Accession Number:

AD0261072

Title:

CRYOPUMPING ROCKET EXHAUST PRODUCTS AT HIGH THROUGH PUTS AND LOW PRESSURE

Descriptive Note:

Corporate Author:

GENERAL DYNAMICS/CONVAIR SAN DIEGO CALIF

Personal Author(s):

Report Date:

1960-12-01

Pagination or Media Count:

1.0

Abstract:

Preliminary analyses are presented for the de ign of a cryopumping system to freeze out large mass flow rates of rocket exhaust products. The controlling design factors, results of preliminary analysis, and test data to show feasibility, are included. This investigation was initiated to support the rocket exhaust plume radiation studied cond cted at Convair. The aim was to remove the products of combustion of a 100 lb. thrust engine burning JP-4 and gaseous o ygen within a 12 foot diameter tank 2 feet in length. The desired background pressure surrounding the nozzle was 11000 mm of Hg. The series of measurements being taken requi ed rocket operation of a period up to 3 minutes. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE