Methods for controlling guided missiles, as well as guided missiles and aircraft

Abstract

A method for controlling at least one guided missile (3) to be launched from an aircraft (2) during flight, a guided missile (3) and an aircraft (2) are proposed, wherein at least one mission command (N) is transmitted from the aircraft (2) to the guided missile (3) by means of a light signal (L).

Description

Technical area

[0001] The present disclosure relates to a method for controlling at least one guided missile to be launched from an aircraft during flight, to a guided missile and to an aircraft. Technical background

[0002] Guided missiles, especially cruise missiles, can be launched from aircraft and then move autonomously toward a target based on predefined mission data and their internal control system. Launching typically occurs from pylons attached externally to the aircraft or platforms. The mission and control data can be transmitted to the guided missile via a cable-based data link, for example, before or after the missile is attached to the respective pylon.

[0003] A mechanical trigger installed on the missile, such as a contact pin or anchor cable connected to an electrical sensor or switch, can signal the missile's control system that it is attached to the pylon. Alternatively, the missile can be housed in an aircraft's weapons bay. As soon as the missile is released from the pylon or released from the weapons bay, the mechanical sensor signals the missile's control system that it must now begin its mission, for example, firing its engine, positioning any wings, etc.

[0004] EP 4 060 282 B1, for example, relates to a guided missile with a sleeve-shaped missile body, at least one engine for generating forward thrust, a flight direction control device, and an aerodynamic extension. The flight direction control device is rotatably mounted on an upper region and / or a lower region of the sleeve-shaped missile body for adjusting a flight direction of the guided missile. The aerodynamic extension has an aerodynamic cross-sectional shape arranged on a left side and / or a right side of the sleeve-shaped missile body.

[0005] DE 10 2004 029 487 B4 relates to an aircraft having a fuselage with a landing gear arranged on the underside of the fuselage and with an upper side of the fuselage arranged opposite thereto, wherein - a weapon carrier device is arranged on the upper side of the fuselage, - the weapon carrier device is arranged above the landing gear bays of the main landing gear and above an engine flow channel, viewed in the cross-section of the fuselage at the location of a main landing gear, - the aircraft has a flight computer device with a control and mission function and an actuating device for moving control surfaces for controlling the aircraft, wherein the control and mission function has a flight guidance function for guiding the aircraft to a target point or drop-off point and a weapon drop-off function for dropping at least one weapon that can be carried in the weapon carrier device based on a specification,- the aircraft has a function assigned to the control and mission functions, respectively, and a flight attitude sensor system with which the aircraft can be rotated about its longitudinal axis so that a component of the resulting lift force from the underside of the fuselage runs against the direction of gravity, and - an altitude sensor is assigned to the flight computer device, and the control and mission function has a terrain-following flight function based on the altitude data determined by the altitude sensor.

[0006] Alternatively, guided missiles can be launched from the cargo bays of transport aircraft. For this purpose, the missiles can be dropped from the air, for example, in a metal transport rack using a parachute according to the appropriate standard. Here, too, mission and control data are usually transmitted to the missile in advance via cable. For example, breakaway connectors can be used to disconnect the data connection during launch.

[0007] A disadvantage of state-of-the-art methods and systems for launching guided missiles is that data cables can be damaged, and after launch, no data can be transmitted to the missile. Mechanical triggers can jam or be triggered inadvertently, which also applies to wireless data transmission via radio waves, particularly since these can inadvertently transmit data to an indefinite number of guided missiles simultaneously. Furthermore, with state-of-the-art methods, the launch frequency, capacity, and number of launchable guided missiles are limited by the respective technical conditions. Description

[0008] The objective can be considered to be to provide an improved delivery system and method for the air delivery of guided missiles, such as cruise missiles, drones, or similar. In particular, the objective can be to simplify the handling of air-delivered guided missiles while simultaneously making them safe and reliable. Another objective can be to increase delivery capacities.

[0009] This object is achieved by the subject matter of independent claim 1 and the subordinate claims 9 and 10. Further embodiments emerge from the dependent claims and from the following description.

[0010] In particular, the object is achieved by a method for controlling at least one guided missile to be launched from an aircraft during flight, wherein at least one mission command is transmitted from the aircraft to the guided missile by means of a light signal.

[0011] In the case of a guided missile, the problem is solved in particular by the missile being designed to carry out a corresponding procedure.

[0012] In the case of an aircraft, the task is solved in particular by the aircraft being designed to carry out a corresponding procedure.

[0013] A corresponding delivery system can comprise a corresponding guided missile, a corresponding aircraft, and / or a corresponding data processing device. The method can therefore be carried out by a data processing device or with the aid of a computer, which can be implemented as a control unit, computing device, and / or server. A computer program can comprise instructions which, when executed by a data processing device or a computer, cause the computer to carry out the method. A computer-readable storage medium, a computer-readable data carrier, and / or a data carrier signal can store or transmit the computer program. A corresponding computer-readable data carrier can be present as a computer-readable medium and / or data carrier signal.

[0014] The guided missile may include an optical transceiver. The optical transceiver may be arranged on the guided missile in such a way that it is capable of receiving and / or transmitting light signals from the aircraft even after the guided missile has been launched.

[0015] For example, the transceiver can be arranged on top of the guided missile.

[0016] A weapons bay and / or cargo bay of the aircraft can be configured to accommodate the guided missile and equipped with a transceiver for transmitting light signals to the guided missile and / or receiving light signals from the guided missile. Alternatively or additionally, the transceiver can be mounted in an external area of ​​the aircraft such that light signals can be transmitted to and / or received from the guided missile after it has been launched.

[0017] In this way, data can be transmitted wirelessly to a large number of guided missiles, preventing mechanical errors during launch and increasing launch capacity. The respective transceivers can be targeted by light signals and / or masked if necessary to prevent reception of the light signal, which can contribute to improving the technical security of data transmission. Unlike radio connections, data transmitted by light signals cannot be intercepted or manipulated outside the transmission range, such as in a cargo hold, thus increasing the information security of data transmission.

[0018] According to one embodiment of the method, it can be provided that the at least one mission command is transmitted before and / or after launch. For example, the at least one mission command before launch can serve the guided missile as a general mission specification, with which a large portion of mission data, a selection of mission data, and / or a plurality of missions are or will be transmitted to the guided missile. After launch, the at least one mission command can complete, complement, correct, and / or serve to select a mission. Thus, data transmission can be designed flexibly, eliminating the need for radio transmission of commands, thus avoiding the associated sources of error.

[0019] According to one embodiment of the method, the at least one mission command can include a control command for the guided missile. For example, the at least one mission command can be linked to at least one control command, or vice versa. This further helps to design the data transmission flexibly and eliminates the need for radio transmission of commands, thus avoiding associated sources of error.

[0020] According to one embodiment of the method, the light signal can be transmitted to a transceiver integrated into the guided missile before and / or after launch. The integrated transceiver can ensure a seamless data connection between the aircraft and the guided missile before and / or after launch, with transceivers located inside or outside the aircraft on the aircraft side establishing the data connection. This also helps to ensure flexible and secure data transmission, eliminating the need for radio command transmission.

[0021] According to one embodiment of the method, the light signal can be transmitted to a transceiver temporarily connected to the guided missile prior to launch. The transceiver temporarily connected to the guided missile can be connected to the missile, for example, via a plug connection. This plug connection can be automatically released when the guided missile is launched. This allows data to be transmitted to and received from the guided missile securely and precisely, particularly within the aircraft.

[0022] According to one embodiment of the method, the at least one mission command can be part of at least one mission data set for a mission of the guided missile. A plurality of mission data sets can be transmitted to the guided missile according to a respective plurality of missions. This further contributes to a flexible and secure data transmission, whereby the transmission of commands via radio can be dispensed with.

[0023] According to one embodiment of the method, it can be provided that the at least one mission command for the guided missile is transmitted in an individually encrypted manner. Thus, the at least one mission command can be transmitted specifically to at least one predetermined guided missile. This increases both the safety and the capacity and frequency of launching guided missiles from the cargo bays of transport aircraft.

[0024] According to one embodiment of the method, it can be provided that a plurality of guided missiles to be deployed simultaneously and / or successively receive at least one mission command via a light signal. Thus, the guided missiles can be successively prepared for deployment and / or deployed simultaneously in a predetermined sequence, individually or in small groups or pairs. This helps to increase the capacity and frequency of deploying the missiles from the cargo bays of transport aircraft.

[0025] Alternatively or additionally, the object is achieved by a method for controlling at least one guided missile to be launched from an aircraft during flight, wherein at least one control command is transmitted from the aircraft to the guided missile by means of a light signal.

[0026] According to one embodiment of the method, the at least one control command can be transmitted before and / or after deployment. For example, the at least one control command before deployment can place the guided missile into a standby mode for deployment, or similar. After deployment, the at least one control command can inform the guided missile of the deployment. This eliminates the need for radio transmission of commands, thus avoiding the associated sources of error.

[0027] According to one embodiment of the method, the at least one control command can comprise an activation instruction for the guided missile. After launch, the at least one control command can activate the guided missile via the control unit to begin its mission. This eliminates the need for mechanical triggers and associated error sources.

[0028] According to one embodiment of the method, it can be provided that the light signal is transmitted after launching, and that the activation instruction instructs the guided missile to activate its propulsion unit. Thus, the propulsion unit can be activated from the aircraft at a predetermined time. This can, for example, help eliminate the use of launching racks and / or parachutes, which could impair the speed and orientation of the guided missile after launching, which would have to be compensated for by the guided missile following its detachment from the launching rack and / or parachute. This improves the efficiency of the launching process. The capacity and frequency of launching guided missiles from cargo bays of transport aircraft can be increased.

[0029] According to one embodiment of the method, the guided missile can be essentially inactive before receiving the at least one control command. Thus, the guided missile can be in a kind of sleep mode before receiving the at least one control command. This helps to increase safety during deployment.

[0030] According to one embodiment of the method, the at least one control command can comprise a mission command for a guided missile mission and / or be part of a mission data set for the mission. Thus, mission details can be specified and / or communicated before and / or after the launch, such as a launch altitude, launch speed, weather conditions, mission updates, mission assignments, trajectory data and / or changes to a planned trajectory of the guided missile, or similar. This helps to increase the flexibility of launch operations and boost the capacity and frequency of launching missiles from cargo bays of transport aircraft.

[0031] According to one embodiment of the method, it can be provided that the at least one control command for the guided missile is transmitted in an individually encrypted manner. Thus, the at least one control command can be transmitted specifically to at least one predetermined guided missile. This increases both the safety and the capacity and frequency of launching guided missiles from the cargo bays of transport aircraft.

[0032] According to one embodiment of the method, it can be provided that a plurality of guided missiles to be deployed simultaneously and / or successively receive at least one control command via a light signal. Thus, the guided missiles can be deployed successively in a predetermined sequence, individually or in small groups or pairs simultaneously. This helps to increase the capacity and frequency of missile deployment from the cargo bays of transport aircraft.

[0033] Alternatively or additionally, the object is achieved by a receiving device for guided missiles for airborne deployment from aircraft, wherein the receiving device comprises a container with a receptacle for at least one guided missile, which is designed to disintegrate in a predetermined manner by an air flow prevailing during airborne deployment.

[0034] In the case of a depositing device, the object is achieved in particular in that the depositing device has a corresponding receiving device and / or is designed to interact with the receiving device.

[0035] Through disintegration, the guided missile contained in the container can be released. In other words, the container is separated from the guided missile through its disintegration. Disintegration preferably occurs passively, i.e., without active intervention on the part of the guided missile and / or the receiving device or the container. Alternatively or additionally, active disintegration aids can be provided to initiate, promote, and / or complete disintegration of the container. These disintegration aids can be triggered, for example, by control signals and / or by the air flow and can contain pressure containers, explosives, or similar, whereby an effect that at least partially disintegrates the container can be achieved.

[0036] The deployment device can provide at least one deployment track and / or at least one compartment, preferably a plurality of compartments arranged side by side and / or one above the other, for containers for receiving guided missiles, from which the containers can be deployed. The deployment device can comprise a frame that forms the compartments. From the frame, the guided missiles and / or the containers receiving them can be deployed, for example, onto respective deployment tracks. A deployment track can comprise or have a material with increased lubricity, be coated and / or covered therewith, at least in sections, to promote the sliding of containers with guided missiles from the deployment device.

[0037] The solution according to the invention has the advantage that the container, including the guided missile, can be deployed in flight and detaches from the missile in the process, without the need for additional aids such as parachutes or the like. The container can therefore be used both for transporting and for deploying the guided missile. The receiving device can encompass the container and / or be designed as such. This means that the container itself can form the receiving device. This helps to improve the airborne delivery of guided missiles, such as cruise missiles, drones, or the like. In particular, the handling of airborne guided missiles can be simplified and, at the same time, made safe and reliable.

[0038] According to one embodiment of the receiving device, it can be provided that an inner contour of the receiving device corresponds, at least in part, to an outer contour of the at least one guided missile. The receiving device can be designed as a negative mold of a casing of the guided missile or complementary to the guided missile. The receiving device can be formed in a receiving part and / or in a cover part of the container. In this way, the guided missile can be received in the container with as close a fit as possible. This promotes transport protection for the guided missile, which further simplifies its handling.

[0039] According to one embodiment of the receiving device, an attack zone can be formed on the container, which faces in a flight direction of the aircraft and / or the guided missile and is designed to promote disintegration of the container by an airflow prevailing during deployment. The attack zone can be arranged on the container in such a way that the container advantageously tears open and releases the guided missile with as little residue as possible. This simplifies deployment and increases deployment capacities and frequencies.

[0040] According to one embodiment of the receiving device, the attack zone can be provided to taper from a front side of the container toward the receptacle. The attack zone can thus be designed to appropriately concentrate an air flow prevailing during deployment in such a way as to generate a dynamic pressure that induces or promotes disintegration of the container. This can further facilitate the tearing open of the container and the release of at least one guided missile with as little residue as possible.

[0041] According to one embodiment of the receiving device, the engagement zone can be configured, at least in sections, to be wedge-, pyramid-, conical-, and / or truncated-cone-shaped. Such a configuration of the engagement zone can be selected according to the respective requirements in order to generate and direct a dynamic pressure as desired, which induces or promotes disintegration of the container. This can further facilitate the rupture of the container and the release of at least one guided missile with as little residue as possible.

[0042] According to one embodiment of the receiving device, a centerline of the attack zone can be arranged substantially parallel to and / or on a center axis of the container. The attack zone can be designed symmetrically to the center axis of the container. This can promote the most uniform and balanced disintegration of the container and its detachment from the guided missile, ideally without negatively affecting its trajectory after release.

[0043] According to one embodiment of the receiving device, at least one predetermined breaking point, which promotes disintegration, and / or a passage for passing a transmission medium, cable, and / or light signal from outside the container into its receptacle can be formed on the container. Furthermore, at least one notch in the form of a recess and / or a cutout can be formed on the container to allow attachment of aids, such as lifting and / or lashing devices, for transporting the container together with the guided missile contained therein. The predetermined breaking point, passage, and / or notch can improve the handling of the guided missile and help promote the desired disintegration of its container.

[0044] According to one embodiment of the receiving device, the container can be made, at least in sections, from a lightweight material that disintegrates itself due to the air flow. Lightweight materials can be, for example, paper, cardboard, papier-mâché, fiber materials, foams, and / or other lightweight materials, ideally without the use of heavy, rigid, and / or hard materials such as metal parts. The material of the container can be formed, at least in sections, with honeycombs, porous, ribbed, corrugated, and / or honeycomb structures with the formation of cavities. On the one hand, this facilitates the handling of the container itself. On the other hand, it prevents the container from causing damage upon impact with the ground after it has been set down and disintegrated. Furthermore, the disintegration itself is promoted. Short description of the characters

[0045] Some details are described in more detail below using the attached drawings. The illustrations are schematic and not to scale. Like reference numerals refer to like or similar elements. They show: Fig. 1 a schematic perspective view of an air delivery system with an aircraft and guided missiles that can be launched from it. Fig. 2 a schematic sectional view of a container for guided missiles along a Fig. 4 shown section line AA. Fig. 3 a schematic sectional view of the guided missile container along a Fig. Section line BB shown in Figure 5. Fig. 4 a schematic side view of the guided missile container. Fig. 5 a schematic rear view of a container for guided missiles. Fig. 6 a schematic rear view of the air delivery system with the aircraft ready to deliver the guided missiles. Fig. 7 a schematic perspective view of the air delivery system with the guided missile launched from the aircraft. Detailed description

[0046] Fig. 1 shows a schematic perspective view of an air-drop system 1 with an aircraft 2 and guided missiles 3 launchable therefrom, extending in a longitudinal direction X, a transverse direction Y, and an elevation direction Z, which together form a Cartesian coordinate system. To control the air-drop system 1, at least one data processing device 4 is provided, with the aid of which control data sets S with control commands T and / or mission data sets M with mission commands N can be processed in the form of computer-readable instructions. The aircraft 2 and / or the guided missile 3 can carry out an air-drop procedure and missions with the aid of the computer program 4 on the basis of the corresponding computer-readable instructions contained therein.

[0047] The computer program 5 can be stored, at least in sections, on a computer-readable data carrier 6 and can define a control data set S described therein with control commands T, a mission data set M with mission commands N, as well as other data sets, parameters, identifiers, keys, and / or process steps, as well as regulate their generation, use, and / or handling. The computer-readable data carrier 6 can be present as a computer-readable medium 7 and / or data carrier signal 8. In particular, the data carrier signal 8 can be designed to be bidirectionally transmittable via light signals, cable connections, and other wired and / or wireless transmission means 9, as well as communication networks between the aircraft 2 and the guided missile 3.

[0048] Control units 10 of the airborne drop system 1 can be configured as data processing devices 4 and / or comprise these and optical transceivers 11, or can be connected to them for data transmission at least via respective data transmission means 9. The control units 10 can further comprise a control unit 12 and a data storage unit 13. With the aid of the control unit 12, functions and components of the aircraft 2 and / or the guided missile 3 can be controlled, in particular based on corresponding mission data sets M, mission commands N, control data sets R, and / or control commands R, which can be stored in the data storage unit 13. Accordingly, the respective control unit 10 in the aircraft 2 and / or guided missile 3 can function as a data source Q or transmitter and / or as a data sink R or receiver.

[0049] The aircraft 2 has, for example, a fuselage 20 with a cargo bay 21 designed as a cargo hold for guided missiles 3. In Fig. 2 shows a part of the fuselage 21 including the cargo compartment in a schematic sectional view along a plane extending parallel to the longitudinal direction X and the vertical direction Y and extending above the guided missile 3 arranged in the cargo compartment 21. The cargo compartment 21 has an opening 22 facing opposite a flight direction F of the aircraft 2 and / or the guided missile 3, which opening is designed to be closable with a flap 23. In the present example, a plurality of guided missiles 3 are arranged in the cargo compartment 21, namely two rows of three guided missiles 3 each, spaced apart from one another in the transverse direction Y.

[0050] In the cargo hold 21, the transceivers 11 provided on the aircraft can be arranged in such a way that they can exchange data with the guided missiles 3 via light signal L, in particular corresponding mission data sets M, mission commands N, control data sets R and / or control commands R. In the present example, the transceivers 11 are laid out between the two rows of guided missiles 3. Each transceiver 11 assigned to the aircraft 2 corresponds to two transceivers 11 of a respective guided missile 3. Thus, an aircraft-side control unit 10 designed as a main computer H (master) can communicate with at least one guided missile-side control unit 10 designed as a satellite computer I (slave), for example with a plurality of guided missile-side control units 10 simultaneously. The communication can be carried out for each guided missile 3 with an individual encryption V orbe provided with a corresponding key and thus secured.

[0051] For example, the transceivers 11 of the aircraft 2 are arranged in a chain along the guided missiles 3 or between the rows of guided missiles 3. The individual transceivers 11 of the aircraft 2 can be connected to one another and to the control unit 10 using transmission means 9 in the form of cables K. The control unit 10 serves, at least temporarily, as a data source Q on the aircraft side for the control units 10 of the guided missiles 3, which are at least temporarily configured primarily as a data sink R. The transceivers 10 can be provided with data interfaces and / or buses, such as USB or similar, corresponding to the respective requirements, both on the aircraft side and on the guided missile side, via plug-in connections. In this way, the transceiver 11 can be removably attached to the aircraft 2 or its control unit 10 and / or to the guided missile 3 or its control unit 11.

[0052] The guided missile 3 has an outer shell 30 that can accommodate its control unit 10. The guided missile 3 can have a propulsion unit 31, for example, a jet and / or rocket engine, and flight aids 32, for example, in the form of wings and / or fins, which can be controlled or regulated by the control unit 10 using appropriate drives and / or actuators (not shown). In the present example, the guided missile is accommodated in a receiving device 40 such that it can be released from the cargo compartment 21 via the flap 23 from the opening 22 during flight, opposite the direction of flight F.

[0053] Fig. Figure 2 shows a schematic sectional view of a container 41 for guided missiles 3 as a possible part of the receiving device 40 along a Fig. 4 shown section line AA. The container 41 has a receiving part 42 with a trough-like receptacle 43 formed therein, which is covered by a lid-like cover part 44 (see Fig. 3 to 5). The receptacle 43 can essentially be designed as a negative mold of the casing 30 of the guided missile 3. Thus, the guided missile 3 can be embedded in the container 41 in a virtually form-fitting manner.

[0054] The container 41 can essentially comprise and / or consist of materials that, on the one hand, are capable of enclosing the guided missile 3 in a protective manner against external influences and, in particular, of protecting it from transport damage. On the other hand, appropriate materials can be selected such that the container 41 allows it to be released from the aircraft 2 with the guided missile 3 contained therein. Thus, the materials, design, and / or structure of the container 41 can enable its independent detachment from the guided missile 3 as quickly as possible after release.

[0055] For example, the container 41 can be made of paper, cardboard, papier-mâché, fiber materials, foams, and / or other lightweight materials, and, if possible, without the use of heavy, rigid, and / or hard materials, such as metal parts. Lightweight materials have the advantage that, after being released from the aircraft 2, they cause little or no damage when they hit the ground. In particular, the materials can decompose upon settling. In other words, the container 41 can be designed such that it is disintegrated by air currents upon settling. To promote its disintegration, the material of the container 41 can be formed, at least in sections, with honeycombs, porous, ribbed, corrugated, and / or honeycomb structures with the formation of cavities.

[0056] Attack zones 45 can be formed on the container 41, for example, pointing in the direction of flight F and promoting disintegration of the container 41 by appropriately directing air streams impinging on the container 41 opposite to the direction of flight F. For example, an attack zone 45 can be formed on a front side 46 of the container 41 pointing in the direction of flight F. For example, the attack zone 45 can be conical, with a base of the cone pointing in the direction of flight F and its tip pointing toward the receptacle 43. A central axis of the cone can run along a central axis C of the container 41.

[0057] For example, the attack zone 45 can be designed such that, upon deployment, it concentrates a dynamic pressure generated by the airflow in the structure of the container 41 in such a way that the container disintegrates as quickly and efficiently as possible and is thereby detached from the guided missile 3. In any case, it can be advantageous if the attack zone 45 tapers toward the receptacle 43, opposite to the direction of flight F. For this purpose, the attack zone 45 can be wedge-shaped, conical, truncated cone-shaped, and / or pyramid-shaped.

[0058] Furthermore, predetermined breaking points 47, passages 48, and / or recesses 49 can be arranged or formed on the container 41. Predetermined breaking points 47 and / or passages 48 can be arranged in combination as cuts, slits, planes, and / or weak points in such a way that, on the one hand, they promote disintegration of the container 41 upon setting down and, on the other hand, they enable the passage of transmission media 9, cables K, and / or light signals L through a wall from outside the container 41 into or out of the receptacle 43. Thus, the predetermined breaking points 47 and / or passages 48 can be arranged correspondingly to the attack zone 45 in such a way that they facilitate disintegration of the container and / or access to the guided missile 3 accommodated in the receptacle 43 for control devices 10 and / or transceivers 11 to be arranged outside and / or inside the container 41.

[0059] For example, the predetermined breaking points 47 and / or passages 48 can extend parallel and / or obliquely to the central axis C and / or flight direction F and / or form a connection or passage between the attack zone 45 and the receptacle 43. Thus, a symmetrical arrangement of the predetermined breaking points 47 and / or passages 48 can help to distribute the forces acting on the container 40, particularly during deployment, as evenly or symmetrically as possible, for example, with respect to the central axis C, so that the container 41 is regularly detached from the guided missile 3. Thus, the container 41 can literally tear open, particularly in the area of ​​the predetermined breaking points 47 and / or passages 48, and release the guided missile 3. The recesses 49 can also be arranged symmetrically on the container 41 and serve to accommodate loading aids (not shown), such as hooks, lifting equipment, lashing equipment, fork tines of forklift trucks, or the like.to be inserted into the container 41, attached to the guided missile 3 and / or supported on it or underneath it.

[0060] Fig. Figure 3 shows a schematic sectional view of the container 41 for guided missiles 3 along a Fig. 5. Here it is clear that any predetermined breaking points 47 and / or passages 48 can also be provided and / or formed in the cover part 44 now placed on the receiving part 42. For example, the incisions 49 are provided in such a way that the forks of a forklift truck (not shown) can be guided under the guided missile 3. Alternatively or additionally, a dividing line between the receiving part 42 and the cover part 44 can run, for example, along the central axis C. In order to gain access to the guided missile 3 arranged in the receptacle 43, the cover part 43 can be completely or partially removed, for example by providing recesses, plugs and / or closures (not shown) in the region of predetermined breaking points 47, passages 48 and / or incisions 49 in such a way that they allow direct access to the receptacle or partial removal or opening of the container 41.

[0061] Fig. 4 shows a schematic side view of the container 41 for guided missile 3. Fig. Figure 5 shows a schematic rear view of a container 41 for guided missiles 3. It is clear here that the container 41 can be configured essentially cuboidally. This can help simplify the manufacture, handling, stowage, and / or deployment of the container 41. Furthermore, the container can be sealed, coated, packaged, or treated in any other desired manner, internally or externally, to meet specific requirements.

[0062] Fig. Figure 6 shows a schematic rear view of the air-delivery system 1 with the aircraft 2 ready to deliver the guided missiles 3. Thus, during flight, the hatch 23 to the cargo compartment 21 or any other carrier or receiving compartment for the guided missiles 3 can be opened. The guided missiles 3 or the containers 41 of the receiving device 40 that receive them are visible through the opening 22. The receiving device 40 can form a delivery device 50 or merge into it. For example, a combined receiving and / or delivery device 40, 50 can be provided.

[0063] The receiving and / or depositing device 40, 50 can form at least one compartment 51 for guided missiles 3 or containers 41 receiving them. For example, a plurality of compartments 51 are provided, which can be arranged next to, above, and / or below one another. In this way, a plurality of guided missiles 3 or containers 41 receiving them can be deposited simultaneously or in a predetermined sequence. The depositing device can have depositing tracks 52 over which the guided missiles 3 and / or containers 41 receiving them can slide out of the receiving and / or depositing device 40, 50, counter to the direction of flight F.

[0064] For example, the landing tracks 52 can be arranged on the flap 23 and / or integrated therein. Guide elements 53 can be provided which at least partially delimit a landing path for the guided missiles 3 and / or the containers 41 receiving them. For example, the guide elements 53 can be designed as guide rails which laterally delimit the landing tracks in order to support or guide the guided missiles 3 and / or the containers 41 receiving them, particularly in and against the transverse direction Y, during landing. The landing track can be provided with or coated with a material that promotes sliding, for example certain plastics such as Teflon or the like.

[0065] Fig.7 shows a schematic perspective view of the air delivery system 1 with the guided missile 3 released from the aircraft 2. During release, the guided missile 3 may initially be in a resting state. After release, the container 41 can detach from it and / or the guided missile 3 can receive a control command T, for example in the form of an activation instruction U, preferably via a light signal L, which can be sent, for example, from a transceiver 11 mounted inside and / or outside the aircraft 2 to the guided missile 3 so that the latter receives it using its transceiver 11. The activation instruction U can activate the guided missile 3 and, for example, cause it to start its mission. Through the activation, the guided missile can activate its propulsion unit 31, for example by igniting its engine. In addition, flight aids 32 can be brought into a flight position orintervene in the flight path of the guided missile 3 by being extended or moved in some other way to influence the flight path of the guided missile 3. List of reference symbols 1 air settling system 2 Vehicle / Aircraft 3 guided missiles 4 Data processing facility 5 computer program 6 computer-readable data carrier 7 computer-readable medium 8 Data carrier signal 9 Transmission means 10 Control unit 11 Transceiver (optical) 12 Control unit 13 Data storage unit 20 hull 21 cargo space 22 Opening 23 flap 30 cover 31 Drive unit 32 Flight assistance 40 Recording device 41 container 42 Recording part 43 recording 44 Cover part 45 Attack zone 46 Front 47 Predetermined breaking point 48 passage 49 Notch / Recess 50 settling device 51 compartment 52 settling track 53 Guide element C Central axis F Flight direction H Main computer / Master I Satellite computer / Slave K Cable L light signal M Mission Data Set N Missionary Order Q Data source / transmitter R Data sink / receiver S tax data record T control command U Activation instruction X Longitudinal direction Y transverse direction Z Altitude direction QUOTES CONTAINED IN THE DESCRIPTION

[0000] This list of documents submitted by the applicant was generated automatically and is included solely for the convenience of the reader. This list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions. Cited patent literature

[0000] EP 4 060 282 B1

[0004] DE 10 2004 029 487 B4

[0005]

Claims

[1] Method for controlling at least one guided missile (3) to be released from an aircraft (2) during flight, characterized by , that at least one mission command (N) is transmitted by light signal (L) from the aircraft (2) to the guided missile (3). [2] Method according to claim 1, characterized by , that at least one mission order (N) is transmitted before and / or after deployment. [3] Method according to claim 1 or 2, characterized by , that at least one mission order (N) includes a control order (T) for the guided missile (3). [4] Method according to at least one of claims 1 to 3, characterized by , that the light signal (L) is transmitted to a transmitter receiver (10) integrated into the guided missile (3) before and / or after deployment. [5] Method according to at least one of claims 1 to 4, characterized by, that the light signal (L) is transmitted to a transmitter receiver (10) temporarily connected to the guided missile (3) before release. [6] Method according to at least one of claims 1 to 5, characterized by , that at least one mission order (N) is part of at least one mission data set for a mission of the guided missile (3). [7] Method according to at least one of claims 1 to 6, characterized by , that at least one mission order (N) for the guided missile (3) is transmitted in an individually encrypted form. [8] Method of at least one of claims 1 to 7, characterized by , that a large number of guided missiles (3) to be launched or launched simultaneously and / or successively each receive at least one mission order (N) by light signal (L). [9] Guided missile (3), characterized by that it is designed to carry out a process according to at least one of claims 1 to 8. [10] aircraft (2), characterized by that it is designed to carry out a method according to at least one of claims 1 to 8.

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