Please provide annotated answer for 9a and 9b. Thank you! A spacecraft is powere

Question

Please provide annotated answer for 9a and 9b. Thank you! A spacecraft is powered by a solar panel array which has a total area A of 9.25 m2. The panels have an efficiency of 30%. What is the power available from the panels at Earth's distance from the Sun? Assume the luminosity of the Sun L Sun = 3.839 times 1026 W, and the radius of Earth's orbit (1 Astronomical Unit, AU ) REO = 1.50 times 1011m. Planet Saturn orbits the sun at 9.5 AU distance. What power will the same panels deliver in the vicinity of Saturn? Given this, explain why solar panels are not used for spacecraft sent to Saturn:

Explanation / Answer

a)

Intensity at earth , I = Power/(4*pi*d^2)

I = 3.839 * 10^26/(4 *pi*(1.50*10^11)^2)

I = 1358 W/m^2

Hence, Power available , P = I*area * efficiency

P = 1358 * 9.25 * 0.30

P = 3780.7 W

power to satellite available is 3780.7 W

b)

Intensity at saturn , I = Power/(4*pi*d^2)

I = 3.839 * 10^26/(4 *pi*(9.5 *1.50*10^11)^2)

I = 15.1 W/m^2

Power avaiable = I*area * efficiency

Power avaiable = 15.1 * 9.25 * 0.30

Power avaiable = 41.8 W

the Power avaiable at saturn is 41.8 W

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