Rotorcraft Electrical Braking via Generator Resistance
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Solution Overview
Problem
Traditional disc-and-caliper braking systems for rotorcraft are heavy, complex, space-consuming, expensive, and increase fuel consumption, necessitating a more efficient and lightweight braking solution that utilizes existing components.
Innovation Solution
A braking system that includes a generator with an armature mechanically coupled to the rotor hub assembly, where an electrical resistance is applied to slow or stop the rotor hub assembly, potentially using existing components like alternators or hydraulic pumps to convert kinetic energy into electrical or fluid energy, reducing the need for additional parts and complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If disc-and-caliper braking systems are used, then braking functionality is achieved, but weight increases
Solution Approach 1:
The generator is used for dual purposes: normal electrical power generation during flight operations and braking during landing. By mechanically coupling the generator's armature to the rotor hub assembly and applying electrical resistance to the generator, the same component serves both propulsion and braking functions, eliminating the need for a separate braking subsystem and reducing overall weight
Solution Approach 2:
The patent replaces the mechanical disc-and-caliper friction braking system with an electrical braking system. Instead of using mechanical friction between brake pads and discs, the system uses electrical resistance applied to the generator to convert kinetic energy into electrical energy, thereby slowing the rotor hub assembly. This substitution eliminates heavy mechanical braking components while achieving the same braking effect
2Reliability
If disc-and-caliper braking systems are used, then braking functionality is achieved, but device complexity increases
Solution Approach 1:
The generator serves multiple functions: normal electrical power generation during flight and braking during landing. By using the existing generator and its electrical system for braking, the patent avoids adding a separate braking subsystem with its own sensors, actuators, and control mechanisms, thereby reducing overall system complexity
Solution Approach 2:
The patent merges the braking function with the existing generator and electrical system. The armature of the generator, which normally generates electricity, is used as the braking element by applying electrical resistance to it. This consolidation eliminates the need for separate braking components and simplifies the overall system architecture
3Reliability
If disc-and-caliper braking systems are used, then braking functionality is achieved, but space consumption increases
Solution Approach 1:
The generator, which is already installed in the rotorcraft for electrical power generation, is used for braking as well. By mechanically coupling the armature to the rotor hub assembly and applying electrical resistance, the system achieves braking functionality without requiring additional space for separate braking components
Solution Approach 2:
The patent replaces the space-consuming mechanical disc-and-caliper system with a compact electrical braking system. The electrical resistance applied to the generator requires minimal additional space compared to the mechanical friction system, thereby reducing the overall volume occupied by braking components
4Reliability
If disc-and-caliper braking systems are used, then braking functionality is achieved, but fuel consumption increases
Solution Approach 1:
The kinetic energy of the rotating rotor hub assembly, which must be dissipated during braking, is converted into electrical energy by the generator. This electrical energy can be used to power onboard systems or stored in batteries, transforming what would be wasted energy into a useful resource. This energy recovery process reduces the overall energy consumption of the rotorcraft compared to traditional friction braking that simply dissipates energy as heat
Solution Approach 2:
The generator serves dual purposes: normal electrical power generation during flight and energy recovery during braking. By capturing kinetic energy during landing and converting it to electrical energy, the system reduces the total energy consumption of the rotorcraft, thereby reducing fuel consumption
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 solution reduces the weight and complexity of rotorcraft braking systems, conserves energy, and allows for modulated braking, enhancing safety and reducing costs by leveraging existing componentry and eliminating the need for separate braking subsystems.
Implementation Method 1
a generator having an armature mechanically coupled to the rotor hub assembly such that the armature is rotatable in response to rotation of the rotor hub assembly
Implementation Method 2
The braking unit is adapted to apply an electrical resistance to rotation of the armature, thereby reducing a rotational speed of the rotor hub assembly
Data Source
AI summary
A braking system for a rotorcraft having a rotor hub assembly includes a generator having an armature mechanically coupled to the rotor hub assembly such that the armature is rotatable in response to rotation of the rotor hub assembly and a braking unit in selective electrical communication with the generator. The braking unit is adapted to apply an electrical resistance to rotation of the armature, thereby reducing a rotational speed of the rotor hub assembly.