VTOL Aircraft with Six Tilt-Propulsion Units
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Solution Overview
Problem
Current VTOL aircraft designs fail to achieve redundant and controllable vertical flight while maintaining speed, range, and payload capacity, often resulting in loss of aircraft and occupants due to propulsion unit failures, limited maneuverability, and susceptibility to Vortex Ring State.
Innovation Solution
A VTOL aircraft configuration with six synchronously rotatable propulsion units distributed around the aircraft, allowing for continued flight after propulsion unit failure, improved maneuverability, and reduced susceptibility to Vortex Ring State, using a combination of flapped wings and propulsion units for yaw control and thrust vectoring.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a helicopter configuration is used for VTOL flight, then vertical takeoff and landing capability is achieved, but speed and range are limited due to retreating blade stall and inefficiency
Solution Approach 1:
The aircraft divides the propulsion system into six separate propulsion units distributed across three wings, allowing independent control of each unit. This segmentation enables the aircraft to maintain vertical flight capability while achieving forward speed by coordinating the propulsion units, avoiding the retreating blade stall limitation of helicopters.
Solution Approach 2:
The wings are designed to be dynamically adjustable, transitioning from a vertical configuration for takeoff and landing to a horizontal configuration for forward flight. This dynamic reconfiguration allows the aircraft to optimize its aerodynamics for each flight mode, achieving both VTOL capability and high forward speed.
2Ease of operation
If a helicopter configuration is used for VTOL flight, then vertical flight capability is achieved, but range is limited due to power consumption and inefficiency
Solution Approach 1:
The propulsion system is segmented into six independent units that can be controlled separately, allowing the aircraft to optimize power distribution based on flight conditions. This enables efficient power usage during both vertical flight and forward flight, extending the aircraft's range compared to conventional helicopters.
Solution Approach 2:
The six propulsion units serve multiple functions: they provide vertical lift during takeoff and landing, generate thrust during forward flight, and can be independently controlled to optimize power consumption. This multi-functionality eliminates the need for separate systems for different flight modes, improving overall efficiency and range.
3Reliability
If redundant propulsion units are added to achieve continued flight after failure, then reliability is improved, but device complexity increases
Solution Approach 1:
The propulsion system is divided into six independent, identically configured units, each capable of providing sufficient thrust for continued flight if others fail. This modular segmentation simplifies the redundancy architecture compared to having multiple complex propulsion systems, as each unit is standardized and can be independently controlled.
Solution Approach 2:
Each propulsion unit is positioned at specific locations on the wings with identical characteristics, creating a symmetric distribution that simplifies control and redundancy management. This local uniformity allows the system to maintain balance and stability even when one or more units fail, reducing the complexity of failure compensation.
4Ease of operation
If six propulsion units are distributed around the aircraft, then maneuverability is enhanced, but device complexity increases
Solution Approach 1:
The propulsion system is segmented into six identical units positioned at the tips of three wings, creating a symmetric arrangement that simplifies control. This distributed segmentation allows enhanced maneuverability through independent control of each unit while maintaining a relatively simple overall architecture compared to concentrated propulsion systems.
Solution Approach 2:
The propulsion units are positioned asymmetrically at the wing tips rather than uniformly distributed, creating an optimized moment arm for maneuvering. This asymmetric positioning enhances rotational control and maneuverability while the modular nature of the units keeps the overall system complexity manageable.
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
Enables safe and stable continued flight after propulsion unit failure, enhances maneuverability, and reduces Vortex Ring State susceptibility, achieving VTOL flight with speed, range, and payload capacity comparable to fixed-wing aircraft.
Implementation Method 1
six synchronously rotatable, thrust producing propulsion units located about the lateral axis of the aircraft
Implementation Method 2
contain two or more flapped wing panels affixed outboard of the propulsion units to provide yaw control during vertical flight
Data Source
AI summary
A vertical takeoff and landing aircraft having a fuselage with three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are vertical for vertical flight, and horizontal for forward flight. The aircraft wings are placed such that the rear wing is above the middle wing which is placed above the front wing. The placement of each of the propulsion units relative to the center of gravity of the aircraft about the vertical axis inherently assures continued stability in vertical flight mode, following the loss of thrust from any one propulsion unit. The placement of the propulsion units, viewing the aircraft from the front, is such that each propulsion units' thrust wake does not materially disturb the propulsion unit to its rear. When engine driven propellers or rotors are utilized, flapped wing panels are attached outboard of the forward and/or rearward propulsion units to provide yaw control during vertical flight.