DE102018004549B3 - Launcher for aircraft-supported missiles - Google Patents

Abstract

A launch device for aircraft-supported missiles is presented, having a spring-accelerated catapult, characterized in that a straightening unit can be adapted on the loading dock of an aircraft, the catapult has receiving devices for adapting missiles, a radio link of aircraft and missile can be built up, an electric and / or electronic cable connection between the aircraft and missile is directly buildable, the ejection force is adjustable and a visual inspection of the missile in operational condition is possible at any time.

Description

The invention relates to a modular launcher of aircraft (Lfz) based missiles.

From the patent DE 103 13 279 B4 a movable crane arm for a transport aircraft is known, which is rotatably mounted and pivotally adjacent to a hatch in a cargo hold of the transport plane and at its free end at least one weapon pylon, with the at least one missile in at least one holder or at least a magazine is stowed in the cargo compartment, is receivable and deductible, each weapon pylon and / or missile comprises sensors which measure the prevailing in the region of the missile air flow field or acting on the respective missile air flow forces and to a central data and Forward information processing that position the crane arm and the at least one weapon pylon with the recorded missile so that even an aerodynamically unstable missile without endangering the transport plane during the flight from the open hatch can be discontinued.

Further, the patent discloses DE 103 38 963 B4 a pullout platform for launching missiles from a cargo plane by parachute over the lowered, rear loading dock, with at least one weapon pylon mounted on the underside, to each of which a missile can be fixed and operated, which are repelled by rams from the weapon pylon and with an umbilical plug attached to the pull-out platform to which is attached an umbilical cable which connects the pull-out platform to a weapon control and mission planning container located in a cargo hold of the cargo plane, with the umbilical plug of the pull-out platform each cabled umbilical plug each weapons pylon, whereby the at least one missile communicate even during the extraction of the Ausziehplattform from the hold to the interruption of the cable connection between Ausziehplattform and the weapons control and mission planning container with this and from this with Energi e can be supplied, wherein after disconnection of the cable, the separation of all mounted on the Ausziehplattform missiles from the weapon pylons is triggered by the control signal of a single missile when the Ausziehplattform has left the security area of the transport aircraft behind the loading ramp.

The British disclosure GB 2 173 745 A discloses an unmanned aircraft starter. a start truck mounted start truck and a compression coil spring contained within a cylinder in a spring assembly. The movement of the spring is transmitted through a cable that runs on rollers on the starting car. The arrangement is such that the spring is parallel to the launch rails and, when the spring is released by means of a lock, the movement of the spring is opposite that of the launch vehicle to minimize recoil effects. There are dampers provided to stop the movement of the starter truck and the spring. The cable runs over pulley assemblies and each has a number of pulley wheels so that the overall speed ratio is adjustable.

Next is from the European patent specification EP 1 713 689 B1 an apparatus for carrying an unmanned aerial vehicle, a carrier; a launch carriage and a gripping device comprising known. The gripping means comprises at least one gripping portion arranged to releasably engage a fuselage of the aircraft, the gripping means being arranged with respect to the launch carriage between a first position in which the at least one gripping portion is arranged to receive the gripping portion Hull touched, and a second position is movable, in which the at least one gripping portion is arranged such that it is not in contact with the hull. The invention is characterized by a brake located at least in the vicinity of the gripping device, the brake being changed from a first configuration in which the brake inhibits movement of the gripping device relative to the starting carriage by a first amount to a second configuration can, in which the brake does not inhibit movement of the gripping device relative to the starting carriage or inhibits the movement of the gripping device by a second amount which is less than the first amount.

Last is from the published patent application DE 10 2016 012 924 A1 a spring-accelerated Softlaunchraketensystem with a tensionable lever on the upper launcher, which spans a spring inside the Softlaunchraketensystems and in the launching tube a cartridge can be introduced, in the cartridge is a projectile with a rocket engine / tail and possibly a warhead and at a launch the tensioned spring throws the projectile from the weapon and detonated by a delay of the rocket motor only after leaving the launcher.

• - der Flugkörper für einen sicheren Ausstoß aus dem Startrohr einen sauberen Formschluß mittels eines Sabot, benötigt. Der Sabot hat wiederum den Nachteil, dass er nach dem Flugkörperausstoß umher fliegt und das Luftfahrzeug beschädigen bzw. gefährden kann. Unter Umständen müssen die Bestandteile des Sabot aufwendig gesichert werden.
• - aufgrund des fixen Durchmessers bei den marktverfügbaren Startgeräten diese nur für Flugkörper mit ähnlichem Durchmesser geeignet sind,
• - sich die Startgeräte nur für Flugkörper mit einschwenkbaren bzw. faltbaren Auftriebshilfen wie z.B. Flügel, Kanare, Leitwerken, etc. eignen,
• - die Realisierung einer elektrischen Schnittstelle zu den Flugkörpern im Startrohr / -gerät zur Spannungsversorgung und Kommunikation komplexe und auwendige Lösungen erfordert,
• - die markverfügbaren Startgeräte sind nicht ohne Zusatzaufbauten richtbar im Ausstoßwinkel und in ihrer Ausstoßkraft verstellbar.
• - es nicht möglich ist eine Sichtprüfung im Betrieb an dem Flugkörper durchzuführen, während sich dieser im Startgerät befindet und
• - es keine Möglichkeit gibt, eine Funkverbindung mit Flugkörper zur Kommunikation z.B. für die Vorgabe von Wegpunkten ohne technischen Zusatzaufwand zu realisieren.

The disadvantages of the prior art are in particular that

• - The missile for a safe ejection from the launch tube a clean fit by means of a sabot needed. The sabot in turn has the disadvantage that he after the Missile missile flies around and can damage or endanger the aircraft. Under certain circumstances, the components of the Sabot must be secured consuming.
• - Due to the fixed diameter of the marketable launch devices they are only suitable for missiles of similar diameter,
• - the launchers are only suitable for missiles with swiveling or foldable buoyancy aids such as wings, canaries, tail units, etc.,
• the realization of an electrical interface to the missiles in the launch tube / device for power supply and communication requires complex and autonomous solutions,
• - The mark-available starting devices are not without additional attachments directionally adjustable in the discharge angle and in their ejection force.
• it is not possible to visually inspect the missile while it is in the launcher, and
• - There is no way to realize a radio link with missile for communication, for example, for the specification of waypoints without additional technical effort.

• - welches, unabhängig von seinem Durchmesser, keine Hilfs- oder Unterstützungseinrichtungen benötigt,
• - Auftriebshilfen des Flugkörpers nicht notwendig klappbar ausgeführt sein müssen,
• - elektrische und elektronische Schnittstellen einfach ausführbar sind,
• - der Ausstoßwinkel richtbar und die Ausstoßkraft einstellbar ist, sowie
• - eine Sichtprüfung des Flugkörpers im Startgerät möglich ist.

The object of the invention is therefore to propose a starting device,

• which, regardless of its diameter, does not require any auxiliary or support devices,
• - Buoyancy aids of the missile need not be designed to be foldable,
• - electrical and electronic interfaces are easy to carry out,
• - The ejection angle directable and the ejection force is adjustable, and
• - A visual inspection of the missile in the launcher is possible.

This object is solved by the features of the main claim. Advantageous embodiments are described in the subclaims.

The advantage of the starting device according to the invention lies in particular in that only one aircraft with a hatch to be opened to the rear is necessary for use. On the hatch in the existing mounting options, the straightening unit of the starting device is adapted. Alternatively, it is possible to first fix the straightening unit on a transport pallet or an intermediate frame and then attach them to the loading ramp.

Another advantage of the invention is the receiving device of the missile catapult. It is intended to launch missiles directly onto the catapult as an open sled, to launch the missile on a launch cage surrounding the missile, or to use a semi-enclosing launch tube. The receiving device is primarily dependent on the geometric shapes of the missile. In addition, continue to be relevant, the attachment of the buoyancy means, the center of gravity and the nature of the drive of the missile. For example, a missile with rigidly mounted wings is adapted directly to the open carriage, while a missile with tailplane is also bootable from a launch cage or teilumschließenden starter tube. Of course, all meaningful combinations are executable. The advantageous embodiments of the starting device according to the invention are described in dependent claims 2 and 3.

The advantage of omitting a fully enclosed starter tube is further the simple design of a radio link and the installation of electrical and electronic cable connections. The unfilled geometry offers the possibility of direct connection without having to use further feedthroughs or ejectable sealing elements. In this case, the radio link is used primarily for Flugbghnsteuerung and monitoring, the electrical cable connection to the power supply and the electronic cable connection for information transmission. If necessary, other hose or pipe connections are possible.

Lastly, another advantage of the invention is the possibility of continuous visual inspection of the missile. In contrast to starting devices according to the prior art, in which the missiles disappear in a fully enclosing starter tube, the starting device according to the invention offers the opportunity to observe the missile due to the open recording device to launch and still during the launch, possibly also with cameras to monitor ,

In order not to unnecessarily burden the structures of the missile or to damage it during firing, the launching device according to the invention provides for use of an adjustable spring or different rubber bands. The variety of missile geometries, embodiments, and masses launchable with the launcher require variable launch speeds and acceleration energies realized by the adjustable spring of the present invention. This advantageous embodiment is described in subclaim 4.

It shows the only one 1 an inventive starting device in the side view.

It shows 1 a straightening unit 1 standing on a hatch 2 adapted. Above the straightening unit 1 is a spring-loaded catapult 3 built up. The recording device 4 of the catapult 3 is designed as an open carriage on which a missile 5 in the starting direction 7 is attached. The starting direction 7 of the missile 5 is opposite to the direction of flight 6 ,

LIST OF REFERENCE NUMBERS

1

straightening unit

2

loading hatch

3

catapult

4

recording device

5

missile

6

flight direction

7

start direction

Claims (4)

Launcher for aircraft-based missile, a spring-accelerated catapult (3) comprising, characterized in that - a straightening unit (1) on the loading dock of an aircraft is adaptable, - the catapult (3) receiving means (4) for the adaptation of missiles (5) , - A radio link of the aircraft and missile (5) is buildable, - An electrical and / or electronic cable connection between the aircraft and missile (5) is directly buildable, - The ejection force is adjustable and - A visual inspection of the missile (5) in operational condition is possible at any time. Starting device after Claim 1 , characterized in that the receiving means for adapting missiles is an open carriage. Starting device after Claim 1 , characterized in that the receiving devices for the adaptation of missiles is a launch cage. Starting device according to one of Claims 1 to 3 , characterized in that the ejection force is adjustable due to an adjustable spring.

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