Spacecraft Thermal Balance Calculator

Spacecraft Thermal Control: Compute steady-state orbital equilibrium temperature ($T_{eq}$) considering solar radiation, Earth IR, albedo, and internal power.

Spacecraft & Orbital Environment

Orbit Illumination Condition:

Solar Absorptance $\alpha$:

Thermal Emittance $\epsilon$:

Projected Solar Area $A_{proj}$ ($ ext{m}^2$):

Total Radiating Area $A_{rad}$ ($ ext{m}^2$):

Internal Dissipation $Q_{int}$ (W):

Solar Flux Constant $G_s$ ($ ext{W/m}^2$):

Earth Albedo Factor $a$:

Earth IR Emission $q_{IR}$ ($ ext{W/m}^2$):

Thermal Equilibrium Results

Equilibrium Temp (°C)

-- °C

Equilibrium Temp (K)

-- K

Total Heat Input $Q_{in}$

-- W

$\alpha / \epsilon$ Ratio

Orbital Heat Influx Breakdown

• Direct Solar Absorbed: -- W

• Earth Albedo Absorbed: -- W

• Earth Infrared Absorbed: -- W

• Internal Subsystem Dissipation: -- W

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Spacecraft Thermal Balance Calculator

Spacecraft & Orbital Environment

Thermal Equilibrium Results

Orbital Heat Influx Breakdown

Frequently Asked Questions