EP1739384A1 - Throwable nose hull as well as flying body with throwable nose hull - Google Patents

Abstract

Ejectable nose cone for a missile comprises longitudinal segments (15, 16) held together by a releasable mechanism that actively moves the segments apart when released. An independent claim is also included for a missile with an ejectable nose cone as above.

Description

The invention relates to a detachable front hood for a missile, which is divided longitudinally into at least two parts, and which is held together by releasable connecting means. The invention further relates to a missile with such a disposable front hood.

Ejectable hoods are used in missiles, for example, to protect the sensitive viewfinder optics, in particular the radransparent dome, during a flight to the site from external influences such as particle impact or heat. Attachment hoods generally obstruct the view of the sensitive viewfinder system and can therefore only be used in relatively predetermined flight phases or in flight phases in which the missile is not guided through the viewfinder system to the destination. If the missile is to be guided through the viewfinder system to the target, the front hood must be discarded, so that unimpeded target detection is possible.

Abwerfbare Vorsatzhauben are for example from the CH 525 798 , of the DE 102 11 493 B3 and the DE 196 35 851 C2 known. In the CH 525 798 is a Vorsatzhaube described, which consists of a prestressed material, in particular toughened glass. For ejection, a mechanism of action in the missile is actuated pyrotechnically, so that a tip strikes the edge of the intent hood. This shatters the front hood in a variety of small particles.

From the DE 196 35 851 C2 a detachable front hood is known, which is mounted on arranged in grooves radially inwardly resilient retaining members on the missile. To throw off these holding members are deflected by means of unlocking cylinder to the outside and thus out of engagement with the missile.

The unlocking cylinders can be operated with an ignitable gas generator, with a gas spring or pyrotechnic.

By the DE 102 11 493 B3 discloses a drop-front hood for a missile, which is held by a hinge joint and a tear-off attachment to the missile. To throw off an explosive device is ignited, whereby the tear-off fastening is torn open and the front hood pivots about the axis of movement of the hinge joint. Upon reaching a defined swivel angle, the front hood separates automatically from the missile.

An attachment hood and a missile of the type mentioned are from the DE 102 40 040 A1 known. There it is proposed to carry out the front hood at least two parts in the longitudinal direction, wherein the two parts are held together by releasable connecting means. If the connecting means are actuated or released, then the at least two parts open as a result of the back pressure inside the front hood in the manner of a "beak" to the outside and are thereby torn from its anchorage to the missile. To generate the dynamic pressure within the front hood this can be provided at the top with an opening.

According to the CH 525 798 must be introduced into the missile to release the hood required working mechanism. This is disadvantageous for the retrofitting of an existing missile. The in the DE 196 35 851 C2 and the DE 102 11 493 B3 described Abspreiz- or pivoting mechanisms for integrally ejecting the front hood disadvantageously do not prevent the risk of a collision of the discarded front hood with the missile. Finally, in the manner of a "beak" opening intent hood according to the DE 102 40 040 A1 disadvantageously then not be discarded when the back pressure required for opening is not achievable, for example, during a slow flight phase.

The object of the invention is to provide a detachable front hood for a missile, which is easy to retrofit and easily separable from this in each flight phase of the missile. It is another object of the invention to provide a missile with such a planned intent hood, missile and hood are easily separable from each other in each flight phase.

The former object is achieved according to the invention for a detachable hood for a missile, which is longitudinally divided into at least two parts, and which is held together by releasable connecting means, that the connecting means for actively moving apart of the at least two parts are formed when triggered.

In a first step, the invention is based on the consideration that a longitudinally split front hood is easier to eject than a one-piece or cross-split front hood. As a result of the longitudinal division, namely, the individual parts of the attachment hood can be guided past the missile laterally. For this, the individual parts need only be moved apart.

In a further step, the invention is based on the consideration that a safe and simple ejection of the parts of a longitudinally split front hood is achieved when the moving apart of the individual parts can be done independently of the respective flight phase of the missile. This is the case when the connecting means which hold together the parts of the longitudinally split front hood are designed to actively disengage the individual parts when triggered.

In other words, the invention provides that the individual parts of a longitudinally split front hood when dissolving the cohesive connecting means are actively moved apart by this. As a result of the longitudinal division of the individual parts of the attachment hood are pressed radially outward with respect to the missile longitudinal axis. The individual parts of the attachment hood are guided past the missile laterally.

If a missile does not execute a rolling motion, a missile split into two parts can be mounted on the missile so that its joint gap is vertically aligned during flight of the missile. This offers the advantage that during a dropping the two parts of the front hood are always passed laterally on the missile during a sinking or climb flight. The risk of a collision of a missile in the climb or descent with an up or down discarded part of an intent hood does not exist. By a substantially vertical alignment of the joint gap, the effective angle of attack of the parts of the hood, which depends on the angle of incidence of the missile to the flow, minimized. This requires a minimization of the risk of collision of parts of the front hood with the missile.

Since the releasable connection means are arranged in the front hood, a simple retrofitting of existing missiles with such a front hood is possible. As a result of the active moving apart of the parts of the front hood these can be safely dropped both at low and at high airspeed of the missile. The triggering of the parts holding together the connecting means can be activated at any time on the existing electronics in the missile time. Also, a remote release is possible.

As material for the front hood, a metal or a plastic can be used. As a metal is particularly suitable steel. The plastic may optionally be reinforced or jacketed with carbon or glass fibers.

In principle, a wide variety of techniques can be used to actively move apart the at least two parts of the front hood. In particular, a gas spring, an explosive device or a gas generator can be used. It is also conceivable to keep parts of the front hood mechanically prestressed, so that when the connecting means are triggered, the stored mechanical energy is converted into kinetic energy of the diverging parts.

Advantageously, the connecting means comprise a pyrotechnically activatable connecting pin having a bore, in which a propellant charge is used, wherein upon ignition of the propellant, the at least two parts driving apart, gases are released. The high energy releasing propellant within a short time is integrated directly into the connecting pin that holds the parts of the front hood together. The spontaneously released at ignition of the propellant gases are used to divide the parts of the front hood. The integration of the propellant charge in the connecting pin allows the tripping speed to be adapted to the external parameters predetermined by the missile or by the conditions of use. This can be done for example by the choice of material of the connecting pin or by the composition of the propellant.

In an advantageous embodiment of the invention, the at least two parts of the cap are held together by means of the connecting pin axially into one another, forming an inner cavity hollow cylinder, wherein the bore of the connecting pin has an opening to the inner cavity through which the released at ignition of the propellant gases, the Driven hollow cylinder axially apart, flow into the inner cavity. In other words, the at least two parts are inserted into one another via hollow cylinders in the manner of a piston. The gases flowing through the opening into the internal cavity when the propellant is ignited push the two hollow cylinders apart, as a result of which the parts of the ancillary hood are moved apart. The connecting pin ruptures in this disassembly movement in half. About the design or number of introduced openings as well as the shape and size of the inner cavity, the moving apart of the parts of the front hood can be adjusted according to the conditions of use and for an existing type of missile. In the case of a vertical alignment of the joint gap, an axial movement apart of the hollow cylinders means that they drift apart in the transverse direction of the missile longitudinal axis.

In a further advantageous embodiment, the at least two parts are held together directly by means of the connecting pin, wherein the bore extends in the longitudinal direction and in addition to the propellant has a fitted piston, and wherein the piston is driven by ignition of the propellant charge in the longitudinal direction. In this embodiment, the connecting pin which holds the two parts together directly generates an impulse directed outwards or in the longitudinal direction of the connecting pin, whereby the parts of the front cover are moved apart. When the propellant charge of the longitudinally aligned bore is ignited, the gases propel the piston fitted in this bore longitudinally, as a result of which the connecting pin tears apart. The two parts of the connecting pin then have an opposite pulse. In this embodiment, the parts of the front hood need only be designed so that they can be connected to one another via the connecting pin. This can be done, for example, that the parts each have openings mounted in a web, and are held together via these openings by means of the connecting pin formed as a screw or rivet. This technique also allows easy installation of the front hood on the missile.

Advantageously, the connecting pin has a predetermined breaking point. About the predetermined breaking point is ensured that the connecting pin tearing at ignition of the propellant charge at a predetermined location. In the case of the coupling pin provided with a fitted piston, it is advisable to attach the predetermined breaking point essentially transversely to the longitudinal direction of the connecting pin, so that the momentum of the piston driven forward in the longitudinal direction by ignition of the propellant acts on the predetermined breaking point.

In a further advantageous embodiment, the front hood is conical, ogiven or paraboloid. Other aerodynamic shapes of the front hood, which have, for example, a comparison with the hemisphere shape better aerodynamics, are conceivable. These forms have a favorable aerodynamics and thus help to reduce the aerodynamic drag of the missile. For missiles, which have a hemispherical dome due to a necessary large observation angle, such an aerodynamically favorable designed intent hood allows to improve the range. The front hood thus serves as an aerodynamic fairing and reduces the aerodynamic drag of the basic configuration of the missile without Vorsatzhaube. Even in the event that an air-to-air missile with respect to the aerodynamic non-optimized dome shape is to be launched from the ground, an aerodynamically designed intent hood forms the possibility of the shot from an aircraft range also launched from the ground to reach.

For dropping the front hood, it is advantageous if this end is connectable by means of a convex groove with the missile. If the pulse for actively moving apart of the parts of the front hood is transmitted in the front region of the hood, this embodiment allows the parts of the front hood to tilt over this convex groove radially from the missile.

In order to secure the hood securely to the missile, it is advantageous if, for bracing with the missile on the inner circumference of the intent hood a kinking groove for guiding a arranged on the missile pin is introduced. In this case, it is particularly favorable if, with respect to the circumference of the hood, two such grooves offset by 180 ° are introduced, in which the corresponding pins protruding from the structure of the missile are guided along. By simply turning the front hood In this case, an additional mounting option can be created relative to the missile. The kinking groove and the pen arranged on the missile thus form a so-called "bayonet lock".

In the case of the combination of an end-mounted convex groove with the intended for receiving a protruding from the structure of the missile pin kinking groove, the hood can be mounted on the missile or dismantled by first axially on a arranged on the circumference of the missile collar is postponed. In this case, the end-side convex groove of the attachment hood engages with a collar-oriented, forwardly directed concave groove. At the same time, the pin or pins attached to the missile engage in the corresponding kinked grooves of the hood which are attached to the inner circumference. By a slight rotation of the front hood this is then clamped between the pins and the collar on the missile. The circumferential collar also fulfills an axial support function during acceleration of the missile.

The second-mentioned object with regard to a missile is achieved in that according to the invention the missile has a detachable front hood as described above.

Advantageously, in this case, as described, the front hood engages in the end in a circumferentially extending raised collar on the missile. It has been shown in particular that it is sufficient for fastening the front hood and also for dropping their parts when the raised collar is partially interrupted in the circumferential direction. The interruption can also be designed generously.

Fig. 1

in einer perspektivischen Darstellung eine in zwei Hälften längsgeteilte Vorsatzhaube,

Fig. 2

in einem Schnitt eine Vorsatzhaube gemäß Fig. 1 mit Blick auf einen die beiden Hälften zusammenhaltenden Verbindungsstift,

Fig. 3

einen vergrößerten Ausschnitt aus Fig. 2,

Fig. 4

in perspektivischer Darstellung die Innenwandung einer der beiden Hälften der in Fig. 1 gezeigten Vorsatzhaube,

Fig. 5

in perspektivischer Darstellung die Spitze eines zur Aufnahme der Vorsatzhaube vorbereiteten Flugkörpers,

Fig. 6

in einem Schnitt eine Vorsatzhaube gemäß Fig. 1, wobei die Verbindung der beiden Hälften in Form von ineinander steckbaren Hohlzylindern ausgebildet ist und

Fig. 7

einen vergrößerten Ausschnitt aus Fig. 6.

Embodiments of the invention are explained in more detail in a drawing. Showing:

Fig. 1

in a perspective view, a longitudinally split in two halves Vorsatzhaube,

Fig. 2

1 is a view of a connecting pin holding the two halves together,

Fig. 3

an enlarged detail of Fig. 2,

Fig. 4

3 is a perspective view of the inner wall of one of the two halves of the front hood shown in FIG. 1;

Fig. 5

in a perspective view, the tip of a prepared for receiving the front hood missile,

Fig. 6

in a section an attachment hood according to FIG. 1, wherein the connection of the two halves is designed in the form of plug-in hollow cylinders and

Fig. 7

an enlarged detail of Fig. 6.

Fig. 1 shows a perspective view of a two-part split in the longitudinal direction ejectable front hood 10 for a missile. The front hood 10 extends from a tip 12 to one end 13. Clearly visible are the two parts 15, 16, which are set over a running in the longitudinal direction of the attachment hood 10 joint gap 18 together. The front hood 10 has two covers 20 circumferentially partially revolving, which are removable in order to mount the two parts 15, 16 together.

Fig. 2 shows in a section corresponding to FIG. 1 trained attachment hood 10. There are the two parts 15, 16 and the longitudinally extending joint gap 18 can be seen. Also provided for connecting the two parts 15, 16 webs 22, 23 are clearly visible. About a respectively mounted in the web 22 and 23 bore the two halves 15, 16 are held together by means of a connecting pin 25. The connecting pin 25 is designed for this purpose as a screw with a screw head 26 and a thread 27. By means of a thread 27 patch nut 28, the two parts 15, 16 of the cap 10 can be easily connected to each other with a suitable tool. Next, the part 15 is connected to the impulse transmission upon release of the connecting pin 25 via a bolted by means of the external thread 71 end piece 29 fixed to the connecting pin 25. In the part 16 of the screw head 26 is also screwed by means of an external thread 70. The connection pin 25 can also be designed as a connecting pin.

The two parts 15, 16 of the attachment hood 10 as shown in FIG. 2 cohesive connecting pin 25 is shown in detail Fig. 3 can be removed. The connecting pin 25 has the already recognizable in Fig. 2 screw head 26 and at the other end the thread 27 also shown in Fig. 2 on. Inside the connecting pin 25 is a longitudinal direction extending bore 30 introduced. In this bore, a piston 32 and a propellant 33 is introduced. Before the propellant 33 is located in the interior of the connecting pin 25, a squib 35, which is ignited via outgoing leads 36. In the middle of the connecting pin 25, a predetermined breaking point 38 is introduced in the form of a circumferential groove. If the propellant charge 33 is ignited by means of the squib 35, gases develop in an explosive manner in the bore 30, which drive the piston 32 forwards, away from the screw head 26. Due to the forward pulse of the piston 32 and caused by the recoil opposing pulse on the connecting pin 25 of the connecting pin at the predetermined breaking point 38 apart. Due to the forward pulse of the piston 32, which acts on the threaded portion 27 of the connecting pin 25, and the opposite recoil pulse acting on the provided with the screw head 26 portion of the connecting pin 25, both connecting parts are driven apart in the opposite direction. This impulse is transferred to the parts 15, 16 of the attachment hood 10 according to FIG. 2 held together with this connection pin 25. For attachment, the termination piece 29 is connected to the external thread 71 and the screw head 26 is connected to the external thread 70 with the parts 15 and 16 ,

Fig. 4 again shows a perspective view of the inside of a portion 15 of the longitudinally split hood 10 as shown in FIG. 1 or 2. Clearly, the web 22 can be seen, through which the part 15 with the other part 16 of the attachment hood 10 is connectable. For this purpose, a bore 38 is introduced into the web 22. At the end, the part 15 has a circumferential convex groove 40, which is provided for engagement in a correspondingly mounted on the missile concave groove. Approximately in the circumferential center of the part 15, a kinking groove 42 is introduced on the inner circumference. This kinking groove 42 serves to guide a protruding from the contour of the missile. For mounting the front hood it is pushed axially, wherein the corresponding pin is initially guided in the axial direction along the groove 42. Subsequently, the front hood can be clamped in the manner of a bayonet lock by turning against the missile, in which case the corresponding pin 52 is guided in the part of the groove 42 bent in the circumferential direction of the part 15.

5 shows a perspective view of the tip 45 of a missile prepared for receiving a front hood 10 according to FIGS. 1 or 2. At the tip 45 of the missile is a hemispherical dome 47 of IR radiation permeable material arranged. Behind the dome 47 is a gimbaled IR seeker that scans a large solid angle area for target signatures. To accommodate the attachment hood 10, the tip 45 of the missile has a circumferential collar 49, at the end toward the dome forward a circumferential concave groove 50 is introduced. Furthermore, two protruding out of the contour of the missile pins 52 are mounted on the circumference of the tip 45 offset by 180 °, which engage in the bending groove 42 of the respective parts 15, 16 of the adapter hood 10 shown in FIG. 4. To protect the dome 47, a foam body can be inserted between this and the front hood.

Fig. 6 shows in a section again a corresponding to FIG. 1 trained intent hood 10. There are the two parts 15, 16 and the longitudinally extending joint gap 18 can be seen. The two parts 15 and 16 are connected to each other via plug-in hollow cylinder 54, 55 together. The hollow cylinders are held together by a connecting pin 60. For actively moving apart of the two parts 15 and 16, the two hollow cylinders form an inner cavity 57 in the interior, into which the released gases expand when the connecting pin 60 is triggered.

For this purpose, FIG. 7 shows the connection of the two halves 15, 16 via the plug-in hollow cylinders 54 and 55 in detail. In this case, a first hollow cylinder 54 of the part 15 engages in a second hollow cylinder 55 of the part 16. The hollow cylinders 54, 55 are movable into each other. The created by the nested hollow cylinder 54, 55 inner cavity 57 is clearly visible. The two parts 15, 16 of the front hood 10 are held together by a connecting pin 60, to which this has a thread 61. At the head end of the connecting pin 60, a connecting piece 62 is screwed into the part 16. In the inner cavity 57, the connecting pin 60 has a predetermined breaking point 63 in the form of a circumferential groove. Further, the connecting pin 60 shows two opening into the inner cavity 57 openings 64. In the interior of the connecting pin 60 has a bore 65 is introduced, which is completely filled with a propellant 66.

The propellant 66 can be ignited via a squib 62 introduced in the squib 62, to which the squib 67 has a contact 73 for transmitting an ignition pulse.

If the propellant charge 66 in the connecting pin 60 is ignited via the squib 67, the resulting gases escape via the two openings 64 into the internal hollow space 57. At the same time, the predetermined breaking point 63 ruptures. By further expansion in the inner cavity 57, the two hollow cylinders 54, 55 are moved apart. The two parts 15, 16 of the front hood are actively driven apart.

LIST OF REFERENCE NUMBERS

10

nosecone

12

top

13

The End

15, 16

parts

18

joining gap

20

covers

22, 23

web

25

connecting pin

26

screw head

27

thread

28

mother

30

drilling

32

piston

33

propellant

35

squib

36

leads

38

Breaking point

40

convex groove

42

kinking groove

45

Tip of the missile

47

cathedral

49

Federation

50

concave groove

52

pencils

54

first hollow cylinder

55

second hollow cylinder

57

internal cavity

60

connecting pin

61

thread

62

terminating piece

63

Breaking point

64

opening

65

drilling

66

propellant

67

squib

68

leads

Claims (11)

A throw-away hood (10) for a missile which is split longitudinally into at least two parts (15, 16) and which is held together by releasable connecting means,
characterized in that
the connection means are designed to actively move the at least two parts (15, 16) apart when triggered. A throw-away hood (10) according to claim 1,
characterized in that
the connecting means comprise a pyrotechnically activatable connecting pin (25, 60) with a bore (30, 65) into which a propellant charge (33, 66) is inserted, whereby upon ignition of the propellant charge (33, 66), the at least two parts (15 , 16) driving apart, gases are released. A throw-away hood (10) according to claim 2,
characterized in that
the at least two parts (15, 16) are held together by means of the connecting pin (25, 60) via hollow cylinders (54, 55) which can be plugged axially into one another and form an internal cavity (57), the bore of the connecting pin (60) having an opening (64). to the internal cavity (57) through which the gases released upon ignition of the propellant charge (66), the hollow cylinders (54, 55) driving axially apart, flow into the internal cavity (57). A throw-away hood (10) according to claim 2,
characterized in that
the at least two parts (15, 16) are held together directly by means of the connecting pin (25), the bore (30) extending longitudinally and in addition to the propellant (33) having a fitted piston (32), and the piston (32 ) Is driven by ignition of the propellant charge (33) in the longitudinal direction. A throw-away hood (10) according to any one of claims 2 to 4,
characterized in that
the connecting pin (25, 60) has a predetermined breaking point (63). A throw-away hood (10) according to any one of the preceding claims,
characterized in that
it is conical, ogiven or paraboloidal. A throw-away hood (10) according to any one of the preceding claims,
characterized in that
it can be connected at the end by means of a convex groove (40) with the missile. A throw-away hood (10) according to any one of the preceding claims,
characterized in that
for bracing with the missile on the inner circumference a kinking groove (42) for guiding a arranged on the missile pin (52) is introduced. Missile with a detachable front hood (10) according to one of the preceding claims. A missile according to claim 10,
characterized in that
the front hood (10) engages the end in a circumferentially extending raised collar (49). A missile according to claim 11,
characterized in that
the raised collar (49) is partially interrupted in the circumferential direction.

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