DE102014005300B4 - Weapon carrier for attaching at least one unmanned aerial vehicle to a carrier aircraft, weapon system and aircraft - Google Patents

Abstract

Weapon carrier for attaching a plurality of unmanned missiles (2; 2', 2'') to a carrier aircraft (3), with - mechanical aircraft adapter means (14), - electrical aircraft adapter means (15), - a plurality of missile launching devices (16) for receiving the unmanned missiles (2; 2', 2'') and - at least one weapon control computer (40) that can be connected to the missiles (2; 2', 2'') for data transmission, - wherein the electrical aircraft adapter means (15) have connection means (151, 152) for establishing electrical connections between the carrier aircraft (3) and the weapon carrier (1; 1'; 1''; 1'''), which have at least one electrical power supply for the weapon carrier (1; 1'; 1''; 1''') and a data transmission connection between at least one computer (30) of the carrier aircraft (3) and the at least one weapon control computer (40) comprise,characterized in that- the weapon carrier is provided with autonomous sensor means (5) which have an imaging sensor (50) and which are connected to a network structure (11) internal to the weapon computer, to which the weapon control computer (40) is also connected;- for each of the missile launching devices (16; 16', 16''), a missile launching controller (160; 160', 160'') is provided, which is or can be electrically connected to the weapon control computer (40) for data transmission,the weapon carrier (1; 1'; 1''; 1''') is of modular design, so that individual components of the weapon carrier are interchangeable

Description

TECHNICAL AREA

The present invention relates to a weapon carrier for attaching at least one unmanned missile to a carrier aircraft. It also relates to a weapon system comprising such a weapon carrier and at least one unmanned missile that can be attached to it. Finally, the invention also relates to an aircraft with at least one such weapon system.

BACKGROUND OF THE INVENTION

Unmanned missiles that are flown to an operational area by means of a carrier aircraft, such as an unmanned combat drone of the MALE (Medium Altitude Long Endurance) type, and then dropped off from the carrier aircraft, are not only mechanically attached to the carrier aircraft for the flight, but are also electronically connected to the avionics, the navigation system and a weapon control computer in the carrier aircraft, as well as electrically connected to it. This integration of missile and carrier aircraft requires interventions in the hardware and software of the carrier aircraft during the development of an unmanned missile. This in turn requires that the manufacturer of the carrier aircraft discloses the relevant information to the developer of the unmanned missile and that, where appropriate, regulations such as the International Traffic in Arms Regulations (ITAR), with which the USA controls trade in arms and defense goods, must be observed. This integration, which represents an intervention in the carrier aircraft's systems, can also result in the aircraft or parts thereof losing their official approval and consequently having to undergo a new aviation approval review. The developer of the unmanned aerial vehicle is therefore very dependent on the cooperation of the carrier aircraft manufacturer and official approvals (for example from US authorities in accordance with ITAR), and the development time is significantly extended by any new approval of the carrier aircraft and missile combination.

To overcome these disadvantages, a standardized method for coupling a missile to a carrier aircraft would be desirable.

STATE OF THE ART

From the US 6 655 254 B1 A launching device for multiple missiles ('Multiple Airborne Missile Launcher') is known, which is designed to accommodate two missiles. This is made possible by the fact that a bomb carrier device provided on the aircraft does not pick up the unmanned missiles directly, but via an adapter device that has two so-called launcher aircraft units (LAU), each of which can accommodate a missile. This adapter device is attached to the bomb rack unit (BRU) of the carrier aircraft using eyelets (like a conventional bomb).

From the US 8 141 468 B2 An adjustable bomb carrier for a carrier aircraft is known which, by means of special mechanical devices, enables different bomb loads to be carried on the carrier aircraft and which in this way allows the realisation of variable bomb load configurations.

From the WO 2008/ 121 431 A2 An ammunition control unit is known that integrates at least one weapon into military vehicles, such as aircraft.

For such integration, the ammunition control unit provides an interface between the existing electronics of the military vehicle and the electronics of the weapon. The device includes input/output interfaces for communication with the vehicle and the weapon, a processor and a memory, and reconfigurable logic stored in the memory and executable by the processor.

From the US 7 610 841 B2 A system for attaching a load to an aircraft is known, comprising an aerodynamically efficient on-board storage facility consisting of removable, mountable fuel tanks on the outside of the aircraft. The conventional external fuel tank is modified so that the external shape of the tank is substantially retained, while the interior of the tank is suitably restructured. This allows the introduction of internal, airborne attachment means, control means for the operation of the airborne storage facility, and support means for the operation of the airborne storage facility. For example, the airborne storage facility may be a multiple rocket launcher.

From the GB 2 502 960 A A sensor system is known that is mounted on an aircraft fuselage via an interface with a pylon. The sensor system comprises a payload that is essentially a storage unit. The payload may include a ram air turbine, sensors, a processor and a transceiver. The aerodynamic properties, moments of inertia and mass distribution of the storage unit are designed to match those of a storage unit with another payload already certified for the aircraft.

The product sheet of Marvin Engineering Co., Inc. (https://marvineng.com/wpcontent/uploads/sites/5/2018/01/LAU-127_128_129-Launcher.pdf) refers to the LAU-127, 128, 129 missile rail launcher. The missile rail launcher is configured for the F-15, F16 and F-18 as well as other aircraft types.

The weapon carriers known from the state of the art mainly feature mechanical devices for transporting and dropping missiles or bombs. They conduct and distribute electrical signals (energy, discrete signals, data bus) between the carrier aircraft and the weapon, push the weapon away from the carrier pneumatically or by means of gas pressure during a drop launch, or guide the missile in a rail during a rail launch.

DESCRIPTION OF THE INVENTION

The object of the present invention is therefore to enable the attachment of unmanned missiles to a carrier aircraft without having to intervene deeply in the systems of the carrier aircraft during the development of the missile, as has been the case up to now. Furthermore, the invention is intended to create a weapon system with unmanned missiles that can be integrated into a carrier aircraft more quickly. In addition, a unit consisting of a carrier aircraft and such a weapon system is to be specified.

The part of the problem directed at the attachment of unmanned missiles to a carrier aircraft is solved by a weapon carrier with the features of patent claim 1. Furthermore, the weapon carrier according to claim 1 enables the attachment of several individually deployable and controllable missiles. In this way, different missiles can also be attached and controlled in an advantageously simple manner. In addition, the modular design of the weapon carrier enables the weapon carrier to be easily and quickly adapted to different application spectrums.

This weapon carrier according to the invention is characterized by the presence of mechanical aircraft adapter means, electrical aircraft adapter means, at least one missile launching device for receiving the at least one unmanned missile and at least one weapon control computer that can be connected to the at least one missile for data transmission, wherein the electrical aircraft adapter means have connection means for establishing electrical connections between the carrier aircraft and the weapon carrier, which comprise at least one electrical energy supply for the weapon carrier and a data transmission connection between at least one computer of the carrier aircraft and the at least one weapon control computer.

ADVANTAGES

The modular design of the weapon carrier according to the invention makes it particularly advantageous to achieve the configurability of a weapon system consisting of a weapon carrier and a missile. This modular design with the weapon control computer provided in the weapon carrier enables the armament-specific functions to be shifted from the carrier aircraft to the weapon system and thus the armament-specific functions in the carrier aircraft to be reduced. This minimizes the need to adapt the carrier aircraft by shifting the functions to the weapon carrier and by the configurability of the weapon carrier and missile when the armament is modified, thus ensuring the missile manufacturer's sovereignty over the armament of a carrier aircraft from a third-party manufacturer to a large extent.

• • kurze Entfernung / größere Entfernung
• • mobil / immobil
• • gepanzert / ungepanzert
• • aufgeklärt / unaufgeklärt

die geeignete Waffensystemkonfiguration selber vor Missionsbeginn zusammenzustellen, wobei der Anpassungsbedarf des Trägerluftfahrzeugs in Bezug auf das Anwendungsspektrum minimiert ist.The user of the missile is thus able to adjust the target characteristics

• • short distance / longer distance
• • mobile / immobile
• • armored / unarmored
• • enlightened / unenlightened

to assemble the appropriate weapon system configuration before the start of the mission, whereby the need for adaptation of the carrier aircraft in relation to the application spectrum is minimized.

In contrast, the weapon carriers known from the state of the art do not contain their own electronics or avionics that would be able to carry out weapon-specific functions that previously resided in the carrier aircraft, thus shifting value creation and sovereignty from the carrier aircraft to the armament system.

A particularly advantageous development of the invention is one in which for each of the missile launchers devices, a missile launch controller is provided which is electrically connected or connectable to the weapon control computer for data transmission. This enables several individually deployable and controllable missiles to be attached to a weapon carrier.

Preferably, the at least one missile launching device is provided with mechanical missile adapter means and electrical missile adapter means. This not only creates flexibility with regard to the attachment of a weapon system to different carrier aircraft, but also creates the possibility of attaching different missiles to the carrier aircraft without major interventions in the carrier aircraft.

It is also advantageous if the weapon carrier has a data link communication device that is or can be electrically connected to the weapon control computer for data transmission and that is or can be connected to an antenna that is preferably provided on the weapon carrier. This creates a direct communication option between the weapon carrier and the missile or a control center or a telemetry station that does not require the resources of the carrier aircraft, i.e. is self-sufficient in this respect.

Preferably, the weapon carrier has an imaging sensor. Target detection or target recognition can thus be carried out autonomously by the weapon carrier without having to use the resources of the carrier aircraft.

It is advantageous if the weapon carrier has a target illumination device. This enables the use of missiles with a semi-active homing head.

If the weapon carrier has a data recording system for recording operating data of the weapon carrier and/or of the at least one missile, wherein the data recording system is connected or connectable to the data link communication device for telemetry data transmission, telemetry data transmission can be carried out autonomously by the weapon carrier.

The independence of the weapon carrier from the carrier aircraft is further increased if the weapon carrier has an autonomous power supply system.

The present invention also includes a weapon system comprising a weapon carrier according to the invention and at least one missile attachable thereto.

Preferably, the missile is also modular and can be configured to suit a specific application. The modular design of the missile and its configurability, in conjunction with the modular and also configurable weapon carrier, create a highly flexible weapon system that can be adapted at short notice to different applications and to different carrier aircraft.

The configurability of the missile preferably includes hardware configurability and/or software configurability.

The invention further comprises an aircraft with at least one weapon system according to the invention.

Preferred embodiments of the invention with additional design details and further advantages are described and explained in more detail below with reference to the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

• 1 eine schematische Darstellung einer ersten Ausführungsform eines erfindungsgemäßen Waffenträgers;
• 2 eine schematische Darstellung einer zweiten, abgewandelten Ausführungsform des erfindungsgemäßen Waffenträgers;
• 3 eine schematische Draufsicht auf einen Waffenträger mit zwei nebeneinander angeordneten Flugkörpern entsprechend 1 und
• 4 eine schematische Draufsicht auf einen Waffenträger mit jeweils zwei hintereinander und nebeneinander angeordneten Flugkörpern entsprechend 2.

It shows:

• 1 a schematic representation of a first embodiment of a weapon carrier according to the invention;
• 2 a schematic representation of a second, modified embodiment of the weapon carrier according to the invention;
• 3 a schematic plan view of a weapon carrier with two missiles arranged side by side according to 1 and
• 4 a schematic plan view of a weapon carrier with two missiles arranged one behind the other and one next to the other according to 2 .

PRESENTATION OF PREFERRED EMBODIMENTS

In 1 A first embodiment of a weapon carrier 1 according to the invention for attaching at least one unmanned missile 2 to a carrier aircraft 3 is shown in a schematic representation.

The weapon carrier 1 has a frame 10, which as a mechanical structural element accommodates the individual components described below. The frame 10 is surrounded by an aerodynamic housing cover 12, which is only partially shown in the figure. This housing cover 12 can be made of metal or plastic and can, for example, be their material, shape and/or paintwork give them stealth properties.

The weapon carrier 1 is provided on its upper side with mechanical aircraft adapter means 14 which are mechanically firmly connected to the frame 10 and which have suspensions 140, 142 with which the weapon carrier 1 can be attached to corresponding load-carrying hooks (not shown) of the carrier aircraft 3.

Furthermore, the weapon carrier 1 is equipped with electrical aircraft adapter means 15, which can be connected to electrical devices of the carrier aircraft 3, for example a computer 30 of the carrier aircraft 3. This connection is made via an umbilical plug 152 provided on the top of the frame, which can be electrically connected to the carrier aircraft 3 by means of an umbilical cable 151. The electrical aircraft adapter means 15 have further devices, which are described further below.

The weapon carrier 1 is equipped on its underside with a missile launching device 16 which is designed to accommodate the unmanned missile 2. The missile launching device 16 is also provided with mechanical missile adapter means 18 and electrical missile adapter means 19. The mechanical missile adapter means 18 are also firmly connected to the frame 10, so that a load transfer between the mechanical missile adapter means 18 and the mechanical aircraft adapter means 14 is possible via the structures of the frame 10.

The mechanical missile adapter means 18 comprise a load-depositing device 180, which in the example shown comprises two releasable hooks 181, 182 and (not shown) impact arms, as are conventionally used as bomb release units (BRU) in military aviation. Eyelets 20, 21 of the unmanned missile 2 are suspended from the load-receiving hooks 181, 182 in a manner known to those skilled in the art. Furthermore, the missile-depositing device 16 is provided on its underside with an umbilical plug 190, which can be electrically connected via an umbilical cable 191 to an umbilical plug 22 on the top of the unmanned missile.

The electrical aircraft adapter means 15 and the electrical missile adapter means 19 are formed by a weapon carrier electronics 4, the components described below of which have properties or elements which adapt signals, data or electrical voltages to the aircraft (aircraft adapter means) or to the missile (missile adapter means).

The weapon carrier electronics 4 have a weapon control computer 40, which is electrically connected to the aircraft-side umbilical connector 152 via a Milbus 41 and can be connected to the computer 30 of the aircraft 3 via the umbilical cable 151. The weapon control computer 40 is in turn electrically connected to a controller 160 assigned to the missile launching device 16 for data transmission via a network structure 11 provided in the weapon carrier 1, for example an Ethernet. Each missile launching device is assigned such a controller.

Furthermore, the weapon carrier electronics 4 has a safety device 42, which is also connected to the aircraft-side umbilical connector 152 and to the network structure 11. A power distributor 44 supplies the electrical devices provided in the weapon carrier 1 with electrical energy, which it also receives from the aircraft 3 via the umbilical connector 152 and the umbilical cable 151.

The weapon carrier 1 is further provided with autonomous sensor means 5, which have an imaging sensor 50, for example a CCD sensor or an IR sensor or other imaging sensors. A laser target illuminator 52 is provided in the weapon carrier 1 to assist the sensor means 5 in object detection, in that the laser target illuminator 52 illuminates the area detected by the sensor means 5. The sensor means 5 are connected on the one hand to the network structure 11 in the weapon carrier 1 and on the other hand via a video data line 51 to a video recording device 54, which is also connected to the network structure 11. Also connected to the network structure 11 is a data link communication device 56, which has an antenna 57, which sends and receives signals for data exchange, preferably with a remote missile or with a ground station. A wind generator 58 is provided as an autonomous power supply, which generates electrical energy by means of a wind turbine (not shown) which is set in rotation by the incoming air and a generator driven by the wind turbine and supplies it to the safety device 42 via a safety energy line 59.

The weapon carrier 1 also has a compressed air compressor 13, which generates compressed air for actuating the hooks 181, 182 and the impact arms of the load-setting device 180 by means of electrical energy from the energy distributor. The compressed air is supplied via a compressed air line 13' of the Missile launching device 16. The sensor means 5 are also supplied with compressed air via a further compressed air line 13", which is required, for example, for sensor cooling.

The weapon carrier 1 is modular in design so that individual components of the weapon carrier 1 are interchangeable. For example, the missile launching device 16 with its mechanical missile adapter means 18 can be replaced by a variant which is 2 and has two missile launching devices 16', 16" for two missiles 2', 2" arranged one behind the other. Accordingly, two controllers 160', 160" are also provided, each of which is assigned to one of the missile launching devices 16' or 16".

An external programming computer 60 and an external power supply device 62 of an external programming device 6 can be connected to the internal network structure 11 and to the aircraft-side umbilical connector 152. The weapon carrier 1 can be individually configured by means of the external programming computer 60, wherein the electrical aircraft adapter means 14 and/or the electrical missile adapter means 19 are connected to the aircraft 3 or to the missile 2, 2', 2" and the corresponding missile configuration (for example according to 1 or according to 2 are customizable).

The 3 shows a schematic plan view of one of the 1 Variant corresponding to the embodiment shown with two missiles 2, 2A mounted next to each other on corresponding missile launchers, each with a controller.

The 4 shows a schematic plan view of one of the embodiments in 2 corresponding variant, in which, however, two short missiles 2', 2'', 2'A and 2''A are mounted next to each other and one behind the other on corresponding missile launchers, each with a controller.

The modularity of the weapon carrier 1, 1', 1'' according to the invention is demonstrated by the weapon carrier configurations shown in the table below.

In a first configuration of the weapon carrier 1' ( 3 ), which is referred to as "Configuration A", two missiles 2, 2A are provided side by side, each with a missile launcher. The following components are provided for this configuration:

Weapon carrier configuration A:

• - Weapon control computer 40
• - Safety device 42
• - Energy distributor 44
• - Air compressor 13
• - two missile launcher controllers 160
• - two missile launchers 16
• - Video recording device 54
• - CCD/IR sensor (Sensor 50)
• - Laser target illuminator 52
• - semi-active laser seeker

In a second, alternative configuration of the weapon carrier 1' (configuration B), which also provides for two missiles 2, 2A arranged side by side, the following components are provided:

Weapon carrier configuration B:

• - Weapon control computer 40
• - Safety device 42
• - Energy distributor 44
• - Air compressor 13
• - two missile launcher controllers 160
• - two missile launchers 16
• - Video recording device 54
• - Data link communication device 56
• - CCD/IR seeker head

The modularity is particularly evident in the fact that configuration A provides a semi-active laser seeker with a laser target illumination device, while configuration B provides a CCD/IR seeker together with a data link communication device.

Accordingly, for example, in the 4 Different configurations can be implemented modularly in the variant shown. In a first configuration of the weapon carrier 1'' (configuration C), the following components are provided:

Weapon carrier configuration C:

• - Weapon control computer 40
• - Safety device 42
• - Energy distributor 44
• - Air compressor 13
• - four missile launcher controllers 160', 160''
• - four missile launchers 16', 16''
• - Dummy search head (GPS guided).

Another alternative exemplary configuration of the 4 The embodiment shown has the following components:

Weapon carrier configuration D:

• - Weapon control computer 40
• - Safety device 42
• - Energy distributor 44
• - Air compressor 13
• - four missile launcher controllers 160', 160''
• - four missile launchers 16', 16''
• - CCD IR sensor (Sensor 50)
• - Laser target illuminator 52
• - semi-active laser seeker

A key aspect of the weapon carrier according to the invention is, in addition to the flexible and rapid adaptability to different carrier aircraft models achieved by the aircraft adapter means, the modular design of the weapon carrier with exchangeable components. This modular design enables the weapon carrier to be easily and quickly adapted to different application spectrums and, in conjunction with hardware and software missile adapter means, enables flexible adaptation to different missiles, which are also modular in design and can be configured for specific purposes.

• - automatisches Erkennen (plug-in and play) der vorliegenden Konfiguration, also der im Waffenträger eingebaute Komponenten und der angebauten Flugkörper, mittels eines Gegenstücks am Umbilical-Stecker 152 vom Trägerluftfahrzeug oder von einem an den Umbilical-Stecker 152 ansteckbaren Bedienpanel durch Alive-Abfragen;
• - Interaktion mit einem Avionik System eines Trägerluftfahrzeugs entsprechend Mil-Standard 1760 oder Universal Armament Interface (UAI);
• - Interaktion mit einem externen Bedienpanel beim Test von Waffenträger und angebauten Flugkörpern;
• - Steuerung des internen Netzwerk-Datenverkehrs als Master;
• - Steuerung der internen Geräte (Sicherheitseinrichtung, Energieverteiler, Datenlink-Transceiver, CCD/IR-Sensor, Laserzielbeleuchter, Telemetrie-Recording, Druckluftkompressor);
• - lokales Speicher-Management-System für Schiessbereichs-Berechnung (LAR = launch acceptable region), Order of Engagement, Release-Order/Sequenzing, Jettision Management;
• - Steuerung der angebauten Flugkörper über die jeweiligen Kontroller.
• - Missionsplanungs-Funktionen für stationäre Ziele mit Planung, Laden, Verifizieren von Missonsdaten;
• - Steuerung des Laden und Löschens von Kryptokeys in die Flugkörper, in ein Onboard-Telemetriesystem und in das Datenlinksystem zur Signalverschlüsselung über ein externes Bedienpanel;
• - Lebensdauerüberwachung (Life-Cycle-Monitoring) zwecks Erzeugung eines Zustandsberichts (Health-Statement).

The functions of the weapon control computer 40 include the following activities:

• - automatic recognition (plug-in and play) of the current configuration, i.e. the components installed in the weapon carrier and the attached missiles, by means of a counterpart on the umbilical connector 152 of the carrier aircraft or of a control panel pluggable to the umbilical connector 152 by means of alive queries;
• - Interaction with an avionics system of a carrier aircraft according to Mil-Standard 1760 or Universal Armament Interface (UAI);
• - Interaction with an external control panel when testing the weapon carrier and attached missiles;
• - Control of internal network traffic as master;
• - Control of internal devices (safety device, power distributor, data link transceiver, CCD/IR sensor, laser target illuminator, telemetry recording, compressed air compressor);
• - local memory management system for launch acceptable region calculation (LAR), order of engagement, release order/sequencing, jettision management;
• - Control of the attached missiles via the respective controllers.
• - Mission planning functions for stationary targets with planning, loading, verification of mission data;
• - Control of the loading and deletion of crypto keys in the missiles, in an onboard telemetry system and in the data link system for signal encryption via an external control panel;
• - Life cycle monitoring to generate a health statement.

• - ein sicheres Auslösen des Absetzvorgangs (Release) von angebauten Flugkörpern in Abhängigkeit vom Zustand der durch den Windgenerator 58 bereitgestellten Sicherheitsenergieversorgung;
• - ein sicheres Durchschalten eines Release-Consent-Signales zur Freigabe des Absetzvorgangs zu den angebauten Flugkörpern;
• - das Steuern der Verteilung von elektrischer Energie zu den angebauten Flugkörpern;
• - eine sichere Freigabe der Laseraktivierung;
• - eine sichere Freigabe der Datenlinkaktivierung.

The functions of the safety device 42 include the following activities:

• - a safe triggering of the release of attached missiles depending on the state of the safety energy supply provided by the wind generator 58;
• - a secure transmission of a release consent signal to authorize the launch of the attached missiles;
• - controlling the distribution of electrical energy to the attached missiles;
• - a safe release of the laser activation;
• - a secure release of the data link activation.

• - kontrolliertes Durchschalten der elektrischen Energie zu den internen Verbrauchern des Waffenträgers 1, 1', 1'' und zu den Flugkörpern 2, 2', 2'';
• - kontrolliertes Durchschalten der elektrischen Energie für sicherheitskritische Schaltfunktionen zur Sicherheitseinrichtung 42.

The functions of the energy distributor 44 include the following activities:

• - controlled switching of electrical energy to the internal consumers of the weapon carrier 1, 1', 1'' and to the missiles 2, 2', 2'';
• - controlled switching of electrical energy for safety-critical switching functions to the safety device 42.

• - die Interaktion (Signal- und Datenaustausch) des Waffenträgers mit dem angebauten Flugkörper mittels einer MMSI-Schnittstelle unter Kontrolle des Waffen-Steuerungscomputers 40;
• - das Steuern von Funktionen der Flugkörper-Absetzvorrichtung 16, 16', 16'', insbesondere der Haken 181, 182, der (nicht gezeigten) Stößel und der (nicht gezeigten) Abpratzarme.

The functions of the respective controller 160, 160', 160'' associated with a missile launcher 16, 16', 16'' include the following activities:

• - the interaction (signal and data exchange) of the weapon carrier with the attached missile by means of an MMSI interface under the control of the weapon control computer 40;
• - controlling functions of the missile launching device 16, 16', 16'', in particular the hooks 181, 182, the tappets (not shown) and the impact arms (not shown).

• - Übertragung von Video- und Steuerdaten zwischen dem Waffenträger und den sich im Flug befindlichen Flugkörpern, falls der jeweilige Flugkörper mit einem CCD/IR-Suchkopf mit Zieltracker konfiguriert ist.

The functions of the data link communication device 56 include the following activity:

• - Transmission of video and control data between the weapon carrier and the missiles in flight, if the respective missile is configured with a CCD/IR seeker head with target tracker.

• - Sensierung des vom Sensor erfassbaren Szenarios, wobei die Sensordaten via Datenlink an den Waffenträger übertragen werden, falls der Flugkörper nicht mit einem abbildenden Suchkopfsensor konfiguriert ist, sondern mit einem semi-aktiven Laser Suchkopf; von dort werden die Sensordaten über eine DatenSchnittstelle (Mil-Std 1760 bzw. UAI) zum Trägerluftfahrzeug und von dort mittels dessen Kommunikationsanlagen zu einer Bodenstation, in der sich der Pilot befindet, weitergeleitet.

The functions of the CCD/IR sensor (Sensor 50) include the following activities:

• - Sensing of the scenario that can be detected by the sensor, whereby the sensor data is transmitted to the weapon carrier via a data link if the missile is not configured with an imaging seeker sensor but with a semi-active laser seeker; from there the sensor data is forwarded via a data interface (Mil-Std 1760 or UAI) to the carrier aircraft and from there via its communication systems to a ground station where the pilot is located.

• - Falls der Flugkörper mit einem semi-aktiven Laser-Suchkopf konfiguriert ist, erfolgt mittels des Laserzielbeleuchters 52 des Waffenträgers die Markierung des Zieles.

The functions of the laser target illuminator 52 include the following activities:

• - If the missile is configured with a semi-active laser seeker, the target is marked using the laser target illuminator 52 of the weapon carrier.

A modularly configurable missile designed for use on the weapon carrier according to the invention has a standard interface 'Miniature Mission Store Interface' (MMSI, AS 5725) to the missile launching device of the weapon carrier. The missile is also designed as a modular system. Before use, the missile is configured by assembling it from always-usable and alternative modules, depending on the mission, which are mechanically and electrically compatible with each other. The weapon carrier must be equipped with a weapon carrier configuration that matches a missile configured in this way.

• - Rudermaschinen;
• - IMU/GPS Sensorik;
• - Waffen-Steuerungscomputer, der die eingebauten Module erkennt und die Software automatisch konfiguriert (Marsch/Endlenkung, Flugzustandsregelung, Zündverfahren, Kommunikation zum Waffenträger etc.);
• - Thermalbatterie;
• - elektronische Safe-Arm-Unit und Zünder.

The configurable missile always has the following missile modules:

• - rowing machines;
• - IMU/GPS sensors;
• - Weapon control computer that recognizes the installed modules and automatically configures the software (cruise/final guidance, flight state control, firing procedure, communication with the weapon carrier, etc.);
• - Thermal battery;
• - electronic safe arm unit and detonator.

• - Air-Frame: kurze Struktur (2, 4) oder lange Struktur (1, 3);
• - Suchkopf: semi-aktiver Laser (für man-in-the-loop-Steuerung) oder CCD/IR (für man-in-the-loop-Steuerung) oder Dummy (rein GPS gelenkt);
• - Gefechtskopf: Penetrator oder Blast/Fragmentation, programmierbar, insensitiver Sprengstoff;
• - Mittel zur Vergrößerung der Reichweite (Reichweitenzusatz): Booster (beim Release oder vor der Zielpenetration zündbar) und/oder Gleitflügelsatz (ausklappbar, zum Beispiel an der Unterseite);
• - Kommunikationszusatz: Datenlink-Kommunikationsvorrichtung.

The configurable missile can also have the following alternative missile modules:

• - Air-Frame: short structure ( 2 , 4 ) or long structure ( 1 , 3 );
• - Seeker head: semi-active laser (for man-in-the-loop control) or CCD/IR (for man-in-the-loop control) or dummy (purely GPS guided);
• - Warhead: penetrator or blast/fragmentation, programmable, insensitive explosive;
• - Means of increasing the range (range extension): booster (can be ignited on release or before target penetration) and/or gliding wing set (foldable, for example on the underside);
• - Communication accessory: data link communication device.

• Flugkörper-Konfiguration A (in Verbindung mit Waffenträger-Konfiguration D):
  • für Zielmuster: kurze Entfernung, ungepanzert, mobil, zeitkritisch (target of opportunity), urbanes Szenario:
    • immer zu verwendende Flugkörper-Module:
      • - Air Frame: kurze Struktur
      • - Suchkopf: Dummy (GPS gelenkt)
      • - kein Reichweitenzusatz
      • - Gefechtskopf: Blast/Fragmentation
      • - Kommunikation: ohne Zusatz
• Flugkörper-Konfiguration B (in Verbindung mit Waffenträger-Konfiguration C):
  • für Zielmuster: kurze Entfernung, armiert, immobil, aufgeklärt immer zu verwendende Flugkörper-Module:
    • - Air Frame: lange Struktur
    • - Suchkopf: Dummy (GPS gelenkt)
    • - Reichweitenzusatz: Booster
    • - Gefechtskopf: Penetrator
    • - Kommunikation: ohne Zusatz
• Flugkörper-Konfiguration C (in Verbindung mit Waffenträger-Konfiguration C):
  • für Zielmuster: große Entfernung, armiert, immobil, aufgeklärt immer zu verwendende Flugkörper-Module:
    • - Air Frame: lange Struktur
    • - Suchkopf: Dummy (GPS gelenkt)
    • - Reichweitenzusatz: Gleitflügelsatz und Booster für Endanflug
    • - Gefechtskopf: Penetrator
    • - Kommunikation: ohne Zusatz
• Flugkörper-Konfiguration D (in Verbindung mit Waffenträger-Konfiguration B):
  • für Zielmuster: große Entfernung, armiert, immobil, unaufgeklärt (target of opportunity) immer zu verwendende Flugkörper-Module:
    • - Air Frame: lange Struktur
    • - Suchkopf: CCD/IR (mit Zieltracking)
    • - Reichweitenzusatz: Gleitflügelsatz und Booster für Endanflug
    • - Gefechtskopf: Penetrator
    • - Kommunikation: Datenlink zum Waffenträger
• Flugkörper-Konfiguration E (in Verbindung mit Waffenträger-Konfiguration A):
  • für Zielmuster: große Entfernung, gepanzert, mobil, zeitkritisch immer zu verwendende Flugkörper-Module:
    • - Air Frame: lange Struktur
    • - Suchkopf: semi-aktiver Laser
    • - kein Reichweitenzusatz
    • - Gefechtskopf: Penetration
    • - Kommunikation: ohne Zusatz

The modules of the missile kit system enable various missile variants, for example:

• Missile configuration A (in conjunction with weapon carrier configuration D):
  • for target pattern: short range, unarmored, mobile, time-critical (target of opportunity), urban scenario:
    • Missile modules to always be used:
      • - Air Frame: short structure
      • - Search head: Dummy (GPS guided)
      • - no range addition
      • - Warhead: Blast/Fragmentation
      • - Communication: without additional
• Missile configuration B (in conjunction with weapon carrier configuration C):
  • for target pattern: short range, armed, immobile, reconnaissance missile modules to be used at all times:
    • - Air Frame: long structure
    • - Search head: Dummy (GPS guided)
    • - Range extension: Booster
    • - Warhead: Penetrator
    • - Communication: without additional
• Missile configuration C (in conjunction with weapon carrier configuration C):
  • for target patterns: long range, armed, immobile, reconnaissance missile modules to be used at all times:
    • - Air Frame: long structure
    • - Search head: Dummy (GPS guided)
    • - Range extension: Gliding wing set and booster for final approach
    • - Warhead: Penetrator
    • - Communication: without additional
• Missile configuration D (in conjunction with weapon carrier configuration B):
  • for target patterns: long range, armed, immobile, undetected (target of opportunity) missile modules to always be used:
    • - Air Frame: long structure
    • - Seeker head: CCD/IR (with target tracking)
    • - Range extension: Gliding wing set and booster for final approach
    • - Warhead: Penetrator
    • - Communication: Data link to the weapon carrier
• Missile configuration E (in conjunction with weapon carrier configuration A):
  • for target patterns: long range, armoured, mobile, time-critical missile modules that can always be used:
    • - Air Frame: long structure
    • - Seeker head: semi-active laser
    • - no range addition
    • - Warhead: Penetration
    • - Communication: without additional

The respective modular structure of the weapon carrier according to the invention and the associated missile or missiles creates a highly flexible armament unit which, due to the provision of autonomous components in the weapon carrier, is more independent of the carrier aircraft than the armaments known from the prior art, so that the weapon carrier according to the invention with its armament can be flexibly adapted to different carrier aircraft.

Reference signs in the claims, the description and the drawings serve only to improve the understanding of the invention and are not intended to limit the scope of protection.

List of reference symbols

1

Waffenträger

1'

Waffenträger

1''

Waffenträger

2

Flugkörper

2'

Flugkörper

2''

Flugkörper

3

Trägerluftfahrzeug

4

Waffenträgerelektronik

5

autonome Sensormittel

6

externe Programmiereinrichtung

10

Rahmen

11

Netzwerkstruktur

12

Gehäuseabdeckung

13

Druckluftkompressor

13'

Druckluftleitung

13''

Druckluftleitung

14

mechanische Luftfahrzeugadaptermittel

15

elektrische Luftfahrzeugadaptermittel

16

Flugkörper-Absetzvorrichtung

16'

Flugkörper-Absetzvorrichtung

16''

Flugkörper-Absetzvorrichtung

18

mechanische Flugkörperadaptermittel

19

elektrische Flugkörperadaptermittel

20

Öse

21

Öse

22

Umbilical-Stecker

30

Computer

40

Waffen-Steuerungscomputer

41

Milbus

42

Sicherheitseinrichtung

44

Energieverteiler

50

Sensor

51

Videodatenleitung

52

Laserzielbeleuchter

54

Videoaufzeichnungsgerät

56

Datenlink-Kommunikationseinrichtung

57

Antenne

58

Windgenerator

59

Sicherheitsenergieleitung

60

externer Programmiercomputer

62

externe Stromversorgungseinrichtung

140

Aufhängung

142

Aufhängung

151

Umbilical-Kabel

152

Umbilical-Stecker

160

Kontroller

160'

Kontroller

160''

Kontroller

180

Lastabsetzvorrichtung

181

auslösbarer Haken

182

auslösbarer Haken

190

Umbilical-Stecker

They refer to:

1

gun carrier

1'

gun carrier

1''

gun carrier

2

Missiles

2'

Missiles

2''

Missiles

3

Carrier aircraft

4

Weapon carrier electronics

5

autonomous sensor means

6

external programming device

10

Frame

11

Network structure

12

Housing cover

13

Air compressor

13'

Compressed air line

13''

Compressed air line

14

mechanical aircraft adapter means

15

electrical aircraft adapter means

16

Missile launcher

16'

Missile launcher

16''

Missile launcher

18

mechanical missile adapter means

19

electric missile adapter means

20

eyelet

21

eyelet

22

Umbilical connector

30

computer

40

Weapon control computer

41

Milbus

42

Safety device

44

Energy distributor

50

sensor

51

Video data line

52

Laser target illuminator

54

Video recording device

56

Data link communication device

57

antenna

58

Wind generator

59

Safety energy line

60

external programming computer

62

external power supply device

140

suspension

142

suspension

151

Umbilical cable

152

Umbilical connector

160

Controller

160'

Controller

160''

Controller

180

Load depositing device

181

releasable hook

182

releasable hook

190

Umbilical connector

Claims (11)

Weapon carrier for attaching a plurality of unmanned missiles (2; 2', 2'') to a carrier aircraft (3), with - mechanical aircraft adapter means (14), - electrical aircraft adapter means (15), - a plurality of missile launching devices (16) for receiving the unmanned missiles (2; 2', 2'') and - at least one weapon control computer (40) that can be connected to the missiles (2; 2', 2'') for data transmission, - wherein the electrical aircraft adapter means (15) have connection means (151, 152) for establishing electrical connections between the carrier aircraft (3) and the weapon carrier (1; 1';1'';1'''), which have at least one electrical power supply for the weapon carrier (1; 1';1'';1''') and a data transmission connection between at least one computer (30) of the carrier aircraft (3) and the at least one weapon control computer (40) comprise, characterized in that - the weapon carrier is provided with autonomous sensor means (5) which have an imaging sensor (50) and which are connected to a network structure (11) internal to the weapon computer, to which the weapon control computer (40) is also connected; - for each of the missile launching devices (16; 16', 16''), a missile launching controller (160; 160', 160'') is provided, which is or can be electrically connected to the weapon control computer (40) for data transmission, the weapon carrier (1; 1';1'';1''') is of modular design, so that individual components of the weapon carrier are interchangeable Weapon carrier after Claim 1 , characterized in that - the missile launching devices (16; 16', 16'') are provided with mechanical missile adapter means (18) and electrical missile adapter means (19). Weapon carrier after Claim 1 or 2 , characterized in that the weapon carrier (1; 1';1'';1''') has a data link communication device (56) which is or can be electrically connected to the weapon control computer (40) for data transmission and which is or can be connected to an antenna (57) which is preferably provided on the weapon carrier (1; 1';1'';1'''). Weapon carrier according to one of the preceding claims, characterized in that the autonomous sensor means (5) comprise an imaging sensor (50). Weapon carrier according to one of the preceding claims, characterized in that the weapon carrier (1; 1';1'';1''') has a target illumination device (52). Weapon carrier after one of the Claims 3 until 5 , characterized in that the weapon carrier (1; 1';1'';1''') has a data recording system (54) for recording operating data of the weapon carrier (1; 1';1'';1''') and/or the missiles (2; 2', 2''), wherein the data recording system (54) is connected or connectable to the data link communication device (56) for telemetry data transmission. Weapon carrier according to one of the preceding claims, characterized in that the weapon carrier (1; 1';1'';1''') has an autonomous power supply device (58, 59). Weapon system comprising a weapon carrier (1; 1'; 1''; 1''') according to one of the preceding claims and several missiles (2; 2', 2'') attachable thereto. Weapon system according to Claim 8 , characterized in that the missiles (2; 2', 2'') are modular in construction and can be configured to adapt to a specific application. Weapon system according to Claim 9 , characterized in that the configurability of the missiles (2; 2', 2'') comprises a hardware configurability and/or a software configurability. Aircraft with at least one weapon system according to one of the Claims 8 until 10 .

Images