T3-04 Solar Lock & Dawn Recovery

1. Cosine Incidence & Solar Array Alignment

Photovoltaic solar wings generate electrical power proportional to the cosine of the incidence angle between the panel surface normal and the solar vector (P = P_max · max(0, n̂ · ŝ)). When the vessel is misoriented, array efficiency drops to zero and the avionics bus drains battery reserves.

2. Sun-Vector Acquisition & Lock

Your spacecraft begins oriented away from the Sun with zero solar generation:

• Observe Solar Telemetry: Inspect [PWR_SOLAR] and attitude telemetry to determine the Sun direction relative to the solar array normal axis.
• Execute Precision Slew: Use reaction wheels and RCS thrusters to rotate the spacecraft until solar incidence efficiency exceeds 85% (generating at least 20.0 kW).
• Hold Solar Lock: Arrest angular rates below 0.20 deg/s and sustain continuous solar lock for 5.0 seconds.

3. Prompt Your Autonomous Agent

Ask Antigravity to add solar array alignment to your flight computer:

Read /api/specs/hardware/solar_arrays and /api/specs/hardware/reaction_wheels.
Update our flight computer to complete mission T3-04 (Solar Array Sun-Tracking Lock):
1. Slew the spacecraft to align the solar array normal vector with the Sun vector.
2. Achieve >= 85% solar cosine efficiency (>= 20.0 kW output) in [PWR_SOLAR] telemetry.
3. Damp angular rates below 0.20 deg/s and hold solar lock for 5.0 seconds.