11.) SpaceX is developing a remote sensing satellite to monitor their Starlink Satellite Network for a minimum of 12 years. The satellite will operate in a circular orbit at an altitude of483 km.

a.)Determine the satellite's angular radius at this altitude.

b.) Calculate the spacecraft's orbital period at this altitude (in minutes).

c.) Determine the maximum time of eclipse (TE) and the time in sunlight (TS) for this altitude.

12.) Continuing with Problem 11, the next phase of development is to determine the electrical power subsystem requirements. The operational subsystem total bus power requirement is known to be28 Watts. The planned payload is a14 Vsensory system (model this system at24.5 ?) and accompanying14 Vcooling system (model this system at28 ?). The payload will only be operated during the sunlit portion of the satellite's orbit. From this information:

a.) Determine the total payload power requirement.

b.) Using the eclipse and sunlight times, calculate the power duty cycle for the payload.

c.) Determine the average payload power requirement.

13.) The battery for this mission is a new version of the Tesla Powerwall with an impressive96%depth of discharge. Using this information and data from Problems 11 and 12:

a.) Determine the energy (Whr) required while the spacecraft is in the eclipse portion of the orbit.

b.) What is the required battery capacity adjusted needed to support power requirements during the eclipse portion of the orbit?

c.) Determine the energy (Whr) required while the spacecraft is in the sunlit portion of its orbit.

d.) What it the total energy (Whr) the solar panels must generate during the sunlit portion of the orbit?

14.) The satellite will be equipped with 2 state-of-the-art solar panels that have an efficiency of31.5%. each panel is0.2 mwide by0.5 mlong. Due to the low altitude, these panels will lose2.85%of their efficiency each year. Using this information and the data from Problems 11-13:

a.) Calculate the solar array surface area.

b.) Calculate the beginning-of-life total array power.

c.) Calculate the end-of-life array power.

15.) Based on the total power requirement from Problem 14:

a.) What is the power the solar array must generate while in sunlight?

b.) What is the solar array's power margin?

c.) Comment on these results.

Equation 13 - 3:1 = = Equation 13 - 4:P = Vi Equation 13 - 5: Pout = Pin cos 8 Equation 13 - 6: PSA = PinAeff Use Equation 13 - 6 (with added degradation): PSA = PinAzzy (1 - array degrade) Misson Life Equation 13 - 7: p = sin-1 Rearth h + REarth 2p Equation 13 - 8:TE = 360* P TS = P - TE Also used: Equation 4 - 27: P = 2n CR = - FEclipse DOD IS Duty Cycle = Frayload AV = Ppayload & Duty Cycle EsARequired PSA Required IS PSA Margin = PSACOL - PSARequired Esunlit = (Prayloud + PBus ) T'S