Integrated Aircraft Control Stick for Simpler Multi-Axis Control

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Solution Overview

Problem

Existing aircraft flight control systems are complex, non-intuitive, and require separate controls for yaw, pitch, and roll, often involving heavy rudder pedals and multiple levers, which complicate cockpit design and maintenance.

Innovation Solution

A single control stick with a moveable element that allows graduated input for controlling yaw, pitch, and roll, integrated with ergonomic design and intuitive finger and thumb controls for enhanced cockpit simplicity and reduced weight.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If separate controls (rudder pedals, thrust lever, spoiler lever, control stick) are used for yaw, pitch, roll and thrust control, then each control function can be independently optimized, but the cockpit becomes complex and requires multiple controls increasing weight and maintenance difficulty

Engineering Contradiction:
Improvecontrol intuitivenessVSAvoidcockpit control complexity
Core Design Contradiction:
Ease of operationVSDevice complexity

Solution Approach 1:

The patent combines multiple separate flight control functions (yaw, pitch, roll, and thrust control) into a single integrated control stick. The control stick includes a main body for pitch and roll control, with integrated rudder pedals for yaw control and a thrust lever for thrust control, all merged into one unified control assembly. This eliminates the need for separate controls and reduces cockpit complexity while maintaining intuitive operation through a centralized interface.

Inventive Principle:
Principle #5Merging (Combining)

Solution Approach 2:

The control stick is designed as a multi-functional device that performs multiple flight control functions simultaneously. The main body handles pitch and roll, the integrated rudder pedals handle yaw, and the thrust lever handles thrust control. This universal control stick can perform all flight control functions that previously required separate dedicated controls, reducing the overall number of controls needed in the cockpit.

Inventive Principle:
Principle #6Universality (Multi-functionality)

2Ease of operation

If multiple separate controls (rudder pedals, thrust lever, control stick) are used for different flight functions, then each control can be independently positioned for optimal ergonomics, but the overall cockpit weight increases and installation/maintenance becomes more difficult

Engineering Contradiction:
Improvecontrol ergonomicsVSAvoidcockpit control weight
Core Design Contradiction:
Ease of operationVSWeight of moving object

Solution Approach 1:

The patent merges multiple separate control components (control stick, rudder pedals, thrust lever) into a single integrated control assembly. This consolidation reduces the total weight of moving parts in the cockpit control system, as the combined structure eliminates redundant mounting hardware, separate linkages, and multiple independent control mechanisms that would be required for separate controls.

Inventive Principle:
Principle #5Merging (Combining)

3Ease of repair

If multiple separate controls are used for yaw, pitch, roll and thrust, then each control can be independently maintained, but the overall maintenance complexity and time required increases

Engineering Contradiction:
Improvecontrol maintenance accessibilityVSAvoidmaintenance complexity
Core Design Contradiction:
Ease of repairVSDevice complexity

Solution Approach 1:

The integrated control stick consolidates multiple control functions into a single maintainable unit. While individual components (rudder pedals, thrust lever) remain distinguishable, they are mounted as part of the unified control stick assembly, allowing maintenance personnel to access and service all functions through a single approach, reducing the time and complexity of overall maintenance operations.

Inventive Principle:
Principle #5Merging (Combining)

Data Source

PatentEP4631852A1Flight control system
Publication Date: 2025.10.15 RATIER FIGEAC SAS
  • EP4631852A1 patent drawingFigure 1
  • EP4631852A1 patent drawingFigure 2
  • EP4631852A1 patent drawingFigure 3~4

AI summary

A flight control system for an aircraft is provided. The aircraft has a set of principle axes including a roll axis and a pitch axis. The flight control system comprises a control stick (100) that is configured to move forwards and backwards and left and right to control movement of the aircraft about its roll and pitch axes, such movement of the control stick thus providing a first set of inputs to the flight control system. The control stick comprises a further input in the form of a moveable element (116) that can be moved between a range of positions and that is configured to provide a graduated input to the flight control system based on the position of the moveable element relative to a default position of the moveable element, the moveable element being positioned on a side or front portion of the control stick (100).