MTech Space Mechanics syllabus for 2 Sem 2020 scheme 20MAE251

Module-1 Space Environment 0 hours

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.

Module-2 Basic Concepts and the General N-Body 0 hours

Basic Concepts and the General N-Body:

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, 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.

A d v e r t i s e m e n t
Module-3 Satellite Injection and Satellite Perturbations 0 hours

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.

Module-4 Interplanetary Trajectories 0 hours

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.

Module-5 Ballistic Missile Trajectories 0 hours

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 outcomes:

At the end of the course the student will be able to:

1. Apply the basic concepts of space mechanics and the general N-body.

2. Explain satellite injection and satellite orbit perturbations.

3. Distinguish between interplanetary and ballistic missile trajectories

 

Question paper pattern:

The SEE question paper will be set for 100 marks and the marks scored will be proportionately reduced to 60.

  • The question paper will have ten full questions carrying equal marks.
  • Each full question is for 20 marks.
  • There will be two full questions (with a maximum of four sub questions) from each module.
  • Each full question will have sub question covering all the topics under a module.
  • The students will have to answer five full questions, selecting one full question from each module.

 

Textbook/ Textbooks

1 Rocket Propulsion and Space Dynamics Cornelisse, J.W. W.H.Freeman&co 1984

2 Introduction to Space Dynamics Thomson, Dover Publications, Revised edition 2012

 

Reference Books

1 Elements of Astromechanics Vande Kamp, P., Pitman 1979

2 Space Flight Dynamics Willian E. Wiesel Create Space Independent Publishing Platform 3rd Edition 2010

3 Rocket Propulsion Elements George P. Sutton and Oscar Biblarz Wiley India 7 th edition,

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