Flight Control Device Stiffness Modulation via Dual Motor Segmentation
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Solution Overview
Problem
Pilots face increased complexity in controlling convertible aircraft during takeoff and landing due to the need for different piloting techniques, and existing flight control devices with spring and motor mechanisms can change the anchor point when modifying force relationships, which is undesirable.
Innovation Solution
A flight control device with an electrical assistance system that includes a second motor member to modulate the spring's stiffness continuously without changing the anchor point, allowing for intuitive assistance to pilots by adjusting the return force and damping the spring's movement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the anchor point of the spring is moved by the motor member to modify the force relationship, then the force return for the pilot is adjusted for different flight stages, but the anchor point changes which is not desirable when the pilot is already imposing movement on the spring
Solution Approach 1:
The patent divides the motor member into two distinct parts: a first motor member that moves the anchor point of the spring to adjust the force relationship, and a second motor member that modifies the stiffness of the spring without changing the anchor point. This segmentation allows independent control of force relationship adjustment and stiffness modification, resolving the contradiction by enabling force return adjustment without unwanted anchor point migration during pilot operation.
Solution Approach 2:
The patent introduces dynamic stiffness modification through the second motor member, which can continuously adjust the spring stiffness in response to pilot input. This dynamic adjustment capability allows the system to adapt the force characteristics during operation without the anchor point changing, providing smooth and intuitive control assistance while maintaining anchor point stability.
2Ease of operation
If the spring stiffness is modified continuously without changing the anchor point, then the electrical assistance system provides intuitive assistance to pilots, but an additional motor member is required
Solution Approach 1:
The patent replaces traditional mechanical stiffness adjustment mechanisms with an electrical assistance system using a second motor member. This motor member can modify the spring stiffness through electrical control, providing continuous and precise adjustment without the complexity of mechanical linkages. The electrical substitution enables intuitive pilot assistance while managing system complexity through modern control technology.
Solution Approach 2:
The patent changes the physical parameter of spring stiffness dynamically through the second motor member, allowing continuous adjustment of the force characteristics. By modifying the stiffness parameter independently of the anchor point position, the system provides adaptable force return that responds to pilot needs during operation, enhancing ease of operation despite the added motor member.
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
The device provides enhanced control assistance to pilots by modifying the spring's stiffness and damping, making it easier to manage operating limits and prevent overloading, while maintaining intuitive operation and allowing for emergency lever movement.
Implementation Method 1
a spring and a motor member that are arranged in such a manner that a first end of the spring is constrained to move in rotation with the lever and a second end of the spring is constrained to move in rotation with an outlet shaft of the motor member... the spring is stressed by a movement of its first end relative to its second end, thereby generating a return force on the stick
Implementation Method 2
a first motor member that are arranged in such a manner that a first end of the spring is constrained to move in rotation with the lever and a second end of the spring is constrained to move in rotation with an outlet shaft of the first motor member
Implementation Method 3
a second motor member that is distinct from the first motor member and that is arranged in such a manner that its outlet shaft is constrained to move in rotation with the first end of the spring... enables the stiffness of the spring to be modulated more accurately by opposing or assisting relative movement between the first end of the spring and the second end of the spring
Data Source
Figure 1~2
Figure 3
Figure 4a~4b
AI summary
The invention relates to a flight control device (1) for an aircraft, the device comprising a mount (2), a lever (3) pivotally mounted on the mount, and mechanical means for generating a return force for the lever, said means including a spring (6) and a first motor member (13) that are arranged so that a first end of the spring is constrained to move in rotation with the lever and a second end of the spring is constrained to move in rotation with an outlet shaft of the first motor member. According to the invention, the flight control device includes an electrical assistance system (18) for assisting said mechanical means for generating a return force.