Tilting Fuselage Multirotor Aircraft for Faster Cruise and VTOL
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Solution Overview
Problem
Existing multirotor aircraft systems are limited by slow cruising speeds, high complexity, and high production and maintenance costs, with challenges in transitioning between vertical takeoff and landing and horizontal flight modes.
Innovation Solution
A tilting fuselage design that keeps wings and engines stationary relative to the flight path, allowing the aircraft's cockpit and cabin to rotate for different flight modes, utilizing propellers for lift and thrust, and incorporating a thrust controlling system to simplify flight control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If multirotor systems use conventional fixed-wing designs with stationary fuselages, then forward flight speed is improved, but vertical takeoff and landing capability is lost
Solution Approach 1:
The fuselage is made dynamically tiltable relative to the wings and propellers, allowing it to rotate between vertical (for hover) and horizontal (for forward flight) orientations. This dynamic reconfiguration enables the aircraft to switch between vertical takeoff/landing and high-speed forward flight modes, resolving the contradiction between speed and versatility.
Solution Approach 2:
The aircraft is divided into functionally independent segments: stationary wings with propellers for lift and thrust generation, and a separately tilting fuselage for mode transition. This segmentation allows the propulsion system to remain fixed while the fuselage adapts its orientation, enabling both vertical and horizontal flight capabilities.
2Adaptability or versatility
If tilt-rotor systems with large span propellers and turbo-prop engines are used, then vertical takeoff and landing capability is achieved, but device complexity and cost increase
Solution Approach 1:
Instead of tilting the propellers and engines as in conventional tilt-rotor designs, this invention tilts the fuselage while keeping the wings and propellers stationary. This inversion of the tilting mechanism simplifies the system by eliminating complex rotating engine mounts and propeller tilt mechanisms, reducing both device complexity and cost while maintaining VTOL capability.
3Ease of operation
If multirotor systems use electric motors and batteries, then maneuverability is improved, but weight increases and endurance decreases
Solution Approach 1:
The propellers serve multiple functions: they generate lift during vertical takeoff and hover, and generate forward thrust during horizontal flight. This multi-functionality eliminates the need for separate lift and thrust propulsion systems, reducing overall system weight while maintaining maneuverability through differential propeller control.
4Adaptability or versatility
If multirotor systems overcome gravity continuously with thrust, then vertical flight capability is maintained, but energy consumption increases
Solution Approach 1:
The aircraft changes its operational parameters by tilting the fuselage to transition between vertical and horizontal flight modes. During horizontal flight, the wings generate aerodynamic lift to support the aircraft weight, dramatically reducing the thrust required compared to continuous vertical hover. This parameter change from pure thrust-based support to aerodynamic lift support significantly reduces energy consumption.
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
The design achieves higher cruising speeds, reduces complexity and costs, and enhances safety and maneuverability, making it suitable for various sizes from small aircraft to airliners, with potential applications in urban and intercontinental transportation.
Implementation Method 1
The aircraft propellers produce forward thrust while wing shaped wings produce the lift
Implementation Method 2
rotating aircraft's cockpit and cabin (fuselage) for modes of the flight
Data Source
Figure 1~2
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Figure 5~6
AI summary
VTOL aircraft that takeoff and land as a multirotor and cruises as airplane. The aircraft comprises two major parts: First; winged carrier frame comprises wings, engines, propellers and landing gears. Second; tilting fuselage comprises cockpit, cabin and tail. Winged carrier frame is basically X/H frame multirotor that its thruster carrying arms are wing shaped. Aircraft vertically takeoff as multirotor after gaining safe altitude and forward airspeed then changes its flying axis that wings and thrust direction parallel to horizon. Lift generated by wings and thrust generated by thrusters that aircraft has basic airplane flying characteristics. Fuselage tilted to keep payload parallel to the horizon. Speed reduced, winged carrier frame and fuselage returned to multirotor for landing. It is easier to rotate fuselage than thrusters or wings. It is better to adjust thrust levels than vectoring to reduce the moving parts and aerodynamic effects.