Aircraft Thrust Matching Using an Incumbent Engine Model
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Solution Overview
Problem
Conventional methods for matching the transient and steady-state engine characteristics of new powerplants to original engines in aerospace applications are inadequate, especially during fast maneuvers, and automated control systems are costly to implement.
Innovation Solution
A method that uses a model of an incumbent powerplant to modify commanded thrust, applying it to a new powerplant to emulate the original engine's performance, involving a controller with torque split logic and a thrust command modification unit to adjust the thrust between a heat engine and an electric motor, allowing for efficient matching of aircraft performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If automated control systems are used to compensate for multiple engine thrust asymmetry, then handling characteristics during fast transients are improved, but system cost increases significantly
Solution Approach 1:
The patent creates a virtual model (copy) of the incumbent powerplant's transient characteristics and applies it to the new powerplant through software-based thrust modification. This avoids the need for expensive physical automated control systems while achieving similar performance matching. The virtual model replicates the original engine's acceleration and deceleration behavior to maintain handling characteristics.
2Reliability
If pilot adjusts aircraft control surfaces to manage multiple engine thrust asymmetry, then steady state performance is maintained, but performance during fast transients deteriorates
Solution Approach 1:
The patent pre-calculates and stores transient characteristic data from the incumbent powerplant in a lookup table or database. During operation, the system retrieves pre-computed thrust modification values based on current operating conditions, enabling rapid response during fast transients without requiring real-time complex calculations or physical adjustments.
Solution Approach 2:
The patent implements dynamic thrust modification that adapts to changing flight conditions. The system continuously monitors engine parameters and adjusts the thrust modification factor in real-time based on the retrieved transient characteristics, allowing the control system to respond dynamically to fast transients while maintaining steady-state performance.
3Ease of manufacture
If new powerplant is implemented without thrust modification, then development cost is reduced, but aircraft performance matching deteriorates
Solution Approach 1:
The patent modifies the thrust parameter of the new powerplant by applying a modification factor derived from the incumbent powerplant's transient characteristics. This software-based parameter adjustment allows the new powerplant to match the original aircraft's performance without physical modifications to the engine hardware, maintaining low development costs while achieving accurate performance matching.
Data Source
AI summary
A method of controlling a multi-engine aircraft includes receiving input for commanded thrust and modifying the commanded thrust using a model of an incumbent powerplant to generate a modified commanded thrust for matching aircraft performance with a new powerplant to the aircraft performance with the incumbent powerplant. The method includes applying the modified commanded thrust to the new powerplant.