EP4111127A1

EP4111127A1 - Missile fin-folding device, missile, and method for operating a missile

Info

Publication number: EP4111127A1
Application number: EP21706569.7A
Authority: EP
Inventors: Josef Klevanski; Etienne Dumont; Waldemar Rotärmel; Ivaylo Petkov
Original assignee: Deutsches Zentrum fuer Luft und Raumfahrt eV
Current assignee: Deutsches Zentrum fuer Luft und Raumfahrt eV
Priority date: 2020-02-27
Filing date: 2021-02-18
Publication date: 2023-01-04
Also published as: WO2021170484A1; DE102020105188A1; DE102020105188B4

Abstract

The invention relates to a missile fin-folding device (7) comprising an actuation mechanism (37) for folding out and rotating a fin (1). The actuation mechanism (37) has two degrees of freedom which are independent of each other. In this manner, a pivoting movement (5) can be produced according to one degree of freedom, said pivoting movement being used to pivot the fin (1) outwards out of an operating position in which the fin rests against the missile, and a rotational movement (4) can be generated by means of which the attack angle of the fin (1) can be modified relative to an incoming flow.

Description

MISSILE FIN FLAP DEVICE, MISSILE AND PROCEDURE FOR

OPERATING A MISSILE

TECHNICAL FIELD OF THE INVENTION

During the flight of a missile, in particular a reusable missile or a so-called "launcher" that is returning to earth, different flight phases occur (in particular an ascent phase, a tilt-over maneuver phase, a ballistic phase, an aerodynamic descent phase, a Braking phase, an approach phase with an extension of landing elements and a landing phase), in which the missile must adopt different aerodynamic geometries in order to bring about the aerodynamic properties required for the respective flight phase. For this purpose, fold-out fins are used, which can be used to change the aerodynamic properties. The fold-out fins can be folded in during the ascent phase, the tilt-over maneuver phase and the ballistic phase and thus (at least largely) aerodynamically ineffective, while they can be unfolded during the aerodynamic descent phase, the braking phase, the approach phase and the landing phase can to bring about the desired aerodynamic influence. The fins can be designed, for example, as so-called grid fins or as flat fins (so-called “plain fins”). In the unfolded state, the influence of the fin (in addition to the geometry of the fin itself) on the flow conditions of the missile is dependent on an angle of attack of the fin with respect to the flow around the missile. For this background to the invention, reference is made to J. Klevanski, T. Ecker, J. Riehmer, B. Reimann, E. Dumont, C. Chavagnac: Aerodynamic

Studies in Preparation for CALLISTO-Reusable VTVL Launcher First Stage Demonstrator; 69th International Astronautical Congress (IAC), Bremen, Germany, 1. -5. October 2018; IAC-18-D2.6.3, pages 1 to 10. The fins serve to ensure and / or improve the stability of the missile and / or to control the same in atmospheric flight phases. The fins may be folded out in order to be able to bring the fin into effect only selectively in certain flight phases. On the other hand, it may be necessary to fold in the fins in order to minimize a negative effect of the unfolded fin on the aerodynamic properties of the missile (for example an undesired additional drag or a destabilizing effect) in the take-off phase. Folding in the fins may also be necessary to bring the missile into a spatially compact state with the fins folded in, which can be advantageous for storing and / or transporting the missile and / or for launching the missile from a launch canister or launch shaft .

The present invention relates to a missile-fin deployment device which enables a fin to be folded out. The invention also relates to a missile with such a missile-fin deployment device. Finally, the invention also relates to a method for operating a missile with a missile fin deployment device.

STATE OF THE ART

WO 2014/197046 A2 discloses a missile designed as a projectile, in which fins are arranged in the rear end region of the missile. The fins can be pivoted about an axis oriented parallel to the longitudinal axis of the missile. In the folded-in state, the fins are integrated into the surface of the missile in such a way that a longitudinal axis of the fin is oriented in the circumferential direction or tangential to the surface of the missile, while one is oriented parallel to the transverse axis of the fin in the longitudinal direction of the missile. In the unfolded state, the longitudinal axis of the fin extends radially or normal to the lateral surface of the missile and thus transversely to the longitudinal axis of the missile, while the transverse axis of the fin continues to be oriented parallel to the longitudinal axis of the missile. WO 2008/147453 A2 also discloses a pivoting of fins arranged in the rear end region of a missile designed as a projectile about pivot axes which are oriented parallel to the longitudinal axis of the missile. Alternatively, WO 2008/147453 A2 also proposes an embodiment in which the fins are arranged in radial shafts in the rear end region of the missile. In the folded-in position, the fins are initially held in the shafts by means of a holding device. The fins are in the radially outer one The end region is mounted so as to be pivotable about a pivot axis which is oriented tangentially to the circumferential direction of the missile. The holding effect of the holding device can be overcome by means of centrifugal forces exerted on the fins as a result of a rotation of the missile, whereby the fins can be folded out radially outward about the pivot axis from the shafts.

EP 2 433 084 B1 discloses a missile which, on the one hand, has fins serving for roll stabilization in the rear end area, which are received in radial slots and can be pivoted outward about a pivot axis that is oriented tangentially to the surface of the missile. In the pivoted-in state, the fins are spring-loaded in the direction of pivoting out, the fins initially being prevented from pivoting outwards by a lock. The locking mechanism is destroyed when the fins are swiveled out by the springs. In addition, the missile has centrally arranged pivotable wings which, in the pivoted-in state, are also received in radial slots of the missile and can be pivoted out about a pivot axis oriented transversely to the longitudinal axis of the missile. The wings are swiveled out when the missile in the form of a projectile emerges from the muzzle or after the highest point of the ballistic phase has been reached. A tail section of the missile with the foldable fins is rotatably connected to a front section of the missile with the wings via a coupling in the released state of the coupling. Depending on the actuation of the clutch, the roll-stabilizing effect of the fins can thus be activated or deactivated.

EP 1 627200 B1 also discloses a receptacle for pivotable fins in shafts of the missile which extend radially and in the longitudinal direction of the missile. Here, too, the fins are pivoted out about pivot axes which are oriented tangentially to the circumferential direction of the missile.

While the above-mentioned missile-fin unfolding devices have only provided a degree of swiveling freedom for unfolding the fins, EP 1 485668 B1 proposes to ensure that the fins can be unfolded by means of an actuating mechanism in which the degree of freedom of the fins for unfolding on the one hand a rotation and on the other hand, a pivoting of the fin are superimposed. In the folded state, the extends Fin with the longitudinal axis in the longitudinal direction of the missile and the transverse axis tangential to the circumferential direction of the missile. In contrast, when the fin is folded out, the longitudinal axis of the fin extends radially to the missile or normal to the surface of the missile, while the transverse axis of the fin extends parallel to the longitudinal axis of the missile. Via the degree of freedom of the fin, the dependency of the pivot angle of the fin and the angle of rotation of the fin during unfolding is clearly specified by a link guide. The movement along the degree of freedom is brought about by a pretensioned spring, this movement being supported during the unfolding also by the flow around the missile and the fin. Contrary to the action of the spring, the fin is held in the folded position by an unspecified locking mechanism.

US 2009/0126523 A1 discloses an extension mechanism for a control surface. The extension mechanism can be used in a robot, in a transport device, in power or power systems, in household applications etc. The extension mechanism can also be used for an aircraft, a satellite, a spacecraft or a space station, a Turbine, a water wheel, a propeller or a windmill. Furthermore, according to US 2009/0126523 A1, the extension mechanism can also be used for a projectile, which can be arranged in a launch barrel with the control surface retracted, while the control surface can be extended by the extension mechanism during flight operations in order to influence the trajectory of the projectile. By extending the control surface, the surface properties of the projectile can be modified for the purpose of influencing the trajectory of the projectile. The control surface can allow two alternative surface characteristics or a larger number of them. The extension mechanism is arranged in a transverse bore of a base body of the projectile. In order to be able to extend a control surface body forming the control surface transversely to the longitudinal axis of the projectile, the extension mechanism has an electric motor whose drive pinion can be rotated around the longitudinal axis of the projectile. For a translational movement of the control surface body out of the jacket surface of the projectile, the drive pinion meshes with a driven gear, the axis of rotation of which is oriented parallel to the longitudinal axis of the projectile. The output gear drives a shaft, the rotational movement of which is converted into a translational movement of the control surface body transversely to the longitudinal axis of the projectile. The motor with the drive pinion can be displaced relative to the output gear and a likewise driven by the motor drive bevel gear can engage in a Abtriebske gelrad, whose rotational movement about the translational movement axis of the Steuerflächenkör pers is transmitted to the control surface body. By means of this rotary movement, the end region of the control surface body protruding from the jacket surface of the projectile can be rotated, with the result that a changed flow can be brought about.

No. 6,726,147 B1 proposes a mechanism which enables both a change in the angle of attack of a thrust reversing vane and the extension of a fin to take place by means of a single actuator. For this purpose, the actuator drives a spindle which meshes with a spindle nut which is held by the end region of a crank. The crank is coupled to a holding body of the fin via a coupling. Furthermore, the crank is coupled via the coupling to a four-bar chain, which can be used to rotate the thrust reverser blade. The coupling has two drivers which are formed by a locking body Ver. The drivers are each ge leads in a T-shaped guide. The vertical leg of the T is oriented in the circumferential direction around the holding body and limited on one side by the crank and on the other side by a crank of the four-bar chain. The vertical leg of the T is oriented in the longitudinal direction of the holding body. One leg of the horizontal leg is formed by the crank and the other leg of the horizontal leg is formed by the crank of the four-bar chain. The locking body with the drivers is also acted upon by a pretensioned compression spring in the direction of its longitudinal axis. The locking body rests with an end face away from the pivot axis of the fin on the holding body on the fin. In a first adjustment range of the actuator, in which the driver moves in the area of the circumferentially oriented vertical leg of the T of the guide, no expansion of the spring is possible as a result of the guide, so that the fin cannot leave the folded position. In this first setting range of the actuator, the actuation of the actuator leads to a change in the angle of attack of the thrust reversing vane. If, however, the driver at the end of this adjustment area in the area of the horizontal leg of the guide, the compression spring can extend the locking body, so that the fin is folded out about its pivot axis. During this unfolding, the driver moves along a partial limb of the horizontal limb of the T-shaped guide. An actuation of the actuator that then takes place after the unfolding has been completed can be used to pivot the holding body with the fin about the longitudinal axis. OBJECT OF THE INVENTION

The invention is based on the object of proposing a missile-fin unfolding device which is improved in particular with regard to the aerodynamic effects that can be brought about, the actuation, the possibilities of influencing the aerodynamic effects that can be brought about and / or the reliable support of the fin in the unfolded state. Furthermore, the invention is based on the object of proposing a missile with a correspondingly improved missile-fin deployment device. Finally, the invention is based on the object of proposing an improved method for operating a missile with a missile-fin deployment device.

DESCRIPTION OF THE INVENTION

The invention proposes a missile-fin unfolding device which has an actuating mechanism by means of which a fin can be unfolded relative to a missile equipped with the missile-fin unfolding device and in this way can be brought into effect aerodynamically. This can be a fin of any type, in particular a flat fin or a lattice fin. According to the invention, the actuating mechanism has two degrees of freedom for unfolding the fin. These degrees of freedom are a degree of torsional freedom via which the fin can be rotated about its longitudinal axis, and a pivoting degree of freedom via which the fin can be pivoted about a transverse axis. According to the invention, the two degrees of freedom are independent of one another. This means, for example, that according to the invention there is no unambiguous assignment of the pivoting of the fin and the rotation of the same (and vice versa), as is done by the link guide according to EP 1 485 668 B1. According to the invention, it is thus possible, for example, that the fin assumes different pivot positions for the same rotation and / or assumes different rotational positions for the same pivot. The inventive equipment of the actuating mechanism with two independent degrees of freedom enables movements of the fin relative to the missile, which differ from the movements of the fin, which can be ensured by means of actuating mechanisms known from the prior art. Only a few examples that do not limit the invention are mentioned below: a) It is possible, for example, that the pivoting of the fin does not take place at the same time as the rotation of the same, but rather that the pivoting and the rotation are at least partially separated from one another in time. The fin is preferably first pivoted completely to pivot it out, while the fin can then be rotated immediately after the pivoting or also at a later point in time. b) While actuation mechanisms known from the prior art assume that the aerodynamic influence by the fin is only used in two operating positions, namely the least possible influence on the aerodynamics when the fin is folded in and the desired or maximum influence on the aerodynamic properties in unfolded position of the fin

(whereby deviating operating positions of the fin are only accepted during the unfolding of the fin), according to the invention the aerodynamic effect of the fin can also be influenced during flight operations by using at least one degree of freedom. For example, it is possible that, depending on the flight conditions and / or flight phase, an angle of attack of the fin is changed with respect to the flow, for example by rotating the fin in the swiveled-out state into different flow positions. Here, even the rotation can be used to control or regulate the flight characteristics. The missile-fin deployment device according to the invention has a missile-holding area, via which the missile-fin deployment device is held, in particular supported and / or stored, on the missile. Furthermore, the missile fin deployment device has the actuation mechanism. The fin is held on the missile holding area via the actuation mechanism. The actuation mechanism is used to rotate the fin on the one hand with respect to the missile holding area or the lateral surface of the missile about an axis of rotation and on the other hand to rotate the fin to pivot about a pivot axis relative to the missile holding area or the lateral surface of the missile. Thus, on the one hand, a pivoting degree of freedom and, on the other hand, a rotational degree of freedom are provided by means of the actuating mechanism, wherein the actuation along these two degrees of freedom can take place independently of one another. For this purpose, the actuating mechanism has the rotating mechanism on the one hand. By means of the rotation mechanism, the fin can be rotated about the axis of rotation with respect to the missile holding area. On the other hand, the actuating mechanism has the pivoting mechanism. By means of the pivoting mechanism, the fin can be pivoted about the pivot axis with respect to the missile holding area. The twisting mechanism and the pivoting mechanism can be actuated independently of one another, which takes place in particular by separate and independent control of a rotary actuator acting on the twisting mechanism and a pivoting actuator acting on the pivoting mechanism.

In principle, the twisting mechanism and the pivoting mechanism can be designed as desired and can be integrated into the missile-fin deployment device. For a proposal of the invention, the twisting mechanism and the pivoting mechanism are interposed with respect to the flow of force in a mechanical series connection between the fin and the missile holding area. The consequence of this is that the fin is supported on the missile holding area via the twisting mechanism and via this on the pivoting mechanism (or vice versa). Thus, with the pivoting of the pivoting mechanism, the rotation mechanism is also pivoted (or with the rotation of the rotation mechanism, the pivoting mechanism is also pivoted).

Any swivel mechanism can be used within the scope of the invention, for example swiveling via a conventional swivel bearing with a rotary swivel drive which brings about the swiveling and which can swivel one of the wasted parts directly or with the interposition of a gear stage. For a special embodiment of the missile-fin deployment device according to the invention, the pivoting mechanism has a link guide. The link guide can be used to convert any kind of movement of a swivel actuator into a swivel movement, the dependence of the movement of the swivel actuator and the pivoting being able to be specified by the contouring of the link guide. On the one hand, the use of the link guide is advantageous in terms of the possibilities for designing the swivel characteristics. On the other hand, it has been shown that over a Link guide, a very stiff support of the pivoting mechanism and thus the fin relative to the missile holding area can be achieved.

The pivoting mechanism can have an actuator which triggers and / or brings about the pivoting of the fin. The actuator is preferably a translational actuator, by means of which, for example, an actuating element (such as, for example, pushing and / or pulling element) is actuated, which ultimately brings about the pivoting of the pivoting mechanism. For example, the movement of the translational actuator can bring about a movement of the pivoting mechanism along the link guide. There are various possibilities for the design of the (possibly translatory) actuator, of which only two variants are mentioned below:

It is possible for the actuator to have a spring device with one or more springs of any design. The spring device is tensioned in the pivoted-in position of the fin. The tension of the spring represents an energy store. The energy of this energy store can then be used to generate the pivoting movement. In the pivoted-in position, the spring device can be latched or locked via a latching or locking device. The rest or

The locking device can be unlocked or unlocked. With the unlocking of the locking device or the unlatching of the latching device, the energy of the spring device is released, with which the spring device can pivot out the fin.

Delimbing or unlocking may require less energy than the energy required to swing the fin out. Thus, the spring device can be tensioned with the pivoting in of the fin manually or via a separate tensioning device before the missile is launched, and the missile only has to carry a small release device that requires little energy.

It is also possible, however, for the actuator to be a preferably electric drive which generates the translational movement of the actuating element or some other movement which then results in the pivoting mechanism being pivoted. It is possible within the scope of the invention that the pivoting mechanism has a pivot bearing body, with respect to which the fin can be pivoted. For example, the link guide between the fin and the pivot bearing body can be effective. In a pivoted-out position for this proposal of the invention, the fin is supported (with regard to pivoting about the pivot axis) on a support and / or holding device on the pivot bearing body. Preferably, this support and / or holding device only comes into effect when the pivoted-out position is reached and in this position in addition to other supports or articulations. The support and / or holding device can ensure a stiff and reliable support in the pivoted-out position in which the fin is exposed to considerable aerodynamic forces under certain circumstances. The support and / or holding device can be designed as a stop or contact surface. It is also possible that in the swiveled-out position the fin or a holding element of the same is drawn in between contact surfaces, in a holding recess, for example of a guide tube or a guide cone, with which a form-fitting support of the fin on the pivot bearing body can then be ensured.

It is possible for the swivel bearing body to be rotatable relative to the missile via a rotating mechanism. For a particular embodiment of the invention, the pivot bearing body has a holding recess into which the fin enters in the direction of actuation of the pivot actuator. The fin is then secured in the swiveled-out state in a form-fitting manner in the holding recess.

The holding recess and / or the fin preferably have tapering holding surfaces. If the movement of the fin into the holding recess occurs with the actuation of the swivel actuator, the tapering holding surfaces can result in tensioning between the holding surfaces or jamming between them. It is possible that a kind of self-locking occurs on the tapering holding surfaces (depending on the friction conditions and the angle of inclination of the tapering holding surfaces), which secures the fin in the holding recess and in the pivoted-out position.

For a missile-fin folding device according to the invention, the fin is held in the pivoted-in position (preferably exclusively) via the link guide and the articulation of the actuator, whereby the pivoted-in position is secured. In contrast, in the swiveled-out position, there is also the link guide and the articulation of the actuator, the support and / or holding device to the effect, which has the consequence that the support and / or holding device can at least partially relieve the link guide and / or the linkage of the actuator in order to reduce the forces that may be considerable during flight operations act on the Finn to support. An electronic control unit can be present in the missile fin deployment device. The electronic control unit can then have control logic which controls the pivoting mechanism and / or the twisting mechanism (in particular independently of one another). In this case, the control can consist in the control of a drive unit designed as an electric motor. If an actuator with a spring device is used, the control can also consist in unlocking a locking device, which then releases the energy store provided by the pretensioned spring device.

For a possible embodiment of the invention, the control logic controls the

Pivoting mechanism and the twisting mechanism in such a way that for an activation of the fin initially only the pivoting mechanism is actuated until the fin is pivoted out, so that the longitudinal axis of the fin extends radially to the missile. Subsequently, only the twisting mechanism is actuated to twist the fin. The rotation thus takes place separately in time and after the pivoting.

Alternatively or additionally, it is possible for the control logic to process operating parameters during flight operations. These operating parameters can relate to the flow conditions of the missile, the speed of the missile, the orientation of the missile in relation to the flow, the flight phase, the flight altitude and the like. On the basis of the operating variables, the control logic then controls the twisting mechanism during flight operations in such a way that the fin is rotated as a function of the operating variables. For example, the fin can assume a basic position with a predetermined angle of attack and, compared to this basic position, a control can take place by changing the angle of attack in order to bring about or restore desired aerodynamic conditions and to influence flight operations. It is possible, for example, that activation takes place in such a way that the fin is rotated by a maximum of plus / minus 20 degrees, a maximum of plus / minus 15 degrees or a maximum of plus / minus 10 degrees compared to a basic position, depending on the operating parameters. It is possible that a position of the fin, in particular the pivoted-in position of the pivoting mechanism of the fin and / or a pivoted-out position of the pivoting mechanism of the fin, can be secured by means of a latching or locking device. Here, a latching or locking device or a common latching or locking device can secure the pivoting position of the pivoting mechanism and / or the rotational position of the twisting mechanism. A locking device is preferably locked and / or unlocked via an actuator. The same can apply to a locking device. However, it is also possible for a latching device to be "overridden" by actuation of the associated actuator by sufficient actuator forces. The invention also proposes an embodiment of the missile-fin deployment device in which the pivot bearing body is rotatably mounted with respect to the missile. In this case, there is a torsion actuator by means of which the pivot bearing body (and with it the fin) can be rotated. In this case, a translationally actuated actuating element can extend through the pivot bearing body. The actuating element actuated in translation is driven by a pivot actuator, the pivot actuator preferably generating a translational drive movement. The actuating element can, for example, be designed as a pull-and-push rod, a kind of connecting rod or a pendulum support, one end area of the actuation element being articulated on the swivel actuator, while the other end area of the actuation element is articulated (directly or indirectly) on the fin can.

Another solution to the object on which the invention is based is a missile, in particular a missile, which is equipped with a missile-fin deployment device, as explained above. Preferably, multiple such missile-fin unfolding devices with assigned fins are used, the fins preferably being / are arranged in the area of an end face or nose, that is to say in the front end area of the missile during the ascent.

A further solution to the object on which the invention is based is a method for operating a missile. Here, in independent method steps, the fin is unfolded by actuating the pivoting mechanism and the fin is rotated by actuating the twisting mechanism. For a further refinement of this method, operating parameters are processed by means of control logic in flight operations. On the basis of the operating parameters (and their processing), the twisting mechanism is then activated during flight operations in such a way that the fin is twisted in relation to a basic position. This can influence the aerodynamic properties during flight operations.

Advantageous developments of the invention emerge from the claims, the description and the drawings. The advantages of features and of combinations of several features mentioned in the description are merely exemplary and can come into effect alternatively or cumulatively without the advantages necessarily having to be achieved by embodiments according to the invention.

With regard to the disclosure content - not the scope of protection - of the original application documents and the patent, the following applies: Further features can be found in the drawings - in particular the illustrated geometries and the relative dimensions of several components to one another and their relative arrangement and operative connection. The combination of features of different embodiments of the invention or features of different patent claims is also possible in a way deviating from the selected references of the patent claims and is hereby suggested. This also applies to features that are shown in separate drawings or mentioned in their description. These features can also be combined with features of different patent claims. Features listed in the claims may also be omitted for further embodiments of the invention, but this does not apply to the independent claims of the granted patent.

The number of features mentioned in the claims and the description are to be understood in such a way that precisely this number or a greater number than the specified number is present without the need for an explicit use of the adverb "at least". For example, when an element is mentioned, it is to be understood that there is exactly one element, two elements or more elements. These features can be supplemented by other features or be the only features that make up the product in question. The reference signs contained in the claims do not restrict the scope of the subject matter protected by the claims. They only serve the purpose of making the claims easier to understand.

BRIEF DESCRIPTION OF THE FIGURES In the following, the invention is further explained and described with reference to preferred embodiment examples shown in the figures.

Fig. 1 shows a fin of a missile in a three-dimensional representation.

2 shows a missile with a plurality of missile-fin unfolding devices and associated fins in a three-dimensional view obliquely from the front, the fins being in the folded-in state on the lateral surface of the missile.

FIG. 3 shows, also in a three-dimensional view, the missile according to FIG. 2, the fins here being pivoted out via a pivot mechanism.

4 shows, also in a three-dimensional view, the missile according to FIGS. 2 and 3, the fins here being rotated from the operating position according to FIG. 3 by rotating a rotating mechanism.

Fig. 5 shows a sectional view of a pivoting mechanism in the pivoted-in state.

FIG. 6 shows the pivoting mechanism according to FIG. 5 partially pivoted out

State. Fig. 7 shows the pivoting mechanism according to fig. 5 and 6 in the swiveled-out state.

Fig. 8 shows a missile fin deployment device with a twisting mechanism and a pivoting mechanism in a schematic representation. FIGURE DESCRIPTION

In the drawings and the present description of the figures, the same reference symbols are used in some cases for components which are identical or which correspond in terms of their geometry and / or function. In this case, the components are distinguished from one another by the additional letters a, b, ... These components are then partially referred to with or without the supplementary letter, which then means some of these components or all of these components.

1 shows a fin 1 which is designed here as a flat fin, but can definitely have any other contour or geometry and can also be designed as a grid fin. The fin 1 has a longitudinal axis 2 which, when the fin 1 is pivoted out on the missile, is oriented vertically to the lateral surface or radially to a longitudinal axis 9 of the missile. In addition, the fin 1 has a transverse axis 3. The longitudinal axis 2 and the transverse axis 3 define the main plane of extent of the fin 1. In the folded-out state of the fin 1, the transverse axis 3 can correspond to at least one flow component of the flow around the fin 1. In the context of the present description, a rotation of the fin 1 about the longitudinal axis 2 is described as rotation 4. The rotation 4 is preferably carried out for a state in which the fin 1 is completely swiveled out with respect to the missile 6, so that the rotation 4 then takes place about an axis of rotation 34 which is radial to a longitudinal axis 9 of the missile 6 or normal to the lateral surface of the missile 6 is oriented. A pivoting 5 is understood to mean a pivoting of the fin 1 about a pivot axis 33 which corresponds to the transverse axis 3 of the fin 1 (or an axis parallel thereto). The pivot axis 33 is preferably oriented tangentially to the lateral surface of the missile 6.

2 to 4 show a missile 6 with a plurality of missile-fin unfolding devices 7a, 7b, 7c, 7d with fins 1a, 1b, 1c, 1d. The missile fin deployment devices 7 are evenly distributed over the circumference of the missile 6 and are arranged with the same axial extension of the missile 6. The missile fin unfolding devices 7 are arranged in the front end region of the missile 6, which for the exemplary embodiment shown takes place immediately adjacent and behind a nose 8 of the missile 6. Fig. 2 shows the missile fin deployment device 7 in a folded position. In the folded-in position, the fins 1 are placed against the outer surface of the missile 6 or extend tangentially to this. It is possible that the fins 1 are at least partially integrated into corresponding recesses in the outer surface of the missile 6, whereby on the one hand the contouring of the outer surface of the missile 6 and on the other hand the shape of the fins 1 results in an aerodynamically favorable profile of the missile 6 with the missile-fin folding device 7 and the fins 1 can be brought about. In the folded position of the fins 1 according to FIG. 2, the longitudinal axes 2 of the fins 1 extend parallel to the longitudinal axis 9 of the missile 6, while the transverse axis 3 is oriented tangentially or in cross section along the lateral surface of the missile 6.

In the operating position of the missile-fin unfolding devices 7 according to FIG Longitudinal axis 9 of missile 6 extend. The position of the transverse axis 3 or pivot axis 33 has remained unchanged. In this pivoted-out position of the fins 1, the fins 1 are oriented (as far as possible) normal to the flow, so that considerable holding forces have to be applied in order to hold the fins 1 in this pivoted position.

The fins 1 are transferred from the operating position according to FIG. 3 by a rotation 4 about the axis of rotation 34 into the operating position according to FIG. 4, with which the unfolding has taken place. In this operating position, the longitudinal axis 2 of the fins 1 extends radially to the longitudinal axis 9 or normal to the outer surface of the missile 6 (as shown in FIG. 3) . In the unfolded, i.e. pivoted and rotated position of the fins 1 according to FIG. When the missile 6 is in operation, the angle of attack of the fin 1 with respect to the flow can be changed in the swiveled-out pivot position by means of a rotation 4 in the range of plus / minus 20 degrees, plus / minus 15 degrees, plus / minus 10 degrees or plus / minus 5 degrees , with which the aerodynamics of the missile 6 can be influenced.

In FIGS. 5 to 7, a pivoting mechanism 10 of the missile fin deployment device 7 is shown. The pivoting 5 can be brought about by means of the pivoting mechanism 10. In FIGS. 5 to 7, the pivoting mechanism 10 is shown in a section, which runs vertically to the main plane of extent of the fin 1, namely vertically to the transverse axis 3 and along the longitudinal axis 2.

The pivoting mechanism 10 has a pivot bearing body 12. The pivot bearing body 12 has a through recess 13 End of the fin 1 is hinged. The pivot bearing 15 has a pivot axis 11 which is oriented parallel to the transverse axis 3 and parallel to the pivot axis 33. The fin 1 carries a link element 17, which is designed here as a link bolt 18. The link bolt 18 extends parallel to the transverse axis 3. The link element 17 is received in a link 19 of the pivot bearing body 12, whereby a link guide 35 is formed. For the exemplary embodiment shown, the link 19 is designed as a curved elongated hole or curved slot of the pivot bearing body 12, the link 19 guiding the link element 17 on a quarter-circle path. The pivot bearing 15 and the link element 17 are arranged on the longitudinal axis 2 and spaced from one another. The gate 19 is oriented parallel to the longitudinal axis of the missile 6 in the end region in which the gate element 17 is in the pivoted-in state according to FIG. 5. On the other hand, in the pivoted-in state according to FIG. Between these end regions, the link 19 guides the link element 17 on a path corresponding to a quarter circle.

The articulation body 14 can be moved by means of an actuating element 37, in particular by means of a pull rod 20, which is actuated by a pivot actuator 21, radially to the longitudinal axis 9 or normal to the lateral surface of the missile 6 along the through recess 13, whereby the link element 17 is moved from the The end area according to FIG. 5 is moved via an intermediate position according to FIG. 6 into the other end area of the link 19 according to FIG. 7, which is accompanied by the pivoting of the fin 1. In the pivoted-out position according to FIG. 7, the link element 17 and the pivot bearing 15 are arranged on a common axis, which furthermore corresponds to the longitudinal axis 2 of the fin 1, this axis then is oriented normal to the lateral surface of the missile 6 or vertically to the longitudinal axis 9 of the missile 6.

The pivot axis 33, about which the fin 1 is pivoted, corresponds to the momentary pole of the fin 1, which is specified via the pivot bearing 15 and the link guide 35. The pivot axis 35 is thus displaced via the pivoting of the fin 1.

An optional special feature for the illustrated embodiment is the pivot position of the fin 1 in the pivoted-in state according to FIG. 5 exclusively through its articulation on the one hand via the link element 17 in the link 19 on the pivot bearing body 12 and - on the other hand, through the pivot bearing on the articulation body 14 and its support Preset via the actuating element 37 on the pivot actuator 21, which is fixed in terms of its position. The pivot position is fixed by the articulation at the two points mentioned, it being possible to change the pivot position by actuating the pivot actuator 21.

On the other hand, in addition to the articulation via the two points mentioned in the pivoted-out position according to FIG. For this purpose, the end region of the fin 1 is drawn into the holding recess 36 with increasing movement of the link element 17 along the link 19. The interaction of this end region of the fin 1 with the boundary surfaces of the holding recess 36 forms a support and / or holding device 22 via which the fin 1 is additionally supported and / or held. The boundary surfaces of the holding recess 36 form holding surfaces 23 of the support and / or holding device 22 on which the end region of the fin 1 is supported. The holding surfaces 23 can be tapered, as shown, with a correspondingly tapered end region of the fin 1, so that when the fin 1 is pulled into the holding recess 36, the end region of the fin 1 is wedge-like between the holding surfaces 23. Here, depending on the angle of inclination of the holding surfaces 23 and the friction pairing and the friction conditions, a securing self-locking can result. It is also possible for the fin 1 to end with a conical pin which is then received in conical holding surfaces 23.

The pivoting mechanism 10 according to FIGS. 5 to 7 only provides one degree of pivoting freedom. FIG. 8 shows the use of the pivoting mechanism according to FIGS. 5 to 7 together with a twisting mechanism 24 in a missile-fin unfolding device 7:

According to Fig. 8, the pivot bearing body 12, which is formed in two parts here, is rotatably supported by a pivot bearing 25 with respect to the missile 6 with simultaneous axial support by an axial bearing 26. Here, the pivot bearing 25 provides an axis of rotation 34, which in the pivoted state of the Fin 1 coincides with the longitudinal axis 2 of the fin 1. The pivot bearing body 12 here has a hollow shaft 27, the interior space 28 of which opens into the through recess 13. The rotation mechanism 24, the pivot bearing body 12 and with it the fin 1 can be rotated via a rotary actuator 29. For the illustrated embodiment, the rotary actuator 29 is designed as an electric drive. The rotary actuator 29 is here in drive connection with the pivot bearing body 12 via a gear 30.

In the interior space 28 of the hollow shaft 27, the swivel actuator 21 is arranged, which has a translationally moved actuator output element and is preferably also designed as an electric drive. The translationally moved actuator output element of the swivel actuator 21 is coupled to the articulation body 14 via the actuating element 37, so that the movement of the end region of the fin 1, explained on the basis of FIGS , the movement of the link element 17 along the link 19 and thus the pivoting of the fin 1 can be brought about. The operation of the missile fin deployment device 7 is as follows:

During the take-off and / or at the beginning of the flight of the missile 6, the fin 1 is in the folded-in and swiveled-in state according to FIG. 2 and the pivoting mechanism 10 is in the operating position according to FIG. 5. In a flight phase of the missile 6, in which it is necessary to unfold the fins 1, the swivel actuator 21 is first actuated, whereby the end area of the fin 1 is pulled into the through recess 13 via the actuating element 37 and the swiveling 5 of the fin 1 follows is brought about externally. At the end of the actuation of the swivel actuator 21, the end region of the fin 1 sits firmly in the holding recess 36, so that the support and / or holding device 22 becomes effective. The fin 1 is thus in the operating position according to FIG. 3 and the pivoting mechanism 10 is in the operating position shown in FIG. 7.

The rotary actuator 29 is now actuated, which results in a rotation 4 of the pivot bearing body 12, which is also accompanied by the rotation 4 of the fin 1. At the end of the actuation of the rotary actuator 29, the operating position of the fin 1 according to FIG.

4 reached.

In order to change the angle of attack of the fin 1, a rotation 4 of the rotation mechanism 24 and thus the fin 1 can also take place during flight operation by driving the rotary actuator 29 in both directions by any angle.

It is possible for the fin 1 to be rotated in both directions and / or the fin 1 to pivot in and / or out during flight operation by means of the actuators 21, 29. Preferably, however, the fin 1 is merely pivoted out and the fin 1 rotated during flight operations, without the fin 1 having to be pivoted back towards the missile 6.

In the present description of the figures, it was assumed that pivoting

5 of the fin 1 takes place by a pivot angle of 90 °. This is not necessarily the case. Smaller or larger swivel angles are also possible. For example, it is possible that the longitudinal axis 2 of the fin 1 in the pivoted-in state does not extend parallel to the longitudinal axis 9 of the missile 6, but rather forms an acute angle with respect to it. It is also possible that the longitudinal axis 2 of the fin 1 does not extend normal to the lateral surface of the missile 6 in the swiveled-out state, but forms an acute angle to the surface normal of the missile 6, whereby the fin 1 can be inclined forwards or backwards. It is also possible that the transverse axis 3 of the fin 1 is not oriented tangentially to the outer surface of the missile 6 in the pivoted-in state, but rather relative to the outer surface is inclined. It is also possible that, in the unfolded basic position of the fin 1, the fin 1 is already positioned with a small angle of rotation with respect to the oncoming flow.

The pivoting mechanism 10 and the rotating mechanism 24 together form an actuating mechanism 31. The missile-fin deployment device 7 is held on the missile 6 via a missile holding area 32. The missile holding area 32 can be formed by bearing surfaces of the at least one pivot bearing 25 and / or of the axial bearing 26 as well as the supports of the actuators 21, 29. It is also possible, however, for the missile fin deployment device 7 to have a housing in which the rotary bearings 25 and the axial bearing 26 are then arranged and the actuators 21, 29 are also arranged. The housing then forms the missile holding area 32, in which case the missile fin deployment device 7 can be screwed to the missile 6 via the missile holding area 32 or can be fastened to it in some other way.

REFERENCE LIST

fin

Longitudinal axis

Transverse axis

Twist

Pivoting

Missile

Missile fin deployment device

nose

Longitudinal axis

Pivoting mechanism

Swivel axis

Swivel bearing body

Through recess

Articulation body

Swivel bearing

Pivot pin

Backdrop element

Link bolt

Backdrop

pull bar

Swivel actuator

Support and / or holding device

Holding surface

Twist mechanism

Pivot bearing

Thrust bearings

Hollow shaft

inner space

Rotary actuator

transmission

Operating mechanism

Missile holding area Swivel axis rotation axis link guide retaining recess actuating element

Claims

PATENT CLAIMS

1. Missile-Fin Ausklappeinrichtung (7) with a) a fin (1) which has a longitudinal axis (2) and a transverse axis (3) which has a

Define the main extension plane of the fin (1), b) a missile holding area (32) or missile (6) and c) an actuating mechanism (31) via which the fin (1) is attached to the missile holding area (32) or missile (6) is held and cb) the fin (1) can be rotated about an axis of rotation (34) with respect to the missile holding area (32) or missile (6) and can be pivoted about a pivot axis (33), d) the actuating mechanism (31) da) has a rotating mechanism (24) by means of which the fin (1) can be rotated about the axis of rotation (34) with respect to the missile holding area (32) or missile (6), and db) has a pivoting mechanism (10) , by means of which the fin (1) can be pivoted about the pivot axis (33) relative to the missile holding area (32) or missile (6), characterized in that e) the pivot axis (33) of the transverse axis (3) of the fin (1 ) or a parallel one

Corresponds to the axis, f) the rotating mechanism (24) and the pivoting mechanism (10) can be operated independently of one another and g) in the folded position of the missile-fin unfolding device (7) ga) the fin (1) is placed against a lateral surface of the missile (6) and gb) the transverse axis (3) is oriented tangentially to the surface of the missile (6) or is oriented in cross section along the surface of the missile (6).

2. missile-Fin Ausklappeinrichtung (7) according to claim 1, characterized in that the twisting mechanism (24) and the pivoting mechanism (10) with respect to the Power flow in mechanical series connection between the fin (1) and the missile holding area (32) or the missile (6) are interposed.

3. Missile-fin unfolding device (7) according to one of the preceding claims, characterized in that the pivoting mechanism (10) has a link guide (35).

4. Missile-fin unfolding device (7) according to one of the preceding claims, characterized in that the pivoting mechanism (10) has an actuator which triggers and / or brings about the pivoting of the fin (1).

5. missile-fin unfolding device (7) according to claim 4, characterized in that the actuator is a pivot actuator (21) which has a translationally moved actuator output element.

6. missile-fin unfolding device (7) according to claim 4 or 5, characterized in that the actuator has a spring device which is tensioned in the pivoted operating position of the fin (1) and is locked via a locking device, the locking device being unlockable, with which the spring device folds out the fin (1).

7. missile-fin unfolding device (7) according to claim 4 or 5, characterized in that the actuator is a drive.

8. missile-fin unfolding device (7) according to any one of the preceding claims, characterized in that the pivoting mechanism (10) has a pivot bearing body (12), with respect to which the fin (1) can be pivoted, the fin (1) in a pivoted-out position is supported with regard to pivoting about the pivot axis (33) on a support and / or holding device (22) on the pivot bearing body (12).

9. missile-fin unfolding device (7) according to claim 8, characterized in that the pivot bearing body (12) via the rotating mechanism (24) relative to the missile (6) can be rotated.

10. missile-fin unfolding device (7) according to claim 8 or 9 in relation to one of claims 4 to 7, characterized in that the pivot bearing body (12) has a holding recess (36) into which the fin (1) in the direction of actuation of the actuator occurs and in which the fin (1) is positively secured.

11. Missile-fin unfolding device (7) according to claim 10, characterized in that the holding recess (36) and / or the fin (1) have tapered holding surfaces (23).

12. Missile-Fin Ausklappeinrichtung (7) according to one of claims 8 to 11 in direct or indirect reference back to claims 3 and 4, characterized in that the fin (1) a) in the pivoted position over the link guide (35) and a Articulation of the actuator is held, and b) is held in the swiveled-out position via the link guide (35), the articulation of the actuator and the support and / or holding device (22), with the support and / or holding device (22) the link guide (35) and / or the linkage of the actuator is at least partially relieved.

13. Missile-fin unfolding device (7) according to one of the preceding claims, characterized in that a control unit is present which has control logic which controls the pivoting mechanism (10) and / or the twisting mechanism (24).

14. Missile-fin unfolding device (7) according to claim 13, characterized in that the control logic is designed such that it controls the pivoting mechanism (10) and the twisting mechanism (24) so that a) for activation of the fin (1) first only the pivoting mechanism (10) is actuated until the fin is pivoted out, and b) then only the twisting mechanism (24) is actuated to rotate the fin (1).

15. Missile-fin unfolding device (7) according to claim 13 or 14, characterized in that the control logic is designed such that it is operating variables in flight operation processed and on the basis of the operating parameters in flight operation controls the twisting mechanism (24) in such a way that the fin (1) is rotated as a function of the operating parameters.

16. Missile-fin unfolding device (7) according to one of the preceding claims, characterized in that at least one position of the fin (1) can be secured by means of a latching or locking device.

17. Missile-fin unfolding device (7) according to claim 8 or one of claims 9 to 16 in relation to claim 8, characterized in that a) the pivot bearing body (12) is rotatably mounted, b) the pivot bearing body (12) by a rotary The actuator (29) is rotatable and c) a translationally actuated actuating element (37) extends through the pivot bearing body (12) and can be moved translationally by a pivot actuator (21).

18. Missile (6) with a missile-fin deployment device (7) according to one of the preceding claims.

19. The method for operating a missile (6) according to claim 18 with the following process steps carried out independently of one another: a) pivoting the fin (1) by actuating the pivoting mechanism (10) and b) rotating the fin (1) by actuating the twisting mechanism (24 ).

20. The method according to claim 19 when referring back to claim 13, characterized in that operating variables are processed by means of the control logic in flight operation and, on the basis of the operating variables in flight operation and after the fin (1) has been pivoted out, the rotation mechanism (1) is actuated by the pivoting mechanism (10). 24) is controlled in such a way that the fin (1) is rotated in relation to a basic position.