Function-oriented and reconfigurable missile

Abstract

missile(10), comprising: a first component (100); and a second component (200); where the first component and the second component are executed, To define the capabilities of the missile, at least in part: wherein the first component (100) comprises a first module (110) and a second module (120), which have two different and separate capability profiles, and the first component is executed, that the first module (110) or the second module (120) can be selectively activated, thus changing the capabilities of the missile, whereby only one module of the first component (100) can be activated at any one time.

Description

[0001] The invention relates to a flying object. In particular, the invention relates to the functional design of a flying object, e.g., an unmanned flying object.

[0002] Technical devices for missile-based defense technology, such as guided missiles (generally: missiles, especially unmanned aerial vehicles, designed to fly a predetermined route or to reach a given target (autonomously) via a (partially) self-determined route, where a payload can also be transported to the target), are highly complex systems in themselves. They typically consist of various active, data-processing, and interacting components. These components are characterized by static parameters and dynamic capabilities. The individual dynamic capabilities, taken together, determine the overall performance or capabilities of the missile. Such parameters have been stored and used for the design of the missile's overall performance and the necessary central control and regulation system, and have been implemented there.

[0003] In the previously applied paradigm (a scheme for the architecture and functional structure of a missile), performance improvements or new capability profiles could only be implemented by replacing subcomponents and the associated exchange, or by expanding the central control system. Modifying a system was often comparable to developing a new one in terms of the required technical and organizational effort.

[0004] EP 2 405 233 B1 describes a missile. A missile of a rocket launcher has individual components which can be configured via parameters using a central control system. The central control system takes into account the specific parameters or the type designation of an individual component in order to provide the best possible parameterized control for the current configuration.

[0005] The publication DE 10 2008 004 054 B4 describes an unmanned control and surveillance aircraft with a fuselage, navigation, steering and control electronics, multi-sensor equipment and a communication device for data exchange with a mobile aircraft base.

[0006] The publication DE 22 62 630 A describes a missile containing a scanning device and an associated information storage device, arranged in a launch vehicle with opposite propulsion direction, and a control device that, after flying over a target area, causes the missile to separate from the launch vehicle and the missile to fly back.

[0007] The publication DE 10 2008 014 257 A1 describes

[0008] The publication DE 10 2005 060 369 A1 describes a guided missile with a sensor unit, a propulsion unit and a payload unit, wherein at least two of the units can be mounted side by side in the longitudinal direction.

[0009] The publication DE 10 2011 015 780 A1 describes a modular small missile with a control device for steering the flight path and a propulsion device, wherein the propulsion device is designed to generate variable thrust.

[0010] Document US 2015 / 0247714A1 describes a modular missile system with a guidance module, which includes a guidance system for directing the modular missile system to a target.

[0011] The task can be viewed as providing a missile characterized by variable capability profiles, allowing for easy switching between these profiles.

[0012] This task is solved by the subject matter of the independent claim. Further developments arise from the dependent claims and from the following description.

[0013] According to one aspect of the invention, a missile is described which comprises a first component and a second component. The first component and the second component are each configured to define at least part of the missile's capabilities, wherein the first component comprises a first module and a second module, which have different and separate capability profiles, and the first component is configured such that the first module or the second module can be selectively activated, thereby changing the missile's capabilities.

[0014] Such a missile could be, for example, an unmanned aerial vehicle (UAV). The first component could be, for instance, a seeker head with various configurations (modules, in a functional sense), each configuration corresponding to a capability profile. The seeker head could, for example, be configured to analyze the missile's surroundings and transmit this information to a control unit or another component of the missile to guide the missile into a specific relative position to a third object. For example, a seeker head could be configured to cause the missile to collide with the third object, maintain a predefined distance and relative position to the third object, track the object, or specify other movement patterns of the missile in relation to the third object.

[0015] Therefore, by having the first component have at least two modules (or a plurality of modules), i.e., at least two different and separate capability profiles which can be activated independently and selectively, the capability profile of the missile can be adapted within the framework of the available modules.

[0016] Modules are predefined configurations of a component and can modify the component's operation once activated. Because multiple modules are part of the component (and a component no longer has only one capability profile), the capability profile of a component, and therefore of the entire missile, can be changed and adapted to a current requirement by activating one of the available modules.

[0017] While one module is activated, i.e., in an active state, the other modules of the same component are deactivated, i.e., in a disabled state.

[0018] According to one embodiment of the invention, only one module of the first component is activated at any given time.

[0019] This clearly defines the capability of the first component and prevents mutual interference between the modules of a component.

[0020] According to a further embodiment of the invention, the second component has a first module and a second module, and the second component is designed such that the first module and the second module of the second component can be selectively activated, thereby changing the capabilities of the missile.

[0021] The same principle applies to the second component as to the first component: the activated module defines the capability profile of the second component, whereby preferably only one module can be activated at any given time t in order to clearly define the capability of the second component and to prevent mutual interference between the modules of the second component.

[0022] According to a further embodiment of the invention, the missile is designed such that each module of the first component can be coupled with each module of the second component in order to define the capabilities of the missile at least partially.

[0023] The components can be designed to complement each other functionally. The first and second components can perform different tasks within the missile, and the missile components can be coupled to each other via predefined interfaces (functional, electrical, and / or mechanical). These interfaces between the components can be referred to as external interfaces. Each component can have an internal interface through which the component's modules are coupled. Therefore, if one module in a component is deactivated and another module is activated, this has no effect on the coupling between the components, i.e., on the external interface. Only the internal interface needs to be adapted to a module. It is conceivable that a component could have several internal interfaces, for example, to accommodate and activate different modules.However, in such a case, it may be particularly relevant that the external interface of a component does not undergo any changes in order to maintain the coupling between the components.

[0024] According to a further embodiment of the invention, the missile is designed to dynamically activate the first module or the second module of the first component during an operating time of the missile.

[0025] This allows, for example, the missile's behavior to be influenced during operation, i.e., during flight, by changing the active modules of a component, thereby altering the missile's capability profile. For instance, a reassessment of the situation might make such a change advisable or even necessary.

[0026] According to a further embodiment of the invention, the missile has a third component, wherein the third component in turn has at least two modules, wherein the missile is designed to activate only one of these two modules of the third component at any given time.

[0027] The same applies analogously to the third component and the modules it contains as was already described above with reference to the first component and its modules.

[0028] The missile can, in principle, have any number of components, each of which can have at least one module or even several. This allows the entire functionality of a missile to be represented by components, with variations of these functions provided by different modules within a component. The components preferably represent generic functions such as the seeker head, propulsion system, control unit, and environmental data analysis, with the modules representing variations of these functions. For example, environmental data analysis using image processing can be performed directly by a module (internal image processing), or by using an external image processing system that sends the environmental images and receives a result from the external image processing system, which then forms the basis for further operations. This result might, for example, contain the coordinates of a target object.

[0029] For the components upstream or downstream of this function, it is generally irrelevant how the component internally arrives at the result; however, a change in the component by selecting a different module represents a change in the overall capability profile of the missile. To continue with this example of internal versus external image processing, external image processing allows changes to be made to the method of image processing without having to modify the missile itself, apart from activating the corresponding module.

[0030] According to a further embodiment of the invention, the first component is an environmental sensor system of the missile. In particular, the first component can be a search head with corresponding sensors and a navigation unit, which is configured to provide navigation data (e.g., taking into account the environment and, if applicable, the position of a target object) along which the missile moves.

[0031] According to another embodiment of the invention, the second component is a control unit of the missile.

[0032] The interlocking system can access output values ​​from the first component, or is supplied with these output values, and ensures a corresponding directional adjustment of the missile. Different modules of the interlocking system can implement the directional adjustment in different ways.

[0033] According to another embodiment of the invention, the third component is an engine of the missile.

[0034] Here too, different modules can control the engine in different ways.

[0035] According to a further embodiment of the invention, the missile further comprises a control unit, wherein the control unit is configured to activate a module of the first component.

[0036] The control unit is thus designed to configure the missile's capability profile without having to influence the interplay and interaction of the components and modules. The components are at least functionally linked through the definition of their respective external interfaces, so that their interplay and interaction are coordinated via these interfaces.

[0037] According to a further embodiment of the invention, the control unit is designed to select one module from each component and thus to define at least part of the capabilities of the missile.

[0038] In other words, the control unit identifies a module for each component that should be activated. This specification of a module for each component can be referred to as a configuration identifier. Such a configuration identifier allows the overall capability profile of the missile to be adjusted with minimal effort.

[0039] The components can also be designed so that modules can be stored within a component at any time and subsequently activated. The modules can, for example, be stored as machine-readable instructions in a memory module, such as persistent memory of any shape and configuration, within the missile.

[0040] The missile can be described in other words as follows: The described missile aims to achieve an increase in overall performance or an adaptation of the system's behavior to new, required situations by replacing individual components, without requiring partial or complete replacement of individual components or the central unit. Additionally, a mission-specific detailed configuration should be dynamically configurable shortly before and during the deployment of such a complex technical system. This would allow the operator to dynamically adapt the missile's behavior profile to the prevailing situation, the mission, and the applicable rules of conduct.

[0041] A missile is assembled from components with different capability profiles. Before the missile begins an operation, or as a result of a change in the situation during the operation, the rules to be applied are transmitted (the configuration identifier), defined, or selected.

[0042] The approach presented here transcends the seemingly established boundary where components are externally defined solely by basic behavior and parameterizable variables. It is based on a functional decomposition of the complex workflows involved in controlling and guiding a missile. The functions, their interactions and dependencies with the environment, as well as the information to be processed and the results or control variables, are identified and encapsulated in small functional units (modules). These units are allocated to a component in which they are realized or implemented. This allocation can occur at different implementation levels: hardware, software, programmable hardware, or through classic mechanical, electrical, hydraulic, and pneumatic control methods, as well as logically to components and subcomponents.Clustering allows functionally similar variations to exist in parallel in different forms; that is, a single component can have different variants of modules. The variants or functional profiles kept in stock do not necessarily require the full functional configuration on the missile. By shifting intelligent components to the individual components, dynamic variant management within the missile is enabled.

[0043] To illustrate this point: Control methods for a missile's propulsion system can vary significantly depending on whether the missile configuration includes or lacks environmental sensors. If current environmental data is considered during control, a situation-adapted control method is possible. Otherwise, a simplified method using a predefined environmental model must be employed.

[0044] To optimize the cost-benefit ratio between missile and threat type, not every missile needs to be equipped with full functionality, such as environmental sensor units. If it includes advanced sensors, the corresponding operating profile can be accessed in the engine. In a different missile configuration without advanced sensors, only the basic operating profile is used. This approach can be applied analogously to all functional areas and components. Thus, control profiles for terrain overflight (comparable to cruise missile characteristics) or low-level overwater flight (comparable to anti-ship missiles) could be stored in parallel. Similarly, different procedures for CDI (classification, discrimination, identification) or for tracking various target spectra can be derived from this methodology.

[0045] The specific combination and sequence used in each case can be determined by the following exemplary conditions: a) The available set of partial capabilities is determined by the existing missile configuration. Different versions and production stages of a specific model within a product line, as well as varying levels of development or quantities of capability profiles, also play a role and determine the possible overall capability profiles. b) Specifications from the operational plan for the specific mission in which the missile is used. This includes factors such as the expected type of target, the nature of the environment, foreseeable changes in the situation during flight, and boundary conditions to be observed in order to avoid collateral damage. c) Dynamic changes in the situation during mission execution are taken into account for adaptive adjustments. A change in the classification result serves as an example. If the target's classification changes during flight, e.g., due to altered specifications or a different target identification, then different rules of conduct must be considered, influencing the applicable capability profile combination.

[0046] Another aspect of the proposed approach is the transfer of central process control to a control unit that simply defines the capability profile, and the tasks are then executed by the components. This control unit implements the predefined profile combination. It coordinates the interaction, specific combination, sequence, and timing of the components and modules. The optimal components and modules are used and called or triggered as needed. In contrast to a central and often monolithic process control system, task execution is distributed and directed from a single point. The necessary rule set is loaded before the mission begins and adapted to the specific situation as required throughout the mission.

[0047] The approach described here enables the coupling of data and processing methods within the associated components. With the ability for different module variants to coexist within a single component, it is no longer necessary to replace the entire component. Depending on the situation, it is sufficient to use a different capability profile.

[0048] This approach to missile development supports an evolutionary development process. If individual components or capabilities are not yet immediately implementable, the missile system can initially be used with simplified capability profiles. Retrofitting promises to be significantly easier, as new modules can be added to the components.

[0049] The application of missiles and the requirements for them can change very rapidly. A planned operational spectrum at the start of development may no longer be of primary importance by the time of introduction. The missile described herein offers the flexibility to easily adapt an existing system to changing operational spectrums. Only a different combination of capability profiles is activated, or, if necessary, new modules are provided and can then be used.

[0050] It will not be possible to develop a specific missile for every operational scenario or environment. The approach described here provides a way to incorporate more capabilities into a single missile. This allows the missile, possibly with limitations or reduced capabilities, to still be used in a different operational environment and for a different type of mission.

[0051] This capability also allows the missile's behavior to be adapted to changing rules of conduct or environmental conditions. This adaptation supports the possibility of still achieving the modified mission objective. If the missile's behavior cannot be changed during an operation, it may be necessary to destroy the missile in flight if external conditions change. For example, a target initially classified as highly threatening might later prove to be less threatening. The rules of conduct change the mission objective from destroy to deflect, intercept, or deter, but not destroy. This change leads to the adaptation of the component capability profiles.Visible effects on the missile may include: reduced thrust, reduced speed, different approach angle, minimized effect, maximized visibility (no approach from a concealed position), as well as mission abort or self-destruction when the mission objective is reached.

[0052] The following section describes exemplary embodiments of the invention in more detail with reference to the accompanying drawings. These show: Fig. 1 a schematic representation of a missile according to an embodiment of the invention; Fig. 2 a schematic representation of a missile according to a further embodiment of the invention; Fig. 3 a schematic representation of a capability profile of a missile according to a further embodiment of the invention; Fig. 4 a schematic representation of a capability profile of a missile according to a further embodiment of the invention;

[0053] Fig. Figure 1 shows a schematic representation of a missile 10, which has five components 100, 200, 300, 400, and 500. Each component fulfills a specific function, such as a search head (first component 100), an evaluation unit (second component 200), and a control unit with a propulsion unit (fifth component 500). The remaining components can fulfill further missile-specific functions.

[0054] Each component has two or more modules, each identified by a letter and a number (the same letter is used for all modules within a component, followed by an ascending number). The first component, 100, has three modules: 110, 120, and 130(A1, A2, A3). Each of these modules represents a variant of a capability profile of the first component, 100. Of the modules 110, 120, and 130, only one can be activated at any given time t. The same applies to the modules of the other components.

[0055] In summary, the capability profile of missile 10 results from the number of active modules per component.

[0056] The active module for each component can be determined by a control unit 50. The control unit 50 can be connected to an operator station via a communication link (not shown), for example, a wireless connection such as a radio link or wireless optical link. Information can be transmitted via this communication link, specifying the configuration, i.e., the capability profile, of the missile. The control unit then activates a set of modules according to the specified configuration information.

[0057] In one embodiment, the control unit 50 contains several sets of capability profiles, from which one capability profile can be selected, or which is activated at a predetermined time and in turn activates the corresponding modules. In the latter case, the capability profile of the missile can be varied according to a predetermined temporal pattern.

[0058] The functionality of components can be extended by adding a module to a component, as is done, for example, in Fig. Figure 2 is shown. Here it is shown that, in contrast to Fig. 1. Component 500 has an additional module 530 besides modules 510 and 520.

[0059] Each component's functionality can be extended without affecting the interfaces between the components. This enables modularity, allowing the capability profile of a missile 10 to be expanded and adapted to a specific requirement by selecting a desired configuration from the available modules to achieve an overall capability profile.

[0060] Fig. 3 and Fig. Figure 4 each shows a capability profile from the set of modules for each component. Each row displays the modules of a component, and the gray-shaded column shows the missile's configured capability profile as the sum of the functions of the activated modules.

[0061] The control unit can be designed to retrieve the capability profiles of the modules within individual components using a uniform scheme. The capability profile can be described by specifying an identifier for the modules to be activated for each component. In the case of Fig. 3 this is [A2;B1;C3;D1; E2] and in the case of the Fig. 4 is [A3; B1; C2; D1; E2].

[0062] The control unit merely specifies which modules are to be activated without interfering with their function or influencing the interaction between modules and components. The specific configuration is predetermined before the missile launch or dynamically adjusted to the situation during flight. The capabilities and limitations for adapting configurations can also be stored in profiles, i.e., a specification of when or under what circumstances a capability profile should be activated. Reference symbol list 10 missiles 50 control unit 100 components 110 Module 120 Module 130 Module 200 components 210 Module 220 Module 300 components 310 Module 320 module 330 module 400 components 410 Module 420 Module 500 components 510 module 520 Module 530 Module

Claims

[1] Missile(10) comprising: a first component (100); and a second component (200); where the first component and the second component are executed, To define the capabilities of the missile, at least in part: wherein the first component (100) comprises a first module (110) and a second module (120), which have two different and separate capability profiles, and the first component is executed, that the first module (110) or the second module (120) can be selectively activated, thus changing the capabilities of the missile, whereby only one module of the first component (100) can be activated at any one time. [2] Missile (10) according to claim 1, wherein the second component (200) comprises a first module (210) and a second module (220) and the second component is configured such that the first module (210) and the second module (220) can be selectively activated, thereby changing the capabilities of the missile. [3] Missile (10) according to any of the preceding claims, wherein the missile is configured such that each module (110, 120) of the first component (100) can be coupled with each module (210, 220) of the second component (200) in order to define at least part of the missile's capabilities. [4] Missile (10) according to any of the preceding claims, wherein the missile is configured to dynamically activate the first module (110) or the second module (120) of the first component during an operating time of the missile. [5] Missile (10) according to one of the preceding claims, further comprising a third component (300) with at least two modules (310, 320), wherein the missile is configured to activate only one of these two modules (310, 320) of the third component (300) at any one time. [6] Missile (10) according to one of the preceding claims, wherein the first component (100) is an environmental sensor of the missile. [7] Missile (10) according to one of the preceding claims, wherein the second component (200) is a control unit of the missile. [8] Missile (10) according to any one of claims 5 to 7, wherein the third component (300) is an engine of the missile. [9] Missile (10) according to one of the preceding claims, further comprising a control unit (50), wherein the control unit (50) is configured to activate a module of the first component (100). [10] Flying object (10) according to claim 9, wherein the control unit (50) is designed to select one module from each component and thus to define at least part of the capabilities of the missile.

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