Aircraft Engine Thrust Imbalance Control Logic

The patent applies local quality by differentiating the inhibition logic based on engine position and failure pattern. The protective function is inhibited only when all engines on a common wing fail, not for isolated engine failures. This localized approach to inhibition maintains thrust balance when truly necessary while preserving protective function availability for other failure scenarios.

The patent segments the engine failure scenarios into distinct categories: single engine failure, dual engine failure on same wing, and dual engine failure on different wings. Each segment has its own inhibition logic, allowing the system to maintain protective function where appropriate while preventing thrust unbalance only in critical same-wing dual failure scenarios.

The patent applies asymmetry by allowing asymmetric thrust distribution when engines have failed. The control means generate maximum thrust on remaining functional engines while accepting or compensating for the asymmetric thrust configuration, rather than enforcing symmetric thrust on all engines regardless of failure status.

The patent implements dynamic thrust control where the protective function adapts its behavior based on real-time engine status. When engine failure is detected, the system dynamically adjusts which engines receive maximum thrust commands, transitioning from a static all-engines-maximum-thrust approach to a dynamic selective maximum thrust approach.