DE10338963B4 - Take-off platform for the deployment of missiles from a transport flight by parachute - Google Patents

Abstract

Slide-out for the Discarding missiles from a transport plane by parachute over the lowered, rear Loading ramp, with at least one weapon pylon mounted on the underside each one missile is fixable and operable, the over Pestle from Weapon pylon repelled can be, and with one attached to the pullout deck Umbilical connector to which an umbilical cable is connected that the pullout platform with one in a cargo hold of the cargo plane arranged weapons control and mission planning containers, here is the umbilical plug the pull-out platform, each with a umbilical plug of each weapons pylon Wired, whereby the at least one missile even during the withdrawal of the Pull-out platform from the hold to the interruption of the cable connection between pullout platform and the weapons control and mission planning container communicate with it and be powered by it can, after disconnecting the cable, the separation of all missiles mounted on the pullout platform from the weapon pylons triggered by the control signal of a single missile, if the pullout platform is the safety area of the transport plane ...

Description

The The invention relates to a pull-out platform and a method, which a military one Transport aircraft as a cost-efficient launch platform for air-to-ground / ship-missile in particular Cruise missiles (MFK) to be used.

• a. Kampfflugzeuge dieser Art sind für Höchstleistungen hinsichtlich Schubkraft, Geschwindigkeit, Beschleunigung- und Wendigkeit/Manövrierfähigkeit, Terrain Following im Tiefstflug etc. ausgelegt, die sie äußerst kostenintensiv in Herstellung, Betrieb, Wartung und Logistik machen. Diese Eigenschaften sind aber nicht erforderlich, um in einem stand-off-Szenario (Wegstrecke von Abgang bis Ziel: 400–500 km) einen MFK zur vorgeplanten Abgangs-Position zu tragen und abzusetzen. Ausreichend wäre dagegen eine Transport-Möglichkeit, mit der MFKs in Höhen von 300 m bis 5000 m bei Geschwindigkeiten von Mach 0.4–0.8 im Geradeausflug abgesetzt werden können. Obige Kampfflugzeuge sind im Vergleich zu Transportflugzeugen kein kosteneffizientes Mittel um MFKs zum Einsatz zu bringen;
• b. Kampfflugzeuge dieser Art transportieren MFKs als externe Lasten (an den Rumpf- oder an den Flügel-Stationen). Der dadurch entstehende aerodyamische Widerstand reduziert in beträchtlichem Maße die Reichweite und Geschwindigkeit des Trägerflugzeuges, was taktische Nachteile mit sich bringt (z.B. Tankflugzeuge sind notwendig, Abhängigkeit von bestimmten Flugplätzen). Ein MFK an einer Außenstation ist zudem während der gesamten Tragflugphase starken Vibrationen ausgesetzt, die seine Zuverläßigkeit reduzieren und damit den Missionserfolg gefährden können;
• c. Kampfflugzeuge dieser Art haben keine onbord-Möglichkeit zur komplexen Missionsplanung. Daher muß die Missionsplanung für die MFKs zur Zeit vor dem take-off erfolgen und die Missionsplanungs-Daten noch am Boden in die MFKs geladen werden (eine Übertragung von Missionsplänen vom fliegenden Kampfflugzeug zum releasten MFK durch Data-Link ist nicht störsicher und oftmals aus taktischen Gründen ausgeschlossen (z.B. Funkstille)). Dadurch wird die Zeit zwischen Ziel-Aufklärung und Ziel-Bekämpfung unnötig verlängert, was den Missionserfolg gefährden kann;
• d. Kampfflugzeuge (Nutzlast circa 6 to) dieser Art können zumeist maximal nur 2 MFKs (bis 3 to) tragen und haben mit dieser Beladung ohne Luftbetankung mit zusätzlichen Treibstofftanks maximale Einsatzradien von 1400 km bei Hoch-Tief-Hoch-Flugprofilen (bzw. 650 km im Tiefflug). Dadurch ergeben sich starke taktische Einsatzbeschränkungen im Vergleich zu Langstreckenbombern wie z.B. B-1 oder B-52;

The use of combat aircraft such as Eurofighter, Tornado, F-18, Mirage or Gripen as a launching platform for MFKs has the following disadvantages:

• a. Fighter aircraft of this type are designed for maximum performance in terms of thrust, speed, acceleration and maneuverability, terrain Following at low speed, etc., which make them extremely costly in manufacturing, operation, maintenance and logistics. However, in a stand-off scenario (distance from departure to finish: 400-500 km), these characteristics are not required to carry and deposit an MFK to the pre-planned departure position. On the other hand, a transport option would be sufficient, with which MFKs at heights of 300 m to 5000 m can be set off at speeds of Mach 0.4-0.8 in straight-ahead flight. The above combat aircraft are not a cost effective means of deploying MFKs compared to transport aircraft;
• b. Combat aircraft of this type transport MFKs as external loads (at the fuselage or wing stations). The resulting aerodynamic drag significantly reduces the range and speed of the carrier aircraft, which results in tactical disadvantages (eg tanker aircraft are required, dependency on certain aerodromes). An MFD at an outdoor station is also exposed to strong vibrations during the entire flying phase, which can reduce its reliability and thus jeopardize the success of the mission;
• c. Combat aircraft of this type have no onboard capability for complex mission planning. Therefore, mission planning for the MFKs must take place before the take-off and the mission planning data must still be loaded into the MFKs on the ground (transmission of mission plans from the flying fighter to the relinquished MFK by Data-Link is not interference-free and often tactical Reasons excluded (eg radio silence)). This unnecessarily prolongs the time between target enlightenment and target combat, which can jeopardize mission success;
• d. Combat aircraft (payload about 6 tons) of this type can usually carry a maximum of only 2 MFKs (up to 3 to) and have with this load without air refueling with additional fuel tanks maximum radii of use of 1400 km at high-low-high flight profiles (or 650 km in low altitude). This results in strong tactical deployment restrictions compared to long-range bombers such as B-1 or B-52;

On the other hand, is currently being used as a replacement for the outdated transporters C160 Transall and C-130 Hercules the tactical military transport A400M developed on the basis of Airbus technologies, its introduction at several big ones European Air Forces in the next Years will be done. The A400M will be used for various tactical roles (multi role transport) are used: transport of military Loads (helicopters, vehicles, containers, troops), tankers, flying Military hospital, etc. The A400M has a cargo hold of 17.71 m in length (23.11 m at open rear loading dock, the loading ramp 6 to carrying capacity has), 4 m width and 3.85 m height on. In addition, a long-distance cruising speed of Mach 0.68 (maximum speed at Mach 0.72) and a tactical payload of 20 to at 6600 km Range (or 30 to at 4500 km).

In order to is the use of a military transport plane like A400M as a launch pad for missiles and guided bombs basically worth considering in terms of cost savings and usage optimization, as a side effect, the development of a costly European long-range bomber can be avoided.

• – Transport-Module und ein Beschleunigungs-Modul, welche im Frachtraum des Transportflugzeuges installiert sind,
• – Schlitten zum Transport von Flugkörpern in den Modulen und für den Schwerkraft-Abwurf,
• – Schienen, in denen sich die Flugkörper-Schlitten bewegen,
• – Verbindungs-Elemente zwischen Modulen, Schlitten und Flugkörper,
• – Vorrichtungen zum Ausfahren des Schlittens aus dem Beschleunigungs-Modul und zum Trennen des Flugkörpers vom Schlitten nach Durchführung des Schwerkraft-Abwurfes.

Out US 4 256 012 a missile launch system for military transport aircraft is known, which consists of the following elements:

• - Transport modules and an acceleration module, which are installed in the hold of the transport aircraft,
• - carriages for transporting missiles in the modules and for gravity ejection,
• - rails in which the missile carriages move,
• - connecting elements between modules, carriages and missiles,
• - Devices for extending the carriage from the acceleration module and for separating the missile from the carriage after carrying out the gravity drop.

• a. die Flugzeugzelle muss modifiziert werden, um die Transport- und Beschleunigungs-Module mechanisch im Frachtraum zu integrieren,
• b. aufwändige Transport- und Beschleunigungs-Module, deren Einbau längere Zeit in Anspruch nimmt,
• c. der Schwerkraft-Abwurf erfolgt ohne dass der Flugkörper mit Energie versorgt wird, wodurch der Flugkörper keine definerte Abgangs-Lenkung im Abwindfeld der geöffneten Laderampe durchführen kann,
• d. die Trennung des Flugkörpers vom Schlitten nach dem Schwerkraft-Abwurf erfolgt rein zeitgesteuert, also unabhängig vom Flugzustand des Flugkörpers, wodurch der Flugkörper leicht in aerodynamisch nicht mehr regelbare Flugzustände geraten kann,
• e. da dieses Flugkörper-Abwurfsystem weder eine Waffen-Steuerungs- noch eine Missions-Planungs-Station umfaßt, können folgende für den Flugkörper essentielle Funktionen nicht durchgeführt werden: Onbord-Missions-Planung, Selbsttest, Initialisierung des GPS-Empfängers, Aufrichtung des Navigations-Systemes.

The following disadvantages are exhibited by this missile launch system:

• a. the airframe must be modified to mechanically integrate the transport and acceleration modules in the cargo hold,
• b. complex transport and acceleration modules, the installation of which takes a long time,
• c. the gravity drop occurs without the missile being supplied with energy, causing the Missile can not perform a defined departure steering in the downwind field of the opened loading ramp,
• d. the separation of the missile from the carriage after the gravity drop is purely time-controlled, so regardless of the flight state of the missile, whereby the missile can easily fall into aerodynamically no longer controllable flight conditions,
• e. Since this missile launch system does not include either a weapon control or a mission planning station, the following functions essential to the missile can not be performed: on-board mission planning, self-test, initialization of the GPS receiver, deployment of the navigation system ,

• – ein Schienensystem,
• – mehrere Rollenschlitten zum Transport der Waffen zum Bombenschacht,
• – mehrere stationäre Flugkörper-Lager-Stationen,
• – ein automatisches Abwurf-Steuerungs-System, das die Bewegung der Rollenschlitten zum/vom Bombenschacht steuert, den Waffen-Abgang vom Rollenschlitten aktiviert und die Neuaufnahme einer Waffe durch einen Rollenschlitten kontrolliert.

A weapon launch system for large civil aircraft such as the Boeing 747 is in US 5,763,811 described, which consists of the following components:

• A rail system,
• - several roller carriages for transporting the weapons to the bomb bay,
• Several stationary missile storage stations,
• An automatic drop control system which controls the movement of the roller carriages to / from the bomb pit, activates the weapon exit from the roller carriage and controls the reentry of a weapon by a roller carriage.

Next the elaborate one Construction of the rail system is the necessity of installation a bomb bay into the cell structure of the wide-body aircraft the main disadvantage of this weapon-throwing system.

• – die Plattform an der Oberseite mit einer Nut und das Raumfahrzeug an der Unterseite mit einer Feder ausgestattet sind,
• – das Raumfahrzeug auf der Plattform positioniert ist,
• – die Trennung des Raumfahrzeuges von der Plattform durch die Schrägstellung der Plattform nach Fallschirm-Airdrop durch Herausgleiten der Raumfahrzeug-Feder aus der Plattform-Nut erfolgt.

In JP 04-260 900 the discharge of a small spacecraft from a transport aircraft is described by means of a reusable Airdrop platform, wherein

• - the platform at the top with a groove and the spacecraft at the bottom are equipped with a spring,
• - the spacecraft is positioned on the platform,
• - The separation of the spacecraft from the platform by the inclination of the platform after parachute Airdrop by sliding out of the spacecraft spring from the platform groove is done.

essential Disadvantage of this platform is that the platform has no Safety features, the unintentional triggering of safety-critical or irreversible actions (e.g., engine start, Prevent extension of the swing-wing).

Out US 5,229,538 is a platform (bomb rack) known, which hangs on a weapon station of a fighter aircraft and can accommodate several intelligent weapons such as JDAM. The platform ensures the power station and the data communication with the weapons computer of the fighter according to MIL-STD 1553 or MIL-STD 1760 via the weapon station by working as a remote terminal in the weapon bus of the fighter aircraft and its own sub-data bus as a bus Controller to the attached weapons, whereby the weapon computer of the fighter aircraft can communicate indirectly with the attached to the platform weapons. This bomb back therefore serves as a communication translator and allows the firing of multiple weapons from only one fighter aircraft weapon station.

EP 1 001 242 describes an interface adapter that allows the firing of weapons with different interface types (eg MK 82 data interface, MIL-STD 1760 interface) from the same weapon station of a combat aircraft. This increases the tactical operational flexibility and capacity of the fighter aircraft, as each weapon can be fired in principle by each weapon station.

Of the The invention is based on the technical problem of a pull-out platform for the Discarding missiles from a transport plane by parachute, which makes it possible a missile, in particular a cruise missile, from a transport plane during safely settle the flight at a predetermined position, wherein no structural changes on the missile and the airframe are necessary. This technical problem is characterized by the features of the Ausziehplattform according to claim 1 and by the Method of depositing a pullout platform with an attached missile a transport aircraft according to claim 8 solved. Advantageous embodiments the Ausziehplattform and the method are shown in the respective subclaims.

• a. die Kosten eines MFK-Verschuß von einem militärischen Transportflugzeug (circa 30 Cent pro 1 to Nutzlast/km) sind geringer als der Verschuß von einem Jagdbomber (circa 25 Euro pro 1 to Nutzlast/km);
• b. großes Kosten-Einsparungs-Potential ergibt sich durch entsprechende Reduzierung der Anzahl der Jagdbomber einer Luftwaffe. Dies macht Mittel für die Beschaffungs-Kosten der durch die Erfindung vorgeschlagenen Vorrichtungen frei;
• c. eine Ausweitung der taktische Einsatzmöglichkeiten resultiert aus der größeren Reichweite des Transportflugzeuges, der größeren Anzahl der mitgeführten MFKs und durch die on-bord Missions-Planungs-Fähigkeit des militärischen Transportflugzeuges als MFK-Abschußplattform;
• d. die Zeit zwischen Ziel-Aufklärung und Zielbekämpfung kann wesentlich reduziert werden, weil ein militärischen Transportflugzeuges, das als MFK-Abschußplattform benutzt wird, im Abgangs-Gebiet lange Zeit (auch ohne Luft-Betankung) kreisen kann und von aktuellen Aufklärungs-Ergebnissen abgeleitete Bekämpfungsaufträge kurzfristig umsetzen kann. Somit kann die Zeit eingespart werden, die ein Jagdbomber am Boden auf die Fertigstellung des Missions-Planes warten muß und die vergeht, bis der Jagdbomber ins Abgangs-Gebiet geflogen ist. Nach Verschuß von 2 MFKs muß der Jagdbomber wieder zu seinem Stützpunkt zurückkehren, währenddessen das militärischen Transportflugzeuges im sicherem Abgangs-Gebiet weiter auf Bekämpfungsaufträge warten kann;
• e. zur Zeit werden oftmals pro MFK 2 Missionen im einem Missions-Plan (z.B. Taurus KEPD 350) geplant und in den MFK am Boden vor take-off geladen. Erst im Flug wird je nach taktischer Situation durch die Jagdbomber-Besatzung entschieden, welche Mission der MFK durchführen soll. Wenn der Missions-Plan onbord komplett erstellt werden kann, muß nur eine Mission pro MFK geplant werden. Damit ergeben sich größere Speicher-Kapazitäten innerhalb der MFK-Rechner für Geländedatenbanken, Geländemodellen etc.. für diese eine Mission, ebenso eine Verkürzung der Zeitdauer, die für die Erstellung des Missionsplanes notwendig ist.
• f. da die durch die Erfindung vorgeschlagenen Vorrichtungen (Ausziehplattform, Weapon Control Mission-Planing Container) als Standard-Paletten handhabbar sind, ist eine Einrüstung bzw. Umrüstung des Transportflugzeuges nicht notwendig, was einen Kostenvorteil darstellt und wodurch das Transportflugzeug nach Belandung und nach Ausladen des Weapon Control Mission-Planung Container sofort für andere Verwendungs-Rollen eingesetzt werden kann.

The invention has several advantages:

• a. the cost of an MFK shipment from a military transport aircraft (approximately 30 cents per 1 to payload / km) is less than the cost of firing a fighter-bomber (approximately 25 euros per 1 to payload / km);
• b. Great cost-saving potential results from corresponding reduction in the number of fighter-bombers of an air force. This frees up funds for the procurement costs of the devices proposed by the invention;
• c. an expansion of tactical capabilities results from the larger range of the transport aircraft, the greater number of MFKs carried and the on-board mission planning capability of the military trans port airplane as an MFK launch platform;
• d. the time between target reconnaissance and target combat can be significantly reduced because a military transport aircraft used as MFK launch platform can circle in the departure area for a long time (even without air refueling) and combat orders derived from current reconnaissance results in the short term can implement. This saves the time a fighter-bomber has to wait on the ground for the completion of the mission plan, and that passes until the fighter-bomber has flown to the departure area. After firing 2 MFKs, the fighter-bomber must return to its base, during which the military transport aircraft in the safe departure area can continue to wait for combat missions;
• e. Currently, two missions per MFK are often planned in one mission plan (eg Taurus KEPD 350) and loaded into the MFK on the ground before take-off. Depending on the tactical situation, it is only in flight that the fighter-bomber crew decide which mission the MFK should carry out. If the mission plan can be completed on-board, only one mission per MFK needs to be planned. This results in larger storage capacities within the MFK calculator for terrain databases, terrain models, etc .. for this one mission, as well as a shortening of the time necessary for the creation of the mission plan.
• f. since the devices proposed by the invention (pullout platform, Weapon Control Mission-Planing Container) are handled as standard pallets, a retrofitting or conversion of the transport aircraft is not necessary, which represents a cost advantage and whereby the transport aircraft after loading and after unloading the weapon Control mission planning container can be used immediately for other use roles.

following the invention is based on a shown in the drawings, preferred embodiment be explained in more detail. It shows:

1 : Schematic architecture of the proposed system with pullout platform and Weapon Control Mission Planing Container (WCMPC) in the hold of a transport aircraft

2 Extending platform in Airdrop position, Airdrop parachute of the pull-out platform is shot into the open air

3 : deployed Airdrop parachute pulls out launch platform with cruise missile into the open

4 : Umbilical cable is pulled off the pullout deck

5 : Separation process of the cruise missile from the pylon of the pullout deck

6 : Loading ramp is closed, next pull-out platform is positioned in aerodynamic position and connected to WCMPC via umbilical cable

7 : State Transition Diagram (Moding) of the main flow control of the main computer of a MFK under a pullout platform

• – Aufklärungs-Ergebnisse und Wetter-Informationen als Grundlage für die Missions-Planung,
• – Almanac-, Ephemeris-, Kryptokey- und PVT-Daten (position, velocities, time) zur Initialisierung der GPS- bzw. Galileo-Receiver des an die Ausziehplattform angehängten Marschflugkörpers,
• – Position, Geschwindigkeit, Euler-Winkel, Drehraten, Mach-Nr, Lever-Arms, Figure of Merit und Status-Infos der Transportflugzeug-Navigation, um die Initialisierung (one-shot-alignment) und die zyklische Stützung (periodic alignment) der Navigations-Systeme der Marschflugkörper vor dem Abgang auszuführen (siehe 7, Mode 'Navigation Alignment'),
• – Zustands-Informationen vom Cargo-Handling-System des Transportflugzeuges wie Laderampe zu/in Bewegung/auf, locks open/closed etc..

1 shows the architecture of the system, which consists of the Weapon Control Mission Planing Container (WCMPC) and one or more pullout platforms, each carrying one or more cruise missiles, and whose elements are operationally deployed in the hold of a military transport aircraft. The proposed system is connected as a monitor to the data network (according to MIL-STD 1553) of the transport aircraft. This requires no software adjustments in the transport aircraft, if necessary, a hardware connection option (plug) must be created. By means of the data monitor function, the proposed system obtains various information from the data network of the transport aircraft such as

• - reconnaissance results and weather information as a basis for mission planning,
• - Almanac, ephemeris, crypto-key and PVT (position, velocities, time) data to initialize the GPS or Galileo receivers of the cruise missile attached to the pullout platform,
• Position, Speed, Euler Angle, Turn Rate, Mach No, Lever Arms, Figure of Merit, and Cargo Transport Navigation Status Info to perform one-shot alignment and cyclic periodic alignment Navigation systems of the cruise missile before the departure to execute (see 7 , Mode 'Navigation Alignment'),
• - Status information from the cargo handling system of the transport aircraft such as loading ramp on / in motion / on, locks open / closed etc ..

moreover the proposed system has a supply interface to Transport aircraft, by means of which the aircraft-typical 3 × 115 V 400 Hz relates it internally to different useful voltages as 28 VDC, 270 VDC converts.

Mechanically, the proposed system is compatible with the width of the cargo pallets used by the transport aircraft so that its elements, such as cargo pallets, can be loaded or unloaded into the cargo hold. Besides, its elements are like usual Cargo Pa During the flight, the lettings are securely fixed in the hold by means of the 'logistic locks' of the guide rails of the cargo hold floor or the 'air drop system locks' are used in the parachute airdrop of the pull-out platforms in the known manner (see US 4349168 ).

• – zusätzlicher aerodynamischer Widerstand reduziert die Reichweite und Geschwindigkeit des Trägerflugzeuges,
• – ein Marschflugkörper als Außenlast ist während der Tragflugphase starken Vibrationen ausgesetzt, wodurch seine Zuverläßigkeit und damit die Wahrscheinlichkeit des Missionserfolges reduziert wird.

An extension platform of the proposed system allows the departure of cruise missiles from inside the transport plane, which eliminates the need for external pylons on the wings which have the following disadvantages:

• Additional aerodynamic drag reduces the range and speed of the carrier aircraft,
• - A cruise missile as an external load is subjected to strong vibrations during the wingflight phase, which reduces its reliability and thus the likelihood of mission success.

A Pullout platform should one or more attached cruise missiles during the Flight of the cargo plane from the cargo compartment to the outside over the lowered rear loading ramp without collision with the transport plane carry and Afterwards, on the command of a cruise missile, the cruise missiles follow release down and push away without touching each other.

For this purpose has a pullout platform as in 1 visible on the bottom of one or more conventional heavy duty pylons (NATO standard) mounted. By means of the hooks, the centering clamps and the centering spigot of the cruise missile, the heavy duty pylon fixes the cruise missile and the umbilical plug of the cruise missile provides the cruise missile with energy and data via the pylon (see MIL-STD 1760). The RTU address lines of the umbilical Milbus (see MIL-STD 1760) of each pylon are encoded with different RTU addresses (see 1 ), so that an attached cruise missile can recognize its position (eg left / middle / right) on the pull-out platform. It also allows the Weapon Control Mission Planing Container Control Console to check which type of pullout deck (number of attached MFKs) is connected to it.

At the top of the pullout deck has an umbilical plug attached to it using the pull-out platform via umbilical cable with the Weapon Control Mission planing container is connected as long as the pull-out platform still in the cargo hold, and its removal direction of the Weapon Control Mission Planing Container is causing the separation from the umbilical cable during the Airdrops relieved and snapped back Umbilical cable is prevented from entering the hold. This umbilical plug is in the pullout platform with the umbilical plugs of the pylons Wired, making the Weapon Control Mission Planing Container the Energize and communicate with MFKs on the pullout deck can.

The umbilical cable, which connects the Weapon Control Mission Planing Container to the pullout platform, provides the discrete control signal that allows the Weapon Control Mission Planing Container control console to eject the Airdrop parachute parachute from the lowered loading ramp (please refer 2 ) upon completion of the exit interaction with the MFKs. By a safety hardware circuit in the Ausziehplattform this signal can ignite the parachute discharge only if at the same time of the MFKs the 28 VDC of the ignited thermal batteries abut umbilical plugs. The main computers of the MFKs attached to the pull-out platform only release this safety circuit via a discrete umbilical signal if they recognize the successful procedure of the 'committed to store separation' according to MIL-STD 1760 and via Milbus in the command word 'critical control' (see MIL-STD 1760) also received the command for parachute ejection.

This Umbilical cable is in its length so dimensioned that it is then subtracted from the pullout deck is when the pullout platform lowered during the Airdrops Loading ramp has left and get a certain safety distance located behind the loading ramp. After removing the umbilical cable The umbilical plug of the pullout deck will become some discreet Signals such as e.g. DC-PW1, DC-PW2 (or unused signals like rel S, BOS LC can be used for see MIL-STD 1760) voltage / currentless, what the MFKs sense and as an indicator of the information 'target platform has left loading ramp 'interpret.

When discrete signal is also the information 'parachute ejected' via umbilical plug of the pylons from the Airdrop parachute system led to the MFKs, whereby the sequencing software of each attached MFK can sense the Airdrop process. From an attached MFK (for example, from the center) is the control signal via umbilical connector over the Structure of the pullout deck wired to all pylons, with the the cartridges of the pylons open the hook and plunger activation to Purposes of separation of the MFKs are ignited by the Ausziehplattform. Thus only one MFK activates the opening the hook and the extension of the pestles of all existing pylons, resulting in a time-synchronized separation of all attached MFKs from the pullout platform given is.

At the top of the pullout platform is a parachute system attached, its parachute on a command in the Weapon Control Mission Planing Container is generated and via umbilical cable to the pull-out platform wired to the rear from the lowered loading ramp to the outside promoted to development and its unfolded parachute the pullout platform together attached MFKs from the hold of the flying cargo plane over the Lowered loading ramp pulls out into the open, if the unfolded parachute so much pulling power developed that the 'air drop system locks' of the guide rails release the translatory movement of the pull-out platform. The Traction rope of the parachute is at the rear end (direction open Loading ramp) attached to the pullout platform, allowing minimal pitch / roll moments by the tensile force of the deployed parachute on the Ausziehplattform after Leaving the lowered loading ramp act to one as possible horizontal position of the pullout platform to reach.

On the Airdrop parachute system can be dispensed with if the Cargo plane over one own equipment, with the Airdrop parachute over the lowered loading ramp can be deployed. In this case the cable must of the Airdrop parachute on the pullout deck attached become. The output of this Airdrop-parachute is then through the loadmaster or the navigator of the transport aircraft initiated, in the same way as with heavy-duty shedding.

On both sides of the pullout platform has feet (see 1 ), on which she stands. The feet have bearing surfaces below, allowing the pullout platform on the transport rollers installed in the cargo hold floor of the transport aircraft to be moved like a cargo pallet in the cargo hold. The bearing surfaces are guided laterally by the guide rails of the cargo compartment floor and have recesses (see US 4349168 ), whereby the Ausziehplattform by means of the 'logistic locks' of the guide rails in the cargo hold can be fixed or by means of the 'air drop system locks' the guide rails only backwards on the lowered loading ramp when a certain tensile force is exceeded (by deployed parachute) is pulled out. The control of the 'logistic locks' or 'air drop system locks' is carried out by means of the cargo handling system of the transport aircraft (Loadmaster).

The system's Weapon Control Mission Planing Container can be loaded into the hold like a cargo pallet and unloaded from the hold (see 'logistic locks'). In it the elements for weapon control and mission planning are summarized. After being loaded into the cargo hold as the first element of the system, it is connected to the power and data network of the transport aircraft (see 1 ). The energy received will be used to operate the Weapon Control Mission Planing Container and its connected pullout platform, including attached MFKs.

Another interface to the Weapon Control Mission Planing Container is the umbilical cable, which connects the control console of the Weapon Control Mission Planing Container to the pull-out platform closest to the loading dock (Airdrop position, see 2 ). By means of this cable, the MFKs of the connected pull-out platform are supplied with energy and data.

• – Steuer-Konsole,
• – Missions-Planung,
• – Mensch-Maschine-Schnittstelle für Missions-Planung und Waffensteuerung.

Inside the Control Mission Planing Container is:

• - control console,
• - mission planning,
• - Human machine interface for mission planning and weapon control.

In addition, a winch is mounted on the outside wall, with which the umbilical cable protruding from the loading dock after an airdrop (see 4 ) can be obtained.

An inexpensive Ethernet network connects these elements (see 1 ).

The control console incorporates the bus control unit (BCU) of the umbilical cable Milbus, with the MFKs attached to the pull-out platform acting as a remote terminal unit (RTU). In addition, it is integrated as a data monitor in the data network of the transport aircraft. By means of Ethernet, it is connected to the man-machine interface to receive operator commands (power on, fire command, parachute-ignition, etc.) to operator displays (test, moding, alignment status, etc.). to visualize and to receive the mission plans which they sent to the MFKs of the connected and activated pull-out platform for memory download (see 7 , Mode 'loading the mission plan') forwarded.

• – aktivieren der Energie-Versorgung der verbundenen Ausziehplattform samt angehängter MFKs durch Lieferung der 3 × 115 V 400 Hz aus dem Versorgungs-Netz des Transportflugzeuges,
• – prüfen durch einen Waffenstations-Check, wieviele MFKs und wo sich MFKs unter der Ausziehplattform befinden,
• – überwachen und auswerten der gemeldeten Selbsttest-Ergebnisse der MFKs (siehe 7, Modes 'Einschalten', 'Einschalt-Test', 'Ausgelöster Test'),
• – download der von der Missions-Planung erhaltenen Missions-Pläne in die MFKs der Ausziehplattform (siehe 7, Mode 'Laden des Missionsplans'),
• – initialisieren der GPS- bzw. Galileo-Receiver der MFKs mit Almanac-, Ephemeris-, Kryptokey- und PVT-Daten, welche die Steuer-Konsole als Daten-Monitor aus dem Datennetz des Transportflugzeuges gewinnt (siehe 7, Mode 'Verteilung'),
• – aktivieren und überwachen des Navigations-Alignments der MFKs, wobei die Steuer-Konsole periodisch Navigations-Daten des Transportflugzeuges, welche sie als Daten-Monitor ermittelt, an die MFKs sendet (siehe 7, Mode 'Navigation Aufrichtung'),
• – aktivieren und überwachen der Abgangs-Interaktion (siehe 7, von Mode 'Vorbereitung Flugkörper-Abgang' bis Mode 'Stop der Interaktion mit dem Träger') mit den MFKs (siehe MIL-STD 1760), in deren Verlauf bei jedem MFK die Thermalbatterie gestartet, die Rudermaschinen entriegelt und Rudervoreinstellung gesetzt wird. Dies erfolgt nur, wenn via Datennetz des Transportflugzeuges (Infos vom Cargo-Handling-System) erkannt ist, dass die Laderampe abgesenkt und die angebundene Ausziehplattform sich in Airdrop-Stellung (nächste an der Laderampe) befindet,
• – MFKs mit der Information versorgen, dass der Airdrop nachfolgend aktiviert wird,
• – aktivieren des Zünd-Signals, welches das Ausstoßen des Fallschirmes (Airdrop-Fallschirmsystem) der Ausziehplattform nach hinten über die abgesenkte Laderampe ins Freie verursacht,
• – versorgen einiger diskreter Signale des Umbilical-Kabels mit Spannung/Strom (DC), welche die MFKs sensieren und durch deren Abfall die MFKs das Abziehen des Umbilical-Kabels von der Ausziehplattform und damit das Verlassen des Laderaums erkennen können.

The main task of the control console is to interact with the MFCs of the pullout platform (compare 'weapon control computer' in fighter bombers), doing the following due to operator input:

• Activating the power supply of the connected pullout platform together with attached MFKs by supplying the 3 × 115 V 400 Hz from the supply network of the transport aircraft,
• - check through a weapons station check how many MFKs and where MFKs are under the pull-out platform,
• - monitor and evaluate the reported Self-test results of MFKs (see 7 , Modes 'switch on', 'switch-on test', 'triggered test'),
• - download the mission plans received from the Mission Planning into the MFKs of the pullout platform (see 7 , Mode 'Loading Mission Plan'),
• Initialize the MFK's GPS or Galileo receivers with Almanac, Ephemeris, Kryptokey and PVT data, which the control console gains as a data monitor from the transport's data network (see 7 , Fashion 'distribution'),
• Activate and monitor the navigation alignment of the MFKs, whereby the control console periodically transmits to the MFKs navigation data of the transport aircraft, which it determines as a data monitor (see 7 , Mode 'Navigation Aufricht'),
• - activate and monitor the departure interaction (see 7 , from mode 'missile departure preparation' to mode 'stop interacting with the wearer') with the MFKs (see MIL-STD 1760), during which the thermal battery is started, the rowing machines are unlocked and the rudder preset is set at each MFK. This only occurs if the data network of the transport aircraft (information from the cargo handling system) detects that the loading ramp has been lowered and the attached platform is in the aerodynamic position (next to the loading ramp),
• - provide MFKs with the information that the airdrop is subsequently activated,
• Activating the ignition signal which causes the ejection platform of the parachute (Airdrop parachute system) to the rear over the lowered loading ramp to the outside,
• - supplying some discrete signals of the umbilical cable with voltage / current (DC) which the MFKs sense and by dropping them the MFKs can detect the removal of the umbilical cable from the pullout platform and thus leaving the cargo compartment.

through the mission planning component of the Weapon Control Mission Planing Containers can be the operator control orders that he has received before take-off or during the flight via radio link be commanded, implement in mission plans. He uses it for that the human machine interface of Weapon Control Mission Planing Containers and processed reconnaissance results and weather information, which the control console as a data monitor from the data network of the Transport airplane wins and mission planning via internal Ethernet available provides.

• A. Der Mode 'Stop der Interaktion mit dem Träger' (siehe 7) wird erst verlassen, wenn die Bestätigung (committed to store separation) des erfolgreichen Abschlußes der Abgangs-Interaktion (ab Mode 'Vorbereitung Flugkörper Abgang') via Milbus zur Steuer-Konsole gesendet worden ist und danach das Steuer-Signal zum Fallschirm-Ausstoß im Kommando-Wort 'critical control' via Milbus (siehe MIL-STD 1760) erkannt wurde.
• B. Im Mode 'Überwachung des Airdrop' (siehe 7) wird erkannt und überwacht, ob der Airdrop-Vorgang korrekt durchlaufen wird: – ob das Airdrop-Fallschirmsystem die Aktivierung des Fallschirms gemeldet hat (siehe 2), – ob die Inertial Measurement Unit (IMU) des Marschflugkörpers die durch die Zugkräfte des Fallschirms erzeugten Beschleunigungen sensiert, – ob die Milbus-Kommunikation durch das Abziehen des Umbilical-Kabel vom Umbilical-Stecker der Ausziehplattform stoppt (siehe 4), – ob diskrete Signale des Umbilical-Kabels spannungs/stromlos werden aufgrund des Abziehens des Umbilical-Kabel vom Umbilical-Stecker der Ausziehplattform.
• C. Falls der Airdrop-Vorgang als korrekt erkannt wird, wird in den Mode 'Plattform-Regelung und Warten auf Abgangs-Ereignis' (siehe 7) gewechselt. In diesem Mode werden folgende Aktionen ausgeführt: – die Autopiloten der angehängten MFKs versuchen die Rolldrehrate der Ausziehplattform auf circa 0°/sec und Nick- und Anstellwinkel der Auszielplattform in dem für den Abgang von der Ausziehplattform zulässigen Bereich zu regeln, – falls obige Bedingungen für den Abgang der MFKs von der Ausziehplattform eine bestimmte Zeitspanne (z.B. 100 ms) vorliegen, aktivieren alle angehängten MFKs jeweils ihr diskretes Steuer-Signal, mit dem die Kartuschen (Catridges) der Pylons zum Öffnen der Haken und zur Stößel-Aktivierung zum Zwecke der Trennung der MFKs von der Ausziehplattform gezündet werden, wobei allerdings nur das Steuer-Signal eines MFKs (z.B. des mittigen MFKs) mit den Kartuschen verkabelt ist, um eine zeitsynchrone Trennung aller angehängten MFKs von der Ausziehplattform zu erreichen. Falls dann der MFK-Stössel (plunger) den Abgang von der Ausziehplattform sensiert (siehe 5), wird in den Mode 'Separation von der Plattform' übergegangen (siehe 7).
• D. Im Mode 'Separation von der Platform' wird durch den Autopiloten die übliche Q0-Control und die Separation-Lenkung durchgeführt. Falls mehrere MFKs von der Ausziehplattform abgesetzt werden, führt jeder MFK die seinem Pylon (siehe RTU-Adresse) zugeordnete Abgangs-Lenkung durch (z.b bei 3 MFKs: linker/rechter MFK nach außen weg, der mittlere MFK nur nach unten), wodurch die Kollision der releasten MFKs vermieden wird. Nach Abschluß dieses Lenk- und Regelvorganges werden die Schwenkflügel ausgefahren und geprüft, ob der MFK ausreichend Geschwindigkeit hat, um das Triebwerk zu starten.
• E. Falls nicht, wird in den Mode 'Abfang-Manöver für Triebwerks-Start' verzweigt, in dem Folgendes ausgeführt wird: – prüfen, wieviel Höhe über Grund (AGL) vorhanden ist, – berechnen eines entspr. Sturzflug-Manövers mit anschließendem Abfang-Manöver, um die Geschwindigkeit so zu erhöhen, dass der Triebwerksstart ermöglicht wird, – durchführen des Sturzflug/Abfang-Manövers, – nach Abschluß des Sturzflug/Abfang-Manövers Wechsel in einen der Marschphasen-Modes (siehe 7), wo dann das Triebwerk gestartet und der gespeicherte Missionsplan ausgeführt wird.
• F. Um die Gefährdung des Transportflugzeuges zu reduzieren, werden die Schwenkflügel der Marschflugkörper weiter (z.B. 10° mehr) aufgeklappt als dies bei einem Verschuß von Jagdbombern üblich ist, um den aerodynamischen Auftrieb des Marschflugkörpers signifikant zu erhöhen und entsprechend seinen Treibstoffverbrauch zu erniedrigen.

The man-machine interface provides 2 operator stations, one for the Weapon System Officer (WSO), who controls the deployment of the pull-out platform, and one for the Mission Planning Officer (MPO), who creates the mission plans for the MFKs. Cruise missiles (MFK), which are fired under a pullout platform by parachute airdrop, have additional features that distinguish them from MFKs, which are used for hunting bombers as an external load:

• A. The Mode 'Stop Interaction with the Carrier' (see 7 ) is only left when the confirmation (committed to store separation) of the successful completion of the departure interaction (from mode 'preparation missile departure') has been sent via Milbus to the control console and then the control signal for parachute ejection in Command word 'critical control' via Milbus (see MIL-STD 1760) was detected.
• B. In the mode 'Monitoring the Airdrop' (see 7 ) is detected and monitored as to whether the Airdrop process is run correctly: - whether the Airdrop parachute system has reported the activation of the parachute (see 2 ) - whether the inertial measurement unit (IMU) of the cruise missile senses the accelerations generated by the parachute's tractive forces, - whether the Milbus communication stops by pulling off the umbilical cable from the umbilical plug of the pull-out platform (see 4 ), - whether discrete signals of the umbilical cable become energized / de-energized due to the removal of the umbilical cable from the umbilical plug of the pull-out platform.
• C. If the Airdrop operation is detected to be correct, the mode 'Platform Control and Waiting for Exit Event' (see 7 ) changed. In this mode, the following actions are performed: - the autopilots of the attached MFKs attempt to control the roll rate of the pull-out platform to approximately 0 ° / sec and the pitch and pitch of the target platform in the range allowed for exit from the pullout deck, if above conditions for For example, if the MFKs leave the pullout deck for a certain amount of time (eg, 100ms), all attached MFKs will activate their discrete control signal, with the cartridges of the pylons opening the hooks and tappet activation for separation however, only the control signal of an MFK (eg, the center MFK) is wired to the cartridges to achieve time-synchronized separation of all attached MFKs from the pullout deck. If then the MFK plunger (plunger) senses the departure from the Ausziehplattform (see 5 ), goes into mode 'Separation from the platform' (see 7 ).
• D. In the Separation from Platform mode, the autopilot performs the usual Q0 control and separation steering. If several MFKs are set down from the pullout platform, each MFK carries out the departure control assigned to its pylon (see RTU address) (eg with 3 MFKs: left / right MFK outwards, middle MFK only downwards) Collision of the released MFKs is avoided. After completion of this steering and control process, the swing wings are extended and checked that the MFK has sufficient speed to start the engine.
• E. If not, the engine start interception maneuver mode is run, which performs the following: - check how much over ground (AGL) is present, - calculate an equivalent dive maneuver followed by interception Manoeuver to increase the speed to allow the engine to start, - perform the dive / intercept maneuver, - change to one of the march phase modes after completion of the dive / intercept maneuver (see 7 ), where the engine is started and the stored mission plan is executed.
• F. To reduce the risk to the transport aircraft, the wings of the cruise missiles are further unfolded (eg 10 ° more) than is usual with a firing of Jagdbombern to significantly increase the aerodynamic lift of the cruise missile and correspondingly lower its fuel consumption.

• 1. der Loadmaster des Transportflugzeuges lädt mittels des Cargo-Handling-Systems des Transportflugzeuges den WCMPC und die Ausziehplattformen samt angehängter MFKs in den Frachtraum. Dabei benutzt er den bordeigenen Ladekran (siehe A400M), um den WCMPC vom anliefernden Lastwagen auf die abgesenkte Laderampe zu heben, wo er durch die eingebauten und angetriebenen Transportrollen nach hinten an das Frachtraum-Ende befördert wird. Danach werden auf die gleiche Weise die Ausziehplattformen in den Frachtraum transportiert. Anschließend fixiert der Loadmaster den WCMPC und die Ausziehplattformen, indem er die 'logistic locks' der Führungsschienen aktiviert. Den WCMPC schließt er an das Energie-Versorgungs- und an das Datennetz des Transportflugzeuges an,
• 2. vor take-off des Transportflugzeuges begeben sich der Missionsplanungs-(MPO) und der Waffensystem-Offizier (WSO) in den WCMPC und bereiten ihre Arbeitsplätze vor,
• 3. während des Fluges des Transportflugzeuges erstellt der MPO MFK-Missionspläne, indem er Bekämpfungsaufträge, Aufklärungsergebnisse und Wetterinformationen an seiner Bedienkonsole verarbeitet,
• 4. nach Fertigstellung der Missionspläne, verbindet der Loadmaster das Umbilical-Kabel des WCMPC mit der Ausziehplattform, die sich in Airdrop-Stellung (vor der Laderampe) befindet. Falls die bordeigene Apparatur zum Ausbringen des Fallschirms benutzt wird, hängt der Loadmaster den Seilzug des Fallschirmes an die Ausziehplattform an,
• 5. danach schaltet der im WCMPC arbeitende WSO die Versorgungsspannung für die Ausziehplattform und damit für die angehängten MFKs ein,
• 6. der WSO prüft, ob jeweils die Hochlaufsequenz und die Selbststest jedes MFKs ok ist;
• 7. der WSO initiiert und überwacht den Download der vom MPO generierten Missionen in die MFKs der angehängten Ausziehplattform,
• 8. danach aktiviert der WSO das Navigations-Alignment der MFKs,
• 9. wenn das vorgeplannte MFK-Abgangs-Gebiet erreicht wird, entfernt der Loadmaster die Safety-Pins an der Ausziehplattform und senkt die Laderampe mittels des Cargo-Handling-Systems ab,
• 10. der WSO aktiviert und überwacht die Abgangs-Interaktion mit den MFKs, wodurch ihre eigene Energie-Versorgung (Thermal-Batterie) aktiviert wird,
• 11. der WSO überprüft, ob alle MFKs ihre Abgangs-Vorbereitung erfolgreich abgeschlossen haben,
• 12. der Loadmaster aktiviert die 'air drop system locks' der Airdrop-Stellung und deaktiviert die 'logistic locks' der Airdrop-Stellung mittels Cargo-Handling-System (Panel),
• 13. der WSO initiiert den Airdrop und beobachtet das Entfalten des Airdrop-Fallschirmes außerhalb des Frachtraumes (siehe 2) und das dadurch verursachte Herausziehen der Auszielplattform aus den Frachtraum (siehe 3). Falls die bordeigene Apparatur zum Ausbringen des Fallschirms benutzt wird, aktiviert der Loadmaster den Fallschirm-Auswurf,
• 14. der WSO und der Loadmaster prüfen, ob die Ausziehplattform den Frachtraum verlassen hat,
• 15. der WSO aktiviert und überwacht das Einziehen/Aufrollen des Umbilical-Kabel mittels der am WCMPC angebrachten Seilwinde,
• 16. der Loadmaster schließt mittels des Cargo-Handling-Systems die Laderampe,
• 17. der Loadmaster öffnet die 'air drop system locks' in der Airdrop-Stellung, öffnet die 'logistic locks' an der zur Laderampe nächst gelegenen Ausziehplattform und bewegt diese mittels der Transportrollen in die Airdrop-Stellung (siehe 6), wo er die Ausziehplattform dann mittels der sich dort befindenden 'logistic locks' fixiert,
• 18. der Loadmaster verbindet dann das Umbilical-Kabel des WCMPC mit der Ausziehplattform, welche sich in der Airdrop-Stellung befindet,
• 19. Siehe Nr.3.

The following describes in sequence how the proposed system is used operationally:

• 1. The loadmaster of the transport aircraft loads the WCMPC and the pullout platforms together with attached MFKs into the cargo compartment by means of the cargo handling system of the transport aircraft. He uses the on-board loading crane (see A400M) to lift the WCMPC from the delivering truck to the lowered loading ramp, where it is transported rearward to the cargo hold end by the built-in and powered transport wheels. Thereafter, the pullout platforms are transported into the cargo hold in the same manner. Then the Loadmaster fixes the WCMPC and the pullout platforms by activating the 'logistic locks' of the guide rails. He connects the WCMPC to the power supply and the data network of the transport aircraft,
• 2. before the take-off of the transport plane, the Mission Planning (MPO) and the Weapons System Officer (WSO) go to the WCMPC and prepare their jobs,
• 3. During the flight of the cargo plane, the MPO prepares MTS mission plans by processing combat missions, reconnaissance results and meteorological information on its console,
• 4. After completion of the mission plans, the Loadmaster connects the umbilical cable of the WCMPC to the pullout platform, which is in aerial position (in front of the loading ramp). If the onboard equipment is used to deploy the parachute, the Loadmaster attaches the pulley of the parachute to the pullout platform,
• 5. Thereafter, the WSO working in the WCMPC switches on the supply voltage for the pull-out platform and thus for the attached MFKs.
• 6. The WSO checks if the startup sequence and the self-test of each MFK are ok.
• 7. the WSO initiates and supervises the download of missions generated by the MPO into the MFKs of the attached pullout platform,
• 8. thereafter the WSO activates the navigation alignment of the MFKs,
• 9. When the pre-routed MFK outflow area is reached, the Loadmaster removes the safety pins on the pullout platform and lowers the loading ramp by means of the cargo handling system,
• 10. the WSO activates and monitors the exit interaction with the MFKs, thereby activating their own energy supply (thermal battery),
• 11. the WSO checks that all MFAs have successfully completed their leaving preparation,
• 12. the Loadmaster activates the 'air drop system locks' of the airdrop position and deactivates the 'logistic locks' of the airdrop position by means of the cargo handling system (panel),
• 13. The WSO initiates the airdrop and observes the deployment of the Airdrop parachute outside the hold (see 2 ) and the resulting withdrawal of the target platform from the cargo hold (see 3 ). If the on-board apparatus is used to deploy the parachute, the Loadmaster activates parachute ejection,
• 14. the WSO and the loadmaster check that the pullout platform has left the cargo hold,
• 15. the WSO activates and monitors the retraction / rewinding of the umbilical cable by means of the winch attached to the WCMPC,
• 16. the loadmaster closes the loading ramp by means of the cargo handling system,
• 17. The Loadmaster opens the 'Air Drop System Locks' in the Airdrop position, opens the 'Logistic Locks' on the pull-out platform closest to the loading dock and moves them using the Transport rollers in the Airdrop position (see 6 ), where he fixes the pull-out platform by means of the 'logistic locks' located there,
• 18. The Loadmaster then connects the umbilical cable of the WCMPC to the pullout platform, which is in the aerial position.
• 19. See no.3.

This can be repeated until all Ausziehplattformen shot are or as long as the fuel supply of the transport aircraft a safe return allowed to the base.

Claims (13)

Extending platform for the deployment of missiles a transport plane by parachute over the lowered, rear Loading ramp, with at least one weapon pylon mounted at the bottom, on each one missile is fixable and operable, the over Pestle from Weapon pylon repelled can be, and with one attached to the pullout deck Umbilical connector to which an umbilical cable is connected that the pullout platform with one in a cargo hold of the cargo plane It also connects the various arms control and mission planning containers is the umbilical plug the pull-out platform, each with a umbilical plug of each weapons pylon Wired, whereby the at least one missile even during the withdrawal of the Pull-out platform from the hold to the interruption of the cable connection between pullout platform and the weapons control and mission planning container communicate with it and be powered by it can, after disconnecting the cable, the separation of all missiles mounted on the pullout platform from the weapon pylons triggered by the control signal of a single missile, if the pullout platform is the safety area of the transport plane has left behind the loading ramp. Pull-out platform according to claim 1, characterized that the umbilical connector connects to the weapon control and mission planning container is disposed at its top. Extending platform according to claim 1 or 2, characterized characterized in that the umbilical cable is used to connect the weapon control and mission planning container having the pullout platform has a length, the safety distance between the rear loading dock of the transport aircraft and the pullout platform corresponds. Extending platform according to one of claims 1 to 3, characterized in that the at least one missile via hooks is attached to the at least one weapon pylon, wherein the at least one Weapons pylon at least includes a cartridge that is for severing of the at least one missile from which at least one weapon pylon is fired to open the hooks and to extend the existing rams. Extending platform according to one of claims 1 to 4, characterized in that it comprises a mechanism with the sure senses whether the pullout platform the cargo space, the lowered loading ramp and the security area of the transport aircraft has left and this information the at least one missile means Umbilical cabling available power. Extending platform according to one of claims 1 to 5, characterized in that for each weapon pylon one fixed Wired Milbus remote terminal coding according to MIL-STD 1760 is implemented, by which each missile its position at the Extending platform recognizes. Extending platform according to one of claims 1 to 6, characterized in that it has feet on the sides, on what she stands for, putting her on the transport wheels that are in the cargo hold floor of the transport plane are installed, such as a freight pallet is moved in the hold, laterally guided and / or locked by guide rails of the cargo hold floor. A method for deploying a pullout platform with at least one attached missile from a cargo plane via the lowered ramp, comprising the steps of: a. Making the electrical connection between the weapon control and the pull-out platform with the at least one attached and connected missile located in the hold of the cargo plane by an umbilical cable, b. Supplying the at least one missile with energy and data through the weapon control, c. Evaluating the self-test result of the at least one missile by the weapon control, d. Activation, execution and check of the erection of the navigation system of the at least one missile by the weapon control, e. Initiation of the irreversible departure preparations of the at least one missile (eg start of the thermal battery, unlocking of the rowing machines, adjustment of the fin preset angle) by the weapon control, f. Check by the gun control whether the at least one missile has reported the successful completion of the irreversible departure preparations, g. Extraction of the pullout parachute connected to the pullout platform from the lowered La derampe of the transport aircraft, h. Extracting the pullout platform together with the at least one attached missile via the lowered loading ramp of the transport aircraft by the tensile force of the unfolded Ausziehfallschirmes, i. Detection of the extraction process by the at least one missile senses and evaluates the accelerations occurring by the extraction process by means of its navigation system, j. Detecting the withdrawal of the umbilical cable from the pullout deck by the at least one missile by evaluating signal states of umbilical signals whereby the at least one missile recognizes that it corresponds to the safety range of the transport aircraft corresponding to the length of the umbilical cable; left, k. Triggering the separation of the at least one missile from the pullout platform by the signal of a single missile, l. Detecting whether the at least one missile is repelled from the Ausziehplattform by the at least one missile checks whether its ram is reported as extended, m. Execution of the departure actions such as outlet steering, opening the engine inlets, unfolding the swing-wing. Method according to claim 8, characterized in that that in step c. after evaluation of the self-test result of Mission plan in which at least one missile is loaded. Method according to claim 8 or 9, characterized that in step d. after successful erection of the navigation system of the at least one missile the pull-out platform is transported close to the rear loading dock, the loading ramp is lowered and the rear hatch is opened as necessary, so that the pull-out platform is in aerial position. Method according to one of claims 8 to 10, characterized that in step g. in close temporal relation to the ejection Ausziehfallschirmes the at least one missile by means of Umbilical connection of parachute ejection is announced. Method according to one of claims 8 to 11, characterized that in step m., if several missiles on the pullout platform attached are, every missile after detected rejection from the pullout platform to his weapons pylon and thus his Position on the Ausziehplattform associated outlet steering performs, thereby a collision of the missiles while the joint departure is prevented. Method according to one of claims 8 to 12, characterized by the further step that the at least one missile after Detecting the separation from the pullout platform, if its speed for the Engine start is too low, a brief dive / interception maneuver plans and perform to increase his speed and to start the engine afterwards.