ON THE OPTIMIZATION OF TWO-STAGE ROCKETS,

Abstract

Equations useful in design studies are derived for determining the optimum weight distribution for two-stage tandem rockets for the case of different structural factors and propellant specific impulses in each stage. Minimization of gross weight for a given required burnout velocity and payload is the criterion of optimization used. For illustrative purposes an example is included in which the optimum distribution is found for a hypothetical chemically-boosted atomic rocket. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jan 29, 1957
Accession Number
AD0605918

Entities

People

  • M. Goldsmith

Organizations

  • RAND Corporation

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Energetic Materials
  • Equations
  • Materials
  • Mathematics
  • Optimization
  • Propellants
  • Specific Impulse

Fields of Study

  • Physics

Readers

  • Regression Analysis.
  • Rocket Propulsion.