III. REFERENCE SYSTEM DESCRIPTION The purpose of this section is to describe the SPS Reference System which has evolved primarily from system definition studies conducted by Boeing Aerospace Company and Rockwell International. The system concept presented herein is the result of numerous trade-off studies and engineering analyses, which are summarized in Appendix A of this report. It should be emphasized that the system described herein is preliminary and incomplete in detail in some areas. Evaluation by both DOEi and NASA will continue to progress with the Reference System evolving and maturing as further details are developed. A. Guidelines and Assumptions The guidelines and assumptions utilized in the Reference System definition are listed below. o SPS operational date is year 2000. o Rate of implementation is two 5 GW systems per year; 300 GW total capacity for costing purposes. o All ground rectennas sized for 5 GW. o SPS operation in geosynchronous orbit. o Systems operating frequency is 2.45 GHz. 2 o Microwave power density not to exceed 23 and 1 mW/cm at center and edge, respectively, of rectenna. o All materials derived from earth resources. o System life is 30 years with no salvage value or disposition costs, o Zero launch rate failure assumed. o Technology availability date is 1990. o No cost margins will be used, o Cost estimates in 1977 dollars, o System weight growth factor (25%) to be reflected in costs. B. System Overview The Reference System is sized for 5 GW DC power output into a conventional power grid. The satellite has one end-mounted antenna which transmits
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