Shared Power Distribution for Independent Slat and Flap Actuation

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Solution Overview

Problem

Current flight control surface actuation systems are complex and heavy due to separate drive systems for each control surface, leading to increased weight and complexity.

Innovation Solution

A secondary flight control system utilizing a common power distribution unit connected to both a slat and flap system, with a T-gearbox to split torque into separate drive lines and clutches to engage/disengage the systems, along with brakes to control torque transmission, and a control system for actuation and monitoring.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If separate drive systems are used for each flight control surface, then each control surface can be independently actuated, but the system weight and complexity increase

Engineering Contradiction:

Improveindependent actuation capabilityVSAvoidsystem weight

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

The patent combines multiple flight control surface drive systems (flap and slat) into a single integrated power distribution unit that shares common power electronics, torque tubes, and control architecture, thereby reducing overall system weight while maintaining independent actuation capability through electronic control of multiple output shafts

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The power distribution unit is designed as a multi-functional device that can simultaneously or independently actuate different flight control surfaces (flaps and slats) through a single unified system, eliminating the need for separate dedicated drive systems for each control surface

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Reliability

If separate drive systems are used for each flight control surface, then each control surface can be independently actuated, but the system complexity increases

Engineering Contradiction:

Improveindependent actuation capabilityVSAvoidsystem complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The patent merges separate drive systems into a unified power distribution unit with common power electronics, shared control architecture, and integrated torque management, thereby reducing the number of independent subsystems and simplifying the overall system complexity

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

While integrating systems, the patent maintains functional segmentation through separate output shafts, torque tubes, and actuation mechanisms for different control surfaces, allowing independent actuation while managing complexity through modular functional divisions within the unified system

Inventive Principle:

Principle #1Segmentation

3Weight of moving object

If a common power distribution unit is used for multiple flight control surfaces, then weight and complexity are reduced, but the ability to independently control each surface may be compromised

Engineering Contradiction:

Improvesystem weightVSAvoidindependent control capability

Core Design Contradiction:

Weight of moving objectVSAdaptability or versatility

Solution Approach 1:

The power distribution unit incorporates dynamic control capabilities with multiple independently controllable output shafts that can be selectively engaged or disengaged through clutches, allowing the system to adapt between different actuation modes (simultaneous or independent) based on flight conditions and control requirements

Inventive Principle:

Principle #15Dynamics

Data Source

PatentUS11111005B2Control of multiple flight control surface systems using single power drive unit

Publication Date: 2021.09.07 HAMILTON SUNDSTRAND CORP

AI summary

A secondary flight control system comprising: a first flight control surface system; a second flight control surface system; and a power distribution unit operably connected to the first flight control surface system and the second flight control surface system, wherein the power distribution unit is configured to generate torque to actuate the first flight control surface system and the second flight control surface system.