DE10337085B4 - Method and device for increasing the range of cruise missiles - Google Patents

Abstract

carrier platform for cruise missiles to Settling from a transport plane, with at least one device for admission and rejection a cruise missile and at least one on-board fuel tank that has one Line connected to an engine of at least one cruise missile is, being in the carrier platform a control system is integrated, which after discontinuation of with at least a cruise missile stocked carrier platform from the transport plane until the repelling of at least one cruise missile of the carrier platform the attitude of the carrier platform by means of control surfaces and the engine of the at least one cruise missile controls.

Description

Field of the invention

The The invention relates to a method and a device that allow the range of existing air / ground or air / ship cruise missiles (MFK) such as. TAURUS KEPD350 or Storm Shadow with additional equipment to enlarge, to thereby the danger of the carrier aircraft by reducing enemy air defense systems.

Discussion of the state of the technique

In Failure of tactical distance missiles in European Air Forces became the development in the 90s of the 20th century started from air-ground / ship MFKs (distance and precision), allowing for Time the following MFK types are pending at European Air Forces or already in use: Taurus KEPD 350/150, Storm Shadow, Scalp EC, Apache. It is for this Combat aircraft of the types Tornado, Harrier, Eurofighter Typhoon, Mirage 2000, Rafale, JAS39 Gripen, Viggen, F-18, which provided usually 2 MFKs (up to 1.5 to per MFK) under the fuselage or wing to Ground or ship target combat wear and shoot can.

During the Iraq wars in 2003 were first MFKs of the type Storm Shadow used on tornado fighter bombers GR4 by the British RAF. The tornadoes started from the air base Ali Al Salem in Kuwait and should about 230 km from Baghdad the MFKs releasen. Soon after crossing the Iraqi border they were using ground-to-air defense missiles (SAM) fired. Only by violent evasive maneuvers, as a result, fuel outer tanks to increase the agility by Jettison were dropped, could prevent a tornado launch become. After the release of MFKs off Baghdad, the remaining fuel was enough just out of order with the utmost Trouble the return to the Kuwaiti Air Force Base (see the report "British Fire Bunker Buster Missiles at Iraq "from 23. 03.03 at www.spacewar.com/news). The MFK-type TAURUS KEPD350 has in its Basic version in the center section about 3 fuel tank elements. If under TAURUS KEPD350 derivatives the provision of space for additional Payload like sensors (search / track radar, integrated ejectable real-time battle damage assessment system, radar / laser warner with countermeasures processors), disturbance equipment (radar, Infrared), submunitions (surface target control) or communication facilities (data link to satellite or to flying command post for transmission of target coordinates) should be necessary; could use 1 or 2 fuel tank elements be removed and installed in the vacant space, the new payload become. The associated range reduction would, however, have compensated by further measures Otherwise, the distance weapons character and thus the tactical advantage throughout would be lost.

For the same Anversierte air-ship fight by MFKs are basically larger ranges as the air defense screen of combat ship associations or aircraft carrier groups 500 km and more is and of course, the airborne MFK shot outside the air defense screen. In addition, often allow only larger MFK ranges at airborne Sea attacks from attack on coastal installations or ships anchored in the harbor (for example, as part of a war scenario in the Pacific-Asian region).

• – die Gefährdung des Trägerflugzeuges reduziert werden soll,
• – optional Raum für zusätzliche Nutztlast geschaffen werden soll,
• – neue Einsatzmöglichkeiten im Rahmen der Seekriegsführung erschlossen werden sollen.

From the above, therefore, a demand for range expansion (target duplication) of existing airborne MFK types can be derived, thereby

• - the endangerment of the carrier aircraft should be reduced,
• - optional space for additional utilization is to be created,
• - new uses in the context of naval warfare are to be developed.

• – ohne eine komplette Neuentwicklung eines Marschflugkörpers durchführen zu müssen,
• – durch Verwendung eines Zusatzkits, der weitgehenst auf existierende Hardware-Elemente zurückgreift,
• – wobei die Kosten für einen MFK-Verschuß im Vergleich zu einem Verschuß durch einen Jagdbomber deutlich reduziert werden sollen.

The desired range expansion is to be implemented

• - without having to perform a complete redevelopment of a cruise missile,
• - by using an additional kit that largely relies on existing hardware elements,
• - whereby the cost of a MFK-Verschuß should be significantly reduced compared to a firing by a fighter-bomber.

• – ob der Marschflugkörper überhaupt ausreichend Schub hat um sich und die angehängten UAVs samt eventueller Munition mit ausreichender horizontaler und vertikaler Beschleunigungsfähigkeit (und damit Manövrierfähigkeit) entsprechend einer vorgeplannten Mission zu bewegen,
• – dass sich die Reichweite des Marschflugkörpers entsprechend verringert, weil sein Treibstoffverbrauch durch die zusätzliche Traglast (UAVs) und den dadurch größeren Luft-Widerstand deutlich erhöht ist,
• – ob überhaupt die Flugzustands-Regelung eines solchen aus unterschiedlichen Flugkörper-Typen zusammengesetzten Flugkörpers durch den Autopiloten des Marschflugkörpers möglich ist,
• – wie die Trennung der UAVs vom Marschflugkörper bzw. vom Booster zuverlässig und kollisionsfrei erfolgen soll in Anbetracht dessen, dass die UAVs mittels "brechbarer Verbindung" (frangible connetion) am Marschflugkörper bzw. am Booster befestigt sind,
• – dass die Verwendung eines Wegwerf-Boosters mit eigenem Triebwerk inklusive Tank für häufige Überwachungs-Missionen ziemlich kostspielig (verschwenderisch) ist.

GB 2377683 A describes an aircraft that is composed of several individual missiles. One variant consists of a cruise missile carrying smaller unmanned air vehicles (UAVs), which after separation from the cruise missile perform a specific mission (surveillance) and then return to the base or to a rally point. Another variant consists of a booster with engine, which also carries UAVs. The cruise missile or the booster transport the UAVs, which are usually driven by propellers, are slow and soaring and carry out long-term monitoring tasks over enemy territory into the operating area, so that the UAVs do not consume their own fuel supply (UAV drive is only started when disconnected ) and therefore theirs Operating time significantly extended. After disconnecting the UAVs, the booster loses its power while the cruise missile performs its pre-planned attack mission. Objective of the GB 2377683 A is an all-in-one-vehicle composed of different types of missile capable of performing both the attack and ISTAR (intelligence, surveillance, target acquisition, reconnaissance) role without the sub-missiles (UAVs) must be released individually by carrier aircraft or ground stations, with an insert extension results for the UAVs carried into the operation area. In GB 2377683 A is not shown

• - whether the cruise missile has sufficient thrust to move itself and the attached UAVs with any ammunition with sufficient horizontal and vertical acceleration capability (and thus maneuverability) according to a pre-planned mission,
• - That the range of the cruise missile is reduced accordingly, because its fuel consumption is significantly increased by the additional load (UAVs) and the resulting greater air resistance,
• Whether the flight state control of such a missile composed of different missile types is possible at all by the autopilot of the cruise missile,
• - how the separation of the UAVs from the cruise missile or the booster should take place reliably and without collision, in view of the UAVs being attached to the cruise missile or the booster by means of frangible connetion,
• - Using a disposable booster with its own engine and tank for frequent surveillance missions is quite costly (lavish).

• – hier die Zielsetzung in der Vergrößerung der Reichweite des Marschflugkörpers liegt (bei GB 2377683 A in der Verlängerung der Einsatzzeit der angehängten UAVs für Überwachungsaufgaben),
• – hier alle unter der Trägerplattform angehängten Flugkörper ihr Triebwerk während der gemeinsamen Marschphase eingeschaltet haben und damit einen Beitrag zum gemeinsamen Fortkommen leisten (bei GB 2377683 A arbeitet nur das Triebwerk des Marschflugkörpers bzw. des Boosters),
• – die Trägerplattform zwar über einen Tank verfügt, aber über kein eigenes, kostspieliges Triebwerk (bei GB 2377683 A verfügt der Wegwerf-Booster über ein eigenes Triebwerk),
• – die Flugzustandssteuerung des Flugobjektes, welches aus Trägerplattform und angehängten Tank und MFKs besteht, nicht durch den Autopiloten eines angehängten MFK erfolgt, sondern durch einen eigens dafür ausgelegten Autopiloten, der im Rechner der Trägerplattform implementiert ist und der sowohl die Kontrolle über die Rudermaschinen der MFKs hat als auch die Navigations-Anlagen der MFKs benutzt (bei GB 2377683 A wird der zusammengesetzte Flugkörper durch den Autopiloten des MFKs gelenkt),
• – die Separation der Marschflugkörper von der Trägerplattform in der selben bewährten Weise und mit den gleichen Mitteln (Pylons) erfolgt wie die übliche Separation eines Marschflugkörpers von einem Jagdbomber (bei GB 2377683 A ist unklar wie dies mit "brechbaren Verbindungen" (frangible connetion) erfolgen soll).

The inventively proposed device and the associated method differ from GB 2377683 A as a result of that

• - Here the objective is to increase the range of the cruise missile (at GB 2377683 A extending the period of use of the attached UAVs for surveillance tasks),
• - all the missiles attached below the carrier platform have switched on their engines during the common march phase and thus contribute to the common progress (at GB 2377683 A works only the engine of the cruise missile or the booster),
• - Although the support platform has a tank, but no own, expensive engine (at GB 2377683 A the disposable booster has its own engine),
• - The flight condition control of the flying object, which consists of carrier platform and attached tank and MFKs, is not done by the autopilot of an attached MFK, but by a specially designed autopilot, which is implemented in the computer of the carrier platform and the control of both the control of the MFKs has used as well as the navigation systems of MFKs (at GB 2377683 A if the composite missile is guided by the MFP's autopilot),
• - The separation of the cruise missiles from the carrier platform in the same proven way and with the same means (pylons) is like the usual separation of a cruise missile from a fighter-bomber (at GB 2377683 A it is unclear how this should be done with "frangible connections" (frangible connetion).

• – ein Feststoffbooster in den vorgeschlagenen Adapter integriert ist oder
• – bei zwei angekoppelten Flugkörpern zunächst das Triebwerk eines Flugkörpers abgebrannt wird und danach das des zweiten Flugkörpers, wodurch der erste Flugkörper somit als Lastträger mißbraucht wird.

JP 2003-139496 A (1) addresses the problem of more effective multi-objective air-to-air missile combat objectives mounted on fighter aircraft outboard load stations. For this purpose, an increase in range is proposed by

• - A solid booster is integrated in the proposed adapter or
• - When two coupled missiles first the engine of a missile is burned and then that of the second missile, whereby the first missile is thus misused as a carrier.

moreover It is proposed that multi-objective combat by means of targeted foreign targeting or by communication between the missiles and by simultaneous Disconnection from the adapter.

• – Vorrichtung zur Aufnahme an einer Waffenstation eines Kampfflugzeuges,
• – Vorrichtung zur Aufnahme von Flugkörpern,
• – parallele Aufnahme von Flugkörpern,
• – Aufnahme von Flugkörpern hintereinander, Kombination mit paralleler Variante,
• – Datenverbindungs-Kabel zwischen den Flugkörper-Aufnahmen,
• – eigene Energie-Versorgung,
• – Feststofftriebwerk (Booster).

The adapter proposed in JP 2003-139 496 A (1) is characterized by the following features:

• Device for receiving at a weapon station of a combat aircraft,
• - device for receiving missiles,
• - parallel recording of missiles,
• - recording of missiles in a row, combination with parallel variant,
• - data link cable between the missile recordings,
• - own energy supply,
• - Solid engine (booster).

• – es handelt sich um einen Adapter für Außenlast-Waffenstationen von Kampfflugzeugen, wobei der Start des Adapters nur aus einem Schienen-Pylon heraus möglich ist,
• – während der Marschphase liefert das Feststofftriebwerk des Adapters den Schub, während die Triebwerke der gekoppelten Flugkörper ausgeschaltet sind,
• – die Triebwerke der angekoppelten Flugkörper werden erst nach der Trennung von dem Adapter gestartet,
• – es gibt keine vorgeplante Flugbahn, ebenso ist der Trennungs-Punkt nicht vorgeplant, sondern erfolgt nach Erkennung von unterschiedlichen Luftzielen,
• – wie die Lenkung und Regelung des Adapters samt gekoppelter Flugkörper erfolgen soll, wird nicht offengelegt,
• – es wird nicht dargestellt, dass der Adapter die Rudermaschinen und die Navigations-Systeme der angekoppelten Flugkörper während der gemeinsamen Marschphase benutzt,
• – in einer dargestellten Variante laufen die Triebwerke der beiden gekoppelten Flugkörper bereits ab Trennung des Adapters vom Trägerflugzeug, wodurch das gestellte Problem der Reichweitenvergrößerung nicht gelöst wird, da der Treibstoff der Flugkörper schon während der gemeinsamen Marschphase verbraucht wird,
• – falls zunächst nur das Triebwerk des ersten Flugkörpers Schub liefert, wird zwar die Reichweitenvergrößerung erreicht, allerdings wird der erste Flugkörper als Booster mißbraucht und steht damit nicht mehr zur Zielbekämpfung zur Verfügung,
• – der Adapter benötigt eine eigene Energie-Versorgung.

The adapter described in JP 2003-139 496 A (1) differs in the following features from the device proposed according to the invention and the associated method:

• - It is an adapter for outdoor load weapons stations of fighter aircraft, the launch of the adapter is possible only from a rail pylon,
• - During the march phase provides the solid the thruster while the engines of the coupled missiles are off,
• The engines of the coupled missiles are only started after disconnection from the adapter,
• - there is no pre-planned trajectory, as well as the separation point is not pre-planned, but takes place after detection of different air targets,
• - how the steering and regulation of the adapter with coupled missiles is to take place is not disclosed
• It is not shown that the adapter uses the rudders and the navigation systems of the coupled missiles during the common marching phase,
• - In a variant shown, the engines of the two coupled missiles run from the separation of the adapter from the carrier aircraft, whereby the problem of the range enlargement is not solved, since the fuel of the missiles is already consumed during the common march phase,
• - If initially only the engine of the first missile delivers thrust, although the range magnification is reached, however, the first missile is abused as a booster and is therefore no longer available for targeting available,
• - The adapter requires its own power supply.

Tasks and Advantages of the invention

Of the Invention is the technical problem underlying a carrier platform for cruise missiles and to provide a method for depositing at least one cruise missile, being existing cruise missiles without major modifications use whose range is to be increased significantly, whereby the Safety of the transport aircraft is increased during use.

This technical problem is due to the characteristics of the carrier platform for cruise missiles Claim 1 and the method steps of the method for settling at least one cruise missile solved according to claim 9.

• – Reduzierung der Gefährdung des Trägerflugzeuges durch Erhöhung der Reichweite des MFK;
• – Reduzierung der Abhängigkeit von Luftwaffenstützpunkten im Ausland (Reichweite des auftankbaren Transportflugzeuges + Trägerplattform-Reichweite + MFK-Reichweite), da die Verhandlungen über die Nutzung ausländischer Militärbasen meist schwierig sind (siehe entspr. Pentagon-Berichte bzgl. der Militäreinsätze in Bosnien, Afghanistan, Irak),
• – kosteneffiziente Implementierung der Reichweitenvergrößerung, weil die Erhöhung der Reichweite ohne die Entwicklung eines völlig neuen Flugkörpers erfolgt und weil die Trägerplattform weitgehend aus vorhandenen Elementen aufgebaut ist;
• – die Konzeption der Trägerplattform (Masse ≈ 4 to) bringt es mit sich, dass die Trägerplattform mit angehängten MFKs und Treibstofftank aus dem Frachtraum eines militärischen Transportflugzeuges wie z.B. A400M oder Antonow AN-70 über die hintere, geöffnete Laderampe wie andere Schwerlasten abgeworfen wird. Dadurch ergeben sich niedrigere Kosten (30 Cent pro 1 to Nutzlast/km) für einen MFK-Verschuß als bei einem Verschuß von einem konventionellen Jagdbomber (25 Euro pro 1 to Nutzlast /km). Zudem muss keine aufwendige Adaption des militärischen Transportflugzeuges vorgenommen werden, wie dies sonst bei der Waffenintegration an Jagdbombern der Fall ist;
• – durch die Verwendung der Treibstofftanks, welche unter der Plattform angehängt sind, ergibt sich die Möglichkeit zur Mitführung weiterer Nutzlast (mit der allerdings eine entsprechende Reduzierung der Reichweite einhergeht). Dadurch ergibt sich eine Ausweitung des taktischen Einsatzspektrums der MFKs. So kann ein Subsystem zur Prüfung des MFK-Wirkung im Ziel (integrated, ejectable real-time battle damage assessment system) mitgeführt werden, das kurz vor dem MFK-Einschlag im Ziel (z.B. bei Pop-up-Angriff am Scheitelpunkt der Trajectory) ausgestoßen wird, mittels Fallschirm stabilisiert wird und dann mittels aufklappbarem Propeller (oben angeordnet) einige Zeit (min. 10 min) über dem Zielgebiet schwebt. Eine Kamera, welche senkrecht nach unten blickt, liefert real-time TV- oder IR-Bilder, die via Satellit oder direkt an einen (fliegenden) Gefechtsstand gesendet werden. Dieses Subsystem verfügt über eine eigene Navigation und Lenkung, durch die es sich genau über dem Ziel (Zielkoordinaten werden vor dem Ausstoß vom MFK übertragen) positionieren kann;
• – die Trägerplattform führt mindestens 2 MFKs mit sich, so dass bei einem luftgestütztem Angriff auf ein fahrendes Schiff ein Twin-Angriff durchgeführt werden kann, bei dem nach Übermittelung der aktuellen Schiffposition via Data-Link, nach erfolgreicher Detection durch die MFK-eigenen Sensoren (IR, Radar) und Abschluß der Angriffs-Bahn-Berechnung (MFKs koordinieren sich via Data-Link) die MFKs aus unterschiedlichen Richtungen und Höhen, gleichzeitig oder zu verschiedenen Zeitpunkten das Schiff attackieren. Auch bei einem Luft-Boden-Angriff auf ein Ziel führen die beiden MFKs zeitlich ihre Mission synchron durch, da sie ja exakt zum selben Zeitpunkt und am gleichen Ort ihre Einzel-Mission beginnen. Dadurch ergibt sich eine perfekte time-overtarget (TOT) performance, welche ebenso bei geschickter Missionsplanung die Wahrscheinlichkeit eines Missionerfolges erhöht.

The invention has several advantages:

• - reducing the risk to the carrier aircraft by increasing the range of the MFK;
• - Reduction of dependency on air bases abroad (reach of refueling transport aircraft + carrier platform range + MFK range) as negotiations on the use of foreign military bases are usually difficult (see according to Pentagon reports concerning the military operations in Bosnia, Afghanistan, Iraq),
• - cost-effective implementation of range expansion, because the increase in range occurs without the development of a completely new missile, and because the carrier platform is largely made up of existing elements;
• - The design of the carrier platform (mass ≈ 4 to) entails that the carrier platform with attached MFKs and fuel tank from the hold of a military transport aircraft such as A400M or Antonov AN-70 over the rear, open loading dock as other heavy loads is dropped. This results in lower costs (30 cents per 1 to payload / km) for a MFK firing than when firing from a conventional fighter-bomber (25 euros per 1 to payload per km). In addition, no elaborate adaptation of the military transport aircraft must be made, as is otherwise the case with the weapon integration of Jagdbombern;
• - the use of the fuel tanks, which are attached below the platform, gives the opportunity to carry another payload (but with a corresponding reduction in range). This results in an expansion of the tactical range of use of the MFKs. Thus, a subsystem for checking the MFK effect in the target can be carried along, which is ejected shortly before the MFK impact at the target (eg at pop-up attack at the apex of the trajectory) stabilized by parachute and then hovered over the target area for some time (at least 10 minutes) by means of a hinged propeller (arranged at the top). A camera looking vertically down provides real-time TV or IR images sent via satellite or directly to a (flying) command post. This subsystem has its own navigation and steering, allowing it to position itself just above the target (target coordinates are transmitted from the MFK before ejection);
• - The carrier platform carries at least 2 MFKs, so that in an airborne attack on a moving ship, a twin attack can be performed in which after transmitting the current ship position via data link, after successful detection by the MFK sensors ( IR, radar) and completion of the attack course calculation (MFKs coordinate via data link) the MFKs from different directions and heights, at the same time or at different times attack the ship. Even with an air-to-ground attack on a target, the two MFKs perform their mission synchronously, as they begin their single mission at exactly the same time and place NEN. This results in a perfect time-overtarget (TOT) performance, which also increases the likelihood of mission success with skillful mission planning.

The advantageous embodiments of the invention are illustrated in the subclaims. The invention will be described with reference to an illustrated in the drawing preferred embodiment be explained in more detail. It shows:

1 : the architecture of the proposed system and its connection to the subsystems of the transport aircraft.

1 shows that the proposed system consists of the carrier platform with attached cruise missiles (MFK) and fuel tank, the control console and the mission planning station. In this case, the control console and the mission planning station are installed in the hold of the transport aircraft and serve to prepare the carrier platform including attached elements for ejection via the open loading ramp and to control the discharge.

The carrier platform has mounted at the bottom gun pylons on which the MFK in the usual Be attached, thereby providing energy and information (see MIL-STD 1760) can be supplied. additionally In each weapon pylon a fuel connection is integrated over which the attached MFK can be supplied with fuel. The release of the MFK from Weapons pylon is carried out in the usual way in combat aircraft (hook on, repulsion by Pestle).

center is at the bottom of the vehicle deck a tank pylon installed on which a fighter aircraft as an outside load usually Used fuel tank is fixed and from the fuel in the fuel systems the MFK can be. This is in the carrier platform a fuel pump integrated, which is controlled by the computer of the carrier platform becomes.

At both sides of the carrier platform are hinged wings installed, which are always folded before release. At the ends the wing are mounted supports on which the carrier platform including attached MFK and fuel tank stands. The supports of the carrier platform are on the powered transport rollers, which in the cargo hold floor of the transport plane are installed, put on and then the carrier platform is complete attached Elements like a standard military pallet from the cargo handling system of the transporter to the cargo hold transported and stored. By the same means becomes the carrier platform promoted to the release position. After dropping the wings the carrier platform unfolded and deliver the for The marching phase requires aerodynamic Boost.

At the top of the support platform, a parachute system is mounted, the parachutes are ejected and deployed after Kommandierung backwards, which pull the support platform together with attached elements on the lowered ramp to the back to the outside (see, eg US4349168 , also US5284310 ) and which stabilize the roll / pitch angle of the carrier platform outdoors for a short time so that the wings of the carrier platform can be unfolded and the engines of the MFK can be started. After successful stabilization, the deployed parachutes are separated from the carrier platform so as not to interfere with the parade phase of the carrier platform including cruise missiles and fuel tank.

The Discard event is sensed by means of the MFK plunger. Is to into the carrier platform a mechanism built in, the extension of the MFK plunger after then allows up, if the carrier platform including attached Elements over the lowered loading ramp by means of the unfolded parachutes into Free is pulled. For this purpose a cable connection is used, by means of derer at a certain distance of the support platform from a point of Loading ramp the movement of the MFK plunger is unlocked upwards. The main computers of the MFK then report the dropping event via weapons pylons at the into the carrier platform integrated calculator.

The carrier platform has its own computing capacity, referred to below as a platform computer. As a bus control unit (MIL-STD1553), the platform computer controls data communication via the umbilical interface (data bus 1) with the RTUs (remote terminal unit) of the attached MFK, in the same way as a weapon control computer of a combat aircraft performs. It also controls the discrete signals such as release consent, DC-PW2, RTU-address-lines etc. (see MIL-STD1760). The same applies to the 3 × 115V 400Hz used to supply the MFK as long as they are connected to the carrier platform and they are in the hold. By means of data bus 1, the platform computer handles the complete interaction with the MFK for testing, mission plan download, navigation alignment of the MFK as well as for sensing the ejection event, engine and steering machine control and navigation data delivery during the joint march phase and separation of the MFK from the carrier platform is necessary. Via data bus 1, the control console can be addressed as an RTU by the platform computer (BCU). The data bus 1 is at the umbilical plug, located at the top of the carrier platform is available. This umbilical plug has the Umbilical cable (see MIL-STD 1760) plugged in, which connects the carrier platform's data and power connection to the control console. From the control console via data bus 1, the platform computer receives its own mission plan as well as the mission plans of the MFK, as well as all the information necessary for the navigation alignment of the MFK. In addition, via data bus 1, all interactions between the control console and the platform computer are transmitted, which are required when carrying out the discharge (start thermal battery, fin-unlock, fin preset, etc.) of the carrier platform via the loading ramp.

• – solange sich die Trägerplattform samt angehängter Elemente im Frachtraum des Transportflugzeuges befindet und noch die Umbilical-Verbindung zur Steuer-Konsole besteht, fungiert der Plattform-Rechner als Datenübermittler zwischen Steuer-Konsole und den Main-Computern der angehängten MFK;
• – nach Abschluß der irreversiblen Release-Interaktion zwischen MFKs und Steuer-Konsole aktiviert der Plattform-Rechner auf Kommando der Steuer-Konsole das Ausstoßen der Fallschirme, um die Träger-Plattform ins Freie zu ziehen;
• – nachdem das Umbilical-Kabel während des Hinausziehens (Fallschirme) der Trägerplattform über die abgesenkte Laderampe vom Umbilical-Stecker der Trägerplattform abgerissen ist, steuert der Plattform-Rechner nach Sensierung des Abwurfereignisses durch die MFKs das Aufklappen der Plattform-Flügel, die Lagestabilisierung der Träger-Plattform via Rudermaschinen, das Absprengen der Fallschirme nach erfolgreicher Lage-Stabilisierung und den Start der MFK-Triebwerke. Nach erfolgreichem Hochlauf der Triebwerke lenkt der Plattform-Rechner die Trägerplattform entlang einer vorgeplannten Flugbahn, wobei er die Navigations-Ergebnisse, die Rudermaschinen und die Triebwerke der MFK benützt und wobei er mittels der in die Trägerplattform eingebauten Pumpe Treibstoff vom mittigen Treibstofftank in die MFKs umpumpt;
• – bei Erreichen eines vorgeplannten Release-Punktes (Teil des Missions-Planes der Trägerplattform) steuert der Plattform-Rechner das Trennen der MFKs von der Trägerplattform durch Öffnen der Haken und Aktivierung der Ausstoß-Stößel der Waffen-Pylons.

The platform calculator performs the following tasks

• - as long as the carrier platform together with attached elements is in the hold of the cargo plane and the umbilical connection to the control console still exists, the platform computer acts as a data transmitter between the control console and the main computers of the attached MFK;
• Upon completion of the irreversible release interaction between the MFKs and the control console, the platform computer, on command of the control console, activates the ejection of the parachutes to pull the carrier platform to the outside;
• - After the umbilical cable is demolished during removal (parachutes) of the carrier platform via the lowered loading ramp from umbilical plug of the carrier platform, the platform calculator controls the unfolding of the platform wings after sensing the ejection event by the MFKs, the position stabilization of the carrier Platform via rowing machines, the parachute parachute after successful stabilization of the position and the start of the MFK engines. After successfully powering up the engines, the platform computer steers the carrier platform along a pre-planned trajectory, using the navigation results, the rudders and engines of the MFK and pumping fuel from the central fuel tank into the MFKs by means of the pump built into the carrier platform ;
• - Upon reaching a pre-planned release point (part of the mission plan of the carrier platform), the platform computer controls the separation of the MFKs from the carrier platform by opening the hooks and activating the ejection plungers of the weapon pylons.

So long itself the carrier platform located in the hold, becomes the platform calculator and the others Consumers of the vehicle platform supplied by 28VDC, which the MFK from the energy system of the Convert transport aircraft via Umbilical coming 3 × 115 V 400Hz and the carrier platform to disposal put. While the output the carrier platform over the lowered loading ramp become the consumers of the carrier platform powered by 28VDC which enabled the MFK from the 270VDC's Win thermal batteries. While The march phase generate the generators of the current MFK engines as well 270VDC, which has been converted to 28V and used by the carrier platform consumers (platform calculator, Pump) available be put.

The Control console is connected as RTU on the data bus 1 and thus via Platform computer connected to the main computers of the MFK. By data bus 2, which is an Ethernet connection is able to communicate with the mission planning station installed in the transport plane, in particular the prepared mission plans for cruise missiles and carrier platform receive and forward. The control console is connected to the avionics data bus of the transport plane tethered as a monitor, allowing thereby the data traffic of this bus does not need to be modified. When Data Monitor allows the control console to navigate data (Almanac, PVT, Position, Speed, Euler angle ..) of the navigation system of the transport aircraft determine which they then cyclically via platform calculator to the MFK main computer forwards. With that you can the MFK perform the initialization of their navigation facilities (GPS, Strapdown Package) as also cyclically for the purpose of navigation alignment support. moreover The control console can provide information about the state of the cargo handling system the transport aircraft such. Loading ramp open / closed, position of Pallets / platforms etc .. gain which they are in the context of security relevant Sequences (e.g., no parachute discharge with the loading ramp closed etc ..) processed.

• – power on für eine angebundene Trägerplattform
• – überwachen der Selbststests des Plattform-Rechners und der MFKs
• – Download der Missions-Pläne für Plattform-Rechner und MFKs
• – Aktivierung des Navigations-Alignments der MFKs
• – Aktivierung und Überwachung der irreversiblen Release-Vorgänge (fire command) in den MFKs (Thermal-Batterie-Start, Fin-Unlock, Fin-Preset, Plunger-Unlock..).
• – Aktivierung des Ausstoßes der Fallschirme über die abgesenkte Laderampe ins Freie, um die Trägerplattform samt angehängter Elemente aus dem Frachtraum zu ziehen.

The control console has a human-machine interface (MMI) by means of which an operator (eg loadmaster) can perform the following activities:

• - power on for a tethered carrier platform
• - monitor the self-tests of the platform computer and MFKs
• - Download mission plans for platform calculators and MFKs
• - Activation of the navigation alignment of the MFKs
• - Activation and monitoring of the fire command in the MFKs (Thermal Battery Start, Fin-Unlock, Fin-Preset, Plunger-Unlock ..).
• - Activation of the parachute output via the lowered loading ramp to the outside to pull the carrier platform together with attached elements from the cargo hold.

Alternatively, this MMI can also be implemented in the mission planning station. Before activating the irreversible release processes and the parachute discharge, the loadmaster must use the MMI of the cargo handling system to set up the "logistic locks" (see eg US5284310 ) Unlock the guide rails, position the carrier platform by means of the transport rollers for release in front of the loading dock, the "air drop system locks" activate, which in fully deployed parachutes and thus concerns a specific traction movement of the carrier platform from the cargo compartment on the lowered Release loading ramp. Then he must lower the loading dock, trigger the irreversible release operations and after successful completion of the same activate the ejection of the parachutes of the carrier platform to the back to the outside, whereby the carrier platform with attached MFKs and fuel tanks is pulled outward (see US4349168 ).

In front Activation of the parachute ejection periodically checks the control console whether there is an electrical connection via cable connection to the planer unlocking mechanism, if not, solve The control console made a mission abortion by which an inadvertent Unfolding the stabilization parachutes is prevented.

The also in the cargo hold of the transport aircraft housed mission planning station is by means of Data bus 2 connected to the control console. It is used for implementation from incoming combat missions in mission plans for carrier platform and MFK. At the top of the MFK is a valve for fuel supply built-in, which fits the fuel port of the Weapons Pylon of the vehicle deck is.

• – Cruise under Plattform: zu Beginn startet der Main-Computer das Triebwerk auf Request des Plattform-Rechners. Während der gemeinsamen Cruise-Phase übergibt der Main-Computer die Kontrolle über Triebwerk und Rudermaschinen dem Plattform-Rechner, wobei der Main-Computer als Datenübermittler agiert. Zudem werden die Navigations-Ergebnisse und Sensor-Meßwerte (GPS, RALT..) an den Plattform-Rechner zyklisch für Lenkungs-Zwecke weitergeleitet.
• – Separation from Plattform: auf ein Kommando des Plattform-Rechners (Haken des Waffen-Pylons geöffnet) übernimmt der Main-Computer die Kontrolle über Triebwerk und Rudermaschinen, lenkt den Marschflugkörper zunächst nach unten weg, steuert das Öffnen der Schwenkflügel und nimmt dann die Cruise-Lenkung entlang der vorgeplannten Trajectory seiner Mission auf.

The flow control software of the main computer of an MFK is modified to introduce two new cruise modes:

• - Cruise under platform: at the beginning the main computer starts the engine on request of the platform computer. During the common cruise phase, the main computer transfers control of the engine and steering machines to the platform computer, with the main computer acting as the data transmitter. In addition, the navigation results and sensor readings (GPS, RALT ..) are forwarded to the platform computer cyclically for steering purposes.
• - Separation from platform: on a command from the platform computer (hook of the weapons pylon opened), the main computer takes control of the engine and steering machines, steers the cruise missile first down, controls the opening of the swinging wings and then takes the cruise Steering along the pre-planned trajectory of his mission.

During the Releases from the transport plane are commanded by the platform computer the preset angles to the main computer that they connect to the rowing machines for execution hand off. After ejection the load space (release detected) is the main computer in the fashion "Separation", in which he the control over the rudders leaves the platform machine, so this is the carrier platform including attached Position-stabilize elements. There is no opening of the MFK-swing wing, as this destruction on the adjacent cruise missile or fuel tank would cause. The blowing off of the cover flaps the engine inlets done so that the lids are blown forward and no damage entry.

Claims (9)

carrier platform for cruise missiles to Settling from a transport plane, with at least one device for admission and rejection a cruise missile and at least one on-board fuel tank that has one Line connected to an engine of at least one cruise missile is, wherein in the carrier platform a Control system is integrated, which after discontinuing with at least a cruise missile stocked carrier platform from the transport plane until the repelling of at least one cruise missile of the carrier platform the attitude of the carrier platform by means of control surfaces and the engine of the at least one cruise missile controls. carrier platform according to claim 1, characterized in that the carrier platform includes at least one tank pylon for receiving tank containers. carrier platform according to claim 1, characterized in that the carrier platform contains at least one integrated tank. carrier platform according to one of the claims 1 to 3, characterized in that the carrier platform via a Mechanism has, the separation of a Ausziehfallschirmes from the support platform after completion of the carrier platform including attached Allows objects. carrier platform according to one of the claims 1 to 4, characterized in that the carrier platform at least from one of the attached cruise missiles with Energy is supplied. carrier platform according to one of the claims 1 to 5, characterized in that the carrier platform for receiving and rejection a cruise missile over one Weapons pylon features. carrier platform according to one of the claims 1 to 6, characterized in that the carrier platform via interfaces features, by means of which the control system of the carrier platform with the or the attached cruise missiles as well communicates with the weapon control in the transport plane. carrier platform according to one of the claims 1 to 7, characterized in that the carrier platform laterally over vertically hinged wings features, which are unfolded after settling from the transport plane. Method for depositing at least one cruise missile by means of Parachute Airdrop from a transport plane with the following steps a. Loaded the tax system with a mission plan as well as loading the to the Carrier platform attached cruise missile with the associated Mission Plan via Control system b. Supply the attached cruise missile with Navigation data of the transport plane via the tax system to the To perform erection of the navigation of the attached cruise missile, c. Activation of the necessary to drop the attached cruise missile Missile capabilities via tax system, d. Ejection of the pull-out parachute of the carrier platform, causing the carrier platform complete with attached cruise missile the loading space over the open one Loading ramp of the transport aircraft is pulled outside, e. Separating the pull-out parachute from the support platform, f. Open the rotary vane and starting the engine of the attached cruise missile, g. Supply of the attached missile with fuel from the supply of Carrier platform and control the flight path through the control system of the carrier platform, H. separation of the attached Cruise missile of the carrier platform at a pre-planned point.