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Spacecraft and antenna sizing

Satellite Power and Lifetime Calculator

Size beginning-of-life power for degradation and eclipse requirements.

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Solar-array power over mission lifetimeBOL: 8166.0 W → EOL: 6124.5 WStartMission endRequired at EOL: 5000 W · Requirement met
The total-degradation model specifies endpoints only; the straight connecting line is an illustrative interpolation, not a measured degradation law. The dashed line marks the required end-of-life load.

Understand the system

Retained power fraction

End-of-life power is beginning-of-life array output multiplied by the retained fraction. If required EOL output is 5 kW, 10% loss needs about 5.56 kW at BOL and 25% loss needs about 6.67 kW. These are degradation estimates, not a full electrical power subsystem design.

PEOL=PBOL(1−d),PBOL=PEOL1−dP_{EOL}=P_{BOL}(1-d),\quad P_{BOL}=\frac{P_{EOL}}{1-d}

P: W or consistent kW; d: fractional loss, 0 ≤ d < 1.

A larger degradation allowance increases required initial array output.

Source: finalExam.pdf · PDF page 3

Common mistakes

  • 30% loss means 70% retention, not division by 0.30.
  • Do not add the degradation percentage directly to EOL power.
  • BOL/EOL sizing alone does not predict mission lifetime.
Formula reference and symbol definitions

BOL to EOL

PBOL=PEOL/(1−d)P_{BOL}=P_{EOL}/(1-d)

P: same units; d: degradation fraction

0 ≤ d < 1; simple retained-power model.

Example: For 5000 W required at EOL and total degradation 25%, PBOL = 5000/0.75 ≈ 6666.67 W.

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Design guide

Use the result with engineering context

Technical content reviewed

When this tool is useful

  • Calculating bol and eol with engineering models
  • Calculating solar degradation with engineering models
  • Calculating battery eclipse support with engineering models

What the result includes

  • Size beginning-of-life power for degradation and eclipse requirements.
  • Explanations, assumptions and links to related satellite calculators

What the model does not guarantee

  • Analytical engineering models do not replace measurements or a mission-specific design review.
  • Spectrum permissions, launch operations and real satellite tracking are outside these calculators.

Worked approach

BOL and EOL

Arrays degrade from radiation and aging. Batteries support eclipse and launch operation; array power also needs recharge and conversion margins. Propellant, battery cycling, thermal stress and component reliability can determine mission lifetime independently of the simple retained-power fraction.

Common decisions

Questions engineers ask

Which topics does Satellite Power and Lifetime Calculator cover?

BOL and EOL; Solar degradation; Battery eclipse support; Lifetime constraints.

How should I check my work in Satellite Power and Lifetime Calculator?

Read the stated assumptions and source references, check units and independently repeat a worked example before relying on the result.

Does Satellite Power and Lifetime Calculator operate real satellite equipment?

No. This is a browser-based educational resource. It does not transmit RF signals, command spacecraft or certify a working link.

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