Multibody flight system

Abstract

Multi-body flight system (10), comprising: a primary missile (1); a plurality of secondary missiles (2), each of which can be coupled to the primary missile (1) via a carrying and release system (11) to produce a launch configuration and can be triggered by the primary missile (1) in flight to produce an operational configuration; and a control system (4) which is designed to release the secondary missiles (2) from the launch configuration of the primary missile (1) during deployment as a function of mission specifications and to allow the primary missile (1) and the released secondary missiles (2) to assume the deployment configuration; wherein the primary missile (1) and the secondary missiles (2) are each designed as guided missiles; wherein the control system (4) comprises a control device (3) of the primary missile (1) and a control device (3) of each of the secondary missiles (2) for individually controlling the missiles (1, 2); wherein the primary missile (1) and the secondary missiles (2) each have a drive which are jointly designed to drive the multi-body flight system as a single guided missile.

Description

[0001] The present invention relates to a multi-body flight system.

[0002] Missiles such as guided missiles are typically designed and optimized for specific, more or less restricted operational scenarios and target constellations. Accordingly, different types of missiles are normally used depending on the application, and these can only be reconfigured to a very limited extent, if at all, in terms of their mechanics and / or aerodynamics immediately before or during a mission. It would therefore be fundamentally desirable if greater flexibility in the deployment of missiles could be achieved. Ideally, a specific missile would be deployable not only in different scenarios, but also under changing technical requirements. In other words, there is a need for a missile that meets different mission requirements for engaging multiple targets, which may only be specified or developed in the course of a future mission.be defined.

[0003] Various systems are provided for coupling loads to external structures of flying platforms. For example, loads or launch devices such as guided missiles can be mechanically and releasably attached to aircraft, e.g., using so-called load locks. Mechanical connection systems used for these and similar purposes include rail launchers, ejection mechanisms, and separation mechanisms via extendable trapezes (so-called scissor mechanisms). For example, US Pat. No. 7,624,947 B2 describes a carriage and release system for the releasable attachment of weapons to an aircraft. Such systems can, in principle, also be used to couple several missiles together to form a multi-body aircraft.

[0004] DE 10 2010 010 508 A1 describes an unmanned aerial vehicle with a payload compartment closed to the outside by a hatch. The hatch can be opened downward, allowing payload elements such as guided missiles to be ejected from the payload compartment.

[0005] DE 10 2005 042 484 A1 describes an unmanned glider with a bomb-carrying device.

[0006] US 2020 / 0 256 644 A1 describes the control of a drone in flight.

[0007] US 2020 / 0 159 255 A1 deals with the control of a guided missile dropped from an aircraft.

[0008] DE 10 2012 022 191 A1 describes a drone aircraft with a carrier system and mission control system for carried controllable drones.

[0009] Against this background, the present invention is based on the object of finding flexibly adaptable solutions for a missile for combating different targets with changing requirements.

[0010] According to the invention, this object is achieved by a multi-body flight system having the features of patent claim 1.

[0011] One idea underlying the present invention is to provide a modular missile that can be divided into individual modules during deployment as needed and depending on the respective scenario. These modules can then perform different tasks individually and / or collaboratively in a swarm as needed. The resulting system is scalable and thus adaptable, and can thus be easily adapted to, for example, logistical, mechanical, and / or aerodynamic aspects or control engineering requirements. In this sense, it is ultimately a morphing missile system that can be adapted for varying complex airspace interactions and, moreover, offers great flexibility for adaptation to possible future and currently unspecified requirements.The system according to the invention can meet the requirements for engaging multiple targets and highly variable and / or dynamic mission requirements, where neither precise information about the mission nor the intended target is required prior to deployment. The multi-body aircraft system can be deployed both airborne and ground-based, or, for example, from a watercraft.

[0012] Advantageous embodiments and further developments emerge from the further subclaims and from the description with reference to the figures.

[0013] According to a further development, the multi-body flight system can be designed for deployment from an aircraft. The control system can be designed to release the secondary missiles from the primary missile after the multi-body flight system has separated from the aircraft.

[0014] At the start of the mission, the multi-body system forms a modular unit and is transported from the airborne carrier platform to a specified drop point. After separation or launch of the multi-body flight system, and depending on the specific mission or situation, it divides into the primary missile and, for example, two or more secondary missiles. The separated missiles then assume an operational configuration depending on the mission requirements. This can include, for example, the alignment, activation, and / or configuration of control surfaces and / or control nozzles, signal transmission devices, measuring instruments, navigation units, and the like.

[0015] It is understood that the multi-body system can also be deployed from a land- and / or water-based platform.

[0016] According to a further development, the primary missile and / or the secondary missiles can be designed with wings and / or control surfaces which align themselves automatically after the secondary missiles are triggered.

[0017] For this purpose, the individual missiles can incorporate appropriate control and / or navigation systems that handle both the transition from the launch configuration to the operational configuration, as well as the subsequent navigation, guidance, and general control of the respective missile. Alternatively or additionally, it is of course possible in principle to monitor and control the individual missiles via a wireless communication link, e.g., via a corresponding system on board the airborne carrier platform or a ground-based command post or similar.

[0018] According to a further development, the wings and / or control surfaces can be designed to be extendable and / or foldable from a fuselage of the respective missile.

[0019] The corresponding elements can thus be stowed in the launch configuration in a space-saving and aerodynamically advantageous manner within the multi-body flight system in a surface-neutral manner and can only be extended for use when necessary.

[0020] According to the invention, the primary missile and the secondary missiles are each designed as guided missiles.

[0021] The multi-body flight system can initially be launched as a unit from an aircraft or similar vehicle and then initially operate as a single guided missile. For this purpose, control jets or other propulsion systems, as well as, for example, wings and / or control surfaces of the individual sub-vehicles, are used jointly. Depending on the mission and situation, the secondary missiles can then be partially or entirely detached from the primary missile to bring the multi-body flight system into operational configuration. The primary missile and the secondary missiles are each designed as guided missiles with their own propulsion and control system, enabling them to operate individually or as a swarm.

[0022] According to a further development, the primary missile and the secondary missiles can each be equipped with a communication device for wireless data exchange between them.

[0023] In this way, the sub-vehicles can communicate with each other in a decentralized manner, exchanging control commands, sensor data, etc. Likewise, the sub-vehicles can be jointly controlled via a wireless communications network. For example, the primary missile can command the secondary missiles depending on the situation and mission specifications. In another example, the primary missile and the secondary missiles can be jointly commanded from the carrier platform.

[0024] According to the invention, the control system comprises a control device of the primary missile and a control device of each of the secondary missiles for individually controlling the missiles.

[0025] The components of the missile, i.e., the primary missile and the secondary missiles, can now be deployed for different tasks in a more or less autonomous manner. For example, the primary missile can perform aerial surveillance tasks, while the secondary missiles fly to a common or separate target.

[0026] It is understood that the control system may alternatively or additionally comprise a control device on the (possibly airborne) carrier platform, on another missile or another mobile unit, and / or as part of a central control center or central operational command. The missile components can thus also be commanded in a centralized manner by a central, possibly mobile, external control system.

[0027] According to a further development, the control devices of the missiles can be designed for collaborative control of the missiles.

[0028] In addition to individual use of the missiles, a swarm-like implementation is envisaged for carrying out specific missions in which the missiles interact with one another. The mission design for these and similar applications can be defined very variably and range from simple formation maintenance to more complex tasks, which may include, for example, interactions with targets and / or the environment. For this purpose, the missiles can communicate wirelessly with each other via respective communication devices in order to exchange target and / or environmental data, sensor and / or position or positioning information. The missiles can be subject to constant control by a central authority. Alternatively, they can also operate as semi- or fully autonomous mobile units to carry out various missions, from surveillance and reconnaissance missions to tactical attacks.

[0029] According to a further development, the secondary missiles can each be coupled laterally or axially to the primary missile and / or side by side or one behind the other to the primary missile.

[0030] In this further development, the secondary missiles can be released from the primary missile in the simplest possible way, laterally, in front, behind and / or downwards from the underside, for example, by utilizing aerodynamic drag and suction effects for the separation process.

[0031] According to a further development, the secondary missiles can have a triangular fuselage cross-section.

[0032] Such a triangular fuselage structure, as expected, offers low visibility. The primary missile and secondary missiles can ideally be designed with a flat shape to further reduce visibility and simultaneously minimize aerodynamic drag, as well as optimize aerodynamic glide and climb characteristics for distant, high-altitude targets or the like. It is understood that, depending on the application and / or specifications, the skilled person can also design different geometric configurations, possibly polygonal cross-sections, for the missile components.

[0033] The above embodiments and further developments can be combined with one another as desired, where appropriate. Further possible embodiments, further developments, and implementations of the invention also include combinations of features of the invention not explicitly mentioned above or described below with regard to the exemplary embodiments. In particular, those skilled in the art will also add individual aspects as improvements or additions to the respective basic form of the present invention.

[0034] The present invention is explained in more detail below with reference to the exemplary embodiments shown in the schematic figures. They show: Fig. 1 schematic perspective view of a multi-body flight system according to an embodiment of the invention; Fig. 2 schematic front view of the multi-body flight system of the Fig. 1 during the transition from a launch configuration to a deployment configuration; Fig. 3 schematic plan view of the multi-body flight system of the Fig. 2 in the deployment configuration; Fig. 4 schematic front view of the multi-body flight system of the Fig. 2 in the deployment configuration; Fig. 5 schematic perspective view of a multi-body flight system according to another embodiment of the invention; Fig. 6 schematic front view of the multi-body flight system of the Fig. 5; Fig. 7 schematic rear view of the multi-body flight system of the Fig. 5; Fig. 8 schematic front view of a primary missile of the multi-body flight system of the Fig. 5 in an operational configuration; Fig. 9 schematic perspective view of the primary missile of the Fig. 8; Fig. 10 schematic front view of a secondary missile of the multi-body flight system of the Fig. 5 in an operational configuration; Fig. 11 schematic perspective view of the secondary missile of the Fig. 10; Fig. 12 schematic front view of a multi-body flight system according to a further embodiment of the invention, for example in a container or launch container; Fig. 13 schematic perspective view of the multi-body flight system of the Fig. 12; Fig. 14 schematic detailed view of an aircraft 14 for transporting a multi-body flight system according to another embodiment of the invention; and Fig. 15 schematic detailed view according to Fig. 14 during the attachment of a multi-body flight system to the aircraft.

[0035] The accompanying figures are intended to provide a further understanding of embodiments of the invention. They illustrate embodiments and, in conjunction with the description, serve to explain principles and concepts of the invention. Other embodiments and many of the noted advantages will become apparent upon review of the drawings. Elements of the drawings are not necessarily shown to scale relative to one another.

[0036] In the figures of the drawing, identical, functionally identical and acting elements, features and components are provided with the same reference symbols, unless otherwise stated.

[0037] Fig. 1 and Fig. 2 show views of a multi-body flight system 10 according to an embodiment of the invention. The multi-body flight system 10 is designed for deployment from an aircraft (not shown), from which it can be transported to a deployment site and dropped or released there.

[0038] Fundamentally, the solution described below aims to provide a missile that can meet diverse mission requirements for engaging multiple targets as flexibly as possible, without requiring any initial details about the specific mission or the targets to be targeted. The solution approach envisages a modular combination of individual missile components, which are initially launched together as a coupled missile from a carrier platform (e.g., an aircraft, a ground vehicle, and / or a watercraft) and then separated to perform a complex, possibly subsequently defined, engagement task individually or in a swarm.

[0039] The current state of development in the field of electronics, sensors, and software for aircraft and missiles requires entirely new approaches to weapon systems. The present concept offers the flexibility and modularity needed to accommodate the ever-increasing complexity and interaction of electronic components. A monolithic aircraft can hardly achieve such flexibility, as certain physical incompatibilities in the technical requirements can hardly be overcome by it, e.g., extreme range requirements with minimal mass under highly agile mission profiles. The use of a swarm of unmanned aircraft in the sense of the present idea offers an interactive, semi- or fully autonomous approach that can combine a wide variety of, initially seemingly incompatible, requirements and can also respond flexibly to future needs.

[0040] The multi-body flight system 10 of the Fig. 1 and Fig. 2 comprises a primary missile 1 and two secondary missiles 2, which are coupled via a carrying and release system 11, e.g. a cargo lock or another suitable fastening, locking and release system, next to each other on an underside 6 of the primary missile 1 along an axial direction of the primary missile 1, i.e. in the flight direction 12. In this launch configuration, the missiles 1, 2 are firmly connected to one another to form an aircraft, which in this form can be attached to an aircraft 14. For this purpose, the primary missile 1 is designed with several suspension eyes 8, via which the multi-body flight system 10 can be hooked into corresponding suspension hooks 9 of a carrying and release system 11 in an aircraft 14, as shown in Fig. 14 and Fig. 15 is indicated by way of example, and can be activated at a location of use.

[0041] The secondary missiles 2 can be triggered by the primary missile 1 in flight to bring the system 10 from the starting configuration into an operational configuration, as shown on the right in Fig. 2. The separation of the missiles 1, 2 occurs as soon as the multi-body flight system 10 is released from the aircraft 14. The specific sequence is regulated by a control system 4, which releases the secondary missiles 2 from the launch configuration during deployment depending on mission specifications and allows the primary missile 1 and the released secondary missiles 2 to assume the deployment configuration. Each missile 1, 2 comprises, as part of the control system 4, a control device 5 and a communication device 3 linked to it for data purposes, via which the missiles 1, 2 can communicate wirelessly with each other and with the aircraft 14 (for example, via a radio network).

[0042] The control devices 5 ensure that the primary missile 1 and the secondary missiles 2 configure themselves automatically after detachment. For example, the wings and control surfaces 7 of both missiles 1, 2 are automatically extended or unfolded and aligned, as shown in Fig. 3 and Fig. 4. Likewise, both missiles 1 and 2 have their own propulsion nozzles and are thus designed as independent guided missiles that can operate individually and / or collaboratively in a swarm to fulfill specific mission requirements.

[0043] An alternative embodiment of the multi-body flight system 10 is described with reference to Fig. 5 to 11. As can be seen from these figures, the design of the primary missile 1 can be developed depending on the aerodynamic and flight-mechanical requirements as well as the specific mission requirements. Likewise, the attachment position of the secondary missiles 2 on the primary missile 1 can be varied.

[0044] As can be seen from the figures, the primary missile 1 is designed to be as flat as possible to meet potential stealth requirements such as inconspicuous radar signatures and low obversability. Furthermore, aerodynamic drag and thus ultimately energy consumption can be minimized, and flight characteristics with regard to glide and climb can be optimized.

[0045] Similar considerations can be made for the secondary missile 2, which in the present case results in a triangular fuselage structure with a curved or rounded outer edge in order to enable the lowest possible visibility with minimal aerodynamic drag.

[0046] The design of the fuselage, wings, and control surfaces 7 can be optimized to suit the specific application, taking into account aerodynamic requirements. To ensure flexibility for future and non-predetermined applications, as many functional technology elements and apertures as possible can be incorporated in an optimized manner, such as: - Search head and distance sensors - Antennas and electronic interference elements - Control and communication electronics - Active systems - extendable and, if necessary, movable wings - Top-hung and folding sashes - Tank systems - Motors, liquid and / or solid fuel propulsion - Suspension elements for connection to a support platform - Parachutes for landing - Control electronics and mechanics

[0047] In this case, secondary missiles 2 and primary missiles 1 can, in principle, have similar or even identical equipment, whereby the primary missile 1 only needs to have additional fastening means for coupling to the carrier platform, i.e. in this case the aircraft 14. Due to the similar design of the missiles 1, 2, it can be achieved that they can interact and cooperate with each other in the operational configuration. For example, the missiles 1, 2 can form a swarm formation with more or less equal rights and act in conjunction. Due to the flexible design, target engagement can be carried out depending on rapidly changing operational scenarios. For example, one system can engage one target jointly or three different targets, whereby the specific task of each missile 1, 2 can also be changed during the operation (e.g.can switch between combat, jamming, and reconnaissance). Missiles 1 and 2 can be integrated into a global information and control cloud. Missiles 1 and 2 can be controlled locally and / or autonomously, as well as centrally by a global entity.

[0048] It will be apparent to those skilled in the art that the electronic equipment of the individual missiles 1, 2 can vary considerably in terms of cost and functionality depending on the respective mission in order to optimize operational capabilities. For example, different equipment of the missiles 1, 2 may be provided for specific missions to implement different functionalities such as reconnaissance, jamming, impact, or the like. By appropriately scaling the missiles 1, 2 in terms of mass, length, width, height, material, etc., highly variable attack, combat, and defense scenarios can be implemented very quickly in an operational area, depending on the requirements.

[0049] Although the above focus was on the use of the system 10 by an aircraft 14, the invention is not limited to this. Water- or ground-based carrier platforms are also conceivable. For example, the system 10 can be adapted for a ground-based application, as shown in Fig. 12 and Fig. 13, can be implemented with appropriate scaling in a container 13 or a launch container. As a supplement, an additional launch engine (booster) in the form of a solid-fuel engine or the like can be embedded in the system 10.

[0050] In summary, an extremely flexible modular multi-body aircraft is provided, which can be reconfigured according to the specific mission requirements and is thus also prepared for potential changes in requirements in the future.

[0051] In the foregoing detailed description, various features have been combined into one or more examples for clarity of illustration. It should be understood, however, that the above description is merely illustrative and not restrictive in nature. It is intended to cover all alternatives, modifications, and equivalents of the various features and embodiments. Many other examples will be readily apparent to those skilled in the art based on their skill in the art in light of the above description.

[0052] The embodiments were chosen and described to best illustrate the principles underlying the invention and their practical application. This will enable those skilled in the art to optimally modify and utilize the invention and its various embodiments for their intended purpose. In the claims and the description, the terms "including" and "having" are used as neutral terms for the corresponding term "comprising."

[0053] Furthermore, the use of the terms “a”, “an” and “an” is not intended to exclude a plurality of features and components described in this way. List of reference symbols 1 primary missile 2 secondary missiles 3 Control device 4 Tax system 5 Communication device 6 Bottom 7 Wing and control surface 8 hanging eyelets 9 hanging hooks 10 Multibody Flight System 11 Carrying and dropping system 12 Flight direction 13 containers 14 aircraft

Claims

[1] Multi-body flight system (10), comprising: a primary missile (1); a plurality of secondary missiles (2), each of which can be coupled to the primary missile (1) via a carrying and release system (11) to produce a launch configuration and can be triggered by the primary missile (1) in flight to produce an operational configuration; and a control system (4) which is designed to release the secondary missiles (2) from the launch configuration of the primary missile (1) during deployment as a function of mission specifications and to allow the primary missile (1) and the released secondary missiles (2) to assume the deployment configuration; wherein the primary missile (1) and the secondary missiles (2) are each designed as guided missiles; wherein the control system (4) comprises a control device (3) of the primary missile (1) and a control device (3) of each of the secondary missiles (2) for individually controlling the missiles (1, 2); wherein the primary missile (1) and the secondary missiles (2) each have a drive which are jointly designed to drive the multi-body flight system as a single guided missile. [2] Multi-body flight system (10) according to claim 1, wherein the multi-body flight system (10) is designed for use by an aircraft (14), wherein the control system (4) is designed to release the secondary missiles (2) from the primary missile (1) after separation of the multi-body flight system (10) from the aircraft (14). [3] Multi-body flight system (10) according to claim 1 or 2, wherein the primary missile (1) and / or the secondary missiles (2) are formed with support and / or control surfaces (7) which align themselves automatically after the secondary missiles (2) are triggered. [4] Multi-body flight system (10) according to claim 3, wherein the wings and / or control surfaces (7) are designed to be extendable and / or foldable from a fuselage of the respective missile (1, 2). [5] Multi-body flight system (10) according to one of claims 1 to 4, wherein the primary missile (1) and the secondary missiles (2) are each designed with a communication device (5) for wireless data exchange among themselves. [6] Multi-body flight system (10) according to one of claims 1 to 5, wherein the control devices (3) of the missiles (1, 2) are designed for collaborative control of the missiles (1, 2). [7] Multi-body flight system (10) according to one of claims 1 to 6, wherein the secondary missiles (2) can each be coupled laterally or axially to the primary missile (1) and / or side by side or one behind the other to the primary missile (1). [8] Multi-body flight system (10) according to claim 7, wherein the secondary missiles (2) have a triangular fuselage cross-section.

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