Syllabus
Dynamics of Particles: reference frames and rotations – energy, angular momentum.
Two Body Motion: equations of motion – Kepler laws – solution to two-body problem – conics and relations – vis-viva equation – Kepler equation – orbital elements – orbit determination – Lambert problem – satellite tracking – different methods of solution to Lambert problem.
Non-Keplerian Motion: perturbing acceleration – earth aspherical potential – oblateness – third body effects – atmospheric drag effects – application of perturbations.
Orbit Maneuvers: Hohmann transfer – inclination change maneuvers, combined maneuvers, bielliptic maneuvers.
Lunar/ Interplanetary Trajectories: sphere of influence – methods of trajectory design – restricted three body problem – Lagrangian points.
Text Books
1. Curtis, H. D., Orbital Mechanics for Engineering Students, 2nd ed., Elsevier (2009).
2. Chobotov, V. A., Orbital Mechanics, 3rd ed., AIAA Edu. Series (2002).
References
1. Wiesel, W. E., Spaceflight Dynamics, 2nd ed., McGraw Hill (1996).
2. Brown, C. D., Spacecraft Mission Design, 2nd ed., AIAA Edu. Series (1998).
3. Escobal, P. R., Methods of Orbit Determination, 2nd ed., Krieger Pub. Co. (1976).
4. Tewari, A., Atmospheric and Space Flight Dynamics: Modeling and Simulation with MATLAB and Simulink, Birkhauser (2007).
Course Outcomes (COs):
CO1: Apply the basic conservation laws and concepts of orbital mechanics for problem solving.
CO2: Design, evaluate and select required orbits for spacecrafts around earth.
CO3: Evaluate and determine suitable orbital transfers needed for space mission design.