EP2977713B1 - Fuselage nose cap for a missile - Google Patents

Description

The invention relates to a hull hood for a missile, with an outer surface, a hood wall forming the outer surface and a force element.

Missiles often have a sensor head with a sensor for detecting a measured variable in the bow area of their fuselage. By way of example, such a measurement variable detection can be carried out with an optical sensor and serve to detect targets of the missile for its route guidance. Usually, the sensor of the sensor head is shielded by a Meßmesendurchlässige shield, also called Dom, against damaging environmental influences, such as particle impact.

Usually, the sensor head is activated only in the last part of the flight of the missile for measuring variable detection, for example, for guidance of the missile immediately before it arrives at the destination. In order to protect the dome until the activation of the sensor head from damaging thermal or mechanical effects during flight of the missile, this is therefore covered with a usual size impermeable hull hood. This is discarded only immediately before the activation of the sensor head, so that unimpeded measurement size detection of the sensor can be carried out through the measuring area permeable dome.

From the DE 10 2010 007 064 A1 is a drop-down hull hood with a nose, a tail and a separator known. The nose and the tail are each made in two parts. The two parts of the nose are repulsible from each other by the separator laterally to the direction of flight and connected to the two parts of the rear via a connecting means. After a repulsion of the nose parts are the Rear parts tear-away and thrown off by the associated with them nose pieces and / or by a flight-related action of the back pressure.

The WO 2011/141 527 A1 describes an aerodynamic hood for a steering ammunition, which has in a region of its inner wall both longitudinally and circumferentially extending trench-shaped predetermined breaking points in order to facilitate a division of the hood.

It is an object of the present invention to provide a low-cost manufacturable and sealed hull hood.

This object is achieved by a trunk hood according to the features of claim 1, wherein the hood wall has a predetermined breaking geometry and the force element is prepared for a destructive division of the hood wall according to the predetermined breaking geometry.

The invention is based on the consideration that the tightness of multi-part fuselage hoods is influenced by the present for dropping the hood joints between the individual parts of the fuselage hood. In order to achieve a sufficient tightness against the action of the back pressure, a dimensionally closely tolerated production and accurate installation of the parts, as well as a complex sealing of the joints may be required. By the invention, a high tightness of the hull hood can be achieved with simple means, since the hull bonnet has a dividable predetermined breaking geometry and thus can be at least partially dispensed with joints. Consequently, the cost of a joint seal can be at least reduced.

The fuselage hood can be prepared for mounting in the bow region of a missile, in particular on a sensor head arranged on the bow, so that the fuselage hood forms a front, in particular the foremost, part of the sensor head. The sensor head can have a target detection device with an optical sensor, which can be shielded by a radiation-permeable shield designed as a dome. The hull cap can be prepared for at least partial coverage of this shield.

The hood wall can be designed as a shell, wherein the outer surface of the hull hood can be formed by the outermost, an environment or a flying atmosphere facing the shell. The hood wall can be a supporting structure of the trunk hood. Alternatively, the hood wall may be a planking or lining of a carrier structure of the fuselage hood.

The hood wall expediently forms a cavity for receiving further parts of the trunk hood, such as, for example, the force element, optionally an electronic unit for its activation, and a take-off shell for embracing the force element.

The force element may comprise means for generating a force and for directly or indirectly introducing this force into the hood wall. Conveniently, the force element prepared to produce the force abruptly and / or initiate. The force can be introduced at least two regions of the hood wall. The producible force of the force element is expediently dimensioned at least as high and can be introduced into the hood wall such that a mechanical overstressing of the predetermined break geometry is caused.

The predetermined breaking geometry can be a defined geometric weakening of the hood wall and can be, for example, a recess, a recess, a bead, a groove, a milled recess or a notch in and / or on the hood wall. Appropriately, the predetermined breaking geometry is arranged on the inside of the hood wall, in particular exclusively. The predetermined breaking geometry can be prepared for receiving lines, for example of electrical lines or pressure lines, so that an additional effort for the production of additional cable guides in and / or on the hood wall is avoided. The predetermined breaking geometry can be covered by a cover layer. The predetermined breaking geometry is expediently arranged along the hood wall in a linear or curved manner. The predetermined breaking geometry can be a defined material weakening of the hood wall, for example by a material arranged locally in the hood wall with a lower mechanical resistance in comparison to another material of the hood wall.

The hood wall is expediently prepared for fracture-mechanical destruction along the intended break geometry, ie for tearing apart and / or breaking, by an action of the force element. Accordingly, the hood wall is constructed so that it preferably breaks along the predetermined breaking geometry when a force, as caused by the force element. The force which can be generated by the force element, its introduction into the hood wall and the arrangement and / or design of the predetermined breaking geometry are expediently coordinated with one another or constructed in such a constructive manner that they are designed according to one Cutting the hood wall resulting fragments are thrown laterally. Expediently, the hood wall can be divided in such a way along the predetermined breaking geometry that predominantly fragments in a geometry substantially predeterminable by the predetermined breaking geometry arise in a substantially predeterminable number.

The invention is particularly advantageous applicable to a provided with wings and / or a tail missile. In such a missile, after launching a hull hood during flight there is a risk that the fuselage hood or portions of the fuselage hood may be propelled rearward by air resistance, impinge on the wings and / or tail and cause damage as a result of the impact. The impact energy and thus the risk of damage are influenced by the mass of the parts. Since the geometry and number of fragments formed after cutting can be predetermined essentially by the predetermined breaking geometry, the invention can be influenced by simple means the mass of the fragments and consequently the risk of damage caused by the dropping of the hull hood.

In an advantageous embodiment of the invention, the hood wall is in one piece, in particular monolithic. As a result, a good tightness of the hull hood can be achieved. On sealing gaps within the hood wall can be omitted. By one piece can also be understood a cohesive connection of identical or different materials, e.g. plastic overmolded metal, or a plastic thread embedded in metal. Monolithic is a one-piece piece of a single material. Advantageously, the hood wall forms at least the major part of the outer surface of the hull hood, in particular at least 80%. Particularly advantageous is the hood wall of the entire hull hood in one piece, in particular monolithic, possibly up to fasteners, such as a screwed threaded ring for attachment to the bow of a seeker head. The hood wall may be made by prototyping, e.g. by spraying, pressing or pouring. Alternatively, the hood wall may have a plurality of segments which each form part of the outer surface of the hull hood.

In a further advantageous embodiment of the invention, the predetermined breaking geometry is formed over at least half of the axial length of the hood wall, in particular over at least half of the axial length of Rumpfbughaube. Under the axial length of the hood wall in the context of the invention, the projected perpendicular to the longitudinal axis of the hull hood is to be understood between the bugseitigsten end and the rearmost end of the hood wall. Conveniently, the length of the hood wall is equal to the length of the trunk hood. The longitudinal axis of the hull hood expediently runs parallel to the longitudinal axis of a coverable by the hull hood sensor head. By such a design of the predetermined breaking geometry, a widespread crack or break propagation in the hood wall can be achieved, and consequently a particularly reliable division of the hood wall can be achieved.

In practice, a course of the predetermined breaking geometry has proven in the longitudinal direction of the hood wall. The longitudinal direction of the hood wall according to the invention is given by a tangent to the intersection of a plane through the longitudinal axis of the hull hood with the hood wall. The longitudinal direction can thus be location-dependent, in particular in the case of a curved hood wall. Thus, it can be achieved in a simple manner that after the division of the hood wall along the predetermined breaking geometry resulting fragments to the outside, so perpendicular to the direction of flight of the missile, are thrown and moved away by the air resistance of the missile.

In another embodiment, the force element on a pyrotechnic propellant. The pyrotechnic propellant serves to generate a force required for the division of the hood wall. The pyrotechnic propellant may be ignited by an at least partially enclosed by the hood wall of the hull hood ignition. Pyrotechnic propellant charges are widely tested and can be easily dimensioned in their mode of action over a wide range of force, whereby the division of the hood wall can be achieved particularly reliable and with a reasonable, not the sensor head affecting force.

Advantageously, the force element has a cylinder piston. The cylinder piston is expediently prepared for a directed acceleration by a pyrotechnic propellant charge. Furthermore, the cylinder piston can be prepared for at least indirect action on the hood wall.

Moreover, it is advantageous if the force element has a closed at one end face with a cylinder bottom hollow cylinder. The hollow cylinder points advantageously an axial bore. Conveniently, the axial bore for axially movable receiving a cylinder piston and / or a pyrotechnic propellant charge is prepared.

In an advantageous embodiment, the pyrotechnic propellant charge is arranged between the cylinder piston and the cylinder bottom and prepared for the acceleration of the cylinder piston along the axial bore. By a predetermined orientation of the axial bore a precise alignment of the direction of action of the cylinder piston or the force generated by the pyrotechnic propellant force can be achieved on the hood wall and consequently a particularly effective destruction of the hood wall can be achieved.

Furthermore, it is advantageous if the cylinder piston is fitted gas-tight in the axial bore of the hollow cylinder. Conveniently, the axial bore of the hollow cylinder is provided with an axial stop for fixing the maximum stroke of the cylinder piston, so that a complete moving out of the cylinder piston is prevented from the axial bore. Advantageously, the gas-tightness is ensured even at maximum stroke of the cylinder piston, for example by a seal arranged on the stop. By such a fit of the cylinder piston in the axial bore can be achieved that remain trapped in an ignition of the pyrotechnic propellant flue gases released, whereby an impairment of the sensor head is avoided.

Furthermore, it is advantageous if the axial bore of the hollow cylinder is arranged aligned radially to the hood wall. Radial to Haubenwandung according to the invention, the axial bore is then aligned when the longitudinal axis of the axial bore is aligned perpendicular to the longitudinal axis of the hull hood. Conveniently, the axial bore is oriented perpendicular to a plane in which a vector of the longitudinal direction of the hood wall and a vector of the longitudinal axis of the fuselage hood lie. In this way it can be achieved that the cylinder piston fitted in the axial bore causes a maximum tensile stress of the predetermined breaking geometry due to its action on the hood wall.

According to the invention, the force element is encompassed by a number of Abdrückschalen arranged on the inner surface of the hood wall. The Abdrückschalen can cover in their tangential extent together at least half of the inner surface circumference. Conveniently, the Abdrückschalen prepared for movement by a force of the force element. Advantageously, the Abdrückschalen cover together at least half of the inner surface circumference at the level of the force element. The Abdrückschalen can be prepared for the transmission of forces, in particular spreading forces on the opposite areas of the inner surface of the hood wall. Preferably, the Abdrückschale consists at least predominantly of metal. Expediently, the ejection shell extends at least over the axial length of the force element, preferably over at least twice the axial length of the force element, in order to achieve a planar arrangement on the inner surface. Due to the preferably flat arrangement of the Abdrückschalen on the inner surface unwanted punctiform penetration of the hood wall due to the force can be avoided.

According to the invention, in each case one ejection shell is arranged on a partial region of the inner surface of the hood wall which is at least partially bounded by the predetermined fracture geometry and prepared for separating the respective partial region from the other partial region. Disconnect in the given context means destructive separation, for example, by breaking or tearing. The subregions bordered at least partially by the predetermined breaking geometry can be formed by an elongated depression, in particular a groove or indentations, arranged on the inner surface of the hood wall, so that a geometric division of the inner surface results. By way of example, in the case of a division of the inner surface, two ejection shells are arranged in two partial regions, one of the ejection shells being arranged on one of the partial regions in each case. In this way, a particularly precise division or breaking the hood wall can be achieved in a definable number of essential fragments.

In a development, the hood wall consists at least predominantly of a plastic. In particular, when using a plastic with low specific gravity (mass per volume) so weight savings can be achieved and a payload of the missile can be increased. Due to the relatively low specific weight also the risk of damage to guide vanes at the rear of the missile can be reduced. Furthermore, in particular thermoplastic materials can be processed by simple means, for example by casting, forming, so that a geometrically complex hood wall can be realized low cost.

Since the Haubenwandung can greatly heat during a flight due to air friction, it has been proven in practice, if the plastic is up to a temperature of 250 ° C under mechanical overuse at least predominantly brittle refractive plastic. It can thus be ensured that even at a high temperature, in particular due to a flight at high speed, the hood wall is broken up in a brittle manner and not deformed in a ductile manner, ie can be reliably ejected. In practice, it has proven particularly useful if the hood wall consists at least predominantly of a polyamide imide, since this type of polymer satisfies the stated requirements.

In a further embodiment, the outer surface of the hood wall on a metal-containing coating, whereby an electrical requirement, in particular to an electromagnetic compatibility, can be fulfilled. Conveniently, the outer surface is formed by the coating.

In a further advantageous embodiment, the hood wall has on its inside a circumferential collar in its circumferential direction with a support surface for resting on a counter surface, wherein the normal vectors of the support surface parallel to the longitudinal axis of the hull hood or describe a rear side widening surface. Rear side in the sense of the invention means in the direction of the stern, facing the rear of the hull hood. Conveniently, the support surface is aligned perpendicular to the longitudinal axis or tilted outwardly, such as an outer surface of a conical section. By the collar with the support surface can be achieved that a longitudinal inertial force of the hull hood, for example, under the effect of a longitudinal acceleration in the amount of 26,000 times the acceleration of gravity, discharged from the hood wall and introduced into the sensor head. Thus, an unwanted overuse and thus an unwanted failure of the hood wall can be avoided. Conveniently, the hull cap is radially centered by the collar on the force element. The collar can be prepared for centering the trunk hood on a sensor head.

One embodiment provides a rear circumferential trained thread for connection to the fuselage nose of a missile. The thread can be introduced directly into the hood wall. The diameter of the thread is suitably at least 8/10 of the diameter of the stern of the hull cap. Conveniently, the thread for connection to the Sensor head of a flying body prepared. Through the thread, a low-cost, detachable connection of the fuselage hood with the fuselage nose or the sensor head can be produced.

Another embodiment provides a rear side threaded sleeve. The diameter of the threaded sleeve is expediently at least 8/10 of the diameter of the tail of the hull hood. Further, it is advantageous if the threaded sleeve has a bow-shaped external thread for connection to the hood wall. The bow in the sense of the invention means in the direction of the bow, the bow tip facing the hull cap. Moreover, it is advantageous if the threaded sleeve has a rear-side formed internal thread for connection to the fuselage nose of a missile. Furthermore, it is advantageous if the thread rotation directions of the internal thread and the external thread are in opposite directions. By mutually opposite threading directions can be achieved that the hull cap can be connected while avoiding rotation about its longitudinal axis, ie without screwing, with the sensor head or the fuselage nose of the missile. Thus, a tearing of any lines between the sensor head and the fuselage nose can be avoided.

In addition, the invention is directed to a missile with a trunk hood according to one of the preceding claims. Conveniently, the missile is a Rohrverschussmunition, ie an ammunition, which is prepared for a Verschuß from a pipe.

Conveniently, the hull hood is glued on its rear side by means of a circumferentially arranged on the hood wall adhesive layer on the fuselage nose of the missile. Conveniently, the adhesive layer is electrically conductive, so that in a simple manner an electrical connection between the fuselage nose and the fuselage hood is achieved. Adhesives can be applied with simple means and can meet high mechanical requirements. This type of connection is therefore particularly cost-effective and highly durable.

Furthermore, the invention is directed to a method for blowing off a hull hood from a sensor head arranged on the bow side of a missile according to the features of claim 13. The method provides that a force element is triggered and this acts at least indirectly on a hood wall forming the outer surface of the hull hood , a predetermined breaking geometry of the hood wall as a result of this

Action fracture mechanically fails, the hood wall is divided and the hull hood is blown off the sensor head of the missile.

The force element may be a pyrotechnic propellant. The force element can generate a gas pressure which acts at least indirectly on the hood wall. The gas pressure can act directly on the hood wall, so that an overpressure arises in a cavity formed by the hood wall, wherein the hood wall bursts due to the overpressure and is divided.

The hull hood is expediently at least predominantly blasted off so that any residual parts of the hull cap remaining on the fuselage bow do not impair a function of the sensor head. Due to the impulse of the blasting, the fragments of the hull hood are advantageously ejected in particular from a wing and / or a tail of the missile. Damage caused by impact of the fragments on the wing and / or the tail can be avoided. Due to the predetermined breaking geometry can be dispensed with the introduction of continuous joints in the hood wall for dividing, whereby a staudruckbedingtes penetration of air during a flight of the missile in the hull hood much more difficult and a high tightness is achieved by simple means.

An advantageous development of the method provides that the force element comprises a pyrotechnic propellant which is ignited to trigger and generates a gas pressure. Further, it is advantageous if the gas pressure acts on a cylinder piston fitted in an axial bore of a hollow cylinder and accelerates it out of the axial bore. Moreover, it is advantageous if a gas which is under the gas pressure remains sealed in a hollow cylinder by the cylinder piston. Conveniently, the cylinder piston is partially ejected from the axial bore, in particular to a predetermined by a stop maximum stroke. The cylinder piston can act indirectly on the hood wall, so that an overuse of the predetermined breaking geometry is effected. By sealing can be prevented that passes through the ignition of the pyrotechnic propellant charge from the hollow cylinder. An impairment of the sensor head by the gas, for example by fogging of an optical sensor, can thus be avoided.

The previously given description of advantageous embodiments of the invention contains numerous features, which are given in the individual subclaims partially summarized in several. However, these features may conveniently be considered individually and summarized to meaningful further combinations. In particular, these features can be combined individually and in any suitable combination with the method according to the invention and the device according to the invention according to the independent claims.

The above-described characteristics, features and advantages of this invention, as well as the manner in which they are achieved, will become clearer and more clearly understood in connection with the following description of embodiments, which will be described in connection with the drawings. The embodiments serve to illustrate the invention and do not limit the invention to the combination of features specified therein, not even with respect to functional features. In addition, suitable features of each embodiment may also be explicitly considered isolated, removed from one embodiment, incorporated into another embodiment to complement it, and / or combined with any of the claims.

FIG 1

eine Rumpfbughaube mit einer Haubenwandung und einem Kraftelement,

FIG 2

einen Flugkörper mit einem Sensorkopf und der Rumpfbughaube aus FIG 1,

FIG 3

ein Sensorkopfgehäuse, verbunden mit einer Rumpfbughaube mit einem Gewinde und

FIG 4

ein weiteres Sensorkopfgehäuse, verbunden mit einer Rumpfbughaube mit einer Gewindehülse.

Show it:

FIG. 1

a trunk hood with a hood wall and a force element,

FIG. 2

a missile with a sensor head and the fuselage hood off FIG. 1 .

FIG. 3

a sensor head housing, connected to a hull hood with a thread and

FIG. 4

another sensor head housing, connected to a trunk hood with a threaded sleeve.

FIG. 1 shows a schematic sectional view of a fuselage hood 2 with an outer surface 4, an outer surface 4 forming hood wall 6 and a force element eighth

The hood wall 6 has a predetermined breaking geometry 12 extending in its longitudinal direction 10. The predetermined breaking geometry 12 is a recess in the hood wall 6 and extends over about 9/10 of the axial length L of the hood wall 6. The hood wall 6 has a further similar 180 ° offset predetermined breaking geometry, which due to the selected cutting plane of the representation in FIG. 1 is not visible. In the present embodiment, the hood wall 6 is monolithic, that is integrally connected, so that the outer surface 4 is free of joints over the entire hood wall 6.

The force element 8 is arranged in the axial direction approximately midway between the nose cone 14 and the rear end 16 of the hull brace 2 in the one-sided open cavity formed by the Haubenwandung 6 and surrounded by two arranged on the inner surface 18 of the hood wall 6 Abdrückschalen 20a, 20b. The inner surface 18 is essentially divided into two parts in the circumferential direction by the predetermined breaking geometry 12 -and the further, as a result of the sectional representation not visible, similar predetermined breaking geometry. The ejection shells 20a, 20b cover in their tangential expansion along the hood wall 6 together the circumference of the inner surface 18 and the tangential expansion of the partial surfaces of the inner surfaces 18a and 18b.

The force element 8 has a pyrotechnic propellant charge 22, a cylinder piston 24 and a closed at its end face 26 with a cylinder bottom 28 hollow cylinder 30 with an axial bore 32. The cylinder piston 24 is arranged axially displaceable in the axial bore 32. The pyrotechnic propellant 22 is disposed between the cylinder piston 24 and the cylinder bottom 28 and prepared for the acceleration of the cylinder piston 24 along the axial bore 32. The cylinder piston 24 is gas-tight fitted in the axial bore 32, wherein a seal 34 is arranged radially between the axial bore 32 and the cylinder piston 24. The axial bore 32 has an axial stop 36 for determining the maximum stroke of the cylinder piston 24. The axial bore 32 is arranged perpendicular to the longitudinal axis 38 of the hull cap 2 and perpendicular to the extension of the predetermined breaking geometry 12.

The Abdrückschalen 20a, 20b cover in the tangential direction in each case a range of about 180 ° of the circumference of the inner surface 18 at the axial height of the force element 8 from. In each case one of the ejection plates 20a and 20b is arranged on in each case one of the partial regions of the inner surface 18a and 18b of the hood wall 6. The division level between the Abdrückschalen 20a, 20b is perpendicular to the alignment of the axial bore 32 and parallel to the course of the predetermined breaking geometry 12. The division plane of the Abdrückschalen 20a, 20b adjacent to the predetermined breaking geometry 12 at.

In the present exemplary embodiment, the hood wall 6 consists of a plastic 42 covered with a metal coating 40. The inner side 44 of the hood wall 6 has a collar 46 circulating in its circumferential direction with a support surface 48 for resting on a mating surface 50, the mating surface 50 being formed by an end face the ejection cups 20a, 20b is formed. In the present exemplary embodiment, the normal vectors of the support surface 48 and the mating surface 50 run parallel to the longitudinal axis 38. In a further embodiment, the normal vectors of the support surface 48 can describe a surface which widens on the rear side. The hull cap 2 comprises an ignition device 54 connected to the power element 8 via an ignition cable 52 for igniting the pyrotechnic propellant charge 22.

To divide the hull cap 2 of the pyrotechnic propellant charge 22 of the power element 8 is controlled and triggered by the ignition device 54 via the ignition cable 52. A gas pressure generated by the triggering of the pyrotechnic propellant charge 22 acts on the cylinder piston 24 fitted in the axial bore 32 of the hollow cylinder 30. The pressurized gas remains trapped by the seal 34 and the fit of the cylinder piston 24 in the axial bore 32 in the cavity between the cylinder bottom 28 and the cylinder piston 24. The cylinder piston 24 is accelerated by the action of the gas pressure in the direction of the axial bore 32 out of this and thus transmits a force to the Abdrückschale 20a, wherein a force opposing this force on the end face 26 and the cylinder base 28 is transferred to the Abdrückschale 20b.

The two Abdrückschalen 20a and 20b arranged on the portions of the inner surface 18a and 18b introduce the force and the reaction force into the hood wall 6, whereby this undergoes a mechanical stress. Since the parting plane between the Abdrückschalen 20a, 20b perpendicular to the alignment of the axial bore 32 and parallel to the course of the predetermined breaking geometry 12, the Haubenwandung 6 is stretched perpendicular to the course Sollbruchgeometrie 12, so that the predetermined breaking geometry with the least possible force of the force element 8 as much as possible - here primarily claimed to train in the circumferential direction - is.

In the further course of time the hood wall 6 is increasingly stretched by the maximum up to the stop 36 from the axial bore 32 sliding out cylinder piston 24 and thereby radially outwardly moving Abdrückschalen 20, whereby the hood wall 6 is increasingly mechanically stressed.

Here, the hood wall 6 experiences in the region of the predetermined breaking geometry 12 due to the groove-shaped weakening by the predetermined breaking geometry 12 the greatest stress. In the further course of time, this stress reaches or exceeds the resistance of the material of the hood wall 6, so that it is destructively divided along the predetermined breaking geometry 12, that is, it is broken and / or torn open.

FIG. 2 shows a schematic representation of a missile 56 with a sensor head 58 and the fuselage hood 2 from FIG. 1 , The hull cap 2 is shown in a longitudinal section and arranged with its rear end 16 at the bow of the sensor head 58, ie on the fuselage nose 64 of the missile 56. The hull cap 2 is adhesively bonded to the fuselage nose 64 of the missile 56 at its rear region 60 by means of an adhesive layer 62 arranged circumferentially on the hood wall 6.

The sensor head 58 has a dome 66 for shielding a sensor of the sensor head 58 against damaging environmental influences. In the present embodiment, the dome 66 is a dome-shaped radiation-transmissive window or an optical lens.

The missile 56 has support surfaces 68 for controlling the trajectory of the missile 56. The wings 68 generate aerodynamic lift during flight. The missile 56 is designed as Rohrverschussmunition, for example as artillery projectile. When the missile 56 is launched, it is fired from a tube and undergoes a large launch acceleration in the range between 10,000 g and 30,000 g.

The longitudinal acceleration of the missile 56 or the trunk hood 2 occurring during launching leads to an inertial force of the trunk hood 2, which is partially discharged from the hood wall 6 via the adhesive layer 62 and introduced into the sensor head 58. In addition, in order not to stress the hood wall too much in this process and to counteract undesirable breakage of the trunk hood 2 in a launch, the inertial force also becomes partial transmitted via the support surface 48 of the circumferential collar 46 on the mating surface 50 of the Abdrückschalen 20 and further transmitted via the Abdrückschalen 20 to the sensor head 58. In this way, a radial overstretching of the rear end 16 of the hood wall 6 can be avoided.

Before a flight of the missile 56, during the take-off phase and during a first part of the flight, the dome 66 is covered by the trunk hood 2. In particular during the flight, the dome 66 or the sensor head 58 is at least temporarily protected against damaging influences, such as particle impact or frictional heat.

After the launch of the missile 56 and during the flight with an axially directed flight direction 70, the force element 8 is driven by the ignition device 54 for firing the hull cap 2 from the bow side arranged sensor head 58 of the missile 56 at a given time and so ignited the pyrotechnic propellant 22 , As a result, the hood wall 6 in the above according to FIG. 1 described way destructively parts. In the present exemplary embodiment, the plastic 42 forming the hood wall 6 is a plastic, which is at least predominantly brittle, up to a temperature of 250 ° C., more particularly a polyamideimide. This ensures that the hull cap 2 breaks even after a strong warming of the hood wall 6 by a flight-induced air friction brittle instead of deforming ductile, so that the hood wall 6 reliably divided along the predetermined breaking geometry 12 and the hull cap 2 is blasted off.

As a result of the destructive division of the hood wall 6, these parts which are located from the inside of the trunk hood 2 are released and are moved away relative to the sensor head 58, counter to the direction of flight 70 and radially. In the absence of the supporting structure of the hood wall 6, internal parts of the trunk hood 2, in particular the force element 8, the ejection cups 20 and the igniter 54, are moved away from the missile so that the dome 66 of the sensor head 58 is exposed.

Due to the preferably sudden force development of the force element 8, the hull cap 2 is blasted off, so that fragments of the hood wall 6 and other parts and / or fractions of the hull cap 2 are thrown radially away from the missile 56. Eventual through the adhesive layer 62 on the fuselage bend 64 remaining parts of the hull cap 2 are immaterial, since they are behind the dome 66. By breaking off the fragments, parts and / or fractions are thrown so far that an impairment, in particular of the wings 68 of the missile 56 is counteracted.

FIG. 3 shows a schematic longitudinal sectional view of a sensor head housing 82a of another sensor head 58a and connected to the sensor head 58a hull cap 2a. The following descriptions are essentially limited to the differences from the previous embodiments, to which reference is made to the features and functions that remain the same. Substantially identical components are basically identified by the same reference numeral and features not mentioned are adopted in the following exemplary embodiments without being described again.

The hull cap 2a has a rear side formed thread 72. In the by FIG. 3 reproduced embodiment, the thread 72 is introduced as an internal thread in the hood wall 6a and has a diameter of about 9/10 of the maximum diameter of the hull cap 2a on. The hull cap 2a is detachably connected to the sensor head 58a via the thread 72. For this purpose, the sensor head 58a on the bow side has a corresponding thread 74. To mount the hull cap 2a on the sensor head 58a, the hull cap 2a is screwed to the sensor head 58a about the longitudinal axis 38a by means of a rotational relative movement to the sensor head 58a.

The schematic sectional view in FIG. 4 shows another sensor head housing 82b of another sensor head 58b, which is connected to a hull cap 2b with a threaded sleeve 76. The threaded sleeve 76 forms the rear end of the fuselage hood 2b and has a bow-side formed external thread 78 for connection to the hood wall 6b and a rear-side formed internal thread 80 with an opposite to the external thread 78 thread rotation direction. The hood wall 6b has a thread 72a for this purpose. The sensor head 58b includes a thread 74a.

To mount the hull cap 2b on the sensor head 58b, the hull cap 2b is screwed about the longitudinal axis 38b to the sensor head 58b and the hood wall 6b via a rotary movement of the threaded sleeve 76. A rotational relative movement between the hull cap 2b and the Sensor head 58b is not absolutely necessary for screwing and can thus be avoided, so that damage to cable connections inside the hull cap 2b is counteracted.

LIST OF REFERENCE NUMBERS

2, 2a, 2b

Rumpfbughaube

4

outer surface

6, 6a, 6b

shroud wall

8th

force member

10

Longitudinal direction.

12

Breaking geometry

14

prow

16

back part

18, 18a, 18b

palm

20a, b

Abdrückschalen

22

pyrotechnic propellant

24

cylinder piston

26

front

28

cylinder base

30

hollow cylinder

32

axial bore

34

poetry

36

attack

38, 38a, 38b

longitudinal axis

40

metal coating

42

plastic

44

inside

46

Federation

48

supporting

50

counter surface

52

ignition cable

54

detonator

56

missile

58, 58a, 58b

sensor head

60

rear area

62

adhesive layer

64

fuselage nose

66

cathedral

68

wings

70

flight direction

72, 72a

thread

74, 74a

thread

76

threaded sleeve

78

external thread

80

inner thread

82a, 82b

Sensor head case

L

axial length

Claims (14)

1. Fuselage nose cap (2) for a missile (56), having an outer surface (4), a cap wall (6) forming the outer surface (4), and a force element (8), wherein the cap wall (6) has a predetermined breaking geometry (12) and the force element (8) is prepared for destructive fragmentation of the cap wall (6) in accordance with the predetermined breaking geometry (12),
   characterized in that
   the force element (8) is enclosed by a number of press-off shells (20) which are arranged on the inner surface (18) of the cap wall (6), wherein in each case a press-off shell (20a, 20b) is arranged on in each case a subregion, which is delimited at least partially by the predetermined breaking geometry (12), of the inner surface (18a, 18b) of the cap wall (6) and is prepared for separating the respective subregion (18a, 18b) from the other subregion (18a, 18b).
2. Fuselage nose cap (2) according to Claim 1,
   characterized in that
   the cap wall forms at least the most part of the outer surface and is monolithic.
3. Fuselage nose cap (2) according to Claim 1 or 2,
   characterized in that
   the predetermined breaking geometry (12) is formed at least across half of the axial length (L) of the cap wall (6).
4. Fuselage nose cap (2) according to one of the preceding claims,
   characterized in that
   the predetermined breaking geometry (12) extends in the longitudinal direction (10) of the cap wall (6).
5. Fuselage nose cap (2) according to one of the preceding claims,
   characterized in that
   the force element (8) comprises a pyrotechnic propellant charge (22), a cylinder piston (24) and a hollow cylinder (30) with an axial bore (32), which hollow cylinder is closed at an end side (26) by a cylinder bottom (28), wherein the cylinder piston (24) is arranged so as to be axially displaceable in the axial bore (32) and the pyrotechnic propellant charge (22) is arranged between the cylinder piston (24) and the cylinder bottom (28) and prepared for accelerating the cylinder piston (24) along the axial bore (32).
6. Fuselage nose cap (2) according to one of the preceding claims,
   characterized in that
   the cap wall (6) consists at least for the most part of a plastic (42).
7. Fuselage nose cap (2) according to Claim 6,
   characterized in that
   the plastic (42) is a plastic which fractures in an at least predominantly brittle manner up to a temperature of 250°C under a mechanical overloading.
8. Fuselage nose cap (2) according to one of the preceding claims,
   characterized in that
   the outer surface (4) of the cap wall (6) has a metal-containing coating (40).
9. Fuselage nose cap (2) according to one of the preceding claims,
   characterized in that
   the cap wall (6) has on its inner side (44) a collar (46), which runs around in its circumferential direction, with a supporting surface (48) for bearing on a counter-surface (50), wherein the normal vectors of the supporting surface (48) extend parallel to the longitudinal axis (38) of the fuselage nose cap or describe a surface which widens on the rear side.
10. Fuselage nose cap (2a, 2b) according to one of the preceding claims,
    characterized
    by a thread (72, 74, 74a, 78, 78a, 80) for connecting to the fuselage nose (64) of a missile (56), which thread is designed to run around on the rear side.
11. Fuselage nose cap (2b) according to one of the preceding claims,
    characterized
    by a thread sleeve (76), which is arranged on the rear side, with an external thread (78), which is formed on the nose side, for connecting to the cap wall (6b) and an internal thread (80), which is formed on the rear side, with a thread direction of rotation, which is opposite to the external thread (78), for connecting to the fuselage nose (64) of a missile (56).
12. Tube-firing munition having a fuselage nose cap (2) according to one of the preceding claims,
    characterized in that
    the fuselage nose cap (2) is adhesively bonded at its rear region (60) to the fuselage nose (64) of the tube-firing munition by means of an adhesive layer (62) which is arranged to run around on the cap wall (6).
13. Method for splitting off a fuselage nose cap (2) from a sensor head (58), which is arranged on the nose side, of a missile (56), in which a force element (8) is triggered and the latter acts at least indirectly on a cap wall (6) which forms the outer surface (4) of the fuselage nose cap (2), and a predetermined breaking geometry (12) of the cap wall (6) fails in terms of fracture mechanics as a result of this action, wherein the cap wall (6) is fragmented and the fuselage nose cap (2) is split off from the sensor head (58) of the missile (56),
    characterized in that
    the force element (8) is encompassed by a number of press-off shells (20) which are arranged on the inner surface (18) of the cap wall (6), wherein in each case a press-off shell (20a, 20b) is arranged on in each case a subregion, which is delimited at least partially by the predetermined breaking geometry (12), of the inner surface (18a, 18b) of the cap wall (6) and its respective subregion (18a, 18b) is separated from the other subregion (18a, 18b) upon triggering of the force element.
14. Method according to Claim 13,
    characterized in that
    the force element (8) comprises a pyrotechnic propellant charge (22) which is ignited for triggering and generates a gas pressure, and the gas pressure acts on a cylinder piston (24) fitted into an axial bore (32) of a hollow cylinder (30) and accelerates said piston out of the axial bore (32), wherein the gas under gas pressure remains enclosed in the hollow cylinder (30) while being sealed by the cylinder piston (24).

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