Rotary Blade Actuator for Independent Rotorcraft Control
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Solution Overview
Problem
Conventional rotorcraft blade control systems rely on redundant electrical or mechanical systems and secondary load paths, which increase complexity, weight, and power consumption, and are unable to efficiently implement independent blade control without these redundancies.
Innovation Solution
A mechanical independent blade control system using a radial fluid device with programmable cams and hydraulic actuation, which generates sinusoidal motion patterns for individual rotor blades without the need for redundant systems, allowing for efficient control of harmonic and reactionless motions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If redundant electrical or mechanical systems are used for blade control, then reliability is improved, but device complexity increases
Solution Approach 1:
The mechanical control system uses the rotorcraft's existing rotational motion and aerodynamic forces to automatically control blade pitch. The system leverages natural physical phenomena (Coriolis effect, centrifugal force) rather than requiring active control systems, reducing complexity while maintaining reliability through passive self-regulation
Solution Approach 2:
The patent replaces electrical control systems with a purely mechanical control mechanism. The mechanical linkage system directly translates rotorcraft motion into blade pitch changes without requiring electrical components, sensors, or electronic control units, thereby reducing device complexity while maintaining functional reliability
2Reliability
If redundant systems are implemented for independent blade control, then reliability is improved, but weight increases
Solution Approach 1:
The control system utilizes the rotorcraft's inherent rotational dynamics and aerodynamic environment to automatically regulate blade pitch. By employing passive mechanical elements that respond to natural physical forces rather than active redundant control components, the system achieves reliability without adding significant weight
Solution Approach 2:
The patent extracts and eliminates redundant electrical systems, sensors, and control electronics from the blade control architecture. The solution retains only the essential mechanical linkage components needed for direct control, thereby reducing weight while maintaining the core functionality through simplified means
3Reliability
If redundant electrical or mechanical systems are used, then reliability is improved, but power consumption increases
Solution Approach 1:
The mechanical control system operates passively by harnessing the rotorcraft's rotational motion and aerodynamic forces to automatically control blade pitch. No external power source is required as the system converts kinetic energy from the rotating rotorcraft into pitch control movements, eliminating power consumption while maintaining reliability through natural physical regulation
Solution Approach 2:
The patent replaces electrical control systems that consume power with a purely mechanical linkage system. The mechanical system directly translates physical motion into control actions without requiring electrical energy, thereby eliminating power consumption associated with motors, sensors, and electronic control while maintaining functional reliability
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 system provides reliable independent blade control, reduces power consumption, and eliminates the need for redundant systems, enhancing rotorcraft efficiency, noise reduction, and vibration control by directly actuating rotor blades with precise mechanical programming.
Implementation Method 1
A mechanical independent blade control system using a radial fluid device with programmable cams and hydraulic actuation
Implementation Method 2
A mechanical independent blade control system using a radial fluid device with programmable cams
Data Source
AI summary
According to one embodiment, a rotary blade actuator includes a housing, a vane disposed within the housing, a shaft disposed at least partially within the housing and coupled to the vane. The vane comprises a first vane surface disposed within a first chamber between a first fluid opening and a second fluid opening and a second vane surface disposed within a second chamber between a third fluid opening and a fourth fluid opening. The first and third fluid openings are configured to provide a first fluid to the first chamber and the second chamber at a first pressure, the second fluid opening is configured to provide a second fluid to the first chamber at a second pressure, and the fourth fluid opening is configured to provide a third fluid to the second chamber at a third pressure different from the second pressure.