Convertible Aircraft Flight System Configuration Adaptation
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Solution Overview
Problem
Current aircraft designs are limited to specific configurations, such as helicopters or airplanes, which restrict their versatility and ability to utilize the advantages of multiple flight types without significant disadvantages.
Innovation Solution
A convertible aircraft system that can be converted into a helicopter, airplane, or gyroplane configuration using a unique flight system comprising a support spar, proximal and distal flight assemblies with lockable rotation mechanisms and hinge mechanisms, allowing for bistable movement of hinged blades to adapt to different flight configurations before, during, or after flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If an aircraft is designed as a fixed configuration (helicopter or airplane), then it can be optimized for specific flight conditions, but it cannot utilize the advantages of multiple flight types
Solution Approach 1:
The patent applies dynamics by making the aircraft structure changeable during operation. The flight assemblies can rotate between horizontal and vertical positions, and the second elongated portions can fold between extended and retracted positions, allowing the aircraft to dynamically adapt between airplane, helicopter, and gyroplane configurations based on flight requirements
Solution Approach 2:
The patent implements multi-functionality through flight assemblies that can serve multiple purposes. The same flight assemblies function as fixed wings in airplane mode, rotating rotors in helicopter mode, and can be locked in intermediate positions for gyroplane operation, eliminating the need for separate specialized aircraft
2Adaptability or versatility
If the aircraft structure is made complex to enable configuration changes, then versatility is improved, but manufacturing and operational complexity increases
Solution Approach 1:
The patent divides the aircraft into modular flight assemblies (proximal and distal) that can independently rotate and fold. Each assembly contains its own drive mechanism and control systems, allowing for standardized manufacturing of repeatable modules rather than custom-built complex structures
3Adaptability or versatility
If the hinged blade is allowed to rotate freely, then helicopter configuration is achieved, but unwanted rotation occurs in airplane configuration
Solution Approach 1:
The lockable rotation mechanism provides dynamic control over the flight assemblies. The mechanism can transition between locked and unlocked states, allowing the same structure to provide both rigid stability for airplane flight and flexible rotation for helicopter operation without requiring separate structural designs
4Force
If the second elongated portion is extended for helicopter configuration, then lift capability is improved, but drag increases in airplane configuration
Solution Approach 1:
The hinge mechanism enables the second elongated portions to dynamically adjust their position based on flight mode. In airplane configuration, they fold back to minimize drag; in helicopter configuration, they extend to maximize lift surface area, optimizing aerodynamic performance for each flight regime
Data Source
AI summary
A convertible aircraft system is provided that can convert to a helicopter configuration, an airplane configuration, or a gyroplane configuration before, during, or after flight. The convertible aircraft system includes a fuselage, a proximal flight assembly, a distal flight assembly, a support spar, and a tail assembly. The fuselage is the main structural body of the present invention. The proximal flight assembly and the distal flight assembly are the flight system of the present invention. The support spar provides an axis of rotation and a pole support for the proximal flight assembly and the distal flight assembly. The tail assembly provides stability during flight of the present invention. In more detail, the tail assembly may comprise at least one vertical stabilizer, at least one horizontal stabilizer, and at least one rudder in order to provide stability during flight of the present invention.