THE EFFECT OF DISPERSION IN TRAJECTORY PARAMETERS ON A NOMINAL MARTLET IV TYPE ORBIT

Abstract

The orbit insertion trajectory for a Martlet 4 three stage gun- boosted rocket can be divided into four phases: gun launch and first glide, first stage burning, second stage burning, second glide, and third state burning. Each phase is defined by a number of parameters which define a trajectory. The characteristics of a Martlet 4 trajectory are the large initial velocity and precise launch angle provided by the gun boost. A total of eighteen parameters can be identified with their associated probable errors. The influence of each individual error on a nominal trajectory leading to a 400 nautical mile orbit is studied. The orbit is found to be most sensitive to muzzle velocity, propellant specific impulse, fuel weight, elevation angle during motor burns, and payload weight. The assumed probable errors in each of these parameters are not likely to prevent a long time orbit.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1967
Accession Number
AD0676877

Entities

People

  • B. A. Aikenhead
  • F. D. Galiana
  • M. C. Delfour

Organizations

  • McGill University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Altitude
  • Attitude Control Systems
  • Burning Rate
  • Circular Orbits
  • Computer Programming
  • Computer Programs
  • Control Systems
  • Elevation
  • Gun Muzzles
  • Muzzle Velocity
  • Nautical
  • Orbits
  • Plastic Explosives
  • Propellants
  • Rocket Engines
  • Specific Impulse
  • Trajectories

Fields of Study

  • Physics

Readers

  • Astronomy and Astrophysics.
  • Rocket Propulsion.
  • ballistics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Orbital Debris