package will provide rendezvous capability to the assembly point within + TBD NM altitude, + TBD° inclination and + TBD° longitude within TBD hours of insertion. The HLLV will insert the payload into a 80 km x 500 km orbit with an inclination equal to the launch site latitude. The OMS package on the payload will circularize at 500 km x 500 km. 2.2 Cargo Orbital Transfer Vehicle (COTV)1 Ground Rules a. The COTV may impose up to .001g1s on the payload in transferring a deployed or partially deployed or assembled SPS to geostationary orbit b. The COTV payloads may be suitable for either single point or multi-point application or thrust loads during orbital transfer. c. Degradation of exposed solar cells during transfer through the Van Allen belt is acceptable, and overall system cost optimization will determine the acceptable level of degradation. d. A power output of 4 GW from the lb payload will be considered available as an upper limit (for dependent OTV's). e. The COTV will provide no services to the payload. f. The COTV mission reliability shall be 0.97 or better. g. Only gaseous propellants will be considered for possible COTV use. h. Reuse of the COTV will be based solely on economics. Mission Requirements a. Launch Site - OTV's shall be launched from and return to the vicinity of the low Earth orbit staging point. b. Cargo OTV Capability - COTV's shall be capable of transporting, unmanned, SPS components and related cargo from the low Earth orbit launch position to the geostationary position as required to install up to seven SPS systems per year. The return capability to the staging point is (TBD). ^The requirements for COTV's will later be developed separately for COTV's suitable for stations assembled or partly assembled in LEO (COTV. ) and those suitable for the GEO assembly option (COTVq).
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