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Baseline Reference Mission [BRM]
MISSION DESCRIPTIONS

Mission 1

Mission 1 is a payload delivery mission to a 150 n.m. circular orbit. The mission will be launched due east and requires a payload capability of 65,000-lb. The purpose of this mission is either the placement in orbit of a 65,000-lb satellite or the placement in orbit of a 65,000-lb satellite and retrieval from orbit of a 32,000-lb satellite. The Orbiter-vehicle on-orbit translational delta V requirements in excess of a 50 X 100 n. mi. reference orbit are 650 ft/sec from the orbital maneuvering subsystem (OMS) and 100 ft/sec from the RCS. The injected margin is based on an SRB mean bulk temperature at 60^F and a first stage maximum dynamic pressure of 680 psf. Other ground rules are described in JCS-07700, Space Shuttle Flight and Ground System Specification, Volume X, Revision B, Appendix 10.12.

Mission 3A

Mission 3A is a payload delivery mission to an orbit at 104^ inclination and return to the launch site. The boost phase shall result in an insertion into an orbit with a minimum apogee of 100 n. mi., as measured above the earth's equatorial radius. The Orbiter-vehicle on-orbit translation delta V requirements is in excess of a 50 X 100 n. mi. reference orbit are 250 ft/sec from the OMS and 100 ft/sec from the RCS. The ascent payload requirement is 32,000 lb. For mission performance and consumables analysis, a return payload of 2500 lb will be assumed (the 2500 lb is included in the 32,000 lb ascent payload weight). The injected margin is based on an SRB mean bulk temperature of 52^F and a first stage maximum dynamic pressure of 650 psf. Other ground rules are described in JSC-07700, Space Shuttle Flight and Ground System Specification, Volume X, Revision B, Appendix 10.12.

Mission 4

Mission 4 is a payload delivery and retrieval mission of a modular spacecraft weighing 32,000 lb at lift-off. The mission will deploy a spacecraft weighing 29,000 pounds in a 150 n. mi. circular orbit at 98 degrees inclination within two revolutions after lift-off. A passively cooperative, stabilized spacecraft, weighing 22,500 pounds, will be retrieved from a 150 n. mi. circular orbit and returned to VAFB. The mission length, including contingencies, will be 7 days. For mission performance and consumables analysis, a cradle weight of 2500 lb will be assumed to be included in the ascent payload weight, but must be added to the retrieved payload weight. The RCS will be loaded full and the minimum on-orbit translation, delta-velocity from the OMS, including post-MECO insertion burn, is a total of 1050.5 ft/sec. The total injected margin is based on a first stage maximum dynamic pressure of 650 psf and includes 1730 lb for the SRB mean bulk temperature of 52^F. Standard provisions shall be included for personnel and stowed equipment. contingency EVA capability shall be provided.

Mission 1Y, 4Y

The BRM-1Y and BRM-4Y missions are assumed to have the same payload requirements as BRM-1 and BRM-4, respectively, The missions are planned for one day with two crewmen. It is assumed that the non-propulsive consumables, personnel and RCS propellants are loaded in accordance with BRM 3A. The OMS propellants are based on delta-velocity required for orbit insertion, circularization and deorbit. for BRM-1Y, the delta-velocity requirement is 690 ft/sec and for BRM-4Y, the delta-velocity is 1000 ft/sec. The difference is attributable to MECO velocity reduction at WTR for ET disposal.