Gyrodyne Rotor Power Management via Autorotation
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Solution Overview
Problem
Gyrodyne aircraft lack efficient systems for managing power during both vertical takeoff and landing and forward flight, leading to complexities in control and maintenance, and existing solutions do not effectively optimize fuel efficiency and cruise speed.
Innovation Solution
The aircraft employs a plurality of rotors powered by electric motors, with a flight control system managing net electrical power to maintain efficient operation, using autorotation and regenerative braking to optimize fuel efficiency and cruise speed, and includes features like fixed pitch rotors and redundant power systems for reliability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If variable pitch rotors and swash plate are used for collective and pitch control, then flight control capability is improved, but device complexity and maintenance requirements increase
Solution Approach 1:
The patent removes the swash plate mechanism from the rotor system, extracting the complex mechanical components while retaining flight control capability through alternative means (electronic control of rotor blade angles or alternative mechanical linkages). This directly addresses the contradiction by eliminating the maintenance-prone swash plate while preserving pitch and collective control functions.
Solution Approach 2:
The patent replaces the mechanical swash plate system with an electronic or simplified mechanical control system. Instead of using the complex interconnected mechanical linkages of a swash plate, the invention employs electronic actuators or alternative mechanisms that achieve the same flight control objectives with reduced complexity and maintenance requirements.
2Speed
If rotor RPM is reduced to decrease drag, then cruise speed is improved, but lift generation capability deteriorates
Solution Approach 1:
The patent employs dynamic adjustment of rotor blade pitch angles in response to varying flight conditions. During cruise flight, the system dynamically reduces rotor RPM to minimize drag while simultaneously adjusting blade pitch to maintain adequate lift. This dynamic control allows the rotor system to adapt its characteristics in real-time, resolving the contradiction between speed and lift generation.
Solution Approach 2:
The patent changes the operational parameters of the rotor system by allowing RPM to vary within a broader range and using blade pitch angle adjustments to compensate. Instead of operating at a fixed high RPM, the system optimizes the combination of RPM and pitch angle to achieve both reduced drag for higher cruise speeds and sufficient lift generation, effectively decoupling the traditional trade-off between these two parameters.
3Speed
If dedicated propulsion engines are used to increase cruise speed, then speed performance is improved, but fuel consumption increases
Solution Approach 1:
The patent makes the rotor system multi-functional by enabling it to perform both lift generation during vertical flight and propulsion assistance during forward flight. The same rotor blades that provide lift during takeoff and landing also contribute to forward thrust during cruise, eliminating the need for completely separate dedicated propulsion engines and reducing overall fuel consumption while maintaining high cruise speed capability.
Solution Approach 2:
The patent merges the lift generation function and propulsion function into a single integrated rotor system. Instead of having separate engines solely for forward propulsion, the invention combines the rotor's lift-producing capability with its ability to generate forward thrust, creating a unified system that improves fuel efficiency while achieving high cruise speeds through coordinated operation of the rotor and fixed wing surfaces.
4Device complexity
If one rotor is used to simplify the aircraft structure, then device complexity is reduced, but control authority and redundancy deteriorate
Solution Approach 1:
The patent segments the rotor system into multiple independent rotor units, each capable of independent control. This segmentation provides several benefits: it distributes the control authority across multiple units, provides redundancy so that failure of one rotor does not catastrophicallly compromise the aircraft, and enables more sophisticated flight control modes including differential rotor operation for enhanced maneuverability and stability.
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 configuration enhances fuel efficiency, increases cruise speed, reduces maintenance costs, and ensures safe operation by automatically stabilizing the aircraft and managing power within predetermined safe regions, even in the event of failures.
Implementation Method 1
Autorotation is an aerodynamic state of a rotor where the only power applied to the rotor is from the airflow through the rotor, which provides the rotational power, and the resulting rotation of the blades provides lift.
Implementation Method 2
using autorotation and regenerative braking to optimize fuel efficiency and cruise speed
Data Source
AI summary
An aircraft includes at least one propulsion engine, coupled to a fuselage, and configured to provide forward thrust to propel the aircraft along a first vector during forward flight. Each of at least two of multiple rotors coupled to the fuselage is coupled to a motor configured to supply power to that rotor and/or to draw power from that rotor. At least two of the rotors are configured to operate during forward flight to provide at least some lift to the aircraft along a second vector. A flight control system is configured to control the rotors that are configured to operate during forward flight in a power managed regime in which a net electrical power, consisting of the sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system.