AS3004 Orbital Mechanics Syllabus:
AS3004 Orbital Mechanics Syllabus – Anna University Regulation 2021
OBJECTIVES:
• To learn the concept of orbital mechanics to find the trajectory/orbit of a space vehicle or a satellite.
• To Determine perturbation of satellite orbits and its mathematical background.
• To explain the concepts of transfer of spacecraft from one orbit to another.
• To explain the trajectory of various spacecrafts.
• To learn the concept of orbital mechanics to free flight phase of ballistic missiles.
UNIT I INTRODUCTION
Celestial sphere, Ecliptic, Right ascension and Declination, Vernal equinox, Solar time and Sidereal time, Kepler’s laws of planetary motion, Keplerian Orbital elements.
UNIT II TWO-BODY PROBLEM AND ORBIT PERTURBATIONS
Two-body problem, Orbit equation, Orbital velocity and Orbital energy, Kepler’s equation and Time of flight, Orbit perturbations, Special and General Perturbation methods.
UNIT III ORBITAL MANEUVERS
Transfer, In-plane orbit changes, Hohmann transfer, Bi-elliptic transfer, Out-of-plane orbit changes, Delta-v requirement and propellant mass for maneuvers.
UNIT IV INTERPLANETARY AND LUNAR TRAJECTORIES
Sphere of Influence, Patched conic approximation with simplified example, Realistic interplanetary mission, Locating the planets, Design of departure and arrival trajectories, Gravity-assist maneuvers, Design of departure and arrival lunar trajectories.
UNIT V APPLICATION OF ORBITAL MECHANICS TO BALLISTIC MISSILES
General ballistic missile problem, Geometry of ballistic missile trajectory, Free flight range, Flightpath angle, Maximum range trajectory, Time of free flight, Effect of launching errors, Influence coefficients, Effect of earth rotation.
TOTAL: 45 PERIODS
OUTCOMES:
After successful completion of this course, the students will be able to
CO1: Apply the concepts of orbital mechanics to find the trajectory/orbit of a space vehicle or a satellite.
CO2: Discuss the perturbation of satellite orbits and its mathematical background.
CO3: Calculate the delta-v required for transferring a spacecraft from one orbit to another.
CO4: Design an approximate trajectory for interplanetary and lunar spacecraft.
CO5: Apply the concepts of orbital mechanics to free flight phase of ballistic missiles
REFERENCES
1. Charles D. Brown, ‘Elements of Spacecraft Design’, First Edition, AIAA Education Series, 2002.
2. Roger R.Bate, Donald D.Mueller, and Jerry E.White, ‘Fundamentals of Astrodynamics’, Dover Publications Inc., 1971.
3. Vladimir A. Chobotov, ‘Orbital Mechanics’, Third Edition, AIAA Education Series, 2002.
4. Howard D. Curtis, ‘Orbital Mechanics for Engineering Students’, Third Edition (Revised), Butterworth-Heinemann, 2013.
5. David A. Vallado and James Wertz (Ed.), ‘Fundamentals of Astrodynamics and Applications’, Fourth Edition, Microcosm Press, 2013.