Advanced Maneuvering Propulsion System (Lockheed Propellant Feed System Design). Volume II -- Propulsion Stage System Design.

Abstract

This volume provides the details of the selected propellant feed system design. The recommended configuration, consisting of a 1.41 ellipsoidal oxidizer tank, a 1.41 ellipsoidal fuel tank with a short cylindrical section and a conical/cylindrical shell has a mass fraction of 0.854, a dry weight of 2028 lb and a delta V capability of 20,197 to 21,765 ft/sec (with a 2000 lb payload) which varied over this range depending on the duty cycle and thrust level used. With prior knowledge of the duty cycle to be performed, i.e. if the mission is known after achieving orbit, the delta V capability rises to 22,800 ft/sec with the same payload weight. Extended mission capability to 180 days is also presented. A summary of the design, assembly plans, performance data and reliability data are given followed by design details, structural analyses and manufacturing plans for each selected vehicle subsystem.

Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1970
Accession Number
AD0511037

Entities

Organizations

  • Rocketdyne

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Assembly
  • Cooperation
  • Fuel Tanks
  • Manufacturing
  • Mass Production
  • Payload
  • Propellants
  • Propulsion Systems
  • Reliability
  • Structural Analysis

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Missile Defense Systems.
  • Rocket Propulsion.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Satellites