JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD

UNIT - I

Basic Concepts: The solar system, comets and meteors, Kepler’s laws and Newton’s law of gravitation, concept of celestial sphere, vernal equinox, ecliptic. Coordinate systems- ECI system, geographic coordinate system, azimuth-elevation coordinate system, ecliptic system, Time systems- sidereal time, mean solar time, Julian date, universal time, ephemeris time.

UNIT - II

Two-Body and Restricted Three Body Problems: N-body problem, two-body problem- simplifying assumptions, Equations of relative motion, Constants of the motion- conservation of angular momentum, Trajectory equation, elliptical orbit- geometry of the ellipse, period of an elliptical orbit, circular orbit, parabolic orbit, hyperbolic orbit. Geometry of the hyperbola, hyperbolic excess speed, Orbital elements. Introduction, equations of motion, Lagrangian points, stability of the Lagrangian points, Jacobi’s integral, accessible regions.

UNIT - III

Basic Orbital Manoeuvres and Orbit Perturbations: Low altitude earth orbits- effect of orbital altitude on satellite life times, direct ascent to orbit, perturbations of low earth orbits due to the oblate shape of the Earth. High altitude earth orbits- the synchronous satellite, launching a high altitude satellite. In-plane orbit changes- adjustment of perigee and apogee height, Hohmann transfer, general coplanar transfer between circular orbits, Out-of plane orbit changes-simple plane change.General overview of orbit perturbations, Earth gravity harmonics, lunisolar gravitational attractions, solar radiation pressure effects, atmospheric drag effects, tidal friction effects and mutual gravitational attraction, earth’s oblateness (J2) effects, critical inclination. Sun-synchronous orbits, J3 effects and frozen orbits, Earth’s triaxiality effects and east-west station keeping.

UNIT - IV

Ballistic Missile Trajectories: The general ballistic missile problem- geometry of the trajectory, free flight range equations, flight path angle equation, maximum range trajectory, time of free flight. Effect of launching errors on range- effect of lateral displacement of the burnout point, cross range error due to incorrect launch azimuth, effect of down range displacement of the burnout point, errors in burn-out flight-path angle, down range errors caused by incorrect burnout height and in correct speed at burnout. The effect of earth rotation- compensating for the initial velocity of missile due to earth rotation, compensating for movement of the target due to earth rotation.

R16 B.TECH AERONAUTICAL ENGG.

UNIT - V

Interplanetary Trajectories: Patched-conic approximation-heliocentric transfer orbit, phase angle at departure, escape from the earth’s sphere of influence, arrival at the target planet, effective collision cross-section. Locating the planets- launch opportunity, synodic period, trajectory type and class, ephemeris calculations, Non-coplanar interplanetary trajectories, Gravity-assist manoeuvre. Fast interplanetary trajectories.

TEXT BOOKS:

• 1. Bate, R.R., Mueller, D.D. and White, J.E., Fundamentals of Astrodynamics, Dover Publications Inc., New York, 1971.

REFERENCES:

• 1. Wiesel, W.E., Spaceflight Dynamics, 3rd edn., McGraw-Hill, New York, 2010.
• 2. Hale, F.J., Introduction to Space Flight, Prentice Hall, 1994.
• 3. Sellers, J.J., Understanding Space: An Introduction to Astronautics, 2nd edn., McGraw-Hill, 2004
• 4. Chobotov, V.A., ed, Orbital Mechanics, 3rd edn., AIAA Education Series, 2002.
• 5. David A. Vallado, Fundamentals of Astrodynamics and Applications,4th edition, Microcosm Press, 2013
• 6. Charles D. Brown, ”Spacecraft Mission Design”, AIAA Education Series, 1998
• 7. Cornelisse, J.W., Schoyer H.F.R. and Wakker, K.F., Rocket Propulsion and Space- flight Dynamics, Pitman, 1979. R16 B.TECH AERONAUTICAL ENGG.