DE102014011035A1 - Hull hood for a missile - Google Patents

Abstract

The invention relates to a hull hood (2) for a missile (56), with an outer surface (4), a hood wall (6) forming the outer surface (4) and a force element (8).
An easily sealable hull cap (2) can be produced at low cost, if the hood wall (6) has a predetermined breaking geometry (12) and the force element (8) for a destructive division of the hood wall (6) according to the predetermined breaking geometry (12) is prepared.

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, the tail parts are entrained by the associated with them nose pieces and dropping and / or by a flight-related action of the back pressure.

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 of the type mentioned, in which the hood wall according to the invention 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, for example, a recess, a Well, be a bead, a groove, a cut 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 that 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 matched to one another or constructed in such a constructive manner that the fragments formed after a division of the hood wall are laterally thrown out. 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 will be propelled rearward by air resistance, impact 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. Under one piece, a cohesive connection of the same or different materials can be understood, for. B. plastic overmolded metal, or a molded plastic in metal thread. 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 can be made by prototyping, z. B. 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 the axial length of the hood wall, in particular over at least half the axial length of the body hood. 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, 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 advantageously has 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.

In an advantageous development, the force element is encompassed by a number of ejection shells arranged on the inner surface of the hood wall, which in their tangential extent together cover at least half of the inner surface circumference. Conveniently, the Abdrückschalen are 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.

In a further embodiment, in each case one Abdrückschale is arranged on each one at least partially bounded by the predetermined breaking geometry portion of the inner surface of the hood wall and prepared for separating the respective portion of the other portion. Disconnect in the given context means destructive separation, for example, by breaking or tearing. The at least partially bounded by the predetermined breaking geometry portions can be formed by an arranged on the inner surface of the hood wall elongated recess, in particular a groove or notches, so that gives a geometric division of the inner surface. 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 is low cost feasible.

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. The thread is expediently prepared for connection to the sensor head of a flying body. 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 on its rear side by means of a circumferentially arranged on the hood wall adhesive layer on Hull bump of the missile glued. 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 blasting off a hull hood from a sensor head arranged on the bow side of a missile. The method provides that according to the invention a force element is triggered and this acts at least indirectly on a forming the outer surface of the hull hood hood wall, a predetermined breaking geometry of the hood wall due to this impact fracture mechanically fails, the hood wall 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.

Show it:

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

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

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

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

1 shows a schematic sectional view of a hull hood 2 with an outer surface 4 , one the outer surface 4 forming dome wall 6 and a force element 8th ,

The hood wall 6 has one in its longitudinal direction 10 running predetermined breaking geometry 12 on. The predetermined breaking geometry 12 is a depression 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 predetermined offset by 180 ° predetermined breaking geometry, which due to the selected section plane of the representation in 1 is not visible. In the present embodiment, the hood wall 6 monolithic, ie integrally connected, so that the outer surface 4 over the entire hood wall 6 is free of joints.

The force element 8th is in the axial direction approximately midway between the nose 14 and the rear end 16 the hull hood 2 in the through the hood wall 6 formed formed on one side open cavity and by two on the inner surface 18 the hood wall 6 arranged ejection cups 20a . 20b encompassed. The inner surface 18 is due to the predetermined breaking geometry 12 - And the other, as a result of the sectional view not visible, similar predetermined breaking geometry - in its circumferential direction essentially divided into two parts. The ejection cups 20a . 20b cover in their tangential extension along the dome wall 6 together the circumference of the inner surface 18 or the tangential expansion of the partial surfaces of the inner surfaces 18a and 18b from.

The force element 8th has a pyrotechnic propellant 22 , a cylinder piston 24 and one on his front 26 with a cylinder bottom 28 closed hollow cylinder 30 with an axial bore 32 on. The cylinder piston 24 is axially displaceable in the axial bore 32 arranged. The pyrotechnic propellant 22 is between the cylinder piston 24 and the cylinder bottom 28 arranged and used to accelerate the cylinder piston 24 along the axial bore 32 prepared. The cylinder piston 24 is gas-tight in the axial bore 32 fitted, with a seal 34 radially between the axial bore 32 and the cylinder piston 24 is arranged. The axial bore 32 has an axial stop 36 to determine the maximum stroke of the cylinder piston 24 on. The axial bore 32 is perpendicular to the longitudinal axis 38 the hull hood 2 and perpendicular to the extension of the predetermined breaking geometry 12 arranged.

The ejection cups 20a . 20b cover in the tangential direction each a range of about 180 ° of the circumference of the inner surface 18 at the axial height of the force element 8th from. One each of the ejection cups 20a and 20b is at each one of the partial areas of the inner surface 18a and 18b the hood wall 6 arranged. The dividing plane between the ejection cups 20a . 20b runs perpendicular to the alignment of the axial bore 32 and parallel to the course of the predetermined breaking geometry 12 , The graduation level of the ejection cups 20a . 20b adjoins the predetermined breaking geometry 12 at.

The hood wall 6 in the present embodiment consists of one with a metal coating 40 covered plastic 42 , The inside 44 the hood wall 6 has a circumferential collar in its circumferential direction 46 with a support surface 48 to rest on a counter surface 50 on, with the opposite surface 50 through an end face of the ejection cups 20a . 20b is formed. The normal vectors of the support surface 48 and the counter surface 50 extend in the present embodiment parallel to the longitudinal axis 38 , In a further embodiment, the normal vectors of the support surface 48 Describe a rearward widening surface. The trunk hood 2 includes one via an ignition cable 52 with the force element 8th connected ignition device 54 for ignition of the pyrotechnic propellant 22 ,

For cutting the trunk hood 2 becomes the pyrotechnic propellant 22 of the force element 8th over the ignition cable 52 through the ignition device 54 triggered and triggered. One by the triggering of the pyrotechnic propellant 22 generated gas pressure acts on the in the axial bore 32 of the hollow cylinder 30 fitted cylinder piston 24 one. The compressed gas remains through the seal 34 and the fitting of the cylinder piston 24 in the axial bore 32 in the cavity between the cylinder bottom 28 and the cylinder piston 24 locked in. The cylinder piston 24 is due to the action of the gas pressure in the direction of the axial bore 32 accelerates out of this and transfers so a force on the Abdrückschale 20a , wherein a reaction force directed counter to this force via the end face 26 and the cylinder bottom 28 on the ejection tray 20b is transmitted.

The two at the subregions of the inner surface 18a and 18b arranged ejection cups 20a respectively. 20b direct the force and the reaction force into the hood wall 6 a, whereby this undergoes a mechanical stress. Because the division between the ejection cups 20a . 20b perpendicular to the alignment of the axial bore 32 and parallel to the course of the predetermined breaking geometry 12 runs, the hood wall 6 perpendicular to the course of predetermined breaking geometry 12 stretched, so that the predetermined breaking geometry with the least possible force of the force element 8th stressed as much as possible - here mainly claimed to train in the circumferential direction - is.

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

Hereby experiences the hood wall 6 in the area of the predetermined breaking geometry 12 due to the groove-shaped weakening by the predetermined breaking geometry 12 the biggest strain. In the further course of time, this stress reaches or exceeds the resistance of the material of the hood wall 6 so that these along the predetermined breaking geometry 12 destructively dissected, so broken and / or torn open.

2 shows a schematic representation of a missile 56 with a sensor head 58 and the trunk hood 2 out 1 , The trunk hood 2 is in a longitudinal section depicting and with her rear end 16 at the bow of the sensor head 58 that is the fuselage bow 64 of the missile 56 arranged. The trunk hood 2 is at her rear area 60 by means of a on the hood wall 6 circumferentially arranged adhesive layer 62 on the fuselage bow 64 of the missile 56 bonded.

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 a dome-shaped radiation-transmissive window or an optical lens.

The missile 56 has wings 68 for controlling the trajectory of the missile 56 on. The wings 68 generate aerodynamic lift during the flight. The missile 56 is designed as Rohrverschussmunition, for example as artillery shell. At the start of the missile 56 this is fired from a tube and experiences here a large launch acceleration in the range between 10,000 g and 30,000 g.

The longitudinal acceleration of the missile during launch 56 or the trunk hood 2 leads to an inertial force of the hull hood 2 partially over the adhesive layer 62 from the hood wall 6 discharged and into the sensor head 58 is initiated. In order not to stress the hood wall too much during this process and an undesirable breakage of the fuselage hood 2 In addition, counteracting a launch, the inertial force is partially over the support surface 48 of the circulating Bund 46 on the opposite surface 50 the ejection cups 20 transmitted and continue on the ejection cups 20 on the sensor head 58 transfer. In this way, a radial overstretching of the rear end 16 the hood wall 6 be avoided.

Before a flight of the missile 56 During the take-off phase and during a first part of the flight, the Dom 66 through the hull bonnet 2 covered. In particular, during the flight, the cathedral 66 or the sensor head 58 so at least temporarily protected against harmful influences, such as particle impact or frictional heat.

After the launch of the missile 56 and during flight with an axially directed direction of flight 70 will break off the hull hood 2 from the sensor head arranged on the bow side 58 of the missile 56 at a given time the force element 8th through the ignition device 54 controlled and so the pyrotechnic propellant 22 ignited. As a result the hood wall becomes 6 in the above according to 1 described way destructively parts. In the present embodiment, the hood wall 6 plastic forming 42 a refractory plastic which is at least predominantly brittle up to a temperature of 250 ° C., more precisely a polyamideimide. This ensures that the hull bonnet 2 even after a strong heating of the hood wall 6 brittle due to a flight-conditioned air friction instead of deforming ductile, so that the hood wall 6 Reliable along the predetermined breaking geometry 12 parts and the hull hood 2 is blown off.

By the destructive fragmentation of the hood wall 6 this dissolves from inside parts of the fuselage hood 2 and becomes relative to the sensor head 58 against the direction of flight 70 and moved radially away from it. In the absence of the supporting structure of the dome wall 6 become interior parts of the hull hood 2 , in particular the force element 8th , the ejection cups 20 and the igniter 54 , moved away from the missile, so that the dome 66 of the sensor head 58 is exposed.

By the preferably sudden force development of the force element 8th becomes the hull hood 2 blown up so that fragments of the hood wall 6 and other parts and / or fractions of the hull bonnet 2 radially from the missile 56 be thrown away. Eventual through the adhesive layer 62 on the fuselage bow 64 remaining parts of the trunk hood 2 are not important because they are behind the cathedral 66 lie. By breaking off the fragments, parts and / or fractions are thrown so far that a deterioration in particular of the wings 68 of the missile 56 counteracted.

3 shows a schematic longitudinal sectional view of a sensor head housing 82a one another sensor head 58a and one with the sensor head 58a connected hull hood 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 trunk hood 2a has a rear trained thread 72 on. In the by 3 reproduced embodiment is the thread 72 as internal thread in the hood wall 6a introduced and has a diameter of about 9/10 of the maximum diameter of the hull cap 2a on. The trunk hood 2a is about the thread 72 detachable with the sensor head 58a connected. For this purpose, the sensor head 58a on the bow side a corresponding thread 74 on. For mounting the fuselage hood 2a on the sensor head 58a becomes the hull hood 2a via a rotational relative movement to the sensor head 58a around the longitudinal axis 38a screwed with this.

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

For mounting the fuselage hood 2 B on the sensor head 58b becomes the hull hood 2 B via a rotary movement of the threaded sleeve 76 around the longitudinal axis 38b with the sensor head 58b and the hood wall 6b screwed. A rotational relative movement between the hull bonnet 2 B and the sensor head 58b is not absolutely necessary for screwing and can thus be avoided, so that damage to cable connections inside the fuselage hood 2 B 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

QUOTES INCLUDE IN THE DESCRIPTION

This list of the documents listed by the applicant has been generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Cited patent literature

• DE 102010007064 A1 [0004]

Claims (15)

Hull hood ( 2 ) for a missile ( 56 ), with an outer surface ( 4 ), one the outer surface ( 4 ) forming hood wall ( 6 ) and a force element ( 8th ), characterized in that the hood wall ( 6 ) a predetermined breaking geometry ( 12 ) and the force element ( 8th ) to a destructive division of the hood wall ( 6 ) according to the predetermined breaking geometry ( 12 ) is prepared. Hull hood ( 2 ) according to claim 1, characterized in that the hood wall forms at least the major part of the outer surface and is monolithic. Hull hood ( 2 ) according to claim 1 or 2, characterized in that the predetermined breaking geometry ( 12 ) at least over half the axial length L of the hood wall ( 6 ) is formed away. Hull hood ( 2 ) according to one of the preceding claims, characterized in that the predetermined breaking geometry ( 12 ) longitudinal ( 10 ) of the hood wall ( 6 ) runs. Hull hood ( 2 ) according to one of the preceding claims, characterized in that the force element ( 8th ) a pyrotechnic propellant ( 22 ), a cylinder piston ( 24 ) and one on a front side ( 26 ) with a cylinder bottom ( 28 ) closed hollow cylinder ( 30 ) with an axial bore ( 32 ), wherein the cylinder piston ( 24 ) axially displaceable in the axial bore ( 32 ) is arranged and the pyrotechnic propellant ( 22 ) between the cylinder piston ( 24 ) and the cylinder bottom ( 28 ) and for accelerating the cylinder piston ( 24 ) along the axial bore ( 32 ) is prepared. Hull hood ( 2 ) according to one of the preceding claims, characterized in that the force element ( 8th ) of a number of on the inner surface ( 18 ) of the hood wall ( 6 ) arranged ejection cups ( 20 ) is encompassed, wherein in each case a Abdrückschale ( 20a . 20b ) in each case at least partially by the predetermined breaking geometry ( 12 ) bounded portion of the inner surface ( 18a . 18b ) of the hood wall ( 6 ) and for separating the respective subarea ( 18a . 18b ) from the other subarea ( 18a . 18b ) is prepared. Hull hood ( 2 ) according to one of the preceding claims, characterized in that the hood wall ( 6 ) at least predominantly of a plastic ( 42 ) consists. Hull hood ( 2 ) according to claim 7, characterized in that the plastic ( 42 ) is up to a temperature of 250 ° C under mechanical overstress at least predominantly brittle refractive plastic. Hull hood ( 2 ) according to one of the preceding claims, characterized in that the outer surface ( 4 ) of the hood wall ( 6 ) a metal-containing coating ( 40 ) having. Hull hood ( 2 ) according to one of the preceding claims, characterized in that the hood wall ( 6 ) on its inside ( 44 ) a circumferential in its circumferential direction collar ( 46 ) with a support surface ( 48 ) for resting on a counter surface ( 50 ), wherein the normal vectors of the support surface ( 48 ) parallel to the longitudinal axis ( 38 ) of the fuselage hood or describe a rear-widening surface. Hull hood ( 2a . 2 B ) according to one of the preceding claims, characterized by a rear side circumferentially formed thread ( 72 . 74 . 74a . 78 . 78a . 80 ) for connection to the fuselage bow ( 64 ) of a missile ( 56 ). Hull hood ( 2 B ) according to one of the preceding claims, characterized by a rear side arranged threaded sleeve ( 76 ) with a bow-shaped external thread ( 78 ) for connection to the hood wall ( 6b ) and a rear-side formed internal thread ( 80 ) with one to the external thread ( 78 ) opposite threading direction for connection to the fuselage nose ( 64 ) of a missile ( 56 ). Pipe ammunition with a hull cap ( 2 ) according to one of the preceding claims, characterized in that the hull bonnet ( 2 ) at the rear ( 60 ) by means of a on the hood wall ( 6 ) circumferentially arranged adhesive layer ( 62 ) on the fuselage bow ( 64 ) of the tubular ammunition is glued. Method for breaking off a trunk hood ( 2 ) from a sensor head arranged on the bow ( 58 ) of a missile ( 56 ) in which, a force element ( 8th ) and this at least indirectly on a the outer surface ( 4 ) of the trunk hood ( 2 ) forming hood wall ( 6 ), a predetermined breaking geometry ( 12 ) of the hood wall ( 6 ) fails as a result of this action fracture mechanics, wherein the hood wall ( 6 ) and the hull bonnet ( 2 ) from the sensor head ( 58 ) of the missile ( 56 ) is blasted off. Method according to claim 14, characterized in that the force element ( 8th ) a pyrotechnic propellant ( 22 ), which is ignited for triggering and generates a gas pressure, the gas pressure on a in an axial bore ( 32 ) of a hollow cylinder ( 30 ) fitted cylinder pistons ( 24 ) acts and this from the axial bore ( 32 ), wherein the gas under gas pressure through the cylinder piston ( 24 ) sealed in the hollow cylinder ( 30 ) remains included.

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