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, ap- plication of perturbations – Orbit Maneuvers: Hohmann transfer, inclination change maneuvers, combined maneuvers, bi-elliptic maneuvers – Lunar/Interplanetary Trajectories: sphere of influence, methods of trajectory design, restricted three body problem, Lagrangian points – Rigid Body Dy- namics: attitude control of spinning and non-spinning spacecrafts.

Same as Reference

1. Howard, D. C., Orbital Mechanics for Engineering Students, 2nd ed., Elsevier (2004).

2. Chobotov, V. A., Orbital Mechanics, 3rd ed., AIAA (2002).

3. Weisel, W. E., Spaceflight Dynamics, 3rd ed., McGraw-Hill (2010).

4. Brown, C. D., Spacecraft Mission Design, 2nd ed., AIAA (1998).

5. Escobal, P. R., Methods of Orbit Determination, Krieger Pub. Co. (1976).

6. Tewari, A., Atmospheric and Spaceflight 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.