IL213934A

IL213934A - Method for controlling a warshot missile

Info

Publication number: IL213934A
Application number: IL213934A
Authority: IL
Inventors: Thomas Kuhn; Wilhelm Hinding; Andreas Beutel
Original assignee: Diehl Bgt Defence Gmbh & Co Kg; Thomas Kuhn; Wilhelm Hinding; Andreas Beutel
Priority date: 2010-07-08
Filing date: 2011-07-05
Publication date: 2014-12-31
Also published as: EP2405233A3; DE102010052202A1; EP2405233B1; EP2405233A2; IL213934A0

Description

METHOD FOR CONTROLLING A WARSHOT MISSILE Pearl Cohen Zedek Latzer P-75058-1L BP 297 ILN1 IE/HH/ak Diehl B6T Defence GmbH £ Co. KG, Alte NuPdorfer Str. 13, 88662 Uberlingen Method for controllxng a warshot missile The invention relates to a method for controlling a warshot missile which contains a data memory, a control means and a mission component, in which the control means controls the mission component during flight of the warshot missile.

In recent decades, the requirements for rocket artillery have changed existentially . While, previously, soft and semi-hard area targets were the focus for national defence purposes, the dominant requirement is now that it is essential to avoid collateral damage and to be highly flexible with respect to the capability to deploy different payloads. Various types of rocket artillery missiles are controlled in order to deploy different payloads to the target, and are detonated in the proximity of the target, at the target or only shortly after impact. Characteristics of a payload are appropriately programmed into a fire control system such that it can fire the missiles specifically, depending on the payloads.

For this purpose, it is known for a missile which has been inserted into a rocket launcher to be identified by the fire control system and to be classified, for example, on the basis of a type designation. The identification can be carried out by a coded interface, for example a plug shape or the like, such that the fire control system can correctly identify the type of missile that has been inserted into the rocket launcher. A missile mission is calculated, and is transmitted to a control means in the missile, on the basis of the data relating to the appropriate rocket type stored in the fire control system - taking account of target coordinates, weather data and, possibly, further data. After the missile has been fired from the rocket battery, the control means controls the flight of the missile in accordance with the data received from the fire control system, which may include a flight trajectory, a detonation time and further data.

One object of the present invention is to specify a method for controlling a warshot missile, by means of which the warshot missile can be controlled in a simple manner, matched to its mission component.

This object is achieved by a method of the type mentioned initially, in which the data memory contains identification data relating to a plurality of different mission components, and the control means reads type data from the mission component, identifies the type of mission component on the basis of the identification data and the type data and carries out control steps as a function of the type of mission component .

In this case, the invention is based on the idea that, in the past, carrying out a mission with a new mission component in a warshot missile that is known per se, for example the deployment of a new warhead, was associated with considerable complexity, because characteristics of the mission component had to be newly integrated in the fire control system and, in particular, had to be qualified. Before the insertion of a new mission component into the known warshot missile, the computer systems of the fire control system therefore have to be supplied with the type data relating to the new mission component, and this process had to be qualified to such an extent that a check is carried out that the algorithms, stored in the fire control system, for calculation of control data for controlling the missile would function correctly with the new type data and in every combat situation. When there are a multiplicity of different mission components, such integration and qualification in different fire control systems is associated with a very large amount of effort. This greatly restricts the flexibility for example of the rocket artillery, for alternative warhead variants.

This problem is solved by the invention in that the production of control data for controlling the mission component can be moved from the fire control system to the control means in the warshot missile. Control data such as this may be data for controlling the flight path of the missile, data for initiating a warhead, data for controlling a firing angle, and the like. In this case, the type data relating to the mission component need not be integrated and qualified in the fire control system, but can be moved to the level of the warshot missile. The tasks of the fire control system can be simplified to the transmission of mission data to the missile, as a result of which the fire control system no longer has to process the specific type data relating to the mission component. The fire control system for a modular artillery rocket system, by way of example, now need know only a single munition type, specifically the generic type of missile, for example the · modular artillery rocket. By way of example, this can deploy different payloads in different warheads, with the control means in the missile being programmed and the data memory in the missile containing data such that it is possible for the control means to calculate the control steps matched to the warhead.

- A - In order to ensure such modularity of the missile, the data memory contains identification data relating to a plurality of different mission components. Identification data is data which the control means can use to identify the type of mission component, for example by comparison of type data relating to the mission component with the identification data. The identification data may be identical to the type data, as a result of which, for example, the type designation is compared with a list of type designations for identification. The type data may be any form of information which identifies the type of mission component. Type data can be detected particularly easily by the control means if it is stored in a data storage means in the mission component and is read by the control means or is transferred to the control means. However, type data may also be hardware information, such as an interface characteristic, for example a plug shape.

The type of mission component is identified by the control means, and the control means is able to use control data in the data memory, which is associated with the corresponding identification data relating to the mission component, and/or control data in the data storage means in the mission component, to suitably configure the algorithms which are stored generically in the control means or data memory, for example for guidance, control and/or mission control, for . the mission component used in the missile. The control steps are correspondingly calculated as a function of the type of mission component with the aid of the control data, and are implemented by the control means during the missile mission. In this case, it is also expedient for the control means to calculate the control steps as a function of the combination of different mission components, in which case the mission components may be mission components that are known from the start or are likewise initially unknown to the control means, as a result of which they must first be identified on the basis of the type data.

For identification, it is sufficient for the control means to identify one of a plurality of type groups of mission components. For example, a completely new mission component may be used, which is not yet known by the control means. Nevertheless, communication can be set up between the control means and the mission component by association with a type group, and the control means can receive data from the mission component for more extensive communication or for calculation of the control steps.

The warshot missile is expediently a missile with a warhead for destruction of a target, in particular a combat rocket, for example a surface-launched rocket, that is to say a surface-to-surface rocket or a surface-to-air rocket, or a sea-borne or air-borne rocket.

The control process and the control steps may be steps for mission control, such as steps for controlling the direction of flight of the missile and/or steps for controlling operation of a mission component, for example for deployment of a warhead, steps for communication with other units, for example for determination of control data, calculation steps for determination of control data, and so on. The control means or the data memory advantageously contains generically stored algorithms for the control steps, and the control means configures these algorithms■ with control data, or directly with the type data.

In one advantageous embodiment of the invention, the warshot missile contains at least one mission component from the group comprising rocket motor, warhead, homing head, fuselage and wing structure. The warshot missile may therefore contain one or more such mission components, which identifies and controls as stated. Each mission component expediently contains a data storage means, which contains the type data and possibly further data, such as operating data or usage data. The data storage means may be pure data memory means, such as ROM, or a control means with a processor .

The identification data stored in the data memory may be subdivided into component groups, for example the component group for the rocket motors, the component group for the warheads, the component group for the homing heads, and the component group for the fuselage and wing structures. Each component group may contain one or more mission components in the same group. For complete initialization of the warshot missile, the control means can check whether a mission component has been provided and identified for each component group and whether the corresponding software component of the control means has been configured, for example on the basis of the type data, such that each mission component is ready to operate.

A further advantageous embodiment of the invention provides that the control means controls the missile on a flight path, and in the process controls the combat component, for example initiates the warhead.

Another embodiment variant of the invention provides that the control means uses the type data relating to the mission component to select data, and transmits this data to a- control unit outside the missile. The-transmitted data can be taken from the data memory or can be produced from such data by the control means, or can be read from the mission component or its data storage means. This allows the fire control point to be informed of which mission component or mission components is or are being used in the missile, thus allowing the external control unit, such as a fire control point, to emit appropriate mission commands to the mission components.

It is likewise advantageous for the control means to furthermore use the data to configure an algorithm in the external control unit. The external control unit can therefore easily determine mission data without itself having to configure the relevant algorithm as appropriate for the - possibly unknown - mission components. The data is expediently that data which the external control unit processes in order to create mission commands. By way of example, operating modes which are possible with the mission component, for example detonation modes of a warhead, are advantageous for use as selected data, which the control means has expediently received from the data storage means in the mission component, and passes onto the external control unit .

Advantageously, the control means receives mission data from an external control unit, in particular mission data which the external control unit has calculated as a function of the algorithm configured by the control means. Mission data may be target coordinates, a firing time, constraints for a trajectory and the like.

It is also proposed that mission data, for example target coordinates or general target data, be transmitted to the control means, in particular from a fire control computer, and that the control means uses the mission data to calculate flight data for the missile. The ■ flight data may be data which characterizes the flight of the missile, such as a configuration of the flight path, an approach direction to the target, an initiation point for the warhead, and the like. The fire control computer which previously normally carried out these tasks can be relieved of them, as a result of which it no longer has to be entrusted with type data relating to the mission component, in such a comprehensive manner.

If the control means knows the target of a flight path of the missile, it can determine whether it is possible to fly to the predetermined target, taking account of the type of mission component, for example the rocket motor. This may be feasible if it is possible to reach the target per se. Feasibility can also be characterized by a predetermined success level relating to hitting a target being reached or exceeded. The success level may be a hit probability, reaching the target at a predetermined approach angle, or before a predetermined time has passed.

If the control means uses type data to determine mission data for a missile mission from target data, then a fire control point can also be relieved of responsibility for the mission, thus making it possible to dispense with more extensive integration of type data in the fire control computer. Use of the type data for identification of the mission component is sufficient, thus allowing control data and target data to be used to calculate the mission data, by using the type data.

The control means advantageously determines a flight trajectory to a predetermined target as a function of the type data relating to the mission component. The flight trajectory can be selected or calculated, and is determined taking account of the warhead type. The control means can receive target coordinates, as the end point of the flight trajectory, from an external control unit.

It is also advantageous for the missile to be in a launcher and for the control means to determine an angular position of the launcher as a function of characteristics of the mission component, and to signal the angular position to an external control unit. The external control unit may be that of the launcher, or a control unit for a fire control system. The angular position may be a specific spatial direction, that is to say a specific direction of a space vector, or angle range, for example around a spatial direction. The angular position may be stated one-dimensionally, for example as an elevation angle, or two-dimensionally . The external control unit can check suitability of the angular position, for example as a function of further missiles in the launcher and angular positions which require this.

Since a plurality of missiles are normally fired in the same direction from a launcher, it is possible for the angular positions signalled from the missiles to the control unit to differ by more than a predetermined threshold value. In this case, the control unit can signal the discrepancy to the control means for the missiles in the launcher, for example with them responding that the signalled angle is unsuitable. It is also possible for the control unit to determine a firing position of the launcher from the various angular positions of the plurality of missiles in the launcher, and to transmit this to the control means in the missile. The firing position may be a compromise between different angular positions, for example an average of the various angular positions.

The control means in the missile can now determine whether the missile can reach a predetermined target in the predetermined manner, as a function of the firing position and the type of mission component. The predetermined manner may be reaching the target at all or reaching it subject to predetermined conditions. The firing position can be positively acknowledged by the control means, such that the launcher is ready to fire the missile.

As mentioned, the warshot missile may contain a plurality of mission components, which are initially unknown by the control means. It is therefore advantageous for the control means to read from the data memory type data relating to a plurality of mission components which have been combined in the warshot missile, whose types are identified on the basis of the identification data and the type data, and to carry out control steps as a function of the combination of the mission components.

The control means is provided with control software, or has access to such control software, which is expediently subdivided into a plurality of software components. In this case, there may be a specific software component for each mission component which, in particular, is associated with only one mission component group and, for example, can be matched by configuration to a mission component in that group. The control software may therefore be usable universally, if at least one software component is created such that-it can be used for a plurality of different mission components, for example a plurality of mission components in a component group, such as different homing heads or different so-called air frames, that is to say fuselage and wing structures. In order to use a specific mission component, the software component is configured as a function of the type data, thus allowing the control means now to control the mission component using the configured software component. The software component may contain a navigation component and/or mission sequence control and/or an image processing component and/or a flight regulator.

The invention also relates to a missile having a fuselage which contains a data memory, a mission component and a control means, which is prepared to control the mission component during a flight of the warshot missile. - li ¬ lt is proposed that the control means be connected for signalling purposes to the data memory, contains the identification data relating to a plurality of different mission components, and the control means is prepared to read type data from the mission component, to identify the type of mission component, and to carry out control steps as a function of the type of mission component. The control means can be prepared by means of appropriate control software for the control means whose running results in such control - for example in conjunction with suitable input signals, such as sensor signals or read signals of type data. For this purpose, the control means expediently has electronic elements, a processor and a data memory, which are necessary or worthwhile for running the control software.

The control means is advantageously prepared for controlling one, more or all of the method steps described above.

If the mission component is a warhead, that is to say for example an explosive charge, an ejected capsule with a sensor or the like, then the control means is expediently prepared to control the missile on a flight path, and to initiate the warhead.

A large number of different warshot missiles can be created easily if they all have a common platform on which the mission components can be built. For this purpose, it is advanta'geous for data distribution for a plurality of mission components in the warshot missile to be connected to the control means via a data bus.

The invention also relates to a system comprising a plurality of warshot missiles as described, which each contain different mission components. It is proposed that the control means for all the warshot missiles be equipped with the same hardware and the same software components. Control means software components associated with the same mission component groups are expediently identical, before configuration. For example, all of the control means are first of all equipped with a software component for the homing head, with all of these software components being identical. The initially identical software components can now be matched by suitable conf guration to the various homing heads, such that they subsequently act differently, corresponding to the homing heads assigned to them.

In addition to those software components which are matched to mission components, for example by configuration, the control means comprises further central hardware components which remain the same in each warshot missile. Components such as these may be an inertial system, which is used to determine the position and the attitude of the warshot missile in space, a GPS system for reception of position data, a voltage supply for processing all the electrical voltages required in the warshot missile from an internal or external voltage source, and data interfaces for transmission of data to receivers outside the warshot missile.

If a new warshot missile having a new mission component is being developed, which is not provided in any of the other warshot missiles, it is sufficient for the control means, for the new warshot missile to be equipped with exclusively the same software components as the control means in the other warshot missiles. The software component can be made ready to operate by configuration of that software component which is associated with the new mission component.

In the sense of a common platform it is particularly advantageous for each warshot missile to have the same mounting frame to which the control means is fitted. A standard control means can thus be built easily. If each warshot missile has the same wiring from an interface to the control means to a plurality of mission components, in particular with the same hardware interfaces, such as plugs, assembly of the warshot missiles can be simplified.

Further advantages will become evident from the following description of the drawing. Exemplary embodiments of the invention are illustrated in the drawing. The drawing and the description contain numerous features in combination, which a person skilled in the art will expediently also consider individually, and will combine them to make worthwhile further combinations.

In the figures: Figure 1 shows a flight path of a warshot missile through a landscape from a launcher to an intended target point, Figure 2 shows a schematic illustration of the warshot missile, Figure 3 shows four different mission component groups, each having a plurality of mission components, Figure 4 shows a schematic . illustration of a control means for a warshot missile, and mission components connected to it, and Figure 5 shows a flow chart of a method for controlling the warshot missile.

Figure 1 shows a warshot missile 2, which is in the form of a surface-to-surface defences rocket, on a flight path 4 which is guided from a launcher 6 to a target point 8 through a landscape 10. The launcher 6 is a goods vehicle with a mobile launcher, into which a modular rocket insert with a plurality of warshot missiles 2 is inserted. However, it is just as feasible for the warshot missile 2 to be launched from a marine vessel or aircraft. The target point 8 is that location in space where it is predicted that the warshot missile 2 will strike its target 12 which, in the illustrated exemplary embodiment, is an armoured vehicle which is intended to be attacked by the warshot missile 2. However, in other exemplary embodiments, the warshot missile 2 can just as well be any desired missile which is intended to fly from a launch point to a predicted enemy location 8 with a target. A fire command, the target coordinates of the enemy location 8 and further mission data are passed from a fire control system 14 to the launcher 6 and to the warshot missile 2 , as is indicated schematically by a building in Figure 1.

Figure 2 shows an enlarged, schematic illustration of the warshot missile 2. In its fuselage as indicated, the warshot missile 2 has a rocket motor 16, a warhead 18 with a data storage means 20, a control means 22, which is connected to a data memory 24, a homing head 26 and a shroud 28, which protects a transparent dome 30 during the approach to the target 12. The control means 22 and the data memory 24 are fitted in a mounting frame in the fuselage. The control means 22 can control the flight of the warshot missile 2 with the aid of schematically indicated actuators for an actuating system 32 for movement of aerodynamic control surfaces, or control fins 34 for short. Analogously- to the data storage means 20, the rocket motor 16, the homing head 26 and the actuating system 32 also contain a corresponding data storage means 20. The components comprising the rocket motor 16, the homing head 26, the warhead 18 and the actuating system 32 are referred to in a generalized form as mission components. Each of the data storage means 20 contains type data relating to the mission component to which is assigned, or in which it is contained. The type data may contain a type designation and operating data for the corresponding mission component .

In order to achieve high flexibility during preparation and in use, the warshot missile 2 is of modular design. It comprises a plurality of component groups, in this exemplary embodiment four, each having a plurality of mission components, with at least one mission component from each component group being fitted in the warshot missile. This makes it possible to create a missile family, in which each warshot missile in the family contains a base and mission components, with the base being the same 'in all the warshot missiles in the family, and with the mission components being combined differently.

The base consists of the control means, which may be a guidance computer with control software, and which may have an inertial measurement unit, a GPS receiver, a power supply, a data link and an electrical and/or logic interface to a launcher. The other components of the warshot missile can be associated with the individual mission components. Warshot missiles in this family can be operated from different platforms against surface, seaborne or airborne targets, can be used over various ranges, may contain various warheads, and may have different guidance strategies and target approaches.

Figure 3 shows the entire component range for a system comprising a plurality of warshot missiles 2, also referred to as a warshot missile family. The component range comprises four component groups: fuselage and wing structures, rocket motors, warheads and homing heads. The group of fuselage and wing structures is annotated "A", and contains: a folding wing structure with associated actuators for small gliding fuselages, a cruciform wing structure with associated actuators and a small fuselage for a solid-fuel motor and a small warhead, a planar wing structure with associated actuators and a large fuselage for a solid-fuel motor and a large warhead, a cruciform wing structure with associated actuators and a small fuselage for a gel-powered motor and a small warhead, a plane wing structure with associated actuators and a large fuselage for a gel-powered motor and a large warhead, and two actuating systems with and without thrust- vector control.

Group "B" of the rocket motors contains a solid-fuel motor, a gel-powered motor, and a multistage motor, in which case these three types of motor are in turn available in various sizes within the family, although these have not been illustrated. Group "C" contains the warheads. The illustration shows a small shaped warhead, for example against vehicles, a large shaped warhead, for example for penetration of buildings, a non-lethal warhead, for example with sensors, and a large warhead with a plurality of small penetrators. The group of homing heads is annotated "D" and contains an IR homing head with image processing for identification and tracking of air-borne targets, a multi-colour IR homing head with image processing for identification of surface targets, a homing head with a semi-active laser and a dummy homing head, which is actually only a missile nose and is used when no homing head is required, for example for surface targets which have reconnoitred very well, and when a pure coordinate approach offers sufficient confidence.

A multiplicity of different warshot missiles can be produced in a modular form from the individual mission components. While the simplest variant of a warshot missile uses a single-stage solid-fuel motor of a conventional type, a controllable gel-powered motor is used for attacking targets at long ranges or for attack modes which overfly the target, for target identification and subsequent attack. A simple variant of the target-seeking sensor system may likewise comprise a semi-active laser homing head, while there may also be more comprehensive variants with image-processing homing heads in various spectral ranges for airborne and surface targets. For clarity reasons, there is no need to individually illustrate the various warshot missiles, since the wide range of variants within the missile family is already evident from the components shown in Figure 3.

The illustrated component range is only one exemplary embodiment. The choice of different mission components is even wider if modern warheads with a programmable effect are considered. All the theoretically possible combinations may possibly not be tactically worthwhile. Nevertheless, it should in general be assumed that the mission components in the various groups can be combined as required.

Figure 4 illustrates one exemplary embodiment of a base. This forms the control means 22 for all the warshot missiles 2 in the family. It contains a plurality of hardware components 36 - 44 which, of course, can also be■ equipped with their own software, and a software module 46 with a plurality of software components 48. The hardware components 36 - 44 are a GPS receiver 36, an inertial measurement unit 38 for position and attitude determination in space, a processor unit 40 with one or more processors for data processing, a bi-directional data link 42 and a power supply 44. In addition, the control means 22 is equipped with interfaces 49: an interface 49 to the GPS antenna, one to the uplink antenna and an interface for communication with external units outside the warshot missile 2, for example with the fire control point 14.

Most of the software components 48 in the software module 46 are assigned to the individual mission components, in which case one or more software components 48 which control the operation of the mission component may be assigned to one mission component. The software components 48 are: an operating system for the control means, a navigation algorithm for processing of the measurement data from the inertial measurement unit and from the GPS receiver, an image processing system, which is associated with the mission components of the homing heads, a guidance computer for formation of the target model, a steering computer with a navigation component for determining the steering rule, for example a line-of-sight rotation rate, and steering control, which is associated with the group of fuselage and wing structures, a flight regulator for determination and control of the actuator positions of the actuators 32, which is likewise associated with the group of fuselage and wing structures, mission sequence control for controlling a sequence of the mission to be carried out by the warshot missile., which is associated with the group of warheads, 'but can also additionally be associated with a different group, and a communication system for communication between the control means 22 and a unit outside the warshot missile 2, for example a fire control point .

The control means 22 is connected for signalling purposes to the individual mission components 50, for example to: an actuating system, and/or fuselage and wing structures, and/or its actuators (Ai) , a controllable motor, whose thrust can be regulated (Bi) , the warheads (Ci) , the homing head (Di) , - a battery (Εχ) , a radar altimeter (F), sensors (Gi) and further actuators (Hi) , in which case the indices indicate that the mission component 50 belongs to a component group with a plurality of group members. The signal connection is provided via a data bus 51, whose wiring has already been laid in the mission components A, that is to say it is part of the mission components A. The wiring from the control means 22 via an interface, for example the data bus 51, to a plurality of mission components 50 may in this case be the same in all the warshot missiles in the family. The mission components 50 and the control means may be connected to the data bus 51, and may communicate directly with one another. The mechanical and electrical interfaces between the control means 22 and the mission components 50 are compatible with the respective mission components 50.

The software components 48 are programmed such that each software component 48 has a .'basic version which ■ can be matched, for example by configuration, to all the members of a component group. This allows the control means to be configured for all possible or worthwhile component combinations. All the functions for all the members of the component group are stored in the software component 48 and can each be switched to be activated by a call. By way of example, there is a flight regulator for each missile fuselage in group A, and this is matched to the payload to be transported.

The missile family expediently has a standard transport and launch container, which forms the interface to the launcher .

One method for configuration and control of the warshot missile 2 will be explained in the following text with reference to a flow chart, which is illustrated in Figure 5.

First of all, in step 52, the rocket insert is loaded into the launcher 6 with, for example, x containers, in each of which there is a warshot missile 2. The type of warshot missile 2, that is to say a warshot missile 2 in the modular family system, may be signalled to the fire control system 14, for example when the rocket insert is connected to the launcher, since the type of warshot missile 2 is also known from the type of rocket insert. The rocket insert, and therefore the type of warshot missile 2, can be identified by defined hardware, for example by the type of data platform for data transmission, from whose type the launcher 6 can at this stage identify the type of rocket . insert .

In step 54, the warshot missiles are supplied with electrical voltage as a result of the loading of the rocket insert or an action by an operator on the ' launcher 6. The control means 22 for the warshot missile 2 is■ automatically started up in step 56, and, in step 58, uses the data bus 51 to request the type data relating to the mission components 50 from their data storage means, for example type designations. In step 60, the control means 22 compares the type data with the identification data which is stored in the data memory 24 and identifies the mission component, for example the warhead 18. By way of example, a multiplicity of designations of different mission components 50 are stored in the data memory 24, such that the control means 22 identifies the types of mission components 50 on the basis of the designation read from or received from the data storage means 20.

Before configuration of the software components 48, all the control means 22 of all the warshot missiles 2 in the family are equipped with the same hardware and the same software components 48, that is to say the software is identical. The identification of the mission components 50 now allows software components 48 to be matched to the mission components 50, as a result of which the software components change from being identical to being customized. This can be done by configuration, which is either carried out on the basis of data from the data memory 24, if the required data for configuration is available there, or on the basis of data from the data storage means 20, which the control means 22 uses for configuration.

The rest of the process will be described in the following text with reference to the mission component 50 of the warhead 18, in which case the method can be used analogously for other mission components 50, with amended steps, corresponding to the mission component 50.

After identification 60, further type data or control data can be read by the control means 22 from the warhead 18 or its data storage means 20, such as: • _ the designation of the- warhead 18, the type of activation of the charge in the warhead 18, that is to say for example whether it is intended to be activated by an impact, only after an impact, by a proximity sensor, or by some other method, • mass characteristics of the warhead 18 for adaptation of the autopilot of the warshot missile 2 and for calculation of the trajectory along which the warshot missile 2 is intended to fly, an elevation table, that is to say a table of the elevation angle of the launcher as a function of the distance between the launcher 6 and the target point 8, the height of the launcher 6 and the height of the target point 8, tables for the apogee and terminal angle, that is to say for example an impact angle, as a function of the distance between the launcher 6 and the target point, and the heights of the launcher 6 and of the target point 8, tables for firing coordinates as a function of the type of warhead 18, the speed and direction of flight of the warshot missile 2 at the target point 8, or shortly before this, and the height of the target point 8, and further data specific for the warhead 18, such as parachute timetables in the case of a payload which is dropped onto the target point 8 by parachute, or the like.

The control means can now configure the corresponding software components (step 62) on the basis of this data or simply on the basis of data which is available simply from the identification, such that they are prepared for controlling the specific mission components 50 in this case.

After identification 60 of the warhead 18 a communication link, which was produced in advance or is produced only at this point, is used between the control means 22 and the fire control system 14. The control means 22 registers with the fire control system 14 with the designation of the warhead 18 (step 64) . The fire control system 14 therefore knows the type of warshot missile 2 and the precise designation of the warhead 18.

After the identification process 60, the control means 22 knows in an entirely general form all of the mission components 50, as a result of which the combination of the mission components 50 in the warshot missile 2 can be passed on to the fire control system 14.

Before and after the registration process 64, the mission components 50 which are actually present in the rocket insert, such as warheads 18, homing heads, motors etc. of the plurality of warshot missiles 2 can be matched to the data of the launcher 6 relating to the rocket insert, in step 66. It is therefore possible to signal to the launcher 6, or to its control unit, which mission components 50 are present in the warshot missiles 2 in the rocket insert. In this case, it is possible to load different mission components 50 in a group into the warshot missiles 2 in the rocket insert, such that, by way of example, some rockets are each loaded with' a first warhead, further rockets are loaded with a second warhead, and a third group of rockets are each loaded with a third warhead.

In addition, it is optionally possible to check whether the software in the control means 22 is up to date as intended. If this is not the case, the software can be updated 68, for example by the control unit of the launcher 6, or by the fire control system 14.

In step 70, the control means 22 configures an algorithm in an external control unit ' in the fire control system 14 using data relating to the mission components 50, such as the warhead 18, such that the control unit can produce mission commands for carrying out the mission. In step 72, the target coordinates of the target point 8 are transmitted from the fire control system 14 to the control means 22 in the warshot missile 2 and, possibly, a target weather report and further data or mission commands.

After this has been done, in step 74, the control means 22 calculates an angular position of the launcher, which is advantageous for firing the warshot missile 2 in the direction of the target point 8. The angular position is a two-dimensional vector comprising an azimuth angle and an elevation angle. The angular position depends on the type of mission of the warshot missile 2 and this in turn depends on the type of warhead, such that the type of warshot is taken into account when calculating the angular position.

The angular position is transmitted to the fire control system 14, which follows the wishes of the control means 22 or, when the warshot missiles 2 in the rocket insert are fired at different destination points, determines a suitable mean value for all the warshot missiles 2. It is also possible for the fire control system 14 to deviate considerably from the angular position desired by the control means 22, thus allowing an off-axis mission to be carried out (with the warshot missile 2 being launched in a direction which is not directed at the target point 8) . The firing direction determined by the fire control system 14 in step 76 is transmitted to the control means 22 and, in step 78, the control means 22 calculates mission parameters from this firing direction, such as: β a flight trajectory from the launcher 6 to the target point 8, β an uncertainty area for the flight trajectory, • by using random influencing variables, possible' uncertainties, ■ as to the extent to which the warshot missile 2 can actually follow this nominal flight trajectory, in which case the influencing variables may be weather factors, tolerance data relating to the rocket motor, and the like, 0 the probability of mission success, and β the flight time to be expected.

The uncertainties can be stated in an uncertainty area or uncertainty tube around the nominal trajectory, within which the warshot missile 2 will fly with a predetermined probability. The probability of mission success also includes finding out whether the mission can be carried out at all with that firing angle, that is ■ to say whether it can be carried out at all or subject to predetermined conditions. The feasibility is dependent on the type of warhead 18, for example its weight, and terminal conditions which are required by the warhead, such as an approach direction to the target 12, and/or a minimum terminal velocity and the like. This data is taken into account when calculating the probability of mission success.

The mission parameters are transmitted from the control means 22 to the fire control system 14, which uses these parameters to determine Go or NoGo for the warshot missile 2. For example, the fire control system 14 checks whether the trajectory complies with all the overflight conditions and whether each point within the uncertainity tube can be flown through without any collisions, for example when flying over the back of a mountain.

After or before the calculation of the mission parameters, the launcher 6 is moved towards the firing direction, in step 80. The warshot missile 2 is then launched from the launcher 6 in step 82, and the flight of the warshot missile 2 is controlled, in step 84, until the warhead 18' is initiated.

The control of the warshot missile 2 by the control means 22 is, of course, matched to the mission components 50 which are present in the warshot missile, as a result of which the control steps are carried out as a function of the combination of the mission components 50. For example, a flight trajectory is dependent on the installed motor, the wing structure, the type of warhead, the weight of the warshot missile, that is to say also on the size of the warhead, and many other parameters.

In principle, the modular system also allows an entirely new mission component 50 to be integrated in a warshot missile which was not yet known about when the software module 46 was created. All that is necessary is to ensure compatibility with the software module 46, and in particular the appropriate software component 48. The appropriate software component can also be matched to the previously unknown mission component 50 by suitable configuration which, - as in the case of known mission components 50 as well - is dependent on the data in the data storage means 20 in the mission component 50, such that it can control the operation of the mission component 50. If a compatible configuration of the new mission component 50 is impossible, only the corresponding, that is to say associated, software component can be updated and integrated in the software module 46, as a result of which even this process is associated with relatively little effort.

List of reference symbols 2 Missile 4 Flight path 6 Launcher 8 Enemy location Landscape 12 Target 14 Fire control system 16 Rocket motor 18 Warhead Data storage means 22 Control means 24 Data memory 26 Homing head 28 Shroud Dome 32 Actuating system 34 Control fins 36 GPS receiver 38 Inertial measurement unit 40 Processing unit 42 Data link 44 Power supply 46 Software module 48 Software component 49 Interface 50 Mission component 51 Data bus 52 Load 54 Voltage supply 56 Start up 58 Check of type data 60 Identification 62 Configuration 64 Registration 66 Matching 68 Update 70 Configuration Transmission of target coordinates Angle calculation Angle calculation Calculation of mission parameters Alignment with the firing direction Missile launch Flight control

Claims

Patent Claims

1. Method for controlling a warshot missile (2) which contains a data memory (24), a control means (22) and a mission component (50), in which the control means (22) controls the mission component (50) during flight of the warshot missile (2), characterized in that the data memory (24) contains identification data relating to a plurality of different mission components (50), and the control means (22) reads type data from the mission component (50), identifies the type of mission component (50) on the basis of the identification data and the type data, and carries out control steps as a function of the type of mission component (50) .

2. Method according to Claim 1, characterized in that the warshot missile (2) contains at least one mission component (50) from the group comprising rocket motor (B) , warhead (C) , homing head (D) , fuselage and wing structure (A) .

3. Method according to Claim 1 or 2, characterized in that the control means (22) uses the type data relating to the mission component (50) to select data, and transmits this data to an external control unit outside the warshot missile (2), and uses the data to configure an algorithm in the external control unit.

4. Method according to one of the preceding claims, characterized in that mission data is transmitted to the control means (22), and the control means (22) uses the mission data to calculate flight data for the warshot missile (2) .

5. Method according to Claim 4, characterized in that the flight data contains a flight trajectory to a predetermined target (12) .

6. Method according to one of the preceding claims, characterized in that the control means (22) reads from the data memory (24) type data relating to a plurality of mission components (50) which are combined in the warshot missile (2) , identifies their types on the basis of the identification data and the type data, and carries out control steps as a function of the combination of the mission components (50) .

7. Method according to one of the preceding claims, characterized in that the control means (22) contains a software component (48) for each mission component, configures said software component (48) depending on the type data, and controls the mission component (50) using the configured software component (48).

8. Method according to Claim 7, characterized in that the control means (22) contains at least one software component (48) from the group comprising navigation component, mission sequence control, image processing component, flight regulator.

9. Warshot missile (2) having a fuselage which contains a data memory (24), a mission ' component (50) and a control means (22) which is prepared■ to control the mission component (50) during flight, characterized in that the control means (22) is connected for signalling purposes to the data memory (24), contains the identification data relating to a plurality of different mission components (50), and the control means (22) is prepared to read type data from the 213934/2 - 31 -mission component (50) , to identify the type of mission component (50), and to carry out control steps as a function of the type of mission component (50) .

10. , Warshot missile according to Claim 9, characterized by a plurality of mission components (50), which are connected to the control means (22) via a data bus (51) .

11. System comprising a plurality of warshot missiles (2) according to Claim 9 or 10, which each contains different mission components (50), characterized in that the control means (22) for all the warshot missiles (2) are equipped with the same hardware and the same software components (48) .

12. System according to Claim 11, characterized by a further warshot missile (2) having a new mission component (50) which is not provided in any of the other warshot missiles (2), with its control means (22) being equipped with exclusively the same software components (48) as the control means (22) in the other warshot missiles (2) and a software component (48) which is associated with the new mission component (50) having been made ready to operate by configuration of the control means (22) .

13. .'System according to Claim 11 or 12, characterized in that each warshot missile (2) has the same mounting frame, to which the control means is fitted.

14. System according to one of Claims 11 to 13, characterized in that each warshot missile (2) has the same wiring from the control means (22) via an interface to a plurality of mission components (50) .