Hybrid Multicopter with Segmented Rotor and Wing Systems
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Solution Overview
Problem
Traditional airplanes require runways for takeoff and landing, limiting their location flexibility, while rotorcraft are less energy efficient and costly, and compound aircraft designs with both rotor and wing elements aim to offer a 'best of both worlds' solution for VTOL and cruise modes, but face challenges in energy efficiency and weight management.
Innovation Solution
A compound aircraft design featuring an array of rotors for vertical flight and wing elements for cruise flight, coupled with a central fuselage housing avionics and a pusher propeller for forward propulsion, along with a hybrid power system using liquid-fuel engines and electric motors, allowing for efficient transition between flight modes and accommodating a detachable cargo container.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If traditional rotorcraft design is used to achieve VTOL capability, then vertical takeoff and landing flexibility is improved, but energy efficiency deteriorates and operating costs increase
Solution Approach 1:
The aircraft is divided into two functional systems: a rotor system for VTOL operations and a fixed-wing system for cruise flight. The rotor system includes multiple rotors that can be independently controlled, while the fixed-wing system includes wings and a pusher propeller. This segmentation allows each system to operate optimally in its designated flight regime, resolving the contradiction between VTOL capability and energy efficiency.
Solution Approach 2:
The aircraft dynamically transitions between rotorcraft mode and fixed-wing mode based on flight requirements. During takeoff and landing, the rotor system provides vertical lift. During cruise, the aircraft transitions to fixed-wing flight where wings generate lift and the pusher propeller provides forward thrust. This dynamic mode switching resolves the energy efficiency contradiction by using the more efficient fixed-wing system for long-distance travel.
2Adaptability or versatility
If compound aircraft design with both rotor and wing elements is used, then both VTOL and cruise capabilities are achieved, but aircraft complexity increases
Solution Approach 1:
The rotor system serves multiple functions: it provides vertical lift during VTOL operations and can be configured to provide forward thrust during transition to fixed-wing flight. The fixed-wing system similarly serves dual purposes by providing lift during cruise and stabilizing the aircraft during mode transitions. This multi-functionality reduces the need for separate dedicated systems, thereby managing complexity while maintaining dual flight mode capability.
Solution Approach 2:
The rotor system and fixed-wing system are merged into a single integrated aircraft structure. The rotors are positioned on booms that extend from the fuselage, and the wings are configured to work in conjunction with the rotors. The pusher propeller is integrated with the rear fuselage structure. This merging approach allows the compound aircraft to achieve dual flight mode capability while managing structural complexity through unified design.
3Use of energy by moving object
If traditional airplane design is used for cruise flight, then energy efficiency is improved, but runway infrastructure requirement limits location flexibility
Solution Approach 1:
The flight operation is segmented into distinct phases: VTOL phase using the rotor system, transition phase where the aircraft converts from vertical to horizontal flight, and cruise phase using the fixed-wing system. This segmentation allows the aircraft to use the appropriate system for each phase, achieving both location flexibility during VTOL and energy efficiency during cruise.
Solution Approach 2:
The aircraft dynamically transitions between vertical and horizontal flight configurations. During takeoff, the rotor system provides vertical lift without requiring a runway. During cruise, the aircraft transitions to fixed-wing mode where wings generate aerodynamic lift and the pusher propeller provides forward thrust, achieving energy efficiency. This dynamic capability resolves the contradiction between location flexibility and cruise energy efficiency.
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 aircraft achieves efficient energy use and extended range by optimizing power distribution between rotor and wing systems, maintaining consistent center of gravity with cargo, and enabling flexible takeoff and landing capabilities.
Implementation Method 1
A rotor array provides vertical thrust for a vertical flight mode
Implementation Method 2
The wing structure is designed to generate a lifting force for the aircraft during horizontal motion
Implementation Method 3
a pusher propeller for forward propulsion
Implementation Method 4
a liquid-fuel engine coupled to a propeller and/or rotor motors
Data Source
Figure 1
Figure 2
Figure 3A~3B
AI summary
A hybrid aircraft embodies an array of rotors for vertical flight positioned on support booms and wing elements for cruise flight coupled to a central fuselage housing avionics and a pusher propeller for forward propulsion. The aircraft accommodates a cargo-carrying container with mating of the surfaces between container and fuselage and latching mechanisms for attaching and detaching the container and vehicle.