Space Mechanics Aero 6th Sem Syllabus for BE 2017 Regulation Anna Univ (Professional Elective I) detail syllabus for Aeronautical Engineering (Aero), 2017 regulation is collected from the Anna Univ official website and presented for students of Anna University. The details of the course are: course code (AE8001), Category (PE), Contact Periods/week (3), Teaching hours/week (3), Practical Hours/week (0). The total course credits are given in combined syllabus.
For all other aero 6th sem syllabus for be 2017 regulation anna univ you can visit Aero 6th Sem syllabus for BE 2017 regulation Anna Univ Subjects. For all other Professional Elective I subjects do refer to Professional Elective I. The detail syllabus for space mechanics is as follows.
Course Objective:
- To introduce concepts of satellite injection and satellite perturbations, trajectory computation for interplanetary travel and flight of ballistic missiles based on the fundamental concepts of orbital mechanics.
Unit I
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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 – Keplers laws of planetary motion and proof of the laws -Newtons universal law of gravitation – the many body problem – Lagrange-Jacobi identity – the circular restricted three body problem – libration points – the 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 – Cowells method and Enckes method -method of variations of orbital elements – general perturbations approach.
Unit IV
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Unit V
Ballistic Missile Trajectories
Introduction to ballistic missile trajectories – boost phase – the ballistic phase – trajectory geometry – optimal flights – time of flight – re-entry phase – the position of impact point – influence coefficients.
Course Outcome:
- Ability to perform satellite injection, satellite perturbations and trajectory control
- Apply orbital mechanics to control ballistic missile.
- Estimate the trajectory/orbit of a space vehicle or a satellite in a suitable coordinate system.
- Calculate the delta-v required for transferring a spacecraft from one orbit to another.
- Perform orbit perturbation analysis for satellite orbits.
Text Books:
- Cornelisse, J.W., Rocket Propulsion and Space Dynamics, J.W. Freeman and Co.,Ltd, London, 1982
- Parker, E.R., Materials for Missiles and Spacecraft, Mc.Graw Hill Book Co. Inc., 1982.
References:
- Sutton, G.P., Rocket Propulsion Elements, John Wiley and Sons Inc., New York, 5th Edition, 1993.
For detail syllabus of all other subjects of BE Aero, 2017 regulation do visit Aero 6th Sem syllabus for 2017 Regulation.
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