Surface Corridor Requirements for Space Launches over the Black Sea

Article Preview

Abstract:

Romanian space project NERVA develops the small rocket launcher for injecting nanosatellites into a very LEO. The launching area security first requires establishing a safe launch corridor on the ground. The first candidate for the experiments with the orbital rocket prototype is the western coast of the Black Sea in Romania. Optimal flight considerations immediately show that the best launch azimuth is on west-east direction, which defines a launching corridor along the Black Sea with the similar orientation. Do to the dense population of the sea shore area and to the rather agglomerated condition on the Black Sea, serious concerns arise regarding the safety measures to be solved, before any space activity above the Black Sea should begin. The main challenge is the safe prediction of the impact point of the space launcher in every moment of the atmospheric ascent, in case of unavoidable failure of the propulsion system. This task is assumed and presented as developed within a recent research activity of the NERVA team.

You might also be interested in these eBooks

Info:

Periodical:

Pages:

799-804

Citation:

Online since:

June 2013

Export:

Price:

Permissions CCC:

Permissions PLS:

Сopyright:

© 2013 Trans Tech Publications Ltd. All Rights Reserved

Share:

Citation:

[1] "Launch Site Safety Assessment, Section 1.0 Eastern Range General Range Capabilities" (PDF). Research Triangle Institute, Center for Aerospace Technology (CAST), Florida Office. Federal Aviation Administration. March 1999.

Google Scholar

[2] Harvey, Brian. Space Exploration 2007. Springer. p.138

Google Scholar

[3] U. Sankar, The Economics of India's Space Programme, Oxford University Press, ISBN.13:978-0-19-568345-5, New Delhi, 2007.

Google Scholar

[4] Kamiya, Setsuko, "Japan a low-key player in space race", Japan Times, June 30, 2009, p.3.

Google Scholar

[5] "Chinese Crewed Capsule 1978". Encyclopedia Astronautica. http://www.astronautix.com/articles/chidoors.htm, Retrieved 2009-05-13.

Google Scholar

[6] China to Build Fourth Satellite Launching Center in Hainan , Staff Writer, Haikou (XNA) Feb 8, 2007.

Google Scholar

[7] Constantinescu, C. E., Rugescu, R. D., Ciochină, S., and Cacoveanu, R. (2010), First flight experiment with the NERVA-1 inertial platform, Proceedings of 2010 International Conference on Mechanical Engineering, Robotics and Aerospace ICMERA-2010, ISBN 978-1-4244-8867-4, IEEE Catalog Number CFP1057L-PRT, December 2-4, Bucharest, Romania, pp.312-316.

DOI: 10.4028/www.scientific.net/amm.325-326.990

Google Scholar

[8] Mayrhofer, M. & Sachs, G. (1997), Orbital stage abort trajectories after separation from carrier, Space Flight Dynamics, Proceedings of the 12th International Symposium held 2-6 June 1997 in Darmstadt, Germany, Edited by T.-D. Guyenne, ESA SP-403. Paris: Eurpoean Space Agency, p.463.

Google Scholar

[9] Mitchell, D. H. (ed., 1970), Flight Separation Mechanisms, NASA SP-8056, Langley Research Center, Hampton, VA 23365, Oct. 1970.

Google Scholar

[10] Bin Xu, Fuchun Sun, Daoxiang Gao, Shixing Wang (2010), Adaptive Neural Control based on HGO for Hypersonic Flight Vehicle without Backstepping, Paper 2010S4-7, ICMERA 2-4 December, Bucharest, Romania.

Google Scholar

[11] V. Pisacane' Fundametals of space systems, second edition, (2005)

Google Scholar

[12] Roshanian, J., and Talebi, M. (2008), Monte Carlo simulation of stage separation dynamics of a multistage launch vehicle, Applied Mathematics and Mechanics, 29 (11), pp.1411-1426.

DOI: 10.1007/s10483-008-1103-z

Google Scholar