Electric Damping of Flight Control Surfaces Using Back-EMF
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Solution Overview
Problem
Conventional aircraft with electrically actuated flight elements face challenges in damping movement during unpowered conditions, leading to potential damage and safety hazards due to lack of hydraulic pressure, which is not effectively addressed by existing mass balance devices that add weight and affect range and maneuverability.
Innovation Solution
A motor control system that utilizes back EMF voltage to create a counter-torque opposing the movement of flight elements, dissipating excess energy as heat, thereby dampening the movement even when motors are unloaded, using a controller, resistor, and switching devices to manage current flow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If mass balance devices are used to dampen flight element movement, then safety is improved, but aircraft weight increases and range and maneuverability deteriorate
Solution Approach 1:
The patent replaces mechanical mass balance devices with an electrical damping system that uses the motor's electromagnetic properties. The motor control system utilizes the motor's back EMF and electrical resistance to create damping forces, eliminating the need for additional mechanical mass balance components and their associated weight penalties.
Solution Approach 2:
The patent makes the motor serve a dual function: propulsion and damping. By controlling the motor's electrical circuit during unpowered conditions, the system uses the motor's own electromagnetic characteristics (back EMF and resistance) to provide damping, eliminating the need for separate damping mechanisms.
2Reliability
If hydraulic systems are used to dampen flight element movement, then safety is improved, but system complexity and weight increase
Solution Approach 1:
The patent replaces hydraulic damping systems with an electrical control system that uses the motor's electromagnetic properties. This substitution eliminates complex hydraulic components (pumps, reservoirs, valves, fluid lines) in favor of a simpler electrical control circuit that leverages the motor's inherent back EMF and resistance characteristics.
Solution Approach 2:
The motor control system uses the motor's own electromagnetic characteristics (back EMF voltage and electrical resistance) to provide damping, eliminating the need for external hydraulic systems. The system essentially uses the motor's natural electrical properties to create the damping effect.
3Weight of moving object
If electrical damping system is implemented, then weight is reduced and safety is improved, but energy management complexity increases
Solution Approach 1:
The damping system uses the motor's own back EMF voltage as the energy source, eliminating the need for external power supplies or energy storage devices. The system automatically generates the necessary voltage through the motor's motion, and the controller simply manages the electrical circuit configuration to achieve damping.
Solution Approach 2:
The patent replaces complex energy management systems with a straightforward electrical circuit control approach. By using switching devices (transistors, MOSFETs, or relays) to connect the motor terminals to resistive loads, the system achieves damping through simple electrical circuitry rather than complex power management electronics.
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
Effectively prevents damage and unsafe conditions by damping the movement of flight elements, enhancing safety and reducing weight-related penalties on aircraft performance.
Implementation Method 1
the back EMF voltage being created by movement of a moveable aircraft structure of the aircraft
Implementation Method 2
dissipating excess energy as heat
Data Source
AI summary
An aircraft system for damping movement of a structural flight element. The aircraft system including a moveable aircraft structure, a power source, a controller, a resistor, and a first transistor connected in series to the resistor. When the power source of the aircraft is providing power, the controller controls the first transistor to prevent current flow through its terminals and through the resistor. Further, when the power source of the aircraft is not providing power, the first transistor allows current generated by a back EMF (electromotive force) voltage to flow through its terminals and through the resistor, the back EMF voltage being created by movement of the moveable aircraft structure.