Accession Number : ADD010965

Title :   Constant Thrust Hybrid Rocket Motor.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : Holzman,A L

Report Date : 10 Jan 1984

Pagination or Media Count : 5

Abstract : This patent discloses a constant thrust hybrid rocker motor having a valve assembly therein which uses a fixed diameter orifice in combination with a valve having a variable sized opening therein in order to provide a regulated flow of oxidizer to the combustion chamber of the rocket motor. By selecting the size of the fixed diameter orifice such that it is slightly less than required to yield oxidizer flow at highest density oxidizer conditions (lowest temperature) and selecting the size of the combination of the fixed orifice and the open position of the variable opening such that it is slightly greater then required at lowest density oxidizer conditions (highest temperature), the operation of the rocket motor can be reliably maintained over a wide temperature range and without experiencing wide pressure variations by regulating the size of the variable opening.

Descriptors :   *Patents, *Bypass valves, *Thrust control, Pressure regulators, Rocket igniters, Combustion chambers, Hybrid rocket engines, Solenoid valves, Feedback, Oxidizers, Gas flow, Plexiglas, Propellant grains, Transducers, Combustion stability, Flow rate, Thrust, Constants, Orifices, Sizes(Dimensions), Variable pressure, Temperature, Range(Extremes)

Subject Categories : Pumps, Filters, Pipes, Tubing, Fittings & Vlvs
      Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE