AS3502 Space Mechanics Syllabus:

AS3502 Space Mechanics Syllabus – Anna University Regulation 2021

OBJECTIVES:

To familiarize students with
• concepts of satellite injection and satellite perturbations
• trajectory computation
• interplanetary travel and
• flight of ballistic missiles
• fundamental concepts of orbital mechanics

UNIT I SPACE ENVIRONMENT

Peculiarities of space environment and its description– effect of space environment on materials of spacecraft structure and astronauts- manned space missions – effect on satellite life time

UNIT II BASIC CONCEPTS AND THE GENERAL N- BODY PROBLEM

The solar system – reference frames and coordinate systems – terminology related to the celestial sphere and its associated concepts – Kepler’s laws of planetary motion and proof of the laws – Newton’s universal law of gravitation – many body problem – Lagrange-Jacobi identity – circular restricted three body problem – libration points – general N-body problem – two body problem – relations between position and time.

UNIT III SATELLITE INJECTION AND SATELLITE PERTURBATIONS

General aspects of satellite injection – satellite orbit transfer – various cases – orbit deviations due to injection errors – special and general perturbations – Cowell’s method and Encke’s method – method of variations of orbital elements – general perturbations approach.

UNIT IV INTERPLANETARY TRAJECTORIES

Two-dimensional interplanetary trajectories – fast interplanetary trajectories – three dimensional interplanetary trajectories – launch of interplanetary spacecraft – trajectory estimation about the target planet – concept of sphere of influence – Lambert’s theorem

UNIT V BALLISTIC MISSILE TRAJECTORIES

Introduction to ballistic missile trajectories – boost phase – ballistic phase – trajectory geometry – optimal flights – time of flight – re-entry phase – position of impact point – influence coefficients.

TOTAL: 45 PERIODS

OUTCOMES:

• Apply understandings to perform satellite injection, satellite perturbations and trajectory control
• Apply orbital mechanics to control ballistic missile.
• Identify the trajectory/orbit of a space vehicle or a satellite in a suitable coordinate system.
• Solvethe delta-v required for transferring a spacecraft from one orbit to another.
• Make use of orbit perturbation analysis for satellite orbits.

TEXT BOOKS:

1. Cornelisse, J.W., “Rocket Propulsion and Space Dynamics”, J.W. Freeman & Co.,Ltd, London, 1982
2. Parker, E.R., “Materials for Missiles and Spacecraft”, Mc.Graw Hill Book Co. Inc., 1982.

REFERENCE:

1. Sutton, G.P., “Rocket Propulsion Elements”, Wiley, New York, 9th Ed., 2017.