DERIVATIONS OF COEFFICIENTS RELATING ASCENT TRAJECTORY DISPERSIONS TO AGENA GUIDANCE AND PERFORMANCE VARIATIONS.

Abstract

Equations are derived which relate errors in vehicle performance parameters and guidance components to the trajectory variation at final-stage cutoff. Expressions are included for the propagation coefficients of the orbit parameters during the parking orbit. These coefficients relate errors in first-burn cutoff conditions to second-burn ignition conditions. A degree of generality is achieved by considering both a two-stage and a three-stage configuration. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1960
Accession Number
AD0613596

Entities

People

  • A. E. Mccaulou
  • J. M. Deerwester

Organizations

  • Lockheed Martin Missiles and Space

Tags

DTIC Thesaurus Topics

  • Ascent Trajectories
  • Coefficients
  • Dispersions
  • Equations
  • Guidance
  • Ignition
  • Orbits
  • Parking Orbits
  • Spacecraft Orbits
  • Trajectories

Readers

  • Calculus or Mathematical Analysis
  • Missile Defense Systems.
  • Space Exploration and Orbital Mechanics.

Technology Areas

  • Space
  • Space - Orbital Debris
  • Space - Spacecraft Maneuvers