the transverse axis 38-38 oriented bearing pin 39, 40, with respect to which the aero-spike 12 is mounted with the alignment elements 14 in the region of bearing eyes 41, 42 pivotable about the transverse axis 38. For the embodiment shown in FIGS. 10 to 12, the alignment elements 14 are formed in the form of a sheet-like body, which extends approximately circular around the Zielsuchkopfdom 6, here centrally carries the Aero-Spike 12, the side of the Zielsuchkopfdoms 6, the bearing eyes 41, 42nd forms and is rotated in the opposite end of the aero-spike 12 for a suitable flow around the longitudinal axis of the end portions.

13 to 15 show a further embodiment for ensuring a pivotability of the aero-spike 12 with the alignment elements 14. In this case, aero-spike 12 and alignment elements 14 are fixedly disposed on an outer sleeve 36, the is supported by a slide bearing pivotable about the longitudinal axis 10-10 relative to an outer cylindrical lateral surface of a hollow cylindrical intermediate body 43. As previously stated for the embodiments according to FIGS. 10 to 12, the sleeve 36 with the associated attachments such as aero-spike 12 and alignment elements 14 can have a center of gravity which is arranged eccentrically to the longitudinal axis 10-10. The intermediate body 13 is supported by bearing bolts 39, 40 in the direction of the transverse axis 38-38 pivotally about this against an inner body 44 of the missile 1, wherein the bearing pins 39, 40 are fixedly connected to the inner body 44 and in bearing eyes of the intermediate body 43 are pivotable or are fixedly connected to the intermediate body 43 and in bearing eyes of the inner body 44 are pivotable.

If a homing head with a homing dome is arranged in the area of a front end surface of the missile, a blunt nasal shape is typically used, which is necessary to ensure the functionality of the seeker head. For fluid mechanical reasons, this form leads to a very high aerodynamic resistance, which occurs for example at supersonic speeds by forming a strong compression shock at the bow. As it passes through the shock, the entropy of the flow medium increases and at the same time the static pressure drops. This causes the so-called wave resistance on the missile, which increases very much from the intensity of the bow thrust and with the speed.

From [1] - [5] it is known that in the case of a straight-ahead flight by using an aero-spike in the form of an "aero-spike" a reduction of the characteristic impedance of up to 80% can be achieved. The rigid arrangement of the aero-spikes on the nose, however, means that in a maneuver flight with an oblique attitude whose effect is no longer optimal and the high bow drag comes about [1, 5]. Therefore, the Aero spikes are mainly used only in ballistic (ie not highly maneuverable) missiles.

According to [1], the effect of an oblique flow with an angle of attack on the resistance gains with optimized aero-spikes, which are rigidly fixed to a nose of the missile, can be stated as follows: if about 50 percent gain is achieved with an angle of attack α = 0 ° could, so at an angle of attack α = 5 ° only a 33-percent, at an angle of attack α = 10 ° only 10-percent and at an angle of attack of α = 15 ° only a 5-percent gain has been demonstrated. About the same numbers also apply to optimized variants of the aero spikes, which were investigated at a Mach number of 4.5 in [5]. It has been repeatedly proven that at angles of attack> 15 ° -17 ° all aero spikes even lead to an increased resistance compared to a blunt reference body (see, for example, [5]).

The relative size of the aero spike may vary for different missions, aero spike types, and speed ranges. From the literature, information on the most effective rigid aero spikes for low supersonic speeds (Mach number between 1.8 and 3) known, said z. B. is dull aero spikes with relative thicknesses usually <0.2 D and a relative length of about (1-2) D, where D denotes the frontal diameter of the missile.

When using an aero-spike, investigations according to [1] have shown that the drag coefficient c _w at Mach 1.8 can be halved from 0.6 to approximately 0.3, which correlates to an absolute gain of 0.3 or 50%. An employment of the missile without aero-spike at 15 ° means an increase in the c _w -value to about 0.8. With an aero-spike, which is conventionally rigidly aligned along the longitudinal axis, the c _w value drops to about 0.72 (10% gain). In an inventive arrangement with an aero-spike, which is adapted to the flight direction and the direction of flow, an absolute gain in the range of 0.3 is to be expected, so that a c _w value of about 0.5 results. That would mean a gain of at least about 25%, compared to 10% for the conventional solution. These effects should become even clearer at higher Mach numbers, as the losses due to wave resistance increase exponentially with the Mach number. The specified reductions in resistance reduction are to be considered as guidelines only. The information is based initially on the profits by improving the aerodynamic performance. Information about the corresponding improvement in performance through more effective target tracking is expected to add to performance.

Constructively, an equilibrium position of the pivot angle 13 may be predetermined, for example via suitable spring elements or detents for a pivoting angle of zero.

LIST OF REFERENCE NUMBERS

1

missile

2

trajectory

3

rocket

4

front face

5

Seeker

6

Zielsuchkopfdom

7

Swivel axis, ball joint

8th

lateral surface

9

flow

10

longitudinal axis

11

angle of attack

12

Aero-Spike

13

swivel angle

14

aligning

15

area

16

Area

17

measuring element

18

signal

19

control device

20

Beaufschlagungssignal

21

actuator

22

Force, moment, way

23

steering signal

24

signal connection

25

memory device

26

extension

27

end

28

carrier

29

ball sleeve

30

joint

31

direction

32

ball seat

33

end

34

admission

35

extension

36

shell

37

material area

38

transverse axis

39

bearing bolt

40

bearing bolt

41

bearing eye

42

bearing eye

43

intermediate body

44

inner body

Claims (12)

A missile for the supersonic range comprising an aero-spike (12) extending upstream from a forward end face (4) of the missile (1), characterized in that the aero-spike (12) is transverse to a longitudinal axis during flight of the missile (10-10) of the missile (1) is pivotable. A missile according to claim 1, characterized in that the aerospike (12) is passively pivotable. A missile according to claim 2, characterized in that at least one alignment element (14) is provided, through which the aerospike (12) is pivotable in accordance with an action of the flow (9) on this alignment element (14). A missile according to claim 3, characterized in that the alignment element (14) is formed with a surface (15). A missile according to claim 3, characterized in that the alignment element (14) is formed with a lattice tail. A missile according to claim 1, characterized in that the aero-spike (12) is actively pivotable. A missile according to claim 6, characterized in that a measuring member (17) for detecting the flight conditions, in particular the angle of attack (11), is provided and, taking into account a measurement signal (18) of the measuring member (17) of the aero-spike (12) actively pivotable is. A missile according to claim 6, characterized in that a memory unit is provided, in which an a priori fixed course of a desired influence of the aero-spike (12) during a flight phase can be stored, and that during the flight phase of the aero-spike (12) under Considering the stored course is actively pivotable. A missile according to claim 6, characterized in that the pivoting of the aero-spike (12) by a steering action of the missile (1) is dependent. Missile according to one of the preceding claims, characterized in that the aero-spike (12) is pivotable together with the front end face (4). A missile according to claim 11, characterized in that the front end face (4) is formed with a Zielsuchkopfdom (6). Missile according to one of the preceding claims, characterized in that the aero-spike (12) at its distal end a thickening, in particular a disc, a sphere, a cone, a teardrop shape or an ellipsoid.

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