Orbit Parameters
Orbital Altitude h
500 km
LEO: 200–2000 / MEO: 2000–35786 / GEO: 35786
Inclination i
51.6 °
Solar Array Parameters
Conversion Efficiency ηsa
28.0 %
Si: 14–18% / GaAs: 28–32% / 3-junction: 35%
Wiring Efficiency ηwire
95.0 %
Annual Degradation d
2.5 %/yr
Design Lifetime L
5 yr
Power Load & Battery
Satellite Load Psat
500 W
Allowed DoD
30 %
Battery Voltage Vbat
28.0 V
Results Summary
—
Orbit Period (min)
—
Eclipse Time (min)
—
Sunlight Fraction (%)
—
Solar Array Area (m²)
—
Battery Capacity (Wh)
—
EOL Power Ratio (%)
Key Equations
Orbit period: $T_{orb} = 2\pi\sqrt{\dfrac{(R_e+h)^3}{\mu}}$
Eclipse time: $T_e = \dfrac{T_{orb}}{\pi}\arcsin\!\left(\dfrac{R_e}{R_e+h}\right)$
EOL power: $P_{EOL} = P_{BOL}(1-d)^L$
Battery capacity: $C_{bat} = \dfrac{P_{sat} \cdot T_e}{DoD \cdot \eta_{bat}}$
Design Note: Always verify the power budget at EOL conditions. GEO satellites face eclipse periods of up to 72 minutes around equinoxes. LEO satellites cycle ~15 times per day (~5,500 cycles/year), making DoD control critical for battery longevity.
Detailed Results
| Parameter | BOL | EOL | Unit |
|---|