DE2027371

The invention concerns a missile, in particular a guided missile, having stabilizing wings and a solid fuel propulsion motor. The fuel of the propulsion motor is divided into two separate fuel charges located axially spaced in the missile. The portion of the interior of the missile between the two f...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	JACOBSON, GUNNAR, OLSSON, OLOF BERTIL
Format:	Patent
Sprache:	eng
Schlagworte:	AEROPLANES AIRCRAFT AMMUNITION AVIATION BLASTING COMBUSTION ENGINES COSMONAUTICS EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION HEATING HELICOPTERS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	The invention concerns a missile, in particular a guided missile, having stabilizing wings and a solid fuel propulsion motor. The fuel of the propulsion motor is divided into two separate fuel charges located axially spaced in the missile. The portion of the interior of the missile between the two fuel charges consists of an empty space, into which the fuel charges deliver their combustion gases and which is surrounded by an annular member forming the external shell of the missile between the two fuel charges and comprising the jet nozzles for the propulsion motor. The two fuel charges have such relative sizes and locations in the missile that their common gravity center coincides substantially with the total gravity center of the missile. The stabilizing wings are attached to the annular member comprising the jet nozzles and are located circumferentially between said jet nozzles.