AIRCRAFT EJECTION DEVICE

FIELD: rocket suspension and forced separation systems. SUBSTANCE: device has load-bearing housing where rocket forced separation mechanism, rocket holding mechanism, onboard connector mechanism and electric automatic control units are arranged. Rocket forced separation drive includes tactical pneum...

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Bibliographische Detailangaben
Hauptverfasser:	REJDEL' A.L, SOKOLOVSKIJ G.A, SUKHOV L.V, ISHCHENKO V.V, VATOLIN V.V
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS,e.g. CANNONS ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS HARPOON GUNS HEATING LAUNCHERS FOR ROCKETS OR TORPEDOES LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	FIELD: rocket suspension and forced separation systems. SUBSTANCE: device has load-bearing housing where rocket forced separation mechanism, rocket holding mechanism, onboard connector mechanism and electric automatic control units are arranged. Rocket forced separation drive includes tactical pneumatic drive and one-time pyrotechnic drive connected by means of working lines. In the upper portion of housing there are wells for ejection device suspension units; free wells are closed with covers. Load-bearing housing is detachable and is rectangular in section; it is provided with side semicylindrical fairings. Its front portion is closed with fairing having arched section of double curvature; tail section is closed by fairing of conical-cylindrical shape with opening doors. Height of housing is equal to half diameter of rocket and width is about 0.3 of rocket calibre. EFFECT: improved aerodynamic characteristics of ejection device; enhanced reliability of holding the rocket. 3 cl, 7 dwg