Dual-Mode Aircraft Throttle Assembly for Hover-Thrust Control
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Solution Overview
Problem
Existing eVTOL aircraft technologies face challenges in energy efficiency and ease of control, particularly for pilots adjusting to dual-mode aircraft operations.
Innovation Solution
A hover and thrust control assembly for dual-mode aircraft featuring a support structure, throttle lever, and linear thrust control that mechanically couples to the aircraft frame, allowing for precise control of vertical and forward propulsors through rotational and linear movements, with haptic feedback and safety features like battery shut-off switches and emergency indicators.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a traditional control system is used for dual-mode aircraft, then the structure is simple, but the ease of operation deteriorates due to the unfamiliar and complex control adjustments required for pilots
Solution Approach 1:
The patent combines multiple control functions into a single integrated control assembly. The throttle lever integrates both vertical thrust control (through rotation) and forward thrust control (through linear movement), allowing pilots to control dual-mode aircraft with one unified interface rather than separate controls for each function.
Solution Approach 2:
The control assembly is designed to perform multiple functions: the throttle lever can control vertical propulsor torque through rotation, control forward propulsor thrust through linear movement, and includes integrated safety features like battery shut-off switches and emergency indicators, making it a universal control solution for dual-mode aircraft.
2Productivity
If separate controls are used for vertical and forward thrust, then the device complexity is low, but the productivity deteriorates due to reduced control efficiency
Solution Approach 1:
The patent merges vertical thrust control and forward thrust control into a single throttle lever assembly. Pilots can simultaneously or sequentially adjust vertical propulsor torque by rotating the lever and forward propulsor thrust by moving it linearly, streamlining the control process and improving operational efficiency.
Solution Approach 2:
While integrating controls, the patent segments the control movements into distinct degrees of freedom: rotational movement controls vertical thrust while linear movement controls forward thrust. This segmentation within integration allows independent control of each function while maintaining a unified interface.
3Reliability
If basic control features are used, then the device complexity is low, but the reliability deteriorates due to lack of safety features for emergency response
Solution Approach 1:
The patent integrates safety features directly into the control assembly structure. Battery shut-off switches and emergency indicators are incorporated into the throttle lever assembly, ensuring that safety functions are readily accessible and integrated with the primary control mechanisms rather than being separate systems.
Solution Approach 2:
The control assembly includes pre-positioned safety features such as battery shut-off switches and emergency indicators that are immediately accessible during normal operation. In case of emergencies, pilots can quickly access these pre-positioned safety mechanisms without needing to locate separate controls, enabling rapid response.
Data Source
AI summary
A combined hover and forward thrust control assembly for a dual-mode aircraft includes a support structure attached to an aircraft frame of an aircraft having at least a vertical thrust propulsor and at least a forward thrust propulsor a throttle lever rotatably mounted to the support structure, wherein rotating the throttle lever in a first direction increases power to at least a vertical thrust propulsor and rotating the throttle lever in a second direction decreases power to at least a vertical thrust propulsor and a linear thrust control mounted on the throttle lever, wherein movement of the linear thrust control in a first direction increases forward thrust of at least a forward thrust propulsor, and movement of the linear thrust control in a second direction decreases forward thrust of the forward thrust propulsor.