AKTU Space Flight Mechanics (BAE052) Syllabus PDF – B.Tech 3rd Year
Space Flight Mechanics BAE052
All syllabus, notes, question bank & PYQ for this subject
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- Semester 5
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Syllabus — Space Flight Mechanics
Download PDFBAE052 · 3 credits · L-T-P 3-0-0
| The students will be able to | Blooms Taxonomy | |
| CO-1 | Understand the Familiarize the basic concepts of orbital mechanics and its description– effect of space environment on materials of spacecraft structure. | K2 |
| CO-2 | Understand the different terminologies related to space flight. The Newton’s universal law of gravitation - the many body problems. | K2 |
| CO-3 | Apply the concept of the different laws of planetary motion and the different types of satellites and missile systems. | K3 |
| CO-4 | Apply the concept of the different phases of satellite and missile launching and their trajectory and the various techniques of satellite injection and further maneuvering. | K3 |
| CO-5 | Apply the concept of the natural means to navigate accurately to the destination and analyze the chart reading and problem occurring on dead reckoning. | K3 |
UNIT-I ( 8 Hours)
Basic Concepts Peculiarities of space environment and its description– effect of space environment on materials of spacecraft structure and astronauts- manned space missions – effect on satellite life time. The solar system – reference frames and coordinate systems – terminology related to the celestial sphere and its associated concepts – Kepler’s laws of planetary motion and proofs of the laws –Newton’s universal law of gravitation - the many body problems, the celestial Sphere.
UNIT-II ( 9 Hours)
The General N-Body Problem The Ecliptic Motion of Vernal Equinox – Sidereal Time – Solar Time -Standard Time – The Earth’s Atmosphere. Study the basic concepts of orbital Mechanics with particular emphasis on interplanetary trajectories. The many body Problem – Lagrange, Jacobian identity The Circular Restricted Three Body Problem – Libration Points – Relative Motion in the N-body Problem – Two – Body Problem – Satellite Orbits – Relations Between Position and Time – Orbital Elements.
UNIT-III (8 Hours)
Satellite Injection and Satellite Orbit Perturbations General Aspects of satellite Injections, Satellite Orbit Transfer, Various Cases – Orbit Deviations Due to Injection – Errors – Special and General Perturbations – Cowbell’s Method- Neck’s Method - Method of vibrations of Orbital Elements- General Perturbations Approach.
UNIT-IV (8 Hours)
Interplanetary Trajectories Two Dimensional Interplanetary Trajectories – Fast Interplanetary Trajectories – Three Dimensional Interplanetary Trajectories – 3-Dimensional Interplanetary Trajectories – Launch if Interplanetary Spacecraft – Trajectory estimation about the Target Planet, Concept of the sphere of influence, Lambert’s theorem.
UNIT-V (8 Hours)
Ballistic Missile Trajectories and Materials The Boost Phase-The Ballistic Phase – Trajectory Geometry- Optimal Flights – Time of Flight – Re-entry Phase – The Position of the Impact Point – Influence Coefficients. Space Environment - Peculiarities - Effect of Space Environment, the Selection of Spacecraft Material.
Reference Books
- Cornelisse, J.W. “Rocket Propulsion and Space Dynamic”, W.H. Freeman & Co., 1984.
- Sutton, G.P., “Rocket Propulsion Elements”, John Wiley, 1993.
- Parker E.R., “Material for Missiles and Spacecraft”, McGraw – Hill Book Co.
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