EP3136042A2 - Wing assembly and missile with wing assembly - Google Patents

Abstract

The invention relates to a wing arrangement (12, 12 ', 12 ") for a missile (2, 2', 2") comprising a support surface (14, 14 ', 14 ") with a control surface (16) attached thereto, which is guided by a Actuator (28, 28 ', 28 ", 50) about a with the missile longitudinal axis (20, 20', 20") at an angle intersecting or parallel to the axis (18) is deflectable, wherein the actuator (28, 28 ' , 28 ", 50) in an interior (26, 26 ', 26") of the support surface (14, 14', 14 ") is arranged and connected to a drive element (38) which partially in the interior (26, 26 ' , 26 ") of the support surface (14, 14 ', 14") is arranged and with a with the control surface (16) fixedly connected to the lever means (36) is connected. Furthermore, the invention relates to a missile (2, 2 ', 2 ") with at least one such wing assembly (12, 12', 12").

Description

The invention relates to a wing assembly for a missile comprising a support surface with a control surface attached thereto, which is deflectable by an actuator about an axis intersecting with a missile longitudinal axis or extending parallel thereto.

Such wing arrangements are used for example in missiles in duck configuration, but also in conventional configurations in which the wings are located in front of the tail. In the case of a duck configuration, four wing arrangements are usually arranged in a cross shape on the fuselage of the missile in the rear region. About arranged within the missile actuators, the control surfaces are deflected. A led out of the fuselage, connected to the actuator linkage ensures a movement of a mounted in or on the control surface and connected to the rod rowing horn and thus to a deflection of the control surface. The wing assemblies are usually designed as plug-in wings for attachment to the missile. By attaching a mechanical connection between the actuator and the control surface is made. In this case, wing assembly and associated actuator to be adjusted so that the control surface is in the zero position, so the control surface is in the plane of symmetry of the wing. In the previously customary wing arrangements, in which the actuator for the control surfaces or rudder surfaces is located inside the fuselage of the missile, this is associated with a lengthy adjustment effort and thus high costs.

It is an object of the invention to provide a wing assembly for a missile that allows easy connection to a missile.

This object is achieved by a wing assembly for a missile according to the features of claim 1. It is proposed that the actuator of a wing assembly for a missile comprising a support surface with a control surface attached thereto, by the actuator to a with a missile longitudinal axis according to the invention is arranged in an interior of the support surface and connected to a drive element which is at least partially - or even completely - arranged in the interior of the support surface and connected to a fixedly connected to the control surface lever means.

The invention is based on the consideration that when mounting a wing arrangement on a missile, in which an actuator for deflecting a control surface is arranged on or in particular within the fuselage, not only interfering with the wing arrangement, but also on the missile during assembly. in particular must be made within the same to precisely adjust the wing assembly. For misalignments of the actuator and / or the associated control element cause a misalignment of the control surface, whereas a misalignment of a control means connected to the lever means not only lead to a misalignment of the control surface in a control of the actuator, but also to damage the actuator itself can. The disadvantage here is thus that the adjustment due to the spatial separation of actuator and lever means for the control surface on two units to be joined together, namely missile and wing assembly, complex and u. U. can also cause modifications or repairs to already otherwise assembled missile.

This disadvantage can be circumvented by the invention. By providing the actuator in the interior of the wing and the partial arrangement of the drive element of the actuator in the interior of the wing and the attachment of the control element connected to the lever means on the control surface no adjustment interventions on the missile itself or on or within the fuselage are required , As a result of this integration or displacement into the wing arrangement, interventions on the missile or within the missile are no longer necessary during final assembly. The wing assembly forms a separate unit to be handled, which can be prefabricated. The adjustment of the zero position of the control surface can thereby made before connection of the wing assembly to a missile and the wing assembly can as a faultless, pre-aligned unit can be easily and quickly attached to a missile.

Another positive effect of the arrangement of the actuator and the partial arrangement of the control element in the interior of the wing is the consequent gain in space within the missile, which is now available for other components and / or for example, allows an enlargement of a fuel tank.

The airfoil and the control surface may be connected by one or more hinges to permit deflection of the control surface about an axis intersecting with or parallel to a missile longitudinal axis at an angle.

The actuator is a control unit in which electrical control signals are converted into a movement of the drive element connected to the actuator, so that this movement can be used by the control element connected to the lever means. The movement of the drive element can be a translatory movement limited in its path. The actuator can be a hydraulic or an electromagnetic actuator. An electromagnetic actuator generally comprises an electric motor for implementing the electrical control signals, with which the mechanical movement is generated and transmitted in a suitable manner to the drive element.

The control element may be designed as a metallic linkage of, for example, steel, aluminum or titanium, but also a use of a fiber composite material for the linkage is conceivable. In particular, the drive element can be designed as a translationally movable push rod with a fastening unit for attachment to the lever means.

The lever means may be made of the same materials as the drive element or the control surface. The lever means may be a rudder horn. The lever means is articulated directly or indirectly connected to the drive element, in particular with a fixing unit of the drive element. Appropriately, the drive element is pivotally connected via, for example, a pin or bolt with the lever means. To receive the lever means the drive element is facing at its the lever means Conveniently fork-shaped end, wherein the connection with the lever means via the aforementioned pin or bolt can be accomplished, which allows a rotational movement between the control element and lever means. For fixed connection of the lever means with the control surface, this can for example be bolted to the control surface, glued or welded, but also an integral Anformung to the control surface is possible. Depending on the design of the control surface, it is also possible to secure the lever means in an interior of the control surface.

The support surface and the control surface may be made of sheet steel to give the wing assembly a great stability. However, other materials such as aluminum, titanium or fiber composites such as CFRP (carbon fiber reinforced plastic) or GRP (glass fiber reinforced plastic) may also be used. The support surface as well as the control surface may be made of solid material and be provided with a recess forming an interior for accommodating the actuator and partial accommodation of the drive element or for accommodating the lever means. Conveniently, however, the airfoil and / or the control surface are formed by a skin-clad framework. Skin and skeleton as well as in the interior of the framework any provided for further reinforcement ribs and / or spars can be made of one of the aforementioned materials. An at least partial foaming of the interior spaces with a foam can also be provided.

Conveniently, the support surface has an outgoing from its interior passage to the outside, via which the drive element is guided out of the support surface for connection to the fixedly connected to the control surface lever means out. If the lever means is mounted in an interior space of the control surface, it is expedient to provide an outward passage from the interior to the control surface, the feedthroughs being arranged relative to one another such that the control element can be introduced into the passage of the control surface via the passage in the support surface ,

Advantageously, the actuator is an electromechanical actuator, preferably a threaded spindle drive. In particular, for the deflection of control surfaces of missiles threaded spindle drives offer in which a simple way a rotational movement in a longitudinal movement can be implemented. With threaded spindle drives can be high traversing speeds as well as high Positioning accuracies achieve what is required for accurate steering of a missile and thus a successful mission. A threaded spindle drive still requires little drive power, which means that it can be realized in a small footprint and can thus be accommodated without difficulty in the interior of a wing. As an alternative to the threaded spindle drive and a gear transmission, in particular a worm gear can be used.

In a preferred variant, the drive element is connected to the spindle or the spindle nut of the threaded spindle drive. Depending on the configuration of the threaded spindle drive, so movable spindle or movable spindle nut, the drive element is connected to the spindle or the spindle nut. If the drive element is connected to a movable spindle, an embodiment of the drive element is available as a translationally movable push rod, wherein the spindle and push rod can be made in one piece.

An advantageous embodiment of the invention provides that the support surface is formed in its root region for attachment to at least one attachment means located on the fuselage of a missile. This allows a simple and quick connection of a wing assembly to a missile. For this purpose, the support surface can be provided, for example, on its side facing the fuselage of the missile with a number of openings, which enable it to be plugged onto corresponding stud bolts arranged directly or indirectly on the fuselage of the missile. The stud bolts can be arranged on a rail which extends in the longitudinal direction of the missile and is mounted on its trunk. By "on the fuselage of a missile" Aufsteckmittel is also understood a Aufsteckmittel, which is arranged in a recess in the usually cylindrical trunk of the missile, so that, for example, the root portion of the support surface is at least partially within this recess. This recess can, for. B. be formed by a correspondingly adapted indentation in the fuselage, so that it is suitable for receiving a relative to the rest of the support surface thickened root portion of the support surface.

As already mentioned, the root area of the support surface may be thickened relative to the rest of the support surface, such as in the form of a rectangular thickening or in the form of a straight cylinder segment which, with its straight surface, can be fastened to a correspondingly flattened surface of the fuselage is. Such thickenings serve the better mountability and stability of a wing assembly. Especially in an interior space in the region of such a thickening, an arrangement of an actuator is advantageous, since space is available for any required, larger-sized actuators.

Another advantageous embodiment of the invention provides that the support surface is provided in its root area with at least one pin which is designed to engage in a recess of a arranged on the fuselage of the missile rail in the manner of a bayonet closure. The pin or pins are conveniently located in the root area of one or both side surfaces of the wing. The pins may then be inserted into recesses of a rail suitable for forming a bayonet catch for locking or securing the wing arrangement to the missile. In order to attach the wing assembly to a rail with U-profile, in which both legs are provided with recesses, are expediently provided on both side surfaces of the support pins. This allows the inclusion of the root portion of the support surface within the rail or within the U-profile and thus a particularly good locking of a wing assembly on a missile. The term "on the fuselage" also means that the rail can be located, for example, in a recess located in the fuselage.

Further, it is advantageous if the actuator is connected to a mechanical switch for changing the direction of rotation of a motor of the actuator. If the actuator is an electromechanical actuator, a direction of movement of the drive element connected to the actuator can be changed via the changeover of the direction of rotation of the motor and thus the control surface can be deflected either positive or negative relative to its zero position via the lever means. By providing such a mechanical switch, one and the same wing arrangement can be quickly and easily transferred from a left-handed variant into a right-handed variant, depending on what is desired for a variant for a wing assembly to be equipped missile. A lengthy changeover of an actuator from left to right turn or vice versa can be omitted.

It is advantageous if the mechanical switch is arranged on the support surface such that it is secured via an actuating element fixed in the fuselage of a missile is switchable. By means of such an arrangement, a desired direction of rotation can thus be predetermined via the missile or its actuating element. Human errors in the assembly of a wing assembly by incorrect or confused wiring of wing assemblies are no longer possible. The wing assembly can be switched and fixed by a switch arranged in this way with regard to the direction of rotation.

Preferably, the mechanical switch is arranged in the interior of the support surface. As a result, the switch is not only protected from external influences that could lead to damage of the switch, but also from accidental actuation of the switch by a person when it introduces the missile, for example, in a launch device for missiles or attached to such. Cleverly, the support surface in this case has in its root portion two openings which are arranged with respect to the mechanical switch that, depending on which of the openings the actuator is guided, one or the other direction of rotation of the motor is adjusted. It is advantageous if the two openings are arranged eccentrically to the plane of symmetry of the support surface. It is envisaged that one of the openings are arranged on the left and the other on the right of the plane of symmetry. Preferably, the openings are located on the side of the wing facing the fuselage of the missile.

In a further advantageous embodiment of the invention it is provided that the actuator for the production of a power and signal supply to the missile is equipped with a cable with connection means, which is designed for producing a power and signal connection to a connection means of the missile. The cable can be dimensioned, for example starting from the actuator in its length so that its connection means, such as a plug, at least up to a rail on the missile for fastening the wing assembly is feasible. To produce the power and signal supply, the rail may be equipped with a corresponding connection means, which is in connection with a control and navigation device of the missile. For example, if an attachment of the wing assembly, in which the wing assembly is held by a positive connection and the connection between the missile or rail and wing assembly by a (missile) axial and / or radial latching movement is realized, and the electrical contact with the same Operation, motion sequence are produced. The Connection means, such as plug and socket, wing assembly and missile or rail - or vice versa - are preferably arranged opposite each other or mounted so that they automatically come into contact with each other during the assembly process. The contact between the connection means, plug and socket, it is done skillfully parallel to a mechanical, axial or radial stop, which serves for accurate positioning or exact alignment of the wing assembly.

The invention also relates to a missile having at least one wing assembly described above. The missile may be designed for a movement in the air, in particular as a missile, but also for a movement underwater in the form of a torpedo.

In an advantageous embodiment, the missile has at least one actuating element in or on its fuselage, which is designed to actuate a mechanical switch. The actuating element is expediently projecting from the surface of the fuselage and is designed such that it can actuate the mechanical switch of a wing arrangement, with which the direction of rotation of a motor of an actuator for a control surface of the wing arrangement can be switched.

In a further advantageous embodiment, the missile has on the surface of its fuselage at least one rail extending in the direction of the missile longitudinal axis for fastening the root region of the wing of the wing assembly. The rail is preferably provided with at least one recess for forming a bayonet closure with a pin arranged in the root area of the supporting surface of the wing arrangement. Cleverly, the rail comprises the actuating element or a passage for the implementation of the actuating element. Conveniently, the rail is provided with a connection means for producing a power and signal connection with a connecting means associated with the actuator of the wing assembly.

Alternatively, the missile or one arranged on the missile, extending in the longitudinal direction of the missile rail may be provided with radially projecting from the missile or the rail studs that allow attaching the wing assembly.

The previous description of advantageous embodiments of the invention includes numerous features, which are given in the individual dependent claims in part to several summarized. Expediently, these features will also be considered individually by the person skilled in the art and combined into meaningful further combinations. In particular, these features can be combined individually and in any suitable combination with the aerodynamic control surface according to the invention and the method according to the invention for mounting an aerodynamic control surface according to the independent patent claims.

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

Fig. 1

eine schematische Darstellung eines Lenkflugkörpers

Fig. 2

einen Schnitt durch eine Flügelanordnung in perspektivischer Darstellung,

Fig. 3

eine an einer Schiene befestigte Flügelanordnung mit integriertem Stellantrieb in schematisch-perspektivischer Darstellung,

Fig. 4

eine schematische Darstellung eines Querschnitts durch einen Flugkörper mit vier Flügelanordnungen,

Fig. 5

eine vereinfachte schematische Darstellung eines Schnitts durch eine alternative Flügelanordnung und den zugehörigen Rumpf eines Flugkörpers,

Fig. 6

eine schematische Darstellung eines Querschnitts durch den Flugkörper gemäß Fig. 5 mit vier alternativen Flügelanordnungen und

Fig. 7

eine schematische Darstellung eines Querschnitts durch einen Flugkörper mit vier Flügelanordnungen entsprechend einer weiteren Alternative.

Show it:

Fig. 1

a schematic representation of a missile

Fig. 2

a section through a wing assembly in perspective view,

Fig. 3

a mounted on a rail wing assembly with integrated actuator in a schematic perspective view,

Fig. 4

a schematic representation of a cross section through a missile with four wing assemblies,

Fig. 5

a simplified schematic representation of a section through an alternative wing arrangement and the associated fuselage of a missile,

Fig. 6

a schematic representation of a cross section through the missile according to Fig. 5 with four alternative wing arrangements and

Fig. 7

a schematic representation of a cross section through a missile with four wing assemblies according to a further alternative.

Identical parts are designated by the same reference numerals.

Fig. 1 shows a missile 2 in the form of a missile with a seeker head 4, an active part 6 and a rocket engine 8. The seeker is connected to a control and navigation device 10, the electronics of optical information of the seeker 4 generates steering signals for steering the missile 2. Using the steering signals arranged on the fuselage 3 of the missile 2 wing assemblies 12 are adjusted so that the missile 2 is guided in its flight through the air. More precisely, via the control and navigation device 10 connected to the wings 14 control surfaces 16 of the wing assemblies 12 are adjustable. The control surfaces 16 are presently deflectable about an axis 18 which intersects with the missile longitudinal axis 20 of the missile 2 at a 90 ° angle.

In Fig. 2 a section through part of a wing assembly 12 is shown. Not visible is the root portion 22 of the formed by the two side surfaces 24 support surface 14 can be seen is formed by the side surfaces 24 interior 26 in which an actuator 28 for deflecting the control surface 16 about the axis 18 can be accommodated. The accommodated in the interior 26 actuator 28 is in Fig. 3 shown and described in detail, in the present case, its location is indicated only by dashed lines. The support surface 14 is formed by a skeleton planked with aluminum skin, of which in Fig. 2 which are also made of aluminum spars 30 can be seen. The control surface 16 is also made of aluminum. Schematically illustrated are two hinges 32 which allow the deflection of the control surface 16 about the axis 18. Also indicated only schematically by dashed lines is the interior 34 in the control surface 16, in which a lever means 36 is firmly glued in the form of a rudder horn, which is connected via a drive element 38 in the form of a linearly movable push rod with the lever means 36 articulated. The push rod has preferably at its end facing the lever means 36 a fastening unit in the form of a fork-shaped configuration, wherein the articulation point of the lever means 36 comes to lie between the fork and the fork, the lever means 36 via one of its two fork arms and a through the articulation point in the lever means 36 extending bore led pin holds. Not shown in the support surface 14 and control surface 16 provided cylindrical passages to the respective interior 26, 34, which serve to facilitate the passage of the drive element 38 from the interior 26 in the support surface 14 in the interior 34 of the control surface 16. schematically indicated, however, is a connected to the actuator 28 cable 40 with a connection means 42 in the form of a plug in order to connect the actuator 28 for power and signal supply with housed in the fuselage of the missile 2 control and navigation device 10 can.

Fig. 3 shows a mounted on a rail 44 wing assembly 12 with integrated actuator 28 in a schematic perspective view. The dashed area gives a view into the interior 26 of the support surface 14 or in the interior 34 of the control surface 16. The rail 44 is formed by a U-profile and is attached to the fuselage 3 of the missile 2. The rail 44 is provided with recesses 46, into which can be inserted at the roots 48 in the region of the support surface 14 fixed pins 48 and locked in the manner of a bayonet closure for fixing the support surface 14 on the missile 2. In the interior 26 of the support surface 14 is to see the deflection of the control surface 16 from its zero position of the actuator 28. In the actuator 28 is a threaded spindle drive 50 with a motor 52, a spindle 54 and a spindle nut 56. For movement of the located in the control surface 16 lever means 36, the drive element 38 is connected to the spindle 54. About the motor 52, a linear translational movement of the spindle 54 and thus of the drive element 38 is effected. The degree of movement or thus the adjustment angle of the control surface 16 out of its zero position can be determined via a potentiometer 58 operatively connected to the spindle nut 56. The motor 52 of the threaded spindle drive 50 is a mechanical switch 60, with which the direction of rotation of the motor 52 can be changed and thus the direction of movement of the drive element 38 and thus turn the deflection of the control surface 16 between positive and negative can be changed. The mechanical switch 60 can be actuated via an actuating element 62, which is fastened in the fuselage 3 of the missile, in the form of an index pin. The actuating element 62 is guided over a recess located in the rail 44. Depending on the desired deflection of the control surface 16, the actuation element 62 fastened in the fuselage 3 can be guided through a recess in the rail 44 only by means of an aperture 64, 66 arranged eccentrically to the plane of the plane of symmetry and located on the side of the support surface 14 assigned to the fuselage 3 and a rotational direction of the motor 52 are adjusted. A faulty connection or wiring of the actuator 28 is thereby avoidable. Furthermore, the rail 44 comprises a connecting means 68, which via a cable 70 with the missile 2 or with its control and navigation device 10 is connected to the connecting means 42 of the threaded spindle drive 50 in order to produce a power and signal connection to this.

Fig. 4 shows a schematic representation of a cross section through the provided with four wing assemblies 12 missile 2. You can see the acting on the mechanical switch 60 of the threaded spindle drives 50 actuators 62. All actuators 62 are mounted in the fuselage 3 of the missile 2 so that they are the directions of rotation the motors 52 of the threaded spindle drives 50 set so that a positive rash of the control surfaces 16 results. The openings 64, 66 in the wings 14, which lead to a positive deflection of the control surfaces 16 have been provided in this case by the reference numeral 64 and those which lead to a negative rash, with the reference numeral 66th

Fig. 5 shows a simplified schematic representation of a section through an alternative wing assembly 12 'and the associated fuselage of a missile 2'. It will be discussed below only the differences in terms of the wing assembly 12 and the missile 2. The wing assembly 12 'and the support surface 14' has a thickened root region 22 'compared to the wing assembly 12. As in Fig. 6 represented are the root portions 22 'rectangularly thickened and allow by this thickening in the region of the thickening in comparison to the actuator 28 of the Flügelandordung 12 larger-sized actuator 28' in the interior 26 'of the support surface 14' provide. In order not to impair the aerodynamics caused by the thickened root zones 22 ', the hull 3' of the missile 2 'is provided with recesses 72 for receiving the root regions 22'. The root regions 22 'are thus encompassed by the indentations 72' of the hull 3 'of the missile 2'.

In Fig. 7 is a missile 2 "with four designed according to another alternative wing arrangements 12" to see. The root region 22 "of the supporting surface 14" of such a wing arrangement 12 "is formed by a cylinder segment 74" with a straight surface 76 ", which can be fastened to a corresponding surface of the fuselage 3" of the missile 2 ", also by this type of thickening the root regions 22 "there is the possibility in a simple manner to accommodate a larger-sized actuator 28" in a presently only indicated interior 26 "in the root region 22" of the support surface 14 ".

LIST OF REFERENCE NUMBERS

2, 2 ', 2 "

missile

3, 3 ', 3 "

Hull of 2, 2 ', 2 "

4

seeker

6

active part

8th

Rocket engine

10

Control and navigation device

12, 12 ', 12 "

wing assembly

14, 14 ', 14 "

wing

16

control surface

18

axis

20, 20 ', 20 "

Missile longitudinal axis

22, 22 ', 22 "

root area

24

Side surface of 14

26, 26 ', 26 "

Interior of 14, 14 ', 14 "

28, 28 ', 28 "

actuator

30

Holm

32

hinge

34

Interior of 16

36

lever means

38

driving element

40

electric wire

42

Connection means of 40

44

rail

46

recess

48

pen

50

Screw Actuator

52

engine

54

spindle

56

spindle nut

58

potentiometer

60

mechanical switch

62

actuator

64

opening

66

opening

68

connection means

70

electric wire

72 '

indentation

74 "

cylinder segment

76 "

straight area of 74 "

Claims (15)

A wing arrangement (12, 12 ', 12 ") for a missile (2, 2', 2") comprising a support surface (14, 14 ', 14 ") with a control surface (16) attached thereto, actuated by an actuator (28, 28 ', 28 ", 50) is deflectable about an axis (18) which intersects with the missile longitudinal axis (20, 20', 20") at an angle or extends parallel thereto,
characterized,
that the actuator (28, 28 ', 28 ", 50) a) in an interior space (26, 26 ', 26 ") of the support surface (14, 14', 14") is arranged and b) is connected to a drive element (38) which is at least partially in the interior (26, 26 ', 26 ") of the support surface (14, 14', 14") is arranged and with a with the control surface (16) fixedly connected lever means (36) is connected. Wing arrangement (12, 12 ', 12 ") according to claim 1,
characterized,
that the actuator (28, 28 ', 28 ") is a threaded spindle drive (50). Wing arrangement (12, 12 ', 12 ") according to claim 2,
characterized,
that the driving element (38) with a spindle (54) or a spindle nut (56) of the threaded spindle drive (50) is connected. Wing arrangement (12, 12 ', 12 ") according to one of the preceding claims,
characterized,
in that the support surface (14, 14 ', 14 ") in its root region (22, 22', 22") can be attached to at least one of the fuselages (3, 3 ', 3 ") of a missile (2, 2', 2"). ) is formed Aufsteckmittel located. Wing arrangement (12, 12 ', 12 ") according to one of claims 1 to 3,
characterized,
in that the support surface (14, 14 ', 14 ") is provided in its root region (22, 22', 22") with at least one pin (48) adapted to engage in a recess (46) on the body (3, 3) ', 3 ") of the missile (2, 2', 2") arranged rail (44) is designed in the manner of a bayonet closure. Wing arrangement (12, 12 ', 12 ") according to one of the preceding claims,
characterized,
that the actuator (28, 28 ', 28 ", 50) with a mechanical switch (60) for changing a rotational direction of a motor (52) of the actuator (28, 28', 28", 50) is connected. Wing arrangement (12, 12 ', 12 ") according to claim 6,
characterized,
in that the mechanical switch (60) is arranged on the support surface (14, 14 ', 14 ") in such a way that it is fastened in the fuselage (3, 3', 3") of a missile (2, 2 ', 2 ") Actuator (62) is switchable. Wing arrangement (12, 12 ', 12 ") according to claim 7,
characterized,
in that the mechanical switch (60) is arranged in the interior (26, 26 ', 26 ") of the support surface (14, 14', 14"). Wing arrangement (12, 12 ', 12 ") according to claim 8,
characterized,
in that the support surface (14, 14 ', 14 ") has, in its root region (22, 22', 22"), two openings (64, 66) arranged with respect to the mechanical switch (60), as the case may be through which of the openings (64, 66) the actuator (62) is guided, one or the other direction of rotation of the motor (52) is adjusted. Wing arrangement (12, 12 ', 12 ") according to claim 9,
characterized,
in that the openings (64, 66) are arranged eccentrically to the plane of symmetry of the support surface (14, 14 ', 14 "). Wing arrangement (12, 12 ', 12 ") according to one of the preceding claims,
characterized,
that the actuator (28, 28 ', 28 ", 50) for power and signal supply via the missile (2, 2', 2") is equipped with a cable (40) with a connection means (42) for the production of a Power and signal connection with a connection means (68) of the missile (2, 2 ', 2 ") is formed. Missile (2, 2 ', 2 ") with at least one wing arrangement (12, 12', 12") according to one of the preceding claims. Missile (2, 2 ', 2 ") according to claim 12,
characterized,
in that at least one actuating element (62), which is designed to actuate a mechanical switch (60), is fastened in or on the fuselage (3, 3 ', 3 ") of the missile (2, 2', 2"). Missile (2, 2 ', 2 ") according to claim 12 or 13,
characterized,
in that on the surface of the fuselage (3, 3 ', 3 ") of the missile (2, 2', 2") there is at least one rail (44) extending in the direction of the missile longitudinal axis (20) for fastening the root region (22, 22 '). , 22 ") of the support surface (14, 14 ', 14") is provided and the rail (44) is provided with at least one recess for forming a bayonet closure with a root portion (22, 22', 22 ") of the support surface (14 Arranged pin (48). A missile (2, 2 ', 2 ") according to claim 14,
characterized,
in that the rail (44) is equipped with connection means (68) for establishing a current and signal connection to a connection means ((28, 28 ', 28 ", 50) of the wing arrangement (12, 12', 12")) associated with the actuator (12). 42).

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