GB1243641A - Improvements in rocket motor exhaust nozzle assemblies - Google Patents

Abstract

1,243,641. Thrust vectoring apparatus. IMPERIAL METAL INDUSTRIES (KYNOCH) Ltd., and A. G. WALTERS. 10 June, 1969 [27 June, 1968], No. 30764/68. Heading B7G. [Also in Division F1] An exhaust nozzle assembly for a rocket motor comprises an under-expanded exhaust nozzle 10, Fig. 1, provided with a thrust vectoring control means comprising exhaust deflection members 16, each having an exhaust deflection surface 17, and each being provided with actuation means comprising a piston-rod 14 extending into a housing 13 to a double-acting piston 23, Fig. 3, which is powered by a bleed of the combustion gases flowing from a chamber 24 via a solenoid actuated valve 26. Alternatively, member 16 may be mounted through two pivot points 18 (Fig. 2, not shown), so that it is pivotable about an axis perpendicular to, but displaced from, the longitudinal axis of the nozzle 10. The combustion gases from the chamber 24 may instead be applied through a series of labyrinthine supply ports 30 (Fig. 4, not shown), to a chamber (31), and there be made to exert pressure on the exterior of a flexible membrane in the form of a collapsible bladder (32) whose interior is connected to the passage 25, displacement of gas or hydraulic fluid therein serving to power the piston 23. In an alternative embodiment, Fig. 6, four exhaust deflection members 47 with their corresponding actuation means are mounted interiorly of a ring 46. Their end-plates 49 are secured to the free ends 58 of piston-rods 59 extending from double-acting pistons 60 actuated by hydraulic fluid from a servo control system 63, 64 (Fig. 5, not shown). Movement of the piston-rods 59 causes proportional projection and retraction of the members 47 as before, or reciprocation thereof at frequencies of up to 40 c.p.s.