Oblique Rotor-Wing Aircraft Locking Mechanism
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
High-speed Vertical Takeoff and Landing (VTOL) aircraft designs face inefficiencies due to poor hover capabilities and excessive weight, requiring large propulsion mechanisms that increase drag and reduce efficiency during horizontal flight.
Innovation Solution
The oblique rotor-wing aircraft design incorporates a thrust-vectored propulsion system with multiple operable propulsion systems and a locking mechanism, allowing the rotor-wing to rotate and lock at various angles, decoupling lift generation from forward propulsion and enabling efficient transition between rotary and fixed-wing flight modes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If high-powered propulsion mechanisms are used for vertical thrust in high-speed VTOL aircraft, then vertical takeoff and landing capability is achieved, but weight increases and becomes inefficient during horizontal flight
Solution Approach 1:
The propulsion system is segmented into separate vertical thrust mechanisms (rotors) and horizontal propulsion mechanisms (fuselage engines). The vertical thrust rotors can be locked in place during horizontal flight, allowing the aircraft to use only the lighter fuselage propulsion systems for forward flight, thereby eliminating the weight penalty of carrying heavy vertical thrust mechanisms throughout the entire flight.
Solution Approach 2:
The aircraft employs a dynamic configuration where the rotor wings can rotate and lock at different angles relative to the fuselage. During vertical flight, the rotors are positioned to generate lift; during horizontal flight, they are locked in a streamlined position. This dynamic reconfiguration allows the aircraft to optimize its weight and drag characteristics for each flight phase.
2Power
If overly large propulsion mechanisms are installed to enable horizontal takeoff, then sufficient takeoff power is achieved, but efficiency decreases during cruise flight due to added weight and drag
Solution Approach 1:
The propulsion system is divided into fuselage-mounted engines for horizontal propulsion and rotor-wing systems for vertical lift. This segmentation allows the fuselage engines to be sized appropriately for horizontal flight without needing to be oversized for vertical takeoff, thereby improving cruise efficiency while maintaining sufficient takeoff power through the combined system.
Solution Approach 2:
The rotor-wing assembly serves multiple functions: it generates vertical lift during takeoff and landing, and can be locked in a streamlined position during horizontal flight to reduce drag. This multi-functionality eliminates the need for separate oversized propulsion mechanisms, improving overall energy efficiency across all flight phases.
3Speed
If rotor blades are locked orthogonal to the fuselage after takeoff, then horizontal flight capability is achieved, but transition between rotary and fixed wing modes becomes difficult
Solution Approach 1:
The rotor-wing assembly is designed to be dynamically reconfigurable, allowing smooth transition between rotary and fixed-wing modes. The rotors can rotate freely during vertical flight, then be gradually slowed and locked at an oblique angle relative to the fuselage for horizontal flight. This dynamic transition process is controlled and manageable, avoiding the difficulties of abrupt mode changes.
Solution Approach 2:
The aircraft employs parameter changes during mode transition, including varying rotor speed, adjusting rotor angle relative to the fuselage, and coordinating thrust from multiple propulsion systems. These controlled parameter changes enable smooth and manageable transition between flight modes, improving ease of operation.
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 enhances hover capabilities and allows for efficient long-range flight at higher speeds than current VTOL aircraft, potentially achieving supersonic capabilities while reducing weight and drag, and eliminating asymmetric responses and control coupling issues.
Implementation Method 1
The rotor-wing may rotate about an axis in a first flight mode for vertical takeoff and landing, and/or for hovering. The first flight mode may include one or more rotary flight mode(s) similar to a rotary-wing aircraft (e.g., a helicopter, etc.) wherein one or more rotary wing(s) and/or rotary blades revolve around an axis generating lift and/or thrust
Implementation Method 2
The oblique rotor-wing aircraft may include a thrust-vectored propulsion system. The thrust-vectored propulsion system may include multiple, separately operable propulsion systems. One or more of the multiple propulsion systems may drive the rotation of the rotor-wing about the axis in a first flight mode
Implementation Method 3
The oblique rotor-wing aircraft may comprise a locking mechanism that locks the rotor-wing at an angle oblique to the fuselage responsive to initiation of a second flight mode. During a second flight mode, the rotor-wing may be fixed at an angle oblique to the fuselage
Data Source
AI summary
An oblique rotor-wing aircraft may be capable of vertical take-off and landing, subsonic cruise, transonic cruise, and/or supersonic cruise. The oblique rotor-wing aircraft may comprise one or more of a fuselage, a rotor-wing, a thrust-vectored propulsion system, a locking mechanism, and/or other components. The rotor-wing may be rotatably coupled to the fuselage. The rotor-wing may rotate about an axis in a first flight mode for vertical takeoff and landing. The oblique rotor-wing aircraft may include a thrust-vectored propulsion system that drives the rotation of the rotor-wing about the axis. The thrust-vectored propulsion system may include multiple, separately operable propulsion systems coupled to the rotor-wing and/or the fuselage. The oblique rotor-wing aircraft may comprise a locking mechanism that locks the rotor-wing at an angle oblique to the fuselage responsive to initiation of a second flight mode. The rotor-wing may be fixed at an angle oblique to the fuselage during the second flight mode.