Figure 10.3.13 Ground Segment Configuration The tracking of the satellite could be done by orbit prediction, but the master station could in addition have an automatic beam locking function which assures rectenna pointing in the direction of the satellite. The satellite velocity is 7 km/s corresponding to a ground measured angular velocity of approximately 0.4 7sec. Because the rectenna must have a tracking function to absorb the incident power, beaming to the Antarctica was not found to be feasible. In fact, microwave beaming from a polar orbit is only efficient when the power density on the ground is sufficient to eliminate the need for focusing before rectification. The location of the receiving station should be at a high latitude in order to obtain maximum temporal resolution. 10.3.5 Scheduling The following can be thought of as a template for planning the space to Earth demonstration phase. This schedule is not dependent on the specific design or concept chosen and even does not restrict us to one example. For instance the entire schedule could represent the proposed 800 M USS project or this project could be a small section contained under the “Power generation and transmission research and development program” block. A space to Earth demonstration phase begins with the research and development program for power generation and transmission. A proposed starting date and duration is 01/01/1995, lasting 42 months. The actual start of Demo 2 begins on the 1st January 1997 starting with a concept development, lasting 18 months and followed by 18 months design phase. Schedule chart for Demo 2 is seen in Figure 10.3.14 and the task timeline chart in Figure 10.3.15. The actual development phase (phase C/D study) begins in mid 1999. It is divided into the three typical models: structural & thermal models (checks if the structure and thermal control is good, no flight equipment), engineering models (like real satellite, but with standard components), and protoflight models (real satellite with space qualified electronic components). Each of these models are divided into three phases. The first two phases run parallel and are the payload - power generation and transmission (P/L) and the rest of the spacecraft (platform) excluding the payload (P/F). The third phase is the assembly integration testing (S/L) and integrates these first two phases. Table 10.3.14 gives a detailed explanation of the schedule of the actual proposed development phase. The four months (July-October) of 1994 will be used for the transport and integration of the satellite. Actual launch is expected to be on the 1st November 2004. It is expected that the lifetime of the beaming experirtient be one year with evaluation of results running continuously.
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