Rotorcraft Collective Control Column with Rotational Throttle Interface
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Solution Overview
Problem
Current rotorcraft control systems require separate throttle quadrants and mechanical interconnections, which increase weight, complexity, and reduce available space for additional controls, while also not efficiently enabling smooth transitions between flight and idle states.
Innovation Solution
A collective control column with a rotatable collar that provides distinct inputs for flying and idling, utilizing a spring-biased mechanism to securely position the collar and allow easy switching between these states, reducing mechanical hardware and allowing additional controls to be integrated into the grip area.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate throttle quadrants and mechanical interconnections are used, then reliable control is achieved, but weight and device complexity increase
Solution Approach 1:
The patent combines the throttle control and collective pitch control into a single control column assembly. The throttle quadrant is integrated with the collective pitch lever, allowing both controls to be operated from one location rather than requiring separate throttle quadrants and mechanical interconnections. This merging reduces the number of mechanical components and simplifies the overall control system architecture.
Solution Approach 2:
The control column is designed to perform multiple functions: it provides both collective pitch control and throttle control capabilities. The rotational interface on the control column can be rotated to provide throttle input while the collective lever provides pitch input, making the single assembly universal for both control functions. This eliminates the need for separate dedicated throttle quadrants.
2Adaptability or versatility
If separate throttle quadrants and mechanical interconnections are used, then control functionality is achieved, but available space for additional controls is reduced
Solution Approach 1:
By merging the throttle and collective pitch controls into a single integrated control column, the patent frees up cockpit space that would otherwise be occupied by separate throttle quadrants and their mechanical interconnections. The grip area of the control column provides additional space for mounting extra controls, switches, or displays without requiring additional cockpit real estate.
Solution Approach 2:
The patent utilizes the rotational dimension of the control column by adding a rotational interface that can be turned to provide throttle input. This adds a new degree of freedom to the control column, allowing it to handle both pitch and throttle controls in three-dimensional space rather than requiring separate planar control surfaces.
3Reliability
If traditional mechanical control systems are used, then reliable state control is achieved, but transitions between flight and idle states are not smooth
Solution Approach 1:
The patent replaces traditional mechanical throttle control with an electronic control system. The rotational interface on the control column provides electronic throttle control signals rather than direct mechanical linkage to the throttle actuator. This electronic substitution enables smooth, progressive transitions between flight and idle states through electronic modulation rather than mechanical step changes.
Solution Approach 2:
The electronic control system allows for dynamic, continuous adjustment of throttle position during transitions. Unlike mechanical systems that may have discrete detents or linkage constraints, the electronic system can provide smooth, continuous control throughout the entire range from idle to full power, enabling seamless transitions between operational states.
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 design simplifies the control interface, reduces weight and mechanical complexity, and enables efficient transitions between flight and idle states, while providing additional space for other controls, enhancing operational efficiency and pilot convenience.
Implementation Method 1
utilizing a spring-biased mechanism to securely position the collar and allow easy switching between these states
Data Source
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AI summary
Rotorcraft controls and rotorcraft including such rotorcraft controls are disclosed. An example apparatus includes a collective control column (114, 200, 600) for an aircraft includes a rotational interface rotatable in a first direction to provide a first input and a second direction opposite the first direction to provide a second input; a memory (126) to store instructions; and a processor responsive to the first input to execute the instructions to cause the aircraft to perform operations associated with flying the aircraft, the processor responsive to the second input to execute the instructions to cause the aircraft to perform operations associated with idling the aircraft. (Fig. 2)