JNTUK B.Tech Space Mechanics gives you detail information of Space Mechanics R13 syllabus It will be help full to understand you complete curriculum of the year.
Course Objective
This course is designed with an objective to provide a comprehensive overview of spaceflight mechanics, including both orbit and attitude dynamics. The two-body problem will be solved from first principles to allow the solution of the two-body position-time problem. This analysis will then be used to investigate various modes of orbit transfer. Attitude stabilization will be investigated for both spin- and 3-axis stabilized spacecraft. Finally, the various elements of the class will be brought together to illustrate the mission analysis and design process.
UNIT-I : Basic Concepts:The solar system-Reference frames and coordinate systems-The celestial sphere- The ecliptic-Motion of vernal equinox-Sidereal time-Solar Time-Standard Time-The earths atmosphere
The General N-Body Problem: The many body problem-Lagrange-Jacobi identity-The circular restricted three- body problem-Libration points- Relative Motion in the N-body problem.
UNIT-II : The Two-Body Problem: Equations of motion-General characteristics of motion for different orbits-Relations between position and time for different orbits-Expansions in elliptic motion-Orbital Elements-Relation between orbital elements and position and velocity.
UNIT-III : The Launching Of A Satellite: Launch vehicle ascent trajectories-General aspects of satellite injection-Dependence of orbital parameters on in-plane injection parameters-Launch vehicle performances- Orbit deviations due to injection errors
UNIT-IV : Perturbed Satellite Orbits: Special and general perturbations- Cowell’s Method-Encke’s method-Method of variations of orbital elements- General perturbations approach
UNIT-V : Interplanetary Trajectories: Two-dimensional interplanetary trajectories-Fast interplanetary trajectories-Three-dimensional interplanetary trajectories- Launch of interplanetary spacecraft-Trajectory about the target planet
UNIT-VI : Ballistic Missile Trajectories: The boost phase-The ballistic phase-Trajectory geometry-Optimal flights-Time of flight-Re-entry phase-The position of the impact point-Influence coefficients.
Low-Thrust Trajectories : Equations of Motion-Constant radial thrust acceleration-Constant tangential thrust (Characteristics of the motion, Linearization of the equations of motion- Performance analysis.
TEXT BOOKS
- ”Rocket Propulsion and Spaceflight Dynamics”, J.W.Cornelisse, H.F.R. Schoyer, and K.F. Wakker, Pitman, 1979
- ”Spaceflight Dynamics”, William E.Wiesel, McGraw-Hill, 1997
REFERENCE BOOKS
- Spacecraft Mission Design”, Charles D.Brown, AIAA Education Series, Published by AIAA, 1998
- “Orbital Mechanics”, Vladimir A. Chobotov, AIAA Education Series, AIAA Education Series, Published by AIAA, 2002
- ”Fundamentals of Astrodynamics and Applications”, David.A. Vellado, Microcosm and Kluwer, 2001
Course Outcomes
Upon completion of the module the student is expected to be able to
- An understanding of the methods employed in spaceflight mechanics.
- The ability to solve the two-body problem and two-body orbit transfer problems.
- The ability to analyse the dynamics and control of spin- and 3-axis stabilised spacecraft.
- An appreciation of the importance of spaceflight mechanics in space systems engineering.
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