Sepehr IRISLV-X Booster Family
© C. P. Vick 2013 All Rights Reserved )
Senior Technical Analyst, Globalsecurity.org
Nov. 7-26 through12-7, 2013
Rev. 3
Disclaimer
The opinions and evaluations stated here in are only the authors and cannot be construed to reflect those of any Government agency, company, institute or association. It is based on public information, circumstantial evidence, informed speculation, declassified U.S. intelligence community documents, official Iranian and North Korean government documents and histories, oral histories, interviews and reverse engineering analysis. As with all data regarding the Iranian and North Korean strategic space and ballistic missile programs, this analysis is subject to revision--and represents a work in progress.
IRISLV-X- , Sepehr Space Booster
This is an "estimate" of the approximate required size Iranian space booster Sepehr to accomplish Iran's crewed orbital flight as well as GTO orbits COMSAT launches
Beyond the sub-orbital crewed flight application of the Simorgh-3 booster Iranian crewed orbital flight aspirations will require a far larger more powerful booster Sepehr, IRISLV-X-? The storable highly toxic corrosive liquid propellant RISLV-X- , Sepehr space booster is in the early stages of concept design development along with the published crewed spacecraft design studies. That new booster if developed is probably 5-7 years down the road before operational flights begin. This class booster will be required to facilitate certain unmanned satellite and manned orbital missions envisioned by Iran. Its planned introduction is expected in the 2016-2020 five year plan of Iran space program.
It is believed that the Sepehr will utilizes throughout a fuel of Unsymmetrical Dimethyl hydrazine (UDMH) while its oxidizer is a derivation of (73% Inhibited Red Fuming nitric Acid (IRFNA) & 27% N204 = AK-27S) in all of its main stages. A final BUS stage may utilize all liquid or solid and liquid propulsion. Its performance is expected to be in excess of 300 metric tons thrust utilizing six 50 metric ton thrust engines with a separate first and second stage set of four vernier engines and measure perhaps some 40 meters tall and 3.35 meters in diameter. The low earth orbit crewed spacecraft is believed to be in the estimated 5,650 kilogram range carrying at least a two person crew based on Iranian early design study releases.
