A spacecraft bus, deployable solar arrays, battery, radio and antenna demonstrate allocation of an electrical-power requirement to physical architecture. A live traceability board exposes unallocated requirements and power-budget shortfalls.
• 3D scene parts: Spacecraft bus; deployable solar arrays; battery and conditioner; radio / antenna; requirement allocation board. • Controls: Required usable bus power (200–600 W); Solar-array gross power (300–900 W); Power conditioning efficiency (0.6–0.95 fraction); Required power reserve (0–0.3 fraction); Remove a requirement allocation. • Live readouts: Usable generation (W); Reserve-adjusted margin (W); Allocation coverage (%); Power requirement met (0/1). • Guided experiments: Insufficient generation; Missing trace link. • Four tabs (visual laboratory, curves and measurements, experiments, learn and assess), a model-verification run, a timestamped event log and a trial report.
Usable power = array × efficiency Margin = usable − required × (1 + reserve) Coverage = linked requirements / 4 × 100
Representative systems-engineering teaching example. Equipment geometry and animation time are illustrative; this is not an equipment qualification, safety assessment or certification tool. Only a steady-state power budget is calculated. Four abstract requirements are shown; satisfying this power inequality does not prove spacecraft mission feasibility. Try the preset experiments, then compare the live readouts with the equations.
No. The stated model omits real qualification evidence and system-specific assumptions.
Trace requirements to allocated architecture.
Representative systems-engineering teaching example. Equipment geometry and animation time are illustrative; this is not an equipment qualification, safety assessment or certification tool. Only a steady-state power budget is calculated. Four abstract requirements are shown; satisfying this power inequality does not prove spacecraft mission feasibility.