c. Orbital Parameters - COTV missions shall be between the low Earth orbit staging point (positions TBD) and the geostationary orbit longitudes of the power stations (positions TBD). d. Trip Time - COTV trip time shall be a maximum of 180 days and a minimum as required by an acceleration of O.OOlg's (approx, seven days). Performance Requirements a. Payload Requirements - The COTV shall be capable of transporting from the low Earth orbit staging point to the geostationary location a SPS payload weighing (TBD) tons. For dependent systems, the payload shall provide up to 4 GW of electrical power at (TBD) volts while illuminated by the sun. The time of flight and trajectory for a photovoltaic system shall be consistent with a solar cell degradation of not more than (TBD) % of the total array. The payload will be solar oriented for dependent vehicles and there will be no payload attitude constraint for passive payloads. b. Guidance and Navigation Accuracies - The COTV shall be capable of guidance and navigation accuracy consistent with placing its payload at the geostationary point within (TBD). c. Orbital Maneuvering Capability - The COTV shall have the capability of providing an unscheduled longitude shift of TBD degrees within TBD days and an inclination change of TBD degrees within TBD days after arrival at the initial targeted destination. d. Structural Requirements - The COTV structure shall be compatible with the launch loads associated with the HLLV and/or Shuttle e. Energy Requirements - The COTV shall provide any energy required above that supplied by the payload to meet the flight duration and trajectory requirements. 2.3 Personnel and High Priority Cargo Launch Vehicle (PLV) Ground Rules a. The Personnel and High Priority Cargo Launch Vehicle (PLV) shall be derived from the STS in so far as feasible. Mission Requirements a. Launch Site - The PLV launch site shall be the same latitude as that for the HLLV. b. Abort Capability - Full abort capability, including pad abort, shall be provided.
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