VTOL Aircraft Rotor Redundancy and Thrust Vectoring
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Solution Overview
Problem
Current personal aircraft, particularly vertical takeoff and landing (VTOL) aircraft, are hindered by the complexity and cost of traditional engines, requiring specialized training and infrastructure, making them inaccessible to the general public and limiting their use due to issues like engine loss from foreign object debris and reliance on petroleum-based fuels.
Innovation Solution
A VTOL aircraft design incorporating electric ducted fans or gas-powered rotor units, with a rotating chassis allowing for directed thrust and transition between hover, transition, and forward flight modes, enabled by a flight control computer that simplifies operation and includes a degraded rotor landing protocol for safe landing in case of engine failure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional turbo-fan or turbo-shaft engines are used in VTOL aircraft, then reliable vertical lifting capability is achieved, but the aircraft becomes extremely complex and expensive with high risk of engine loss from foreign object debris
Solution Approach 1:
The patent divides the propulsion system into multiple independent rotor units (typically three or more) distributed across the aircraft. Each rotor unit operates independently, so if one fails, the others can maintain flight. This segmentation replaces the single complex turbo-fan engine with multiple simpler, redundant rotor systems, reducing overall system complexity while maintaining reliability.
Solution Approach 2:
The patent incorporates redundant rotor units that serve as backup systems before failure occurs. The aircraft is designed with more rotor units than strictly necessary for normal operation, so that if one rotor fails due to foreign object debris or other issues, the remaining rotors can compensate and prevent catastrophic failure, cushioning against the harmful effect of engine loss.
2Speed
If tilt-rotor aircraft are used to provide vertical lifting capabilities, then speed and efficiency of conventional fixed wing aircraft is achieved, but the aircraft becomes difficult to maneuver after rotor failure and requires professional pilot training
Solution Approach 1:
The patent positions rotor units at specific locations on the aircraft (such as wingtips and fuselage) to create inherent stability characteristics. The distribution and configuration of rotors are optimized so that the aircraft naturally resists unwanted rotations and maintains stable flight even when one rotor fails. This local arrangement of rotors creates different stability qualities in different parts of the aircraft, making it easier to control without extensive professional training.
3Ease of manufacture
If fixed wing aircraft are used for personal aviation, then affordable operation is achieved, but hangar or ramp space and air strip infrastructure are required increasing overall cost
Solution Approach 1:
The VTOL aircraft combines multiple flight capabilities in one platform: vertical takeoff and landing like a helicopter, forward flight efficiency like a fixed-wing aircraft, and the ability to operate from locations without traditional air strips. This multi-functional design eliminates the need for specialized infrastructure such as hangars and paved runways, allowing operation from grass fields, beaches, or other open spaces, thereby increasing versatility while maintaining affordability.
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 design allows for safe, efficient, and accessible vertical takeoff and landing capabilities, reducing operational costs and training requirements, enabling the VTOL aircraft to be used by non-professionals and providing a versatile transportation solution.
Implementation Method 1
The rotors may be electric ducted fans... Each rotor unit may generate thrust by rotation of a rotor vane
Implementation Method 2
Each rotor unit may be coupled to the fuselage via a rotating or pivoting chassis, which allows each rotor unit to provide directed thrust by movement of the rotor unit about at least one axis
Implementation Method 3
The control management system may include a flight control computer that receives inputs from a plurality of stability augmentation sensors
Implementation Method 4
The impact member may include a material or structure configured to absorb impact forces, decrease an effect on occupants
Data Source
AI summary
The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. The VTOL aircraft may include instructions to perform a degraded rotor landing protocol. The degraded rotor landing protocol may include adjusting a power to an operable rotor unit to control a rate of descent and/or slow a rate of acceleration toward a landing surface. The VTOL aircraft may be configured to impact the landing surface from a substantially vertical configuration, and adjust a thrust vector to cause the aircraft to come to rest in a generally upright configuration.