An Approximate Solution for Rocket Flight with Linear-Tangent Thrust Attitude Control

Abstract

This note presents an approximate solution to the equations of motion written with linear-tangent thrust attitude control. The usefullness of this solution is evaluated by comparison with accurate numerical integration. This comparison shows that the solution gives accuracies sufficient for preliminary calculations for satellite boost vehicles and has a four speed advantage over numerical integration of the same accuracy level.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1959
Accession Number
ADB189157

Entities

People

  • John S. Mackay

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Accuracy
  • Aerodynamic Forces
  • Altitude
  • Artificial Satellites
  • Circular Orbits
  • Coordinate Systems
  • Differential Equations
  • Equations
  • Equations Of Motion
  • Errors
  • Low Altitude
  • Numerical Integration
  • Orbits
  • Specific Impulse
  • Thrust
  • Trajectories
  • Vehicles

Readers

  • Calculus or Mathematical Analysis
  • Robotics and Automation.

Technology Areas

  • Space
  • Space - Spacecraft Maneuvers