Accession Number:

AD0802590

Title:

SYSTEM EFFECTS ON PROPELLANT STORABILITY AND VEHICLE PERFORMANCE

Descriptive Note:

Final technical rept. 1 Mar 65-19 Aug 66,

Corporate Author:

DOUGLAS AIRCRAFT CO INC SANTA MONICA CA MISSILE AND SPACE SYSTEMS DIV

Personal Author(s):

Report Date:

1966-10-01

Pagination or Media Count:

406.0

Abstract:

The objective of this program was to investigate the tradeoff between propellant storability and vehicle performance for the propellant storage and feed subsystem of a hypothetical LF2LH2 space propulsion system. Detailed parametric analyses were conducted on such subsystem problem areas as booster- pump feed system utilization, feed line design, venting requirements and provisions, selection of thermal-control coatings, propellant utilization requirements, selection and design of insulation and tank supports, and pressurization system design. Each area was optimized for a spectrum of mission requirements and design ground rules. Design recommendations were derived on the basis of these results. A full-scale, non-flightweight test article was designed, fabircated, and tested to simulate the propellant storage and feed subsystem. This apparatus incorporated, wherever practical, the recommendations of the study effort. The simulator, which uses LH2 and LN2, will be tested in the Edwards Air Force Base Space Simulation Facility to obtain experimental data for correlating certain thermodynamic analytical models used in this study.

Subject Categories:

  • Liquid Propellant Rocket Engines
  • Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE