Prof. Ram
Krishan Sharma
Karunya
University, Coimbatore, India
Email: ramkrishan@karunya.edu
Qualifications
Ph.D.,
University of Delhi, India
M.Sc.,
University of Delhi, India
Publications
(Selected)
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Perturbations of
Lagrangian points in the restricted three-body problem, Sharma, R. K. 1975,Indian
J Pure and Appl. Math, 6, 1099-1102.
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Periodic orbits
of first kind in the restricted three-body problem when the more massive
primary is an oblate spheroid,Sharma, R. K. 1976, Astronomy and Astrophysics,
50, 257-258.
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Stationary
solutions and their characteristic exponents in the restricted three-body
problem when the more massive primary is an oblate spheroid,Sharma, R. K. &
Subba Rao, P. V. 1976, Celestial Mechanics, 13, 137-149.
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A case of
commensurability induces by oblateness,Sharma, R. K. & Subba Rao,P. V. 1978,
Celestial Mechanics, 18, 185-194.
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The linear
stability of libration points of the photogravitational restricted three-body
problem when the smaller primary is an oblate spheroid,Sharma, R. K. 1987,Astrophysics
and Space Science, 135, 271-281.
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Analytical
approach using KS elements to short-term orbit predictions including J2,Sharma,
R. K. 1989,Celestial Mechanics and dynamical Astronomy, 46, 321-333.
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Periodic orbits
of third kind in the restricted three-body problem with oblateness, Sharma, R.
K. 1990,Astrophysicsand Space Science, 166, 211-218.
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Analytical
approach using KS elements to near-Earth orbit predictions including drag, Sharma,
R. K. 1991, Proc. Royal Soc. Lond., A 433, 121-130.
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. A third-order
theory for the effect of drag on Earth satellite orbits,Sharma, R. K. 1992,
Proc. Royal Soc. Lond., A 438, 467-475.
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Effect of
oblateness on the non-linearity of L4 in the restricted three-body problem,
Subba Rao P. V.&Sharma, R. K. 1997,Celestial Mechanics and dynamical
Astronomy,65, 291-312.
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Analytical
integration of KS element equations with J2 for short-term orbit predictions,Sharma,
R. K. 1997,Planetary and Space Science, 45, 1481-1486.
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Contraction of
satellite orbits using KS elements in an oblate diurnally varying atmosphere,Sharma,
R. K. 1997, 1997,Proc. Royal Soc. Lond., A 453, 2353-2368.
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Contraction of
high eccentricity satellite orbits using KS elements with air drag,Sharma, R.
K. 1998,Proc. Royal Soc. Lond., A 454, 1681-1689.
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Consideration of
lifetime limitation for spent stages in GTO, Sharma, R. K.,.Bandyopadhyay, P.
&Adimurthy, V. 2004,Advances in Space Research, 34, 1227-1232.
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Fourth-order
theories for orbit predictions for low-and high-eccentricity orbits in an
oblate atmosphere with scale height dependent on altitude,Sharma, R. K.&
Raj, M. X. J. 2009,Acta Astronautica, 65, 1336–1344.
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Optimal Reentry
Time Estimation of an Upper Stage from Geostationary Transfer Orbit,
Mutyalarao, M. & Sharma, R. K. 2010 Journal of Spacecraft and Rockets, 47,
686-690.
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Evolution of
periodic orbits in the Sun-Mars system,Dutt, P.&Sharma, R. K. 2011, Journal
of Guidance, Control, and Dynamics, 34,635-644.
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Effect of
Altitude, Right Ascension of Ascending Node and Inclination on Lifetime of
Circular Lunar Orbits, Gupta, S. &Sharma, R. K. 2011,International Journal
of Astronomy and Astrophysics, 1, 155-163.
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Mars
interplanetary trajectory design via Lagrangian points, Eapen, R. T.&Sharma,
R. K. 2014, Astrophysics and Space Science, 353, 65-71.
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Orbit theory
with lunar perturbation in terms of Kustaanheimo-Stiefel regular elements,
Sellamuthu, H.&Sharma, R. K. 2016, Journal of Guidance, Control, and
Dynamics (in press).