Aircraft Control Interface for Four-Axis Finger Operation
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current aircraft control systems require significant pilot effort and training, leading to fatigue due to the need for complex manipulations and ergonomic challenges, especially in 'fly by wire' systems that lack intuitive control over all four axes.
Innovation Solution
A control system featuring a multidirectional control interface, bidirectional control buttons, and a handle that allows pilots to control aircraft along four axes (pitch, roll, yaw, and lift) using finger movements only, eliminating the need for hand or shoulder exertion and incorporating a processing unit to generate control orders based on input parameters.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single control lever with linear annular linkage is used to control all four axes, then device complexity is reduced, but ease of operation deteriorates due to requiring significant pilot effort and special training
Solution Approach 1:
The control system is segmented into multiple independent control elements: a collective pitch lever for vertical movement (lift axis) and a cyclic stick with two mini-joysticks for longitudinal, lateral, and rotational movements (pitch, roll, and yaw axes). This segmentation allows each control element to be optimized for its specific function, reducing the effort required for each individual control action while maintaining overall system functionality.
Solution Approach 2:
The control system transitions from a single-dimensional control lever to a multi-dimensional control interface by adding the cyclic stick with two mini-joysticks. This dimensional expansion allows pilots to control all four axes through combined movements across multiple control elements, distributing the control effort across different spatial dimensions and reducing fatigue.
2Ease of operation
If multiple separate control devices are used for each axis, then ease of operation is improved, but device complexity increases
Solution Approach 1:
The control system merges multiple control functions into an integrated assembly where the cyclic stick incorporates two mini-joysticks, and the collective pitch lever works in coordination with the cyclic stick. This merging reduces the number of separate control devices while maintaining the ability to control all four axes independently, balancing complexity and ease of operation.
Solution Approach 2:
The cyclic stick serves multiple functions by incorporating two mini-joysticks that collectively control pitch, roll, and yaw axes, while the collective pitch lever controls the lift axis. This multi-functionality allows a reduced number of control devices to manage all four control axes, simplifying the overall system while preserving operational ease.
3Measurement precision
If control movements require significant force from the pilot, then control precision is improved, but productivity deteriorates due to pilot fatigue
Solution Approach 1:
By segmenting the control system into specialized elements (collective pitch lever for lift, cyclic stick with mini-joysticks for pitch, roll, and yaw), each control action requires only minimal force appropriate for its function. This segmentation eliminates the need for significant pilot effort while maintaining control precision through dedicated control mechanisms for each axis.
Solution Approach 2:
The control system replaces mechanical linkages (rods, control arms, cables) with a fly-by-wire system that uses electrical signals and force feedback. This substitution eliminates the need for significant mechanical force from the pilot while maintaining control precision through electronic actuation and artificial feel systems.
Data Source
Figure 1~3
Figure 4
AI summary
The present invention relates to a control system (1) for an aircraft (2) enabling a pilot of said aircraft (2) to control aerodynamic means (3), said control system (1) comprising a processing unit (7) for generating control commands, said control commands being transmitted to control devices (4) to modify a position of said aerodynamic means (3) and to pilot said aircraft (2) along four control axes having a pitch control axis, a roll control axis, a yaw movement control axis and a lift control axis, said control system (1) comprising a control member (10) generating control instructions, said control instructions being transmitted to said processing unit (7) generating said control commands under the dependence of said control instructions, said control member (10) being mechanically uncoupled from said control devices (4).