METHOD OF SEPARATION OF NOSE SECTION AND FAIRING AND NOSE SECTION OF RESEARCH ROCKET Russian patent published in 1996 - IPC

FIELD: rocket engineering. SUBSTANCE: method can be used while designing nose parts of research rockets with nose fairing jettisones in flight. Method is based on the fact that nose fairing when jettisoned is given pulse of rotary motion in longitudinal (axial) plane and pulse of translational motion backwards and away from rocket. Method is realized by nose section which carries cylinder 21 with piston 23 and pusher 22 mated to rest 25 on fairing 8 mounted on edge of plate 4. Voltage is supplied to explosive charge 16, gaseous products of combustion penetrate into plunger space under piston and through clearances around small balls 11 into space between control valve 12 and end cap 29. Control valve 12 compresses spring 13 and moves to the left releasing small balls 11 which are sunk with conical surfaces of groove 19 into holes of plunger 10 and the latter moves to the right as far as it will go connecting groove 19 of sleeve with groove 18 of plunger 10. Gases from explosive charge 16 go into space 26, act on piston 23 cutting away pin 24. Pusher 22 gives fairing 8 translational motion through rest 25 with simultaneous rotation in longitudinal plane. EFFECT: improved operational characteristics and quality of generated information due to avoidance of interference from nose fairing. 4 cl, 4 dwg