Accession Number : ADD004570

Title :   Reverse Flow Reaction Control System.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE ARMY WASHINGTON D C

Personal Author(s) : Fink,Robert H

Report Date : 18 Jan 1977

Pagination or Media Count : 3

Abstract : A control system for providing directional control to a missile during boost phase operation. The kinetic energy of the propellant exhaust gases is utilized to pump a vacuum in an annulus located around the rocket nozzle. To provide a reaction force to guide the missile, a closure is removed from one of several reaction nozzles located around the periphery of the aft end of the rocket and in communication with the vacuum chamber and the atmosphere. A thrust is generated by the air flowing through the reaction nozzle, into the vacuum chamber responsive to opening predetermined reaction nozzles. (Author)

Descriptors :   *Patents, *Reaction control systems, *Guided missile components, Nozzle gas flow, Rocket nozzles, Rocket propellants, Boost phase, Directional, Kinetic energy, Canted nozzles, Vacuum chambers, Exhaust gases, Torque, Control jets, Jet flow

Subject Categories : Guided Missiles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE