CRYOPUMPING ROCKET EXHAUST PRODUCTS AT HIGH THROUGH PUTS AND LOW PRESSURE

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 1/1000 mm of Hg. The series of measurements being taken requi ed rocket operation of a period up to 3 minutes. (Author)

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1960
Accession Number
AD0261072

Entities

People

  • J.w. Anderson
  • R.o. Barkdoll

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Combustion
  • Combustion Products
  • Cryopumping
  • Diameters
  • Exhaust Plumes
  • Flow
  • Flow Rate
  • Mass
  • Mass Flow
  • Measurement
  • Physical Properties
  • Plumes
  • Radiation
  • Rocket Exhaust

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Fluid Dynamics.
  • Snow Cover Descriptors for Reptiles and Their Illustrations.