Accession Number:

AD0501370

Title:

PBPS Engine Development Program and System Design

Descriptive Note:

Final rept. 1 Apr 1967-31 Jan 1969

Corporate Author:

AEROJET-GENERAL CORP SACRAMENTO CA LIQUID ROCKET DIV

Personal Author(s):

Report Date:

1969-04-01

Pagination or Media Count:

265.0

Abstract:

The increased size and extended mission duty cycles of planned Post- Boost Propulsion Systems PBPS for Advanced ICBM applications identified the need for improvements in liquid propellant propulsion technology. Although liquid propellant propulsion systems have demonstrated an operational flexibility and performance capability, improvements in the inherent storability, maintainability, and reliability were desired for an optimum strategic weapon system. The PBPS Engine Development Program was initiated to develop a bipropellant N2O4 and MMH attitude control system ACS wherein integral fluidic controls are used to perform ACS propellant flow control, thereby controlling vehicle attitude with a minimum of moving parts. Developmental problems with the fluidic control elements resulted in the termination of the integral fluidic ACS development and the associated minimum ACS engine studies. The program was redirected to provide the development of a conventionally-controlled 75 lb thrust attitude control engine as well as the demonstration testing of PBPS pressurization and positive expulsion propellant tank subsystems. An Aerojet-General proprietary injector concept in conjunction with a bimetallic, conductively-cooled combustion chamber was used in the ACS engine developed. This engine was demonstrated in altitude performance and pulse testing. The monopropellant hot gas pressurization subsystem was used to demonstrate propellant expulsion both monomethylhydrazine and N2O4 from the full-size ring-stabilized expulsion propellant tanks

Subject Categories:

  • Liquid Propellant Rocket Engines
  • Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE