MISSILE

Description

[0001] The invention relates to a missile comprising a fuselage and at least one flow-guiding element arranged on the fuselage, in particular a fin, which is designed to stabilize the guided missile in a flight state.

[0002] Such missiles are generally known from the prior art. The described flow-guiding element arranged on the fuselage, which can also be referred to or considered as a fin, serves to stabilize the missile in flight, in particular for longitudinal stabilization. For this purpose, it is known that several such flow-guiding elements can be arranged, for example evenly distributed in the circumferential direction, on a section of the missile, for example its tail region, in order to achieve the desired stabilizing effect in flight. Since such flow-guiding elements protrude at a sweep angle from the lateral surface of the fuselage or protrude from the lateral surface in a wedge shape, the pack size in that section of the missile increases due to the flow-guiding elements arranged there.

[0003] If the missile is launched from a container, the internal dimensions of the container's compartment, in which the missile is housed for transport and launch, must be larger than those required for the rest of the missile. The use of the flow guide element or the arrangement of the flow guide element on the missile increases the missile's space requirements within the container, so such containers must also be dimensioned accordingly larger.

[0004] A foldable, self-deploying wing for a missile is known from document US 4 351 499 A. Document FR 2 647 892 A1 also discloses a deployable wing for a missile. EP 0 568 487 A1 describes a missile with an attachment folded onto the missile.

[0005] The invention is based on the object of providing an improved missile in which, in particular, stabilization in a flight state is ensured and a packing size is reduced.

[0006] The object is achieved by a missile having the features of claim 1. Advantageous embodiments are the subject of the subclaims.

[0007] As described, the invention relates to a missile, in particular a guided missile, comprising a fuselage and at least one flow-guiding element arranged on the fuselage, specifically a fin, which is designed to stabilize the missile in a flight state. The flight state may, in particular, relate to a state at a flight altitude of >35 km. A flight state can thus be understood as a movement of the missile in a virtually "airless" space. The flight state relates, in particular, to a movement of the missile in a supersonic or hypersonic range. The flight state may further relate to a controlless flight phase in which passive stabilization is achieved by the at least one flow-guiding element.

[0008] The invention is based on the finding that the missile has an actuating device which is designed to transfer the at least one flow guiding element from a packed state, in which the at least one flow guiding element is arranged at a first sweep angle with respect to a lateral surface of the fuselage of the missile, in particular rests on the lateral surface, into the flight state, in which the at least one flow guiding element is arranged at a second sweep angle with respect to the lateral surface of the fuselage of the missile, in particular is erected with respect to the packed state.

[0009] The described actuating device thus enables the at least one flow guide element, in particular all of the flow guide elements or a plurality of flow guide elements, to be transferred between a packed state and a flight state. In the packed state, the at least one flow guide element can, in particular, assume a different sweep angle or the flow guide element can be arranged at a different sweep angle than in the flight state. The sweep angle is understood to be the angle between the transverse axis of the missile and an edge of the flow guide element protruding from the lateral surface. The flow guide element aligned or arranged at the sweep angle thus has a sweep edge whose tip touches the lateral surface, the sweep edge being aligned at the sweep angle relative to the transverse axis.Alternatively, the sweep angle can also be defined relative to the surface of the missile, or relative to the longitudinal axis or an axis parallel to it. The sweep angle essentially indicates the angle at which the flow guide element is positioned relative to the surface of the missile. If the sweep angle is specified relative to the transverse axis, it can be easily converted using the relationship between the transverse axis and the surface, particularly due to a perpendicular arrangement between the transverse axis and the surface.

[0010] Advantageously, the flow guide element can thus be in the packed state or transferred to the packed state for transport, or stored in the packed state for launch or transport in a suitable container. The container can be smaller than containers for missiles commonly used in the prior art, since the container does not need to provide space for the "erected" flow guide elements; instead, it is sufficient to design the space in the container for the packed state of the missile.

[0011] Only when the missile leaves the container can the sweep angle be changed, i.e. the at least one flow directing element can be raised from the packed state into the flight state. This is carried out by the described actuating device, which can transfer the at least one flow directing element from the packed state to the flight state. The actuating device moves at least one element of the missile so that the first sweep angle present in the packed state is transferred to the second sweep angle present in the flight state. The distance between the points along the edge of the flow directing element and the outer surface of the missile increases during the transfer from the packed state to the flight state. The sweep angle defined relative to the transverse axis decreases during the deployment movement from the packed state to the flight state.

[0012] In the flight state, the at least one flow-guiding element is deployed and thus effective for stabilizing the missile. Transitioning from the packed state to the flight state can therefore also be referred to or considered as "deploying," "unfolding," "unfolding," or "unfolding." The first sweep angle, which exists in the packed state, can be selected as small as possible to achieve the smallest possible pack size. In particular, the first sweep angle can be selected so that the at least one flow-guiding element rests optimally on the lateral surface of the fuselage. The first sweep angle can thus be selected in the range of 90° when defined relative to the transverse axis of the missile, or in a range of 0° when defined relative to the lateral surface.A defined deviation of the first sweep angle from the described range can also be selected, for example in a range of 0 to 10°, in particular 5°, in order to give the setup movement, ie the transition to the flight state, a preferred direction.

[0013] The missile is designed so that the at least one flow-guiding element has at least two skins that are pivotally connected to one another at a sweep edge. The "sweep edge" is understood to be the edge of the flow-guiding element that defines the sweep angle, i.e., the edge at which the flow-guiding element protrudes, in particular symmetrically, from the lateral surface of the missile. The skins can be understood, for example, as sheet metal elements that are pivotally connected to one another at the sweep edge. The sweep edge can also be understood as the center edge or fold of the flow-guiding element. When the flow-guiding element is transferred from the packed state to the flight state, i.e., when the first sweep angle is transferred to the second sweep angle, the two skins are pivoted toward one another along the lateral surface so that the sweep edge is positioned between them.The tip of the flow guide element, where the sweep edge touches the surface of the missile's fuselage, is fixed during the setup movement.

[0014] The ends of the planking elements opposite the tip are moved toward each other during the setup movement. The ends of the planking elements opposite the tip can essentially be moved along the outer surface of the fuselage. The remaining corner of the essentially triangular planking elements, which describes the end of the sweep edge opposite the tip, forms the highest point, i.e., the point of the flow control element furthest from the outer surface, especially in flight. The flow control element essentially describes a tetrahedron, a triangular shape, or a triangular pyramid.

[0015] Basically, the actuating device can be designed in any way to perform the deployment movement, i.e. the transfer of the at least one flow guiding element. The actuating device can have at least one corresponding mechanism to pivot the at least two panel elements towards each other so that the transfer of the first pitching angle into the second pitching angle can be carried out. According to one embodiment of the aircraft body, the at least two panel elements of the flow guiding element, in particular in a corner region, can be coupled to an actuating means, in particular a spindle or a cable pull or a rail. The actuating means can be correspondingly coupled to an actuator so that the actuator can generate an actuating movement which can be transmitted via the actuating means to the corner regions of the panel elements.

[0016] The "corner area" of the skinning elements is understood to be the corner area facing the lateral surface of the missile's fuselage and away from the tip of the flow guide element, i.e., facing the tail area of ​​the missile. When coupling the actuating means in this corner area, an articulated or pivoting bearing is advantageous so that no forced coupling occurs. For example, one actuator can drive two different spindles, which optionally have a left-hand thread or a right-hand thread, so that the generated rotational movement causes the skinning elements to move toward each other. Accordingly, a retraction of the cable or a movement along the rail can be generated to erect the skinning elements.

[0017] As described, the actuating device can comprise an actuator that can generate the actuating movement. The actuating device can comprise an actuator, in particular an electric motor, designed to transfer the skin elements from the packed state to the flying state, or a preloaded spring device designed to transfer the skin elements from the packed state to the flying state. As described, the actuator can generate the actuating movement, for example, in an embodiment as an electric motor. Likewise, the actuating device can comprise a preloaded spring that, when triggered, dissipates its spring energy and thereby raises the at least one flow guide element.

[0018] When triggered by the spring device, the flow guide element can also be described as "self-erecting," since it only requires one triggering, and the stored spring energy can then be automatically dissipated. In particular, the spring element of the spring device can be preloaded such that the planking elements are already preloaded against the inner wall of the container. When the missile leaves the container, automatic erection of the at least one flow guide element can be achieved. In contrast, a controlled movement can be carried out by the actuator, for example, by correspondingly controlling the electric motor. This allows the erection movement to be carried out only in a specific flight condition, for example, when a certain flight phase is reached. The at least two planking elements are, in particular, erected symmetrically.

[0019] According to a further embodiment of the missile, the described actuating device or at least a part of the described actuating device can be coupled to the fuselage of the missile by means of a linear guide and can be designed to execute a movement in the axial direction of the missile when the flow guide element is transferred from the packed state to the flight state. The linear guide can be designed, for example, as a slide track. During the deployment movement, the actuating device thus causes a combined movement, namely a pivoting movement of the planking elements towards one another, so that the at least one flow guide element is "put up", so that the sweep angle changes during the transition from the packed state to the flight state. Combined with this, the actuating device orat least one part of the actuating device, for example the actuator and / or the at least one actuating means, performs a linear movement along the longitudinal axis or parallel to the longitudinal axis of the missile, which can in particular be based on the linear guide.

[0020] The described missile can have a control device or be coupled to a control device that is designed to control the at least one actuating device, in particular depending on an operating state of the missile. By means of the control device, several flow guide elements can be transferred from the packed state to the flight state, for example, four flow guide elements arranged distributed in the circumferential direction of the missile's fuselage, which are controlled by four different actuators. The control device can output control signals to the actuators so that they are operated simultaneously, for example, to deploy the flow guide elements simultaneously.Advantageously, in the event of failure of one actuator, the remaining number of flow guide elements, for example two or three flow guide elements, can still be deployed, so that a reduced but possibly still sufficient longitudinal stabilization of the missile can be achieved.

[0021] According to a further embodiment of the missile, a locking device can be provided which is designed to lock the skinning elements when the flight condition is reached. The locking device enables locking to be effected when the skinning elements have been transferred to the flight condition, i.e. when the second sweep angle has been reached by the at least one flow guide element. Once the at least one flow guide element has been unpacked, i.e. transferred to the flight condition, the locking device can be used to ensure that the flight condition is maintained. Forces acting on the flow guide element in the flight condition can thus be introduced via the locking device, for example, into the fuselage of the missile and do not lead to the flow guide element being unintentionally (partially) folded in.

[0022] In other words, the locking device prevents the sweep angle from changing in the flight state or in a locking state caused by the locking device. The locking device can, for example, comprise positive-locking elements, spring elements, or locking elements. Likewise, the locking device can act via a spindle or a spindle drive. The locking device can, for example, be integrated into the actuating device.

[0023] According to one embodiment of the missile, the at least one flow-guiding element of the missile, in particular its skin elements, can define a cavity in which the at least one actuating device is arranged at least in part. The skin elements thus define the cavity, particularly in the direction of flight, resulting in a surface suitable for aerodynamics. Viewed from the nose of the missile, the skin elements enclose or delimit the cavity. The cavity can be open at the rear. The deployed flow-guiding element can, in particular, form a wedge fin.

[0024] In addition to the missile, the invention relates to a launching device for launching a missile, comprising at least one previously described missile accommodated in a receiving device, in particular a container. The container of the launching device can thus be smaller than conventionally used containers. The missile accommodated in the container can be transferred from the packed state to the flight state after leaving the container. The missile is thus in the packed state within the container. The missile, in particular the fuselage of the missile, and thus also the opening of the container or the receiving space of the container can be round or square. The launching device can in particular have a plurality of containers or a container with a plurality of receiving spaces and a plurality of missiles.

[0025] Furthermore, the invention relates to a method for operating a missile, in particular a missile as described above, comprising a fuselage and at least one flow-guiding element arranged on the fuselage, in particular a fin, which is designed to stabilize the missile in a flight state, wherein the at least one flow-guiding element is transferred from a packed state in which the at least one flow-guiding element is arranged at a first sweep angle with respect to a lateral surface of the fuselage of the missile, in particular rests on the lateral surface, to the flight state in which the at least one flow-guiding element is arranged at a second sweep angle with respect to a lateral surface of the fuselage of the missile, in particular is erected with respect to the packed state, wherein the at least one flow-guiding element has at least two planking elements which are pivotally connected to one another at a sweep edge.

[0026] According to the method, it is particularly provided that the at least one flow guide element is deployed after leaving the container. Deployment can occur directly upon leaving the container or based on an event or state of the missile, for example, the release of a booster stage or reaching a certain flight phase.

[0027] All advantages, details and features described with regard to the missile are fully applicable to the launch device and method.

[0028] The invention is explained below using an exemplary embodiment with reference to the figures. The figures are schematic representations and show: Fig. 1a schematic representation of a missile with several flow guide elements; Fig. 2a section of the missile from Fig. 1 in perspective view in a packed state; Fig. 3 the section of Fig. 2 in axial view; Fig. 4 a section of the missile from Fig. 1 in perspective view in a flight condition; and Fig. 5 the section of Fig. 4 in axial view.

[0029] Fig. 1 shows a missile 1, in particular a guided missile, in a schematic side view, which missile 1 has several flow guide elements 2, which are arranged, for example, in the circumferential direction on a fuselage 3 of the missile 1. The flow guide elements 2 are in Fig. 1 shown in a flight state of the missile 1.

[0030] In the flight state, the flow-guiding elements 2 are arranged at a (second) sweep angle 4. In this exemplary embodiment, the sweep angle 4 is defined relative to a transverse axis 5 of the missile 1. It is also possible, as represented by a sweep angle 6, for the sweep angle 6 to be defined relative to an axis parallel to the longitudinal axis 7 of the missile 1, for example, to a lateral surface 8 of the missile 1. Specifically, the sweep angle 4 in the exemplary embodiment shown is defined between the transverse axis 5 and a sweep edge 9 of the flow-guiding element 2.

[0031] In this embodiment, each flow guide element 2 has two planking elements 10, 10', which are pivotally connected to one another at the sweep edge 9. As will be explained below with reference to the Fig. 2-5 As described, the missile 1 has an actuating device 11 which is designed to move the flow guiding elements 2 between a packed state in which the flow guiding elements 2 are arranged at a first sweep angle 12, in the Fig. 1 , 4 , 5 to transfer the flight condition shown.

[0032] Fig. 2 , 3 show in solid representation ( Fig. 2 ) the packing state in which the sweep edge 9 is arranged under the first sweep angle 12, so that the planking elements 10, 10' lie as flat as possible on the lateral surface 8 of the hull 3. Fig. 2 also shows the flight condition in which the sweep edge is positioned at the second sweep angle 4. Fig. 2 , 3 further show an actuator 13 which is designed to move the flow guide element 2 from the Fig. 2 , 3 shown packing state into the flight state.

[0033] The actuator 13 is designed, for example, as an electric motor and is connected to a control device (not shown in detail), for example, a central control device of the missile 1. Assuming appropriate control signals from the control device, the actuator 13 is designed to raise or lower the flow guide element 2. For example, the actuator 13 is coupled to the planking elements 10, 10' via an actuating means 14, for example, two opposing spindles, for example, a first spindle with a right-hand thread and a second spindle with a left-hand thread. Other means, such as cables, rails, and the like, can alternatively be used as the actuating means 14.

[0034] By a corresponding movement of the actuator 13, it is thus possible to move the planking elements 10, 10' coupled to the actuating means 14, in particular to move corner regions 15, 15' of the planking elements 10, 10' towards each other along the lateral surface 8 of the fuselage 3. In this case, the sweep edge 9, at which the two planking elements 10, 10' are pivotably coupled to each other, is straightened and is thus actuated by the Fig. 2 , 3 shown first sweep angle 12 in the Fig. 1 , 4 , 5shown second sweep angle 4. In other words, the movement generated by the actuator 13 transfers the flow-guiding element 2 from the packed state to the flying state and thereby "erects" it. In addition to using the actuator 13 as an electric motor, it is also possible to use a preloaded spring device. In this case, the previously described movement is carried out by dissipating the spring energy, in particular, the two corner regions 15, 15' are moved toward each other, thereby changing the sweep angle of the sweep edge 9, i.e., the flow-guiding element 2 is erected.

[0035] How Fig. 2 , 4As can also be seen, a part of the actuating device 11, for example the actuator 13 and the actuating means 14, is coupled to the fuselage 3 of the missile 1 by means of a linear guide 16, which linear guide 16 is designed to carry out a movement in the axial direction when the flow guide element 2 is transferred from the packed state to the flight state, ie a movement parallel to the longitudinal axis 7.

[0036] For example, Fig. 4 , 5 As can be seen, during the erection movement or during the unfolding movement, the actuator 13 and the actuating means 14 or the actuating means 14 are moved in the axial direction towards the rear of the missile 1. The corner regions 15, 15' describe a circular segment or an arc segment on the lateral surface 8.

[0037] By selectively adopting the packed state or the flight state, packing dimensions can be saved in the packed state, since the flow guide elements 2 of the missile 1 can be "folded" or "tucked" onto the lateral surface 8 of the fuselage 3, so that a container of a launch device with a comparatively small storage space is sufficient for the missile 1. After the launch of the missile 1, in particular after leaving the container, Fig. 2 , 3 shown packing condition in the Fig. 1 , 4 , 5 shown flight state, namely by the actuating device 11 setting up the flow guide elements 2. Each of the flow guide elements 2 can be assigned an independent actuating device 11, for example an independent actuator 13 and independent actuating means 14.

[0038] In the receiving space of the container, it is also possible for the missile 1 to be in a pre-tensioned state, ie, the actuating device 11 has at least one pre-tensioned spring device that pre-tensions the planking elements 10, 10' against the inner wall of the receiving space of the container. When the missile 1 leaves the receiving space of the container, the planking elements 10, 10' are unfolded while dissipating the spring energy, ie, from the Fig. 2 , 3 shown state in the Fig. 1 , 4 , 5 shown flight condition.

[0039] The missile 1 can further comprise a locking device, particularly one integrated into the actuating device 11, which is designed to lock the assumed flight state or to assume a locking state in which the skin elements 10, 10' and thus also the sweep edge 9 are locked. Once the flight state is assumed, the flow-guiding elements 2 cannot be inadvertently folded in, as this is prevented by the locking device. In other words, the locking device blocks an inadvertent change of the second sweep angle 12 in the flight state, so that once the second sweep angle 12 has been assumed, it is maintained by the locking device. The locking device can be formed, for example, as a latching device, a spring device, a positive-locking element, or by a spindle used as an actuating means.

[0040] During the movement performed by the planking elements 10, 10', a tip 17 of the flow guide element 2 remains in its position. The planking elements 10, 10' are thus moved around the fixed tip 17, with the corner regions 15, 15' moving toward each other. The linear guide 16, together with a movable or articulated connection of the actuating means 14 to the corner regions 15, 15', prevents constraining forces.

[0041] The planking elements 10, 10', together with a part of the lateral surface 8 of the fuselage 3 of the missile 1, delimit a cavity 18. The cavity 18 can be open in the direction of the tail of the missile 1, but is closed by the planking elements 10, 10' in the direction of the tip 17 of the missile 1. Reference symbol

[0042] 1 Missile 2 Flow guide element 3 Fuselage 4 Sweep angle 5 Transverse axis 6 Sweep angle 7 Longitudinal axis 8 Shell surface 9 Sweep edge 10, 10' Planking element 11 Actuating device 12 Sweep angle 13 Actuator 14 Actuating means 15, 15' Corner area 16 Linear guide 17 Tip 18 Cavity

Claims

1. Missile (1), in particular a guided missile, comprising a body (3) and at least one flow-guiding element (2), in particular a fin, which is arranged on the body (3) and is configured for stabilizing the missile (1) in a flight state, wherein the missile (1) has at least one actuating device (11) which is configured to transfer the at least one flow-guiding element (2) from a packed state, in which the at least one flow-guiding element (2) is arranged at a first sweep angle (12) in relation to a lateral surface (8) of the body (3) of the missile (1), in particular rests on the lateral surface (8), into the flight state, in which the at least one flow-guiding element (2) is arranged at a second sweep angle (4, 6) in relation to the lateral surface (8) of the body (3) of the missile (1), in particular is set up in relation to the packed state, characterized in that the at least one flow-guiding element (2) has at least two panelling elements (10, 10') which are connected in a pivotable manner to one another at a sweep-angle edge (9).

2. Missile (1) according to Claim 1, characterized in that the at least two panelling elements (10, 10') are coupled, in particular in a corner region (15, 15'), to an actuating means (14), in particular a spindle or a cable pull or a rail.

3. Missile (1) according to Claim 1 or 2, characterized in that the actuating device (11) has an actuator (13), in particular an electric motor, configured, or has a preloaded spring device configured, to transfer the panelling elements (10, 10') from the packed state into the flight state.

4. Missile (1) according to one of the preceding claims, characterized in that the actuating device (11), by means of a linear guide (16), is coupled to the body (3) of the missile (1) and is configured for performing of a movement in the axial direction during the transfer of the flow-guiding element (2) from the packed state into the flight state.

5. Missile (1) according to one of the preceding claims, characterized by a control device which is configured to control the at least one actuating device (11), in particular according to an operating state of the missile (1).

6. Missile (1) according to one of the preceding claims, characterized by a locking device which is configured to lock the panelling elements (10, 10') when the flight state is reached.

7. Missile (1) according to one of the preceding claims, characterized in that the at least one flow-guiding element (2), in particular the panelling elements (10, 10'), delimit a cavity (18) in which is arranged at least sectionally the at least one actuating device (11).

8. Launching apparatus for launching a missile (1), comprising at least one missile (1) according to one of the preceding claims that is accommodated in a receptacle device, in particular a container.

9. Method for operating a missile (1), in particular a missile (1) according to one of Claims 1 to 7, comprising a body (3) and at least one flow-guiding element (2), in particular a fin, which is arranged on the body (3) and is configured for stabilizing the missile (1) in a flight state, wherein the at least one flow-guiding element (2) is transferred from a packed state, in which the at least one flow-guiding element (2) is arranged at a first sweep angle (12) in relation to a lateral surface (8) of the body (3) of the missile (1), in particular rests on the lateral surface (8), into the flight state, in which the at least one flow-guiding element (2) is arranged at a second sweep angle (4, 6) in relation to a lateral surface (8) of the body (3) of the missile (1), in particular is set up in relation to the packed state, characterized in that the at least one flow-guiding element (2) has at least two panelling elements (10, 10') which are connected in a pivotable manner to one another at a sweep-angle edge (9).