DE102021000574A1 - multi-body flight system - Google Patents

Abstract

A multi-body flight system includes a primary missile; a plurality of secondary missiles, each of which can be coupled via a carrying and launching system to the primary missile to create a launch configuration and can be triggered by the primary missile in flight to create a mission configuration; and a control system which is designed to release the secondary missiles from the primary missile as a function of mission specifications during the deployment from the launch configuration and to allow the primary missile and the deployed secondary missiles to assume the deployment configuration.

Description

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

Missiles such as, for example, guided missiles are typically designed and optimized for specific, more or less limited, deployment scenarios and target constellations. Accordingly, depending on the application, different types of missiles are normally used, which can only be reconfigured to a very limited extent, if at all, with regard to their mechanics and/or aerodynamics immediately before or during use. It would therefore be fundamentally desirable if greater flexibility in the deployment of missiles could be achieved. Ideally, a specific missile would not only be usable 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 combating multiple targets, which may only be specified or defined in the course of a future mission.

Different systems are provided for coupling loads to external structures of airborne platforms. For example, loads or launching devices such as guided missiles can be attached to aircraft in a mechanically detachable manner, for example via so-called load locks. Mechanical connection systems used for these and similar purposes include rail launchers, eject launchers and separating mechanisms via extendable trapezoids (so-called scissor mechanisms). For example, the reference describes U.S. 7,624,947 B2 a carrying and triggering system (English: "Carriage and Release System") for the detachable attachment of weapons to an aircraft. In principle, such systems can also be used to couple a plurality of missiles to one another to form a multi-body aircraft.

Against this background, the object of the present invention is to find flexibly adaptable solutions for a missile for combating different targets with changing requirements.

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

Accordingly, a multi-body flight system is provided. The multi-body flight system includes a primary missile; a plurality of secondary missiles, each of which can be coupled via a carrying and launching system to the primary missile to create a launch configuration and can be triggered by the primary missile in flight to create a mission configuration; and a control system which is designed to release the secondary missiles from the primary missile as a function of mission specifications during the deployment from the launch configuration and to allow the primary missile and the deployed secondary missiles to assume the deployment configuration.

One of the ideas on which the present invention is based is to provide a modularly designed missile that can be divided into individual modules in use as required and depending on the respective scenario, which then perform different tasks individually and/or collaboratively in a swarm as required can take over. The system created in this way is scalable and therefore adaptable and can therefore be adapted very well, for example, to logistical, mechanical and/or aerodynamic aspects or requirements of the control technology. In this sense, it is ultimately a morphing missile system that can be adapted for varying complex airspace interactions and also offers great flexibility for future possible requirements that have not yet been defined. The system according to the invention can deal with combating multiple targets and highly variable and/or dynamic mission requirements, for which neither precise information about the mission nor about the targeted target needs to be available prior to the deployment. The multi-body flight system can be used both airborne and ground-based or, for example, from a watercraft.

Advantageous refinements and developments result from the further dependent claims and from the description with reference to the figures.

According to a development, the multi-body flight system can be designed for use by 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.

At the beginning of the mission, the multi-body system forms a modular unit and is transported from the flying carrier platform to a specified drop-off point. After the separation or the dropping of the multi-body flight system and depending on the specific mission or situation, this is divided into the primary missile and, for example two or more secondary missiles. The separated missiles now 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 steering nozzles, signal transmission devices, measuring instruments, navigation units and the like.

It goes without saying that the multi-body system can also be deployed from a land-based and/or water-based platform.

According to a further development, the primary missile and/or the secondary missile can be designed with wings and/or control surfaces, which align themselves automatically after the secondary missile has been triggered.

For this purpose, the individual missiles can include corresponding control and/or navigation devices, which take over both the transition from the launch configuration to the deployment configuration and the further navigation, guidance and general control of the respective missile. In principle, it is of course alternatively or additionally possible to monitor and control the individual missiles via a wireless communication link, e.g. via a corresponding device on board the flying carrier platform or a ground-based command post or the like.

According to a further development, the wings and/or control surfaces can be designed such that they can be extended and/or folded out of a fuselage of the respective missile.

In the starting configuration, the corresponding elements can thus be stowed away within the multi-body flight system in a space-saving and aerodynamically advantageous manner, and can only be extended for use, if necessary.

According to a further development, the primary missile and/or the secondary missile can each be designed as a guided missile.

Different variants are conceivable in this further development. For example, the multi-body flight system can first be dropped from an aircraft or the like as a unit and then initially act as a single guided missile. For this purpose, for example, wings and/or control surfaces as well as control nozzles or other drives of the individual sub-missiles can be used jointly. Depending on the mission and the situation, the secondary missiles can now be detached partially or in their entirety from the primary missile in order to bring the multi-body missile system into the deployment configuration. The primary missile and the secondary missile can each be designed as a guided missile with its own drive and its own control, in order to be able to act individually or as a swarm.

According to a development, the primary missile and the secondary missiles can each be designed with a communication device for wireless data exchange with one another.

In this way, the partial missiles can, for example, communicate with one another in a decentralized manner and exchange control commands and sensor data or the like. Likewise, the sub-missiles can be controlled together via a wireless communication network. For example, the primary missile can command the secondary missiles depending on the situation and mission requirements. In another example, the primary missile and secondary missiles may be commanded jointly from the launch platform.

According to one development, the control system can include a control device for the primary missile and a control device for each of the secondary missiles for controlling the missiles individually.

The sub-missiles, i.e. the primary missile and the secondary missiles, can now be used for different tasks in a more or less autonomous manner. For example, the primary missile can perform air surveillance tasks while the secondary missiles fly to a common or separate target.

It goes without saying that the control system can alternatively or additionally also include 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 a central task force. The sub-missiles can thus also be commanded in a centralized manner by a central, optionally mobile, external controller.

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

In addition to an individual use of the missiles, a swarm-like implementation for the execution of specific missions is thus provided, in which the missiles act together. The mission design can with these and similar applications can be defined very variably and vary from simple formation keeping to more complex tasks, which can include, for example, interactions with targets and/or the environment. For this purpose, the missiles can communicate with one another wirelessly via respective communication devices in order to exchange target and/or environment data, sensor and/or position or positioning information. The missiles can be subject to constant control by a central authority. Alternatively, however, these can also act as semi- or fully autonomous mobile units in order to implement different missions from surveillance and reconnaissance operations to tactical attacks.

According to one development, the secondary missiles can each be coupled laterally or axially to the primary missile and/or to the primary missile next to one another or one behind the other.

In this development, the secondary missiles can be released from the underside of the primary missile in the simplest possible way, laterally, in front, behind and/or, for example, downwards, for example by using aerodynamic resistance and suction for the separation process.

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

Such a triangular fuselage structure is expected to offer low visibility. The primary missile and secondary missiles may ideally be designed accordingly with a flat shape to further reduce visibility while minimizing aerodynamic drag and optimizing aerodynamic glide and climb characteristics for distant high-flying targets or the like. It goes without saying that, depending on the application and/or specifications, the person skilled in the art can also make different geometric configurations, possibly polygonal cross sections, of the sub-missile.

The above configurations and developments can be combined with one another as desired, insofar as this makes sense. Further possible refinements, developments and implementations of the invention also include combinations of features of the invention described above or below with regard to the exemplary embodiments that are not explicitly mentioned. In particular, the person skilled in the art will also add individual aspects as improvements or additions to the respective basic form of the present invention.

• 1 schematische Perspektivansicht eines Mehrkörperflugsystems gemäß einer Ausführungsform der Erfindung;
• 2 schematische Frontansicht des Mehrkörperflugsystems der 1 während des Übergangs aus einer Startkonfiguration in eine Einsatzkonfiguration;
• 3 schematische Draufsicht auf das Mehrkörperflugsystem der 2 in der Einsatzkonfiguration;
• 4 schematische Frontansicht des Mehrkörperflugsystems der 2 in der Einsatzkonfiguration;
• 5 schematische Perspektivansicht eines Mehrkörperflugsystems gemäß einer weiteren Ausführungsform der Erfindung;
• 6 schematische Frontansicht des Mehrkörperflugsystems der 5;
• 7 schematische Rückansicht des Mehrkörperflugsystems der 5;
• 8 schematische Frontansicht eines Primärflugkörpers des Mehrkörperflugsystems der 5 in einer Einsatzkonfiguration;
• 9 schematische Perspektivansicht des Primärflugkörpers der 8;
• 10 schematische Frontansicht eines Sekundärflugkörpers des Mehrkörperflugsystems der 5 in einer Einsatzkonfiguration;
• 11 schematische Perspektivansicht des Sekundärflugkörpers der 10;
• 12 schematische Frontansicht eines Mehrkörperflugsystems gemäß einer weiteren Ausführungsform der Erfindung beispielhaft in einem Container bzw. Startbehälter;
• 13 schematische Perspektivansicht des Mehrkörperflugsystems der 12;
• 14 schematische Detailansicht eines Luftfahrzeugs 14 zum Transport eines Mehrkörperflugsystems gemäß einer weiteren Ausführungsform der Erfindung; und
• 15 schematische Detailansicht gemäß 14 während der Befestigung eines Mehrkörperflugsystems an dem Luftfahrzeug.

The present invention is explained in more detail below with reference to the exemplary embodiments given in the schematic figures. They show:

• 1 schematic perspective view of a multi-body flight system according to an embodiment of the invention;
• 2 schematic front view of the multi-body flight system 1 during transition from a launch configuration to a deployment configuration;
• 3 schematic plan view of the multi-body flight system 2 in deployment configuration;
• 4 schematic front view of the multi-body flight system 2 in deployment configuration;
• 5 schematic perspective view of a multi-body flight system according to a further embodiment of the invention;
• 6 schematic front view of the multi-body flight system 5 ;
• 7 schematic rear view of the multi-body flight system 5 ;
• 8th schematic front view of a primary missile of the multi-body flight system 5 in a deployment configuration;
• 9 schematic perspective view of the primary missile 8th ;
• 10 schematic front view of a secondary missile of the multi-body missile system 5 in a deployment configuration;
• 11 schematic perspective view of the secondary missile 10 ;
• 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;
• 13 schematic perspective view of the multi-body flight system 12 ;
• 14 schematic detailed view of an aircraft 14 for transporting a multi-body flight system according to a further embodiment of the invention; and
• 15 schematic detailed view according to 14 during attachment of a multi-body flight system to the aircraft.

The accompanying figures are intended to provide a further understanding of embodiments of the invention. They illustrate embodiments and are used in connection with the Description of the explanation of principles and concepts of the invention. Other embodiments and many of the foregoing advantages will become apparent by reference to the drawings. The elements of the drawings are not necessarily shown to scale with respect to one another.

In the figures of the drawing, elements, features and components that are the same, have the same function and have the same effect--unless stated otherwise--are each provided with the same reference symbols.

1 and 2 FIG. 1 shows views of a multi-body flight system 10 according to an embodiment of the invention. The multi-body flight system 10 is used by an aircraft (not shown) from which it can be brought to a place of use and dropped or released there.

Basically, the solution described below is concerned with providing a missile that can meet different mission requirements for combating multiple targets as flexibly as possible, with precise information about the specific mission or the targets to be approached not having to be available initially. The approach provides for a modular combination of individual sub-missiles, 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 create a complex, possibly only subsequently defined To carry out the control task individually or in a swarm.

The current state of development in the field of electronics, sensors and software for aircraft and missiles requires completely new approaches for weapon systems. The present concept offers a suitable flexibility and modularity in order to be able to follow an increasing complexity and interaction of electronic components. A monolithic aircraft can hardly achieve such flexibility, since 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 the most diverse, initially seemingly incompatible requirements and can also react flexibly to future requirements.

The multi-body flight system 10 of 1 and 2 for this purpose comprises a primary missile 1 and two secondary missiles 2, which, via a carrying and launching system 11, e.g. ie in flight direction 12 are coupled. In this starting configuration, the missiles 1, 2 are firmly connected to one another to form an aircraft, which can be attached to an aircraft 14 in this form. For this purpose, the primary missile 1 is designed with a plurality of suspension eyes 8, via which the multi-body flight system 10 can be connected to corresponding suspension hooks 9 of a carrying and dropping system 11 in an aircraft 14, as shown in 14 and 15 is indicated by way of example, mounted and can be triggered at a site of this.

The secondary missiles 2 can be triggered in flight by the primary missile 1 in order to bring the system 10 from the launch configuration into a deployment configuration, as is shown on the right in 2 is shown. The missiles 1 , 2 are separated 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 triggers the secondary missile 2 depending on mission specifications during the mission from the launch configuration and the primary missile 1 and the secondary missile 2 can take the deployed configuration. As part of the control system 4, each missile 1, 2 comprises a control device 5 and a communication device 3 coupled thereto in terms of data technology, via which the missiles 1, 2 can communicate wirelessly with one another and with the aircraft 14 (for example via a radio network).

The control devices 5 ensure that the primary missile 1 and the secondary missile 2 configure themselves independently after decoupling. For example, wings and control surfaces 7 of both missiles 1, 2 are automatically extended or folded out and aligned, as shown in 3 and 4 is shown. Both missiles 1, 2 also have their own propulsion nozzles and are therefore designed as independent guided missiles which can act individually and/or collaboratively together in a swarm in order to fulfill specific mission specifications.

An alternative embodiment of the multi-body flight system 10 is with reference to 5 until 11 shown. As can be seen from these figures, the design of the primary missile 1 depending on the aerodynamic and flight mechanical requirements and the specific Develop mission requirements. The attachment position of the secondary missiles 2 on the primary missile 1 can also be varied.

As can be seen from the figures, the primary missile 1 is designed to be as flat as possible in order to meet any stealth requirements such as inconspicuous radar signatures and low visibility properties (“low obversability”). Furthermore, the aerodynamic resistance and ultimately the energy consumption can be minimized and the flight characteristics in terms of gliding and climbing can be optimized.

Corresponding considerations can be made for the secondary missiles 2, which in the present case leads to a triangular fuselage structure with a curved or rounded outer edge in order to enable the lowest possible visibility with minimal aerodynamic resistance.

• - Suchkopf und Abstandssensoren
• - Antennen und elektronische Störelemente
• - Steuer- und Kommunikationselektronik
• - Wirksysteme
• - ausfahrbare und ggf. bewegliche Tragflächen
• - Klapp- und Faltflügel
• - Tanksysteme
• - Motoren, Flüssig- und/oder Feststoffantriebe
• - Aufhängeelemente zur Verbindung an einer Trägerplattform
• - Fallschirme zur Landung
• - Kontrollelektronik und -mechanik

The design of the fuselage as well as the wings and control surfaces 7 can be designed advantageously, depending on the application, taking into account the aerodynamic requirements. In order to guarantee flexibility for future applications that are not specified in advance, as many functional technology elements and apertures as possible can be integrated in an optimized way, such as:

• - Seek head and distance sensors
• - Antennas and electronic jamming elements
• - Control and communication electronics
• - active systems
• - Extendable and possibly movable wings
• - Folding and folding wings
• - tank systems
• - Motors, liquid and/or solid drives
• - Suspension elements for connection to a carrier platform
• - Parachutes for landing
• - Control electronics and mechanics

In principle, the secondary missile 2 and primary missile 1 can have similar or even identical equipment, with the primary missile 1 only having to have additional fastening means for coupling to the carrier platform, i.e. the aircraft 14 in this case. Due to the similar design of the missiles 1, 2, it can be achieved that they can interact and cooperate with one another in the deployment configuration. For example, the missiles 1, 2 can form a swarm formation with more or less equal rights and act as a group. Due to the flexible training, target engagements can be carried out depending on mission scenarios that change at short notice. For example, a system can be used to attack a target together or three different targets, with the specific task of each missile 1, 2 also being able to be changed during use (e.g. it is possible to switch between combat, disruption and reconnaissance). The missiles 1, 2 can be integrated into a global information and control cloud. The missiles 1, 2 can be controlled locally and/or autonomously as well as centrally by a global authority.

It will be apparent to those skilled in the art that the electronic equipment of the individual missiles 1, 2 can be quite different in terms of costs and functionality, depending on the respective mission, in order to optimize possible uses. For example, the missiles 1, 2 can be equipped differently for specific missions in order to implement different functionalities such as reconnaissance, disruption, effect or the like. By suitably 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 area of operation, depending on the requirement.

Although the focus above has been on the deployment of the system 10 from an aircraft 14, the invention is not so limited. Water-based or ground-based carrier platforms are also conceivable. For example, for a ground-based application, the system 10 can do this, as in 12 and 13 shown, are implemented with a corresponding scaling in a container 13 or a starting container. As a supplement to this, an additional starting engine (booster) in the form of a solid fuel engine or the like can be embedded in the system 10 .

All in all, a modular multi-body aircraft that can be used extremely flexibly is provided, which can be reconfigured with regard to the specifically required mission specifications and is therefore also prepared for potential changes in requirements in the future.

In the foregoing Detailed Description, various features have been grouped together in one or more examples to improve the rigor of presentation. However, it should be clear that the above Description is purely illustrative, but 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 immediately and immediately apparent to those skilled in the art in view of the above description.

The exemplary embodiments were selected and described in order to be able to present the principles on which the invention is based and its possible applications in practice in the best possible way. This enables those skilled in the art to optimally modify and use the invention and its various exemplary embodiments in relation to the intended application. In the claims and the description, the terms “including” and “having” are used as neutral terms for the corresponding terms “comprising”. Furthermore, the use of the terms “a”, “an” and “an” should not fundamentally exclude a plurality of features and components described in this way.

Reference List

1

primary missile

2

secondary missile

3

control device

4

control system

5

communication facility

6

bottom

7

wing and control surface

8th

hanging loop

9

hanging hook

10

multi-body flight system

11

carrying and dropping system

12

flight direction

13

Container

14

aircraft

QUOTES INCLUDED IN DESCRIPTION

This list of documents cited by the applicant was generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Patent Literature Cited

• US7624947B2 [0003]

Claims (10)

Multibody flight system (10) comprising: a primary missile (1); several secondary missiles (2), each of which can be coupled via a carrying and launching system (11) to the primary missile (1) to create a launch configuration and can be triggered by the primary missile (1) in flight to create a mission configuration; and a control system (4) which is designed to trigger the secondary missiles (2) from the primary missile (1) depending on mission specifications during the deployment from the launch configuration and the primary missile (1) and the triggered secondary missiles (2) to assume the deployment configuration to let. Multi-body flight system (10) according to claim 1 , the multi-body flight system (10) being designed for use by an aircraft (14), the control system (4) being designed to separate the secondary missile (2) from the primary missile after the multi-body flight system (10) has separated from the aircraft (14). (1) trigger. Multi-body flight system (10) according to claim 1 or 2 , wherein the primary missile (1) and/or the secondary missile (2) are formed with wings and/or control surfaces (7) which align themselves automatically after the secondary missile (2) has been triggered. Multi-body flight system (10) according to claim 3 , wherein the wings and/or control surfaces (7) can be extended and/or folded out of a fuselage of the respective missile (1, 2). Multi-body flight system (10) according to one of Claims 1 until 4 , wherein the primary missile (1) and / or the secondary missile (2) are each designed as a guided missile. Multi-body flight system (10) according to one of Claims 1 until 5 , wherein the primary missile (1) and the secondary missile (2) are each formed with a communication device (5) for wireless data exchange with one another. Multi-body flight system (10) according to one of Claims 1 until 3 , wherein the control system (4) comprises a control device (3) of the primary missile (1) and a respective control device (3) of the secondary missile (2) for individually controlling the missile (1, 2). Multi-body flight system (10) according to claim 7 , wherein the control devices (3) of the missiles (1, 2) for the collaborative control of the missiles (1, 2) are formed. Multi-body flight system (10) according to one of Claims 1 until 8th , wherein the secondary missiles (2) can each be coupled laterally or axially to the primary missile (1) and/or next to one another or one behind the other to the primary missile (1). Multi-body flight system (10) according to claim 9 , wherein the secondary missiles (2) have a triangular fuselage cross-section.

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