Accession Number:

ADD012626

Title:

Gas Generator Fuel Flow Throttle Control System.

Descriptive Note:

Patent,

Corporate Author:

DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Report Date:

1986-10-21

Pagination or Media Count:

9.0

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.

Subject Categories:

  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE