Aircraft Engine Control Integration via Compound AC Generator

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Solution Overview

Problem

Current aircraft systems require separate components and power sources for engine and generator control, leading to increased weight, drag, and mechanical losses due to the need for dedicated hardware and wiring.

Innovation Solution

Integration of a compound AC generator with a co-located generator control unit (GCU) and engine electronic controller (EEC) modules, powered by a permanent magnet generator (PMG), eliminating the need for a separate Permanent Magnet Alternator (PMA) and reducing hardware requirements.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If separate Permanent Magnet Alternator (PMA) and control components are used for engine and generator control, then system reliability and independent power supply are improved, but aircraft weight and device complexity increase

Engineering Contradiction:

Improveindependent power supplyVSAvoidaircraft weight

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

The patent combines the PMA, GCU, and EEC into a single integrated control module mounted on the engine accessory gearbox. This merging eliminates the need for separate control components and wiring harnesses, reducing aircraft weight while maintaining independent power supply capability through the PMG embedded in the generator.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The integrated control module serves multiple functions: the PMG provides independent power supply, the GCU controls generator operation, and the EEC controls engine parameters. This multi-functionality consolidates what were previously separate systems into one universal control unit, reducing overall system weight and complexity.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Reliability

Engineering Contradiction:

Improveindependent power supplyVSAvoidcontrol hardware and wiring

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The patent merges the GCU and EEC into a single integrated control module with consolidated wiring connections to the engine and generator. This integration reduces the number of separate control components and wiring harnesses required, simplifying the overall system architecture while maintaining reliable independent power supply through the PMG.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The patent extracts the control functions from separate airborne systems and relocates them to an integrated module mounted directly on the engine accessory gearbox. This extraction eliminates the need for extensive wiring between distributed control components and reduces system complexity.

Inventive Principle:

Principle #2Taking out (Extraction)

3Reliability

If separate control components and power sources are used, then control functions are reliable, but mechanical losses and gearbox optimization are worsened

Engineering Contradiction:

Improvecontrol function reliabilityVSAvoidmechanical losses

Core Design Contradiction:

ReliabilityVSLoss of energy

Solution Approach 1:

The patent combines all control functions and power supply into a single integrated module mounted on the engine accessory gearbox. This eliminates the need for separate mechanical drive shafts and gear connections that would transmit power to distributed control components, thereby reducing mechanical losses in the gearbox while maintaining reliable control function operation.

Inventive Principle:

Principle #5Merging (Combining)

Applied Scientific Principles

This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.

Function Achieved in This Case

This integration reduces aircraft weight and drag, optimizes the engine gearbox, and minimizes mechanical losses by consolidating power sources and control functions within the engine accessory gearbox.

Implementation Method 1

a permanent magnet generator (PMG) configured to be driven by the shaft to generate an AC power signal

Methodology Applied

Scientific EffectElectromagnetic induction: Electromagnetic Induction

Data Source

PatentEP2942864B1Apparatus and systems for engine and generator control within an aircraft

Publication Date: 2018.12.05 GULFSTREAM AEROSPACE CORP

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AI summary

A system is provided for engine and generator control. The system includes a compound AC generator, a generator control unit (GCU) module and an engine electronic controller (EEC) module. The compound AC generator includes a shaft, and a permanent magnet generator (PMG) configured to be driven by the shaft to generate an AC power signal. The GCU module is configured to control the compound AC generator. The PMG is coupled to the GCU module and the EEC module such that it is configured to simultaneously supply the AC power signal to the GCU module and to the EEC module.