rockets with gleitbarem undercarriage and a startvorrichtung aufhaengung

摘要

827,125. Launching rockets from aircraft. BREVETS AERO-MECANIQUES S.A. March 18, 1958 [March 27, 1957; Aug. 27, 1957], No. 8679/58. Classes 9(1) and 9(2) Rockets to be launched from aircraft and aligned in groups beneath a wing, the uppermost rocket in each group supported by the aircraft and each succeeding rocket supported by the rocket immediately above, are provided with a pivoted latch which engages a shear member on the supported rocket and extends over its nozzle so that after the propellant is ignited and the thrust of the gases on the latch exceeds a predetermined value the member shears and the rocket is released. Each rocket has a sliding tail 3 supporting the forward end by means of slots 3a in the fins engaging the tail 3 of the rocket immediately above, the uppermost rocket tail being engaged by rods (not shown) secured to the aircraft. The tail 3 guides the initial forward motion of the rocket 2 until picked up by the enlarged nozzle end 2a. The latch 5 pivoted in the nozzle wall and provided with a shoulder 7 to limit downward movement of the latch has a keyhole slot 9 to engage the neck of a shear member 8 screwed into the nozzle wall of the rocket below. Thus until the member 8 of the lowermost rocket shears, any forward thrust transmitted to the rocket above when the lowermost rocket is fired is counterbalanced by a rearward thrust transmitted to the latch 5 of the rocket above. The latch 5 has a stem 12 which is received in a groove between projections 10 of the rocket below and locked therein by a spring-pressed member 14 engaging a notch 15 in the stem 12. On release of the lowermost rocket the latch 5 of the rocket above is forced into its recess in the nozzle 2a and locked therein by the tail unit 3. The uppermost rocket hangs from a latch 5 on a support fixed to the aircraft. To ignite the propellant, each rocket is provided with an electric primer 16 having one terminal connected by the rocket casings to an electric energy source in the aircraft, the return circuit being closed by a manually operated switch (not shown) and a movable switch 22a mounted in the rocket and controlled by the latch 5. Thus when the latch 5 is retracted, rocket III in Fig. 10, the switch element 22a moves into contact with a pin 21 to close the circuit to rocket III, the ' circuits of the primers in the rockets above rocket III being held open by their respective latches.