Accession Number : ADD012626

Title :   Gas Generator Fuel Flow Throttle Control System.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : Miller,William H ; McClendon,Samuel E ; Kolodziej,Raymond J ; Brand,Donald L

Report Date : 21 Oct 1986

Pagination or Media Count : 9

Abstract : A gas generator fuel flow throttle control system provides a fuel rich gas to a propellant grain of a small diameter rocket. An adaptive iterative gain technique allows the throttle to closely follow a commanded fuel flow rate as required by a missile processor. Keywords: Air to air missiles; Thrust control; Thrust meters; Combustion chamber gases; Solid rocket propulsion; Adaptive control system.

Descriptors :   *ADAPTIVE CONTROL SYSTEMS, *PATENTS, *GAS GENERATING SYSTEMS, *THROTTLING, ADAPTIVE SYSTEMS, AIR TO AIR MISSILES, COMBUSTION CHAMBER GASES, DIAMETERS, FLOW RATE, FUELS, GAIN, GUIDED MISSILES, ITERATIONS, PROCESSING EQUIPMENT, ROCKETS, SOLIDS, THRUST CONTROL, THRUST METERS, SOLID PROPELLANT ROCKET ENGINES, ROCKET PROPELLANT GRAINS

Subject Categories : Solid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE