Page 210 - Intro to Space Sciences Spacecraft Applications

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Spacecraft Systems
Kaplan, M., Modern Spacecraft Dynamics and Control. New York: John
Wiley & Sons, 1976.

1. A geostationary communications satellite requires 1,OOO watts of power
to serve its payload and spacecraft bus subsystems. Calculate the number
of SSF Silicon solar cells required for a 10-year design life for a spin-
stabilized spacecraft. Compare this result to a 3-axis stabilized design.
2. Estimate the power subsystem mass for each of the spacecraft designs
in Exercise 1 above.
3. The on-orbit mass of a satellite is 1,000 kg. The satellite begins life in
a 66" inclination, 500 km altitude parking orbit achieved by the launch
vehicle. Calculate the mass of propellant required to place the satellite
into its final orbit of 99" inclination and 1,000 km altitude using bipro-
pellant 350.
4. A satellite with a ballistic cross-section of 4 m2 is in an 800 km altitude,
108" inclination orbit where it is expected to perform for 5 years. Cal-
culate the fuel mass required using monopropellant 220. Compare this
result to the case in which the satellite's orbital altitude is 300 km.