Support platform for launching or dropping an unmanned flight object onto a target and method for operating such a support platform

Abstract

A launching platform (1) for launching or dropping an unmanned aerial vehicle (2) at a target, comprising: a shaft-like receiving device (4) for receiving at least one aerial vehicle (2) that can be launched or dropped at a target, wherein at least one control surface element (2.1) is arranged or formed on the aerial vehicle (2), which is reversibly transferable into an operating position and into a non-operating position; a transfer device (5) associated with the receiving device (4), which is configured to transfer the or an aerial vehicle (2) from a first position arranged inside the shaft-like receiving device (4) to a second position arranged outside the shaft-like receiving device (4), or vice versa, wherein the or a further transfer device (6) is provided, the at least one control surface element (2.1) when transferring the missile or missile (2) from the first position to the second position from the non-operational position to the operational position, and / or the or a further transfer device (6) is provided to transfer at least one control surface element (2.1) from the operational position to the non-operational position when transferring the missile or missile (2) from the second position to the first position.

Description

[0001] The invention relates to a carrier platform for launching or dropping an unmanned missile onto a target and a method for operating such a carrier platform.

[0002] Carrier platforms for launching or dropping an unmanned aerial vehicle, such as a guided missile, onto a target and corresponding operating procedures are basically known from the state of the art.

[0003] In particular, it is known in this context that it is necessary for various carrier platforms to accommodate corresponding missiles in a shaft-like receiving device in order not to impair the stealth properties of the respective carrier platform and thus to make it more difficult to locate the respective carrier platform.

[0004] When accommodating such missiles in appropriate mounting systems, the missiles' external dimensions, which can be comparatively large due to fin- or wing-like control surface elements, for example, regularly pose a technical challenge. Therefore, the corresponding mounting systems must be sufficiently large to ensure the desired missile mounting capability, particularly with regard to maintaining the stealth characteristics of the respective carrier platform. However, sufficiently large dimensions of the corresponding mounting systems are not possible for all carrier platforms due to a lack of available installation space.

[0005] In order to address this problem, missiles with fold-out control surface elements have been proposed, which are configured in such a way that they can be accommodated in a receiving device with the control surface elements folded in and thus with smaller dimensions.

[0006] The problem with this, however, is that although the control surface elements can be unfolded after the missile has been transferred from the launcher, they cannot be folded back in. This precludes the missile from being returned to the launcher, which would be advisable, for example, if a launch sequence is aborted due to the stealth characteristics of the launcher platform.

[0007] US 2 630 740 A and US 4 826 105 A each disclose launch platforms that enable irreversible launch of a missile.

[0008] In view of the prior art described above, the object of the invention is to provide a carrier platform which is improved compared to the prior art for firing or dropping an unmanned missile onto a target and an improved method for operating a corresponding carrier platform.

[0009] The problem is solved by the subject matter of the independent claims. The dependent claims relate to possible embodiments.

[0010] A first aspect of the invention relates to a carrier platform for launching or dropping an unmanned aerial vehicle, such as a guided missile, onto a target. The carrier platform is thus generally configured for launching or dropping an unmanned aerial vehicle, such as a guided missile, onto a target. The carrier platform may therefore also be referred to or considered a launch or drop platform.

[0011] The carrier platform can be arranged or configured on an immobile or mobile unit, i.e., in particular, a land vehicle, aircraft, or water vehicle. Although particular advantages arise from arranging or constructing the carrier platform on vehicles, i.e., in particular, aircraft, such as airplanes, the carrier platform can also be arranged or configured on immobile or stationary units, such as ground support platforms.

[0012] The carrier platform comprises a container- or shaft-like receiving device for receiving at least one missile that can be launched or dropped at a target. The receiving device thus delimits or defines a receiving possibility provided by a, e.g., container- or shaft-like receiving volume for receiving one or more missiles that can be launched or dropped at a target. In all embodiments, the receiving device or the receiving volume can also be referred to or considered a weapons bay.

[0013] The carrier platform further comprises a transfer device assigned to the receiving device. The transfer device, which is formed, for example, by a mechanism or comprises such a mechanism, is designed to transfer the or at least one missile received in the receiving device from a first position arranged within the receiving device to a second position arranged outside the receiving device, or vice versa. The or at least one missile received in the receiving device can therefore be transferred into or between several positions by means of the transfer device. In the first position, the at least one missile is arranged orand thus does not protrude beyond the outer contour of the carrier platform, whereby a non-operating state is provided in which the at least one missile cannot be fired or dropped at a target. In the second position, the at least one missile is arranged, in particular completely, outside the receiving device and thus protrudes, in particular completely, beyond the outer contour of the carrier platform, whereby an operating state is provided in which the at least one missile can be fired or dropped at a target. Consequently, a stealth mode of the carrier platform can be implemented with the missile or at least one missile located in the first position and a launch mode of the carrier platform can be implemented with the missile or at least one missile located in the second position.

[0014] Although reference is made here in particular to "at least one missile," the same applies to the equally conceivable embodiment in which several missiles can be accommodated or are accommodated within the receiving device; the missiles can be transferred by means of the transfer device into respective first and / or second positions dependently or independently of one another.

[0015] At least one control surface element, e.g. fin- or wing-like, is arranged or formed on the at least one missile. The at least one missile is configured such that the at least one control surface element can be reversibly transferred into an operating position and into a non-operating position. The aforementioned operating and non-operating states of the at least one missile are typically equally correlated with the operating and non-operating positions of the at least one control surface element. When the at least one missile is in the first position, the at least one control surface element is typically transferred into its non-operating position. When the at least one missile is in the second position, the at least one control surface element is typically transferred into its operating position.Therefore, typically only the at least one control surface element transferred into the operating position enables the at least one missile to be launched at a target in accordance with its intended purpose, i.e. in particular in a controllable manner.

[0016] The transfer device or a further transfer device of the carrier platform, e.g. formed by or comprising a mechanism, is configured to transfer the at least one control surface element from the non-operating position to the operating position when transferring the at least one missile from the first position to the second position. The transfer device or a further transfer device is thus configured, in particular functionally and / or structurally, to act on the at least one missile in order to transfer the at least one control surface element from the non-operating position to the operating position as part of transferring the at least one missile from the first position to the second position.Likewise, the or a further transfer device of the carrier platform is configured to transfer the at least one control surface element from the operating position to the non-operating position when transferring the at least one missile from the second position to the first position. The or a further transfer device is thus configured to act on the at least one missile in a similar manner, in particular functionally and / or structurally, in order to transfer the at least one control surface element from the operating position to the non-operating position as part of transferring the at least one missile from the second position to the first position.

[0017] The transfer of the at least one missile from the first to the second position and of the at least one control surface element from the non-operating position to the operating position, which can be carried out by the respective transfer device(s), can take place at least temporarily simultaneously. Thus, the transfer of the at least one control surface element from the non-operating position to the operating position can take place at least temporarily simultaneously with the transfer of the at least one missile from the first to the second position; thus, for example, temporarily combined movement sequences of the at least one control surface element and the at least one missile can be realized. The same applies to the transfer of the at least one missile from the second position to the first position and the transfer of the at least one control surface element from the operating position to the non-operating position.

[0018] Due to the reversible transferability of the at least one control surface element into the operating and non-operating positions, and vice versa, it is equally possible to make the transfer of the at least one missile between the first and second positions, and vice versa, reversible. On the one hand, this reversibility enables a compact design of the receiving device, the dimensions of which can be selected with regard to the (comparatively reduced) dimensions of the missile or missiles with the control surface element transferred into the non-operating position. On the other hand, this reversibility enables the or at least one missile to be transferred back into the receiving device, which is expedient, for example, in the event of an aborted launch sequence with regard to the stealth properties of the carrier platform, whereby the stealth properties of the carrier platform can be restored, for example.The transfer device associated with the receiving device can thus be configured for the reversible transfer of the missile or missiles from a first position arranged within the shaft-like receiving device to a second position arranged outside the shaft-like receiving device, or vice versa.

[0019] Overall, this provides an improved carrier platform for launching or dropping an unmanned aerial vehicle.

[0020] The transfer of the at least one missile from the first to the second position, or vice versa, may require a, typically prior, transfer of a closure element assigned to the receiving device from a first position, which can also be referred to as the open position and which enables the at least one missile to be transferred from the first to the second position, or vice versa, to a second position, which can also be referred to as the closed position and which does not enable the at least one missile to be transferred from the first to the second position, or vice versa. In other words, the receiving device, ie in particular a receiving opening providing access to the receiving volume of the receiving device, can be reversibly opened and closed via movements of a, e.g., lid-like or lid-shaped, closure element.By locking the receiving device, the carrier platform or a mobile or immobile unit comprising the carrier platform can be converted into stealth mode if necessary.

[0021] As mentioned, the receiving device can delimit or define a container- or shaft-like receiving volume. The dimensions of the receiving volume of the receiving device can correspond to the dimensions of the at least one missile with the at least one control surface element in the non-operating position. Thus, the dimensions of the receiving volume can be selected with regard to the dimensions of the at least one missile with the at least one control surface element in the non-operating position, so that the installation space required for the implementation of the receiving device can be (significantly) reduced.

[0022] The carrier platform can comprise a holding device which is designed to hold the or at least one missile. The holding device can be reversibly movable into a first position arranged within the receiving device and into a second position arranged (further) outside the receiving device. The first position of the holding device typically correlates with the first position of the at least one missile, and the second position of the holding device typically correlates with the second position of the at least one missile. The holding device can comprise at least one, e.g., (electro)mechanical, holding interface for holding the or one missile. A corresponding holding interface can be formed, e.g., by at least one, in particular rail-like or rail-shaped, holding element, which can optionally also be referred to or considered as a launch rail.include such a one.

[0023] Although the transfer device for transferring the at least one missile from the first position to the second position, and vice versa, is typically arranged or configured on the receiving device side, the transfer device for transferring the at least one control surface element from an operating position to a non-operating position, or vice versa, can be arranged or configured on the receiving device side and / or on the at least one missile side. Thus, the transfer device can optionally also be configured in multiple parts, i.e., for example, comprise a plurality of transfer device elements arranged or configured on the receiving device side and / or on the missile side, which are configured to interact to transfer the at least one control surface element from the operating position to the non-operating position, or vice versa.

[0024] Regardless of their respective arrangement, the transfer device for transferring the at least one missile from the first position to the second position, and vice versa, and / or the transfer device for transferring the at least one control surface element from the operating position to the non-operating position, and vice versa, can be designed as or comprise a drive device. A corresponding drive device can be configured to generate a drive force that transfers the at least one missile from the first position to the second position, or vice versa. Alternatively or additionally, a corresponding drive device can be configured to generate a drive force that transfers the at least one control surface element from the operating position to the non-operating position, or vice versa.

[0025] A corresponding drive device can, for example, be designed or configured mechanically and / or (electric)motorically and accordingly comprise mechanical and / or (electric)motorically driven drive elements. Purely by way of example, spring constructions, joint constructions, lever constructions, cable pull constructions, etc. are mentioned in connection with a mechanical drive device, and servomotors are mentioned in connection with an (electric)motorically driven drive device. Hydraulic or pneumatic drive devices with corresponding hydraulic or pneumatic drive elements are equally conceivable.

[0026] The transfer device configured to transfer the or at least one missile from the first position to the second position, and vice versa, can comprise at least one transfer element which, in the first position of the at least one missile, acts, in particular purely structurally, on the at least one control surface element, whereby or by which the at least one control surface element is held in the non-operating position. The at least one transfer element can thus, in the first position of the at least one missile, act, in particular purely structurally, on the at least one missile in such a way that the at least one control surface element cannot be transferred into the operating position.

[0027] Furthermore, when transferring the or at least one missile from the second position to the first position, the at least one transfer element can act, in particular purely structurally, on the at least one control surface element, such that the latter is transferred from the operating position to the non-operating position. The transfer device configured to transfer the at least one missile from the first position to the second position, and vice versa, can thus comprise at least one transfer element which, when transferring the or at least one missile from the second position to the first position, acts on the at least one control surface element, whereby or as a result of which the latter is transferred from the operating position to the non-operating position.

[0028] A corresponding transfer element can, for example, be formed by or comprise at least one wall element delimiting the receiving volume of the receiving device. Starting from or in the state of the at least one missile arranged in the first position, a corresponding wall element can represent a structural blocking measure for transferring the at least one control surface element into the operating position, so that it is not possible for the at least one control surface element to be transferred into the operating position when the at least one missile is arranged in the first position.Starting from the state of the at least one missile arranged in the second position, a corresponding wall element can represent a constructive compulsory measure for the transfer of the at least one control surface element into the non-operating position when the at least one missile is transferred into the first position, so that it is possible for the at least one control surface element to be forcibly transferred into the non-operating position when the at least one missile is transferred into the first position.

[0029] The carrier platform, i.e. in particular the at least one missile, can further comprise a securing device which is configured to secure the at least one control surface element in the operating position. Depending on the specific configuration of the at least one control surface element, a securing device can in particular be configured, e.g. mechanically, hydraulically, or pneumatically, to generate a securing force which secures the at least one control surface element at least temporarily in the operating position. Corresponding securing of the at least one control surface element in the operating position can in particular take place on the basis of a securing signal generated by a control device of the carrier platform. The generation of a corresponding securing signal can correlate with the generation of a launch signal which enables actual launch of the at least one missile.

[0030] At this point, it should be generally noted that the or at least one control surface element can comprise a plurality of control surface element segments movable relative to one another in at least one translational and / or rotational degree of freedom. The control surface element segments can be movable relative to one another into at least one configuration that correlates with the operating position, and can be movable relative to one another into at least one further configuration that correlates with the non-operating position. A degree of freedom of movement can be, for example, a folding degree of freedom of movement, a pivoting degree of freedom of movement, or a sliding degree of freedom of movement.

[0031] In all embodiments, the carrier platform can comprise a hardware- and / or software-implemented control device configured to generate control information controlling the operation of the carrier platform and / or its functional components. The control device can thus be configured, in particular, to generate control information for controlling the operation of at least one transfer device or devices for reversibly transferring the or at least one missile from the first to the second position, or vice versa, and / or for reversibly transferring the at least one control surface element from the operating position to the non-operating position, or vice versa.The control device can, in particular, also be configured to generate control information for implementing coordinated movements of a mentioned closure element between corresponding positions and movements of the at least one missile for transferring it between the first position and the second position. The control device can generate corresponding control information, for example, based on computer-based or manually generated inputs, i.e., e.g., by a user of the carrier platform.

[0032] In all embodiments, the carrier platform can also be referred to or considered a carrier platform system. In particular, a combination of a corresponding receiving device, at least one corresponding missile, and at least one corresponding transfer device can be referred to or considered a carrier platform system.

[0033] A second aspect of the invention relates to a method for operating a carrier platform configured to launch or drop a missile onto a target, in particular a carrier platform according to the first aspect of the invention.

[0034] The method comprises in particular the following steps: providing at least one missile that can be received or is received in a, e.g., shaft-like, receiving device of the or a carrier platform, wherein at least one control surface element is arranged or formed on the missile, which control surface element can be reversibly transferred into an operating position and into a non-operating position; transferring the missile from a first position arranged within the receiving device to a second position arranged outside the receiving device, or vice versa, wherein when transferring the missile from the first position to the second position, the at least one control surface element is transferred from the non-operating position to the operating position, and / or when transferring the missile from the second position to the first position, the at least one control surface element is transferred from the operating position to the non-operating position.The method can be carried out reversibly in connection with transferring the missile from the first to the second position, or vice versa, and in connection with transferring the at least one control surface element from the non-operating position to the operating position, or vice versa. All statements relating to the carrier platform according to the first aspect of the invention apply analogously to the method according to the second aspect of the invention, and vice versa.

[0035] Within the scope of the method, various query criteria can be processed, particularly those that can be implemented or are implemented by the control device, which are explained below as examples: Starting from the missile or a missile in the first position (carrying configuration) – this can equally be accompanied by a stealth mode of the carrier platform or a mobile or immobile unit comprising the carrier platform – target data relating to a target can first be provided or generated. Based on this, the carrier platform can be transferred to a combat readiness mode in a single- or multi-stage process.

[0036] Once the launcher platform is or has been transferred into combat readiness mode, which can be initiated, for example, by automated intervention of a launcher platform control system or another device, or by manual intervention by a launcher platform user, such as a pilot, the basic operational readiness of the missile to be launched or dropped can be checked. If the basic operational readiness of the missile to be launched or dropped is confirmed, the receiving device can be opened and the missile can be transferred from the first position to the second position to establish the missile's launch configuration. Otherwise, error handling and, if necessary, error correction can be performed.

[0037] Establishing the launch configuration typically involves transferring at least one control surface element into the operating position. In the missile's launch configuration, the transfer of at least one control surface element into the operating position is thus complete. Depending on the specific configuration, the missile can be configured to acquire targets in the launch configuration. Furthermore, the missile can be fired or dropped in the launch configuration. Establishing combat readiness is thus complete; the missile is essentially combat-ready.

[0038] If, for whatever reason, the combat-ready missile in its launch configuration is not to be launched or dropped, stealth mode can be restored by moving at least one control surface element to the inoperative position and moving the missile to the first position. This allows the original launch configuration to be restored.

[0039] If the missile in its launch configuration is actually to be launched or dropped, a launch sequence is executed based on a launch command, which culminates in the launch or drop of the missile. Should errors occur during the launch sequence, or should the missile not be launched or dropped for whatever reason, stealth mode can be restored in a safety process by moving at least one control surface element to the inoperative position and moving the missile to the first position.

[0040] Even after the missile has been launched or released, the stealth mode of the carrier platform is typically restored by retracting at least one, in particular rail-like or rail-shaped, support element (launch rail) and closing the receiving device.

[0041] The above operations can of course be carried out, in particular simultaneously, with several missiles from one or more carrier platforms.

[0042] The invention will be explained again below using exemplary embodiments with reference to the figures. Fig. 1 , 2 each a schematic diagram of a carrier platform according to an embodiment; and Fig. 3 , 4 each a flowchart of a method for operating a carrier platform configured to launch or drop a missile onto a target according to an embodiment.

[0043] Fig. 1 shows a schematic diagram of a carrier platform 1 according to a first embodiment in a front view. The carrier platform 1 is configured for launching or dropping an unmanned missile 2, such as a guided missile, onto a target. Fin- or wing-like control surface elements 2.1 are clearly arranged or formed on the missile 2.

[0044] The carrier platform 1 can be arranged or formed on a purely schematically indicated immobile or mobile unit 3, e.g., a land vehicle, an aircraft, or a water vehicle. In particular, the carrier platform 1 is arranged or formed on an aircraft, e.g., an airplane.

[0045] The carrier platform 1 comprises a container- or shaft-like receiving device 4 for receiving a missile 2 that can be launched or dropped at a target. The receiving device 4 thus limits or defines a receiving possibility for receiving a corresponding missile 2 provided by a container- or shaft-like receiving volume. The receiving device 4 or the receiving volume can also be referred to or considered as a weapon bay.

[0046] The carrier platform 1 further comprises a transfer device 5 associated with the receiving device 4. The transfer device 5 is designed to transfer the missile 2 from a Fig. 1 not shown first position of the missile 2 arranged within the receiving device 4 into a Fig. 1 shown second position of the missile 2 arranged outside the receiving device 4, or vice versa. The missile 2 can thus be transferred into or between several positions by means of the transfer device 5. In the first position, the missile 2 is arranged or received, in particular, completely within the receiving device 4 and thus does not protrude beyond the outer contour of the carrier platform 1, whereby a non-operating state is provided in which the missile 2 cannot be fired or dropped at a target. In the Fig. 1 In the second position shown, the missile 2 is arranged, in particular completely, outside the receiving device 4 and thus protrudes, in particular completely, beyond the outer contour of the carrier platform 1, thereby creating an operating state in which the missile 2 can be launched or dropped onto a target. Thus, with the missile 2 or at least one missile 2 located in the first position, a stealth mode of the carrier platform 1 can be implemented, and with the missile 2 or at least one missile 2 located in the second position, a launch mode of the carrier platform 1 can be implemented. The transfer of the missile 2 between the first and second positions takes place in the Fig. 1 shown embodiment, for example, by moving the missile 2 in the directions indicated by the double arrow P1.

[0047] The missile 2 is configured such that the control surface elements 2.1 can be reversibly transferred into an operating position and into a non-operating position. The aforementioned operating and non-operating state of the missile 2 is equally correlated with the operating and non-operating positions of the control surface elements 2.1. When the missile 2 is in the first position, the control surface elements 2.1 are typically transferred into their non-operating position or cannot be transferred into this. When the missile 2 is in the second position, the control surface elements 2.1 are typically transferred into their operating position or can be transferred into this. Typically, only the control surface elements 2.1 transferred into the operating position enable the missile 2 to be fired at a target as intended, i.e. in particular in a controllable manner.

[0048] The carrier platform 1 comprises a further transfer device 6, which is configured to transfer the control surface elements 2.1, as indicated by the double arrows P2, from the non-operating position to the operating position when transferring the missile 2 from the first position to the second position. The transfer device 6 is thus configured, in particular functionally and / or structurally, to act on the missile 2 in order to transfer the control surface elements 2.1 from the non-operating position to the operating position when transferring the missile 2 from the first position to the second position. Likewise, the transfer device 6 is configured to transfer the control surface elements 2.1 from the operating position to the non-operating position when transferring the missile 2 from the second position to the first position.The transfer device 6 is thus equally configured, in particular functionally and / or constructively, to act on the missile 2 in order to transfer the control surface elements 2.1 from the operating position to the non-operating position as part of a transfer of the missile 2 from the second position to the first position.

[0049] The transfer of the missile 2 from the first to the second position and of the control surface elements 2.1 from the non-operating position to the operating position, which can be achieved via the transfer devices 5, 6, can take place at least temporarily simultaneously. Thus, the transfer of the control surface elements 2.1 from the non-operating position to the operating position can take place at least temporarily simultaneously with the transfer of the missile 2 from the first to the second position; thus, for example, temporarily combined movement sequences of the control surface elements 2.1 and the missile 2 can be realized. The same applies to the transfer of the missile 2 from the second position to the first position and the transfer of the control surface elements 2.1 from the operating position to the non-operating position.

[0050] The dimensions of the receiving volume of the receiving device 4 can correspond to the dimensions of the missile 2 with control surface elements 2.1 in the non-operating position. Thus, the dimensions of the receiving volume can be selected with regard to the dimensions of the missile 2 with control surface elements 2.1 in the non-operating position, so that the installation space required for the realization of the receiving device 4 can be (significantly) reduced.

[0051] Due to the reversible transfer of the control surface elements 2.1 into the operating and non-operating positions, and vice versa, it is equally possible to make the transfer of the missile 2 between the first and second positions, and vice versa, reversible. On the one hand, this reversibility enables the indicated compact design of the receiving device 4, the dimensions of which can be selected with regard to the (comparatively reduced) dimensions of the missile 2 with the control surface elements 2.1 transferred to the non-operating position. On the other hand, this reversibility enables the missile 2 to be returned to the receiving device 4, which is expedient, for example, in the event of an aborted launch sequence with regard to the stealth properties of the carrier platform 1, whereby the stealth properties of the carrier platform 1 can be restored.

[0052] The transfer of the missile 2 from the first to the second position, or vice versa, may require a prior transfer of a closure element (optional, therefore not shown) assigned to the receiving device 4 from a first position, which can also be referred to as the open position and which enables the missile 2 to be transferred from the first to the second position, or vice versa, to a second position, which can also be referred to as the closed position and which does not enable the missile 2 to be transferred from the first to the second position, or vice versa. In other words, the receiving device 4, i.e. in particular a receiving opening providing access to the receiving volume of the receiving device 4, can be reversibly opened and closed via movements of a closure element, e.g. a lid-like or lid-shaped one.By closing the receiving device 4, the carrier platform 1 can be converted into a stealth mode if necessary.

[0053] In the Fig. 1 In the exemplary embodiment shown, the carrier platform 1 comprises a holding device 7 which is designed to hold the missile 2. The holding device 7 can, as also indicated by the double arrow P1, be reversibly movable into a first position arranged within the receiving device 4 and into a second position arranged (further) outside the receiving device 4. The first position of the holding device 7 typically correlates with the first position of the missile 2, and the second position of the holding device 7 typically correlates with the second position of the missile 2. The holding device 7 can comprise at least one, e.g., (electro)mechanical, holding interface for holding the missile 2. A corresponding holding interface can, for example, be formed by or comprise at least one, in particular rail-like or rail-shaped, holding element.A corresponding mounting element may also be referred to or considered as a starting rail.

[0054] In the Fig. 1 In the exemplary embodiment shown, the transfer device 5 is arranged or designed to transfer the missile 2 from the first position to the second position, and vice versa, on the side of the receiving device 4. In contrast, the transfer device 6 is arranged or designed to transfer the control surface elements 2.1 from an operating position to a non-operating position, or vice versa, on the side of the missile 2 in the exemplary embodiment. In principle, each transfer device 5, 6 can, if necessary, also be designed in several parts, i.e., for example, comprise several transfer device elements arranged or designed on the receiving device side and / or on the missile side, which are designed to interact to transfer the control surface elements 2.1 from the operating position to the non-operating position, or vice versa.

[0055] Regardless of their respective arrangement, the transfer devices 5, 6 can be designed as drive devices or comprise such a drive device. A corresponding drive device can be configured to generate a drive force that transfers the missile 2 from the first position to the second position, or vice versa. Alternatively or additionally, a corresponding drive device can be configured to generate a drive force that transfers the control surface elements 2.1 from the operating position to the non-operating position, or vice versa.

[0056] A corresponding drive device can be used, as in the Fig. 2 shown embodiment, be mechanically designed or configured and comprise correspondingly interacting mechanical drive elements. For this purpose, the Fig. 2 In the embodiment shown, a cable pull structure 8 and spring-link structures 9 actuated by this are shown as examples of mechanical drive elements. Actuators can be mentioned as examples of drive elements of an (electric) motor drive device. Hydraulic or pneumatic drive devices with corresponding hydraulic or pneumatic drive elements are equally conceivable.

[0057] Based on the Fig. 1 From the exemplary embodiment shown, it can be seen that the transfer device 6 configured to transfer the missile 2 from the first position to the second position, and vice versa, can comprise wall-like transfer elements 6.1, 6.2 which, in the first position of the missile 2, act on the control surface elements 2.1, in particular purely structurally, whereby the control surface elements 2.1 are held in the non-operating position. The transfer elements 6.1, 6.2 can thus act on the missile 2 in the first position, in particular purely structurally, in such a way that the control surface elements 2.1 cannot be transferred into the operating position.

[0058] The transfer elements 6.1, 6.2 can furthermore act on the control surface elements 2.1 when transferring the missile 2 from the second position to the first position, in particular purely structurally, so that these are transferred from the operating position to the non-operating position. The transfer elements 6.1, 6.2 act on the control surface elements 2.1 when transferring the missile 2 from the second position to the first position, whereby or by which these are transferred from the operating position to the non-operating position. Fig. 1 In the embodiment shown, the transfer of the control surface elements 2.1 from the operating position to the non-operating position, and vice versa, is accompanied by a pivoting movement indicated by the double arrows P2.

[0059] As indicated, the transfer elements 6.1, 6.2 are in the Fig. 1 In the exemplary embodiment shown, the wall elements are formed by wall elements that delimit the receiving volume of the receiving device 4. Starting from or in the state of the missile 2 arranged in the first position, the wall elements represent a structural blocking measure for transferring the control surface elements 2.1 into the operating position, so that it is not possible for the control surface elements 2.1 to be transferred into the operating position when the missile 2 is arranged in the first position. Starting from the state of the missile 2 arranged in the second position, the wall elements represent a structural compulsory measure for transferring the control surface elements 2.1 into the non-operating position when the missile 2 is transferred to the first position, so that it is possible for the control surface elements 2.1 to be inevitably transferred into the non-operating position when the missile 2 is transferred to the first position.

[0060] The missile 2 can further comprise a purely schematically indicated securing device 10, which is configured to secure the control surface elements 2.1 in the operating position. Depending on the specific configuration of the control surface elements 2.1, the securing device 10 can be configured, in particular, e.g., mechanically, hydraulically, or pneumatically, to generate a securing force that secures the control surface elements 2.1 at least temporarily in the operating position. A corresponding securing of the control surface elements 2.1 in the operating position can be achieved, in particular, based on a securing signal generated by a hardware- and / or software-implemented control device 11 of the carrier platform 1. The generation of a corresponding securing signal can correlate with the generation of a launch signal enabling the actual launch of the missile 2.

[0061] At this point, with reference to the Fig. 2 It should be added to the exemplary embodiment shown that the control surface elements 2.1 can each comprise a plurality of control surface element segments 2.1.1, 2.1.2 that are movable relative to one another in at least one translational and / or rotational degree of freedom of movement. The control surface element segments 2.1.1, 2.1.2 can be movable relative to one another into at least one configuration that correlates with the operating position, and can be movable relative to one another into at least one further configuration that correlates with the non-operating position. A degree of freedom of movement can be, for example, a folding degree of freedom of movement, a pivoting degree of freedom of movement, or a sliding degree of freedom of movement.

[0062] As mentioned, the carrier platform 1 comprises a control device 11 implemented in hardware and / or software. The control device 11 is configured to generate control information controlling the operation of the carrier platform 1 and / or its functional components. The control device 11 can thus be configured, in particular, to generate control information for controlling the operation of the transfer devices 5, 6 for reversibly transferring the missile 2 from the first to the second position, or vice versa, and / or for reversibly transferring the control surface elements 2.1 from the operating position to the non-operating position, or vice versa.The control device 11 can, in particular, also be configured to generate control information for implementing coordinated movements of the aforementioned closure element between corresponding positions and movements of the missile 2 for transferring the missile between the first position and the second position. The control device 11 can generate corresponding control information, for example, based on computer-based or manual inputs, i.e., e.g., generated by a user of the carrier platform 1.

[0063] The following is based on the Fig. 3 shown flowchart shows a first embodiment of a device with the carrier platforms 1 according to the Fig. 1 , 2The method for operating a carrier platform 1 configured to launch or drop a missile 2 onto a target, which can be implemented in the exemplary embodiments shown, is explained: The method comprises, in particular, the following steps: Providing at least one missile 2 which is or can be received in a shaft-like receiving device 4 of the or a carrier platform 1, wherein at least one control surface element 2.1 is arranged or formed on the missile 2, which control surface element can be reversibly transferred into an operating position and into a non-operating position (step S1); Transferring the missile 2 from a first position arranged within the receiving device 4 to a second position arranged outside the receiving device 4, or vice versa, wherein when transferring the missile 2 from the first position to the second position, the at least one control surface element 2.1 is transferred from the non-operating position to the operating position (step S2), and / or when transferring the missile 2 from the second position to the first position, the at least one control surface element 2.1 is transferred from the operating position to the non-operating position (step S2).

[0064] The method can be carried out reversibly in connection with the transfer of the missile 2 from the first to the second position, or vice versa, and in connection with the transfer of the at least one control surface element 2.1 from the non-operating position to the operating position, or vice versa.

[0065] A further embodiment of a method for operating a carrier platform 1 designed to launch or drop a missile 2 onto a target is described below in connection with Fig. 4 explained: Using the example according to Fig. 4 By way of example, it should be explained that various query criteria, in particular those that can be implemented or are implemented by the control device 11, can be processed within the method: Box 12 indicates that, starting from the missile 1 (carrying configuration) located in the first position—this can equally be accompanied by a stealth mode of the carrier platform 1 or a mobile or immobile unit comprising the carrier platform 1—target data relating to a target can first be provided or generated. Based on this, the carrier platform 1 can be transferred to a combat readiness mode in a single- or multi-stage process.

[0066] As soon as the carrier platform 1 is then transferred into a combat readiness mode, which can be initiated, for example, by an automated intervention of the control device 11 of the carrier platform 1 or another device, or by manual intervention by a user of the carrier platform 1, such as a pilot, the basic operational readiness of the missile 2 to be launched or dropped can be checked (see Box 13). If the basic operational readiness of the missile 2 to be launched or dropped is given, the receiving device 4 can be opened, as indicated by Boxes 16 and 17 (Box 16), and the missile 2 can be transferred from the first position to the second position (Box 17) to establish the launch configuration of the missile 1. Furthermore, the at least one control surface element 2.1 can be transferred to its operating position (Box 18).Otherwise, as indicated by Box 15, error handling and, if necessary, error correction can be carried out.

[0067] The establishment of the launch configuration of the missile 2 indicated by box 14, as indicated by boxes 16-18, is typically also accompanied, as mentioned, by a transfer of at least one control surface element 2.1 into the operating position (see box 18). In the launch configuration of the missile 2, the transfer of at least one control surface element 2.1 into the operating position is thus completed. Depending on the specific configuration, the missile 2 can be configured to acquire targets in the launch configuration. Furthermore, the missile 2 can be fired or dropped in the launch configuration. The establishment of combat readiness (see box 19) is thus completed; the missile 2 is fundamentally combat-ready.

[0068] If the combat-ready missile 2 (see Box 19) in the launch configuration is not to be launched or dropped for whatever reason, stealth mode can be restored by moving at least one control surface element 2.1 to the inoperative position and moving the missile 2 to the first position. In this way, the original launch configuration can be restored (see Box 20).

[0069] If the missile 2 in the launch configuration is actually to be fired or dropped, a launch sequence is processed or carried out based on a launch command (see Box 21), which ends with the launch or drop of the missile 2. Should errors occur during the execution of the launch sequence or the missile 2 is not fired or dropped for whatever reason, the stealth mode can be restored in a safety process (see Box 22) by moving at least one control surface element 2.1 to the non-operating position and moving the missile 2 to the first position.

[0070] Even after the missile 2 has been launched or released, the stealth mode of the carrier platform 1 is typically restored by retracting at least one, particularly rail-like or rail-shaped, support element (launch rail) (see Box 23) and closing the receiving device 4 (see Box 24). Stealth mode is thus restored in Box 25.

[0071] The above in connection with the embodiment according to Fig. 4 The processes described by way of example can of course be carried out, in particular simultaneously, with several missiles 1 of one or more carrier platforms 1. List of reference symbols

[0072] 1 Carrier platform 2 Missile 2.1 Control surface element 2.1.1 Control surface element segment 2.1.2 Control surface element segment 3 Unit 4 Pick-up device 5 Transfer device 6 Transfer device 6.1 Transfer element 6.2 Transfer element 7 Mounting device 8 Cable structure 9 Spring-joint structure 10 Securing device 11 Control device 12 - 25 Box P1Double arrow P2Double arrow

Claims

1. Carrier platform (1) for launching or dropping an unmanned missile (2) at / onto a target, characterized by a shaft-like receiving device (4) for receiving at least one missile (2) which is able to be launched at or dropped onto a target, wherein at least one control surface element (2.1) which is able to be reversibly transferred to an operating position and to a non-operating position is arranged or formed on the missile (2); a transfer device (5) which is assigned to the receiving device (4) and is configured to reversibly transfer the or a missile (2) from a first position, arranged inside the shaft-like receiving device (4), to a second position, arranged outside the shaft-like receiving device (4), or vice versa, wherein the or a further transfer device (6) is configured to transfer the at least one control surface element (2.1) from the non-operating position to the operating position when the or a missile (2) is transferred from the first position to the second position, and the or the further transfer device (6) is configured to transfer the at least one control surface element (2.1) from the operating position to the non-operating position when the or a missile (2) is transferred from the second position to the first position.

2. Carrier platform according to Claim 1, characterized in that the shaft-like receiving device (4) defines a shaft-like receiving volume the dimensions of which correspond to the dimensions of the or a missile (2) having the at least one control surface element (2.1) in the non-operating position.

3. Carrier platform according to Claim 1 or 2, characterized by a holding device (7) which is configured to hold the or a missile (2), wherein the holding device (7) is able to be moved into a first position arranged inside the shaft-like receiving device (4) and into a second position arranged further outside the shaft-like receiving device (4).

4. Carrier platform according to one of the preceding claims, characterized in that the or the further transfer device (6) is designed as or comprises a drive device which is configured to generate a driving force which transfers the at least one control surface element (2.1) from the operating position to the non-operating position, or vice versa.

5. Carrier platform according to Claim 4, characterized in that the or the further transfer device (6) is arranged or formed on or in the shaft-like receiving device (4) and / or on or in the respective missile (2).

6. Carrier platform according to Claim 4 or 5, characterized in that the drive device is designed as or comprises a mechanical and / or motorized drive device.

7. Carrier platform according to one of the preceding claims, characterized in that the transfer device (6) comprises at least one transfer element (6.1, 6.2) which acts on the at least one control surface element (2.1) in the first position of the missile (2), wherein the at least one control surface element (2.1) is held in the non-operating position.

8. Carrier platform according to one of the preceding claims, characterized in that the transfer device (6) comprises at least one transfer element (6.1, 6.2) which, when the missile (2) is transferred from the second position to the first position, acts on the at least one control surface element (2.1) such that the latter is transferred from the operating position to the non-operating position.

9. Carrier platform according to Claim 7 or 8, characterized in that the at least one transfer element (6.1, 6.2) is formed by or comprises a wall element which delimits a shaft-like receiving space of the receiving device (4).

10. Carrier platform according to one of the preceding claims, characterized by at least one missile (2) which is able to be launched at or dropped onto a target, wherein at least one control surface element (2.1) is arranged or formed on the missile (2), and a securing device (10) which is configured to secure the at least one control surface element (2.1) in the operating position.

11. Carrier platform according to one of the preceding claims, characterized in that the at least one control surface element (2.1) comprises a plurality of control surface element segments (2.1.1, 2.1.2) which are able to be moved relative to one another in at least one translational and / or rotational degree of freedom of movement, wherein the control surface element segments (2.1.1, 2.1.2) are able to be moved relative to one another into at least one configuration which correlates with the operating position and are able to be moved relative to one other into at least one configuration which correlates with the non-operating position.

12. Carrier platform according to one of the preceding claims, characterized by a control device (11) for controlling the operation of at least the or the further transfer device (5, 6) for transferring the missile (2) from the first to the second position, or vice versa, and / or for transferring the at least one control surface element (2.1) from the operating position to the non-operating position, or vice versa.

13. Carrier platform according to one of the preceding claims, characterized in that it is arranged or formed on an immobile or mobile unit (3), in particular a land vehicle, aircraft or watercraft.

14. Carrier platform according to one of the preceding claims, characterized in that the transfer device (5) assigned to the receiving device (4) is configured to reversibly transfer the or a missile (2) from the first position, arranged inside the shaft-like receiving device (4), to the second position, arranged outside the shaft-like receiving device (4), or vice versa.

15. Method for operating a carrier platform (1), in particular a carrier platform (1) according to one of the preceding claims, which has been configured to launch or drop a missile (2) at / onto a target, comprising the following steps: - providing a missile (2) which is received or able to be received in a shaft-like receiving device (4) of the carrier platform (1), wherein at least one control surface element (2.1) which is able to be reversibly transferred to an operating position and to a non-operating position is arranged or formed on the missile (2), - reversibly transferring the missile (2) from a first position, arranged inside the shaft-like receiving device (4), to a second position, arranged outside the shaft-like receiving device (4), or vice versa, wherein, when the missile (2) is transferred from the first position to the second position, the at least one control surface element (2.1) is transferred from the non-operating position to the operating position, and, when the missile (2) is transferred from the second position to the first position, the at least one control surface element (2.1) is transferred from the operating position to the non-operating position.

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