Method for Controlling Guided Missiles, and Guided Missile, and Aircraft

This application claims the benefit of German Patent Application Number 102024110249.7 filed on Apr. 12, 2024, the entire disclosure of which is incorporated herein by way of reference.

The present disclosure relates to a method for controlling at least one guided missile to be launched by an aircraft during flight, to a guided missile, and to an aircraft.

Guided missiles, in particular cruise missiles, can be launched from aircraft in order to then move independently to a target based on their pre-determined mission data and their internal control. Launching is usually carried out from pylons attached externally to corresponding aircraft or platforms. The mission and control data can be transmitted, for example, before or after fastening the guided missile to the respective pylon by a data connection to the guided missile established via cable.

A mechanical trigger which is installed on the guided missile, such as a contact pin or anchor cable connected to an electrical sensor or switch, can signal to the guided missile's control that it is fastened to the pylon. Alternatively, the guided missile can be accommodated in an aircraft weapon bay. As soon as the guided missile is detached from the pylon or ejected from the weapon bay, the mechanical sensor of the control of the guided missile signals that it now has to undertake its mission, by which it ignites its engine, for example, moves any wings into flight position, etc.

EP 4 060 282 B1, for example, relates to a guided missile having 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 rotationally mounted on an upper and/or lower region of the sleeve-shaped missile for the adjustment of a flight direction of the guided missile. The aerodynamic extension has an aerodynamic cross-sectional shape, which is disposed on a left side and/or a right side of the sleeve-shaped missile body.

DE 10 2004 029 487 B4 relates to an aircraft having a fuselage with a launching gear disposed on an underside of the fuselage and, disposed opposite thereto, with a fuselage upper side, wherein—on the fuselage upper side a weapon carrier device is disposed,—the weapon carrier device, when viewed in the cross section of the fuselage at the location of a main launching gear, is disposed above launching gear wells of the main launching gear and above an engine flow duct,—the aircraft has a flight computer installation with a control and mission function as well as an actuating installation for the movement of 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 launching point and a weapon launching function for launching at least one weapon which can be carried in the weapon carrier device based on a specification,—the aircraft has a function respectively assigned to the control and mission function and a flight position sensor technology by way of which the aircraft can be rotated about its longitudinal axis to the degree that a component of the resulting lift force runs from the underside of the fuselage counter to the direction of gravity, and—the flight computer installation is assigned an altitude sensor and the control and mission function has a terrain-tracking flight function based on the altitude data determined by the altitude sensor.

Alternatively, guided missiles can be launched from loading bays of transport aircraft. For this purpose, the guided missiles can be launched for example during flight in a metal transport rack using a parachute according to the corresponding standard. Here, too, mission and control data are usually transmitted in advance via cable to the guided missile. For example, break-off plugs can be used to disconnect the data connection when launching.

In methods and systems for dropping guided missiles known in the prior art, it is disadvantageous that data cables can be damaged and no more data can be transferred to the guided missile after release. Mechanical triggers can be jammed or unintentionally triggered, which also applies to wireless data transmission via radio waves, especially since these can transmit data inadvertently to an undetermined number of guided missiles at the same time. In addition, in the case of methods known in the prior art, the dropping frequency as well as the capacity or number of guided missiles that are able to be launched is restricted by the respective technical conditions.

It can be considered an object to provide an improved launching system and method for launching guided missiles, such as cruise missiles, flying drones, or the like, in the air. In particular, it can be considered an object to simplify the handling of guided missiles to be launched in the air and to design them to be safe and reliable at the same time. It can also be considered an object to increase launching capacities.

This object may be achieved by the subject matter of one or more embodiments described herein.

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

In the case of a guided missile, the object may be achieved in particular in that said guided missile is designed to carry out a corresponding method.

In the case of an aircraft, the object may be achieved in particular in that said aircraft is designed to carry out a corresponding method.

A corresponding launching system can comprise a corresponding guided missile, a corresponding aircraft and/or a corresponding data processing installation. The method can therefore be carried out accordingly by a data processing installation, or with the aid of a computer, which can be implemented as a control apparatus, computer installation and/or server. A computer program can comprise commands which, when the program is executed by a data processing installation or a computer, prompt the latter 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.

The guided missile can comprise an optical transceiver. The optical transmitter can be disposed on the guided missile in such a manner that it is capable of receiving light signals from the aircraft and/or sending light signals to the aircraft even after the guided missile has been launched. For example, the transceiver can be disposed on an upper side of the guided missile.

A weapon bay and/or a loading bay of the aircraft can be designed for receiving the guided missile and can be equipped with a transceiver for transmitting light signals to the guided missile and/or receiving light signals from the guided missile. Alternatively or in addition, the transceiver can be mounted in an external region of the aircraft in such a manner that light signals can be transmitted to and/or received by the guided missile after launching.

In this way, data can be specifically transmitted wirelessly to a multiplicity of guided missiles, thereby avoiding mechanical errors during launching and increasing launching capacities. Respective transceivers can be actuated in a targeted manner by light signal and/or covered if necessary to avoid reception of the light signal, which can contribute toward improving the technical reliability of the data transmission. In contrast to wireless connections, data transmitted by light signals cannot be intercepted or manipulated outside the transmission range, such as a cargo hold, which increases the information security of the data transmission.

According to one embodiment of the method, it can be provided that the at least one mission command is transmitted before and/or after launching. For example, the at least one mission command before launching the guided missile can serve as a general mission specification by way of which a majority of mission data, a selection of mission data and/or a multiplicity of missions are/is transmitted to the guided missile. After launching, the at least one mission command can complete, complement, correct the mission data, and/or serve to select a mission. Thus, the data transmission can be flexibly designed while dispensing with the transmission of commands via radio, thus avoiding the associated sources of error.

According to one embodiment of the method, it can be provided that the at least one mission command comprises 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 furthermore helps to design the data transmission to be flexible and to avoid the transmission of commands by radio, thus avoiding the associated sources of error.

According to one embodiment of the method, it can be provided that the light signal is transmitted to a transceiver integrated in the guided missile before and/or after launching. The integrated transceiver can ensure a seamless data connection between the aircraft and the guided missile before and/or after launching, whereby transceivers disposed within or outside the aircraft can establish the data connection on the aircraft side. This additionally helps to design the data transmission to be flexible and secure, while being able to dispense with the transmission of commands via radio.

According to one embodiment of the method, it can be provided that the light signal is transmitted to a transceiver temporarily connected to the guided missile before being launched. The transceiver temporarily connected to the guided missile can be connected to the guided missile by means of a plug connection, for example. This plug connection can be automatically released when the guided missile is launched. Thus, in particular within the aircraft, data can be securely and specifically transmitted to the guided missile and received from the latter.

According to one embodiment of the method, it can be provided that the at least one mission command is part of at least one mission data set for a mission of the guided missile. A multiplicity of mission data sets can be transmitted to the guided missile so as to correspond to a respective multiplicity of missions. In addition, data transmission is designed to be flexible and secure, while the transmission of commands via radio can be dispensed with.

According to one embodiment of the method, it can be provided that the at least one mission command for the guided missile is transmitted so as to be individually encrypted. Thus, the at least one mission command can be specifically transmitted to at least one predetermined guided missile. Both the safety as well as the capacity and frequency of launching guided missiles from cargo holds of transport aircraft can be increased in this way.

According to one embodiment of the method, it can be provided that a multiplicity of guided missiles to be launched, or launched, simultaneously and/or successively each receive at least one mission command by light signal. Thus, the guided missiles can be prepared for launch and/or launched successively in a predetermined sequence individually, or simultaneously in small groups or as pairs. This helps to increase the capacity and frequency when launching the missiles from cargo holds of transport aircraft.

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

According to one embodiment of the method, it can be provided that the at least one control command is transmitted before and/or after launching. For example, the at least one control command before launching can set the guided missile in a standby mode for the launch or similar. After launching, the at least one control command can inform the guided missile about the launch. This eliminates the need to transmit commands by radio and avoids sources of error associated therewith.

According to one embodiment of the method, it can be provided that the at least one control command comprises an activation instruction for the guided missile. After launching, the at least one control command can activate the guided missile with a view to the latter starting its mission. This allows mechanical triggers to be dispensed with, and the associated sources of error to be avoided.

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 engine unit. Thus, the engine unit can be activated from the aircraft at a predetermined time. This may help, for example, to avoid the use of launching racks and/or parachutes, which could affect the speed and orientation of the guided missile after launching, which would have to be compensated for by the guided missile after its release from the launching rack and/or parachute. The efficiency of the launching procedure can be improved in this way. The capacity and frequency of launching guided missiles from cargo holds of transport aircraft can be increased.

According to one embodiment of the method, it can be provided that the guided missile is substantially 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 launching.

According to one embodiment of the method, it can be provided that the at least one control command comprises a mission command for a mission of the guided missile and/or is part of a mission data set for the mission. Thus, mission details can be defined and/or communicated before and/or after launching, such as, for example, a launching altitude, launching speed, weather conditions, mission updates, mission assignments, flight path data and/or changes of a planned guided missile flight path or similar. This helps to increase the flexibility of launching procedures and increase the capacity and frequency when launching the missiles from cargo holds of transport aircraft.

According to one embodiment of the method, it can be provided that the at least one control command for the guided missile is transmitted so as to be individually encrypted. Thus, the at least one control command can be specifically transmitted to at least one predetermined guided missile. Both the safety as well as the capacity and frequency of launching guided missiles from cargo holds of transport aircraft can be increased in this way.

According to one embodiment of the method, it can be provided that a multiplicity of guided missiles to be launched, or launched, simultaneously and/or successively each receive at least one control command by light signal. Thus, the guided missiles can be launched successively in a predetermined sequence individually, or simultaneously in small groups or as pairs. This helps to increase the capacity and frequency when launching the missiles from cargo holds of transport aircraft.

Alternatively or additionally, the object is achieved by a receptacle device for guided missiles for launching from aircraft in the air, wherein the receptacle device comprises a container having a receptacle for at least one guided missile, which container is designed to disintegrate in a predetermined manner due to an air flow prevalent during launching in the air.

In a launching device, the object may be achieved in particular in that the launching device has a corresponding receptacle device and/or is designed to interact with the receptacle device.

The guided missile received in the container can be released as a result of the disintegration. In other words, the container is separated from the guided missile by its disintegration. The disintegration is preferably passive, i.e., without active intervention on the part of the guided missile and/or the receptacle device or the container. Alternatively or additionally, active disintegration aids can be provided to initiate, promote and/or carry out a disintegration of the container. These disintegration aids can be triggered, for example, by control signals and/or by the air flow and include pressure vessels, explosives or similar, as a result of which an effect that at least partially disintegrates the container can be achieved.

The launching device can provide at least one launching track and/or at least one compartment, preferably a plurality of compartments that are disposed next to one another and/or on top of one another for containers for receiving guided missiles, from where containers can be launched. The launching device can comprise a rack that forms the compartments. The guided missiles and/or their receiving containers can be launched from the rack, for example on respective launching tracks. A launching track can at least in portions comprise or include a material with increased sliding capability, or be coated and/or covered with the latter in order to facilitate containers with guided missiles sliding off the launching device.

The solution according to the invention has the advantage that the container including guided missiles is launched during flight and in the course of this releases itself from the guided missile without requiring further aids, such as parachutes or similar. This means that the container can be used for both transporting and launching the guided missile. The receptacle device can comprise the container and/or be designed as such. This means that the container per se can form the receptacle device. This helps to improve the launching of guided missiles, such as cruise missiles, flying drones, or similar, in the air. In particular, the handling of guided missiles to be launched during flight can be simplified and at the same time designed to be safe and reliable.

According to one embodiment of the receptacle device, it can be provided that an internal contour of the receptacle corresponds at least in portions to an external contour of the at least one guided missile. The receptacle can be designed as a negative shape of a casing of the guided missile, or be complementary to the guided missile, respectively. The receptacle can be formed in a receptacle part and/or in a cover part of the container. In this way, the guided missile can be received in the container so as to be encased ideally in a form-fitting manner. This facilitates a transport protection of the guided missile, which helps to furthermore simplify its handling.

According to one embodiment of the receptacle device, it can be provided that an attack zone is formed on the container, which points in a flight direction of the aircraft and/or of the guided missile and is designed to facilitate disintegration of the container by an air flow prevalent during launching. The attack zone can be disposed on the container in such a way that the container advantageously rips open and releases the guided missile ideally without residue. In this way, launching can be simplified and launching capacities and frequencies increased.

According to one embodiment of the receptacle device, it can be provided that the attack zone tapers from a front of the container in the direction of the receptacle. The attack zone can thus be designed to concentrate an air flow prevalent during launching in a suitable manner in order to generate a back pressure which initiates or facilitates disintegration of the container. Thus, ripping of the container and an ideally residue-free release of the at least one guided missile can be furthermore facilitated.

According to one embodiment of the receptacle device, it can be provided that the attack zone is at least in portions designed to be wedge-shaped, pyramid-shaped, conical and/or frustoconical. Design embodiments of this type of the attack zone can be selected according to the respective requirements so as to generate and direct a back pressure as desired, which initiates or facilitates disintegration of the container. In this way, ripping of the container and an ideally residue-free release of the at least one guided missile can be furthermore facilitated.

According to one embodiment of the receptacle device, it can be provided that a center line of the attack zone is disposed so as to extend substantially parallel to and/or on a central axis of the container. The attack zone can be designed to be symmetrical in relation to the central axis of the container. In this way, an ideally uniform and balanced disintegration of the container and its release from the guided missile can be facilitated, ideally without negatively impacting its flight path after launching.

According to one embodiment of the receptacle device, it can be provided that at least one disintegration-facilitating predetermined breaking point and/or a passage for leading through a transmission means, cable and/or light signal from outside the container is integrally molded on the container in its receptacle. Furthermore, at least one cut-out in the form of a clearance and/or a recess can be formed on the container in order to be able to attach aids thereto, such as lifting and/or lashing means, for transporting the container including guided missiles received therein. Predetermined breaking point, passage and/or cut-out can improve the handling of the guided missile and help facilitate the desired disintegration of its container.

According to one embodiment of the receptacle device, it can be provided that the container is at least partially made of a lightweight material that self-disintegrates due to the air flow. For example, paper, cardboard, paper mâché, fibrous materials, foam materials and/or other lightweight materials can be formed as lightweight materials, ideally without the use of heavy or rigid and/or hard materials, such as metal parts. The material of the container can at least in portions be formed with honeycombs, pore structures, rib structures, wave structures and/or honeycomb structures while forming cavities. On the one hand, this thus facilitates the handling of the container per se. On the other hand, it prevents the container from causing damage after it has been launched and has disintegrated upon hitting the ground. Moreover, the disintegration per se is facilitated.

shows a schematic perspective view of an air launching systemwith an aircraftand guided missileswhich are able to be launched from the latter, which extends in a longitudinal direction X, a transverse direction Y and a height direction Z, which conjointly define a Cartesian coordinate system. For controlling the air launching system, at least one data processing installationis provided, with the aid of which control data sets S with control commands T and/or mission data sets M with mission commands N in the form of computer-readable instructions can be processed. The aircraftand/or the guided missilecan carry out an air launching method and missions with the aid of the computer program, based on corresponding computer-readable instructions contained therein.

The computer programcan be stored at least in portions on a computer-readable data carrierand define a control data set S, described herein, with control commands T, a mission data set M with mission commands N and other data sets, parameters, markings, keys and/or process steps, and manage their generation, use and/or handling. The computer-readable data carriercan be present as a computer-readable mediumand/or data carrier signal. In particular, the data carrier signalcan be designed to be bi-directionally transmittable via light signals, cable connections and other wired and/or non-wired transmission meansand communication networks between the aircraftand the guided missile.

Control apparatusesof the air launching systemcan be designed as data processing installationsand/or comprise these as well as optical transceivers, or be connected thereto in a data-transmitting manner at least by respective data transmission means. The control apparatusescan furthermore comprise a control unitand a data storage unit. With the aid of the control unit, functions and components of the aircraftand/or the guided missilecan be controlled, in particular on the basis of 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. Accordingly, the respective control unitin the aircraftand/or guided missilescan function as a data source Q or transmitter and/or as a data sink R or receiver.

The aircrafthas, for example, a fuselagewith a cargo bay, designed as a cargo hold, for guided missiles. Shown inis part of the fuselageincluding the cargo hold in a schematic sectional view along a plane that extends parallel to the longitudinal direction X and the height direction Y and extends above the guided missiledisposed in the cargo hold. The cargo holdhas an openingfacing opposite a flight direction F of the aircraftand/or the guided missile, which is designed to be closable with a hatch. In the present example, a plurality of guided missilesare disposed in the cargo hold, namely two rows of three guided missilesmutually spaced apart in the transverse direction Y.

In the cargo hold, the aircraft-provided transceiverscan be disposed in such a way that they can exchange data with the guided missilesby a 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 transceiversare set out between the two rows of the guided missiles. One transceiverassigned to the aircraftis in each case two transceiversof in each case one guided missile. Thus, an aircraft-side control apparatusdesigned as a main computer H (master) can communicate with at least one guided missile-side control apparatusdesigned as a satellite computer I (slave), for example with a multiplicity of guided missile-side control apparatusessimultaneously. The communication can be provided with an individual encryption V or a corresponding key for a respective guided missile, and thus be secured.

For example, the transceiversof the aircraftare set out in a chain along the guided missilesor between the rows of the guided missiles. The individual transceiversof the aircraftcan be connected to one another and to the control apparatuswith the aid of the transmission meansin the form of cables K, which serve on the aircraft side at least predominantly as a data source Q for the control apparatusesof the guided missiles, which are at least temporarily predominantly designed as a data sink R. The transceiverscan be provided both on the aircraft and on the guided missile with data interfaces and/or buses corresponding to the respective requirements by way of plug connections, for example, USB or similar. Thus, the transceivercan be releasably attached to the aircraftor its control apparatusand/or to the guided missileor its control apparatus, respectively.