Free-Wing Multirotor Layout for Stable Pitch Climb and Descent
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Solution Overview
Problem
Existing multirotor aircraft configurations face inefficiencies and complexities during vertical takeoff and landing, hover, and horizontal flight due to fixed connections between wings and propulsion systems, leading to energy losses, mechanical complexity, and reliability issues, especially in windy conditions.
Innovation Solution
A multirotor aircraft design featuring a chassis with three or more vertical rotors, a free wing that rotates freely around a horizontal axis, and a fixed horizontal rotor, allowing for constant pitch angle flight during climbing and descending, reducing energy consumption by distributing weight on the wings and using vertical rotors primarily for lift and horizontal rotors for forward thrust.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If the wing and propulsion system are fixed in relation to the chassis, then the structure is simple and rigid, but energy losses and inefficiencies occur during takeoff, landing, and hover especially in windy conditions
Solution Approach 1:
The patent applies the dynamics principle by making the wing freely rotatable around a horizontal axis instead of being fixed to the chassis. This allows the wing to dynamically adjust its orientation relative to the airflow during different flight phases (takeoff, hover, landing), optimizing aerodynamic efficiency in each condition without requiring complex active control systems. The free rotation mechanism enables passive adaptation to wind conditions while maintaining structural simplicity.
2Ease of operation
If aircraft with constant wing are built with chassis, wings and engines joined together rigidly, then the structure is stable, but the aircraft must adjust pitch angle to climb or lower which creates discomfort and requires additional stabilizing devices
Solution Approach 1:
The patent enables the wing to rotate freely around a horizontal axis, allowing it to maintain optimal aerodynamic orientation during climbing and descending flights. This dynamic adjustment capability eliminates the need for pitch angle changes of the entire aircraft structure, providing comfort for passengers or equipment while avoiding the need for complex stabilizing devices. The free-rotating wing adapts passively to flight conditions, maintaining stability without additional mechanical complexity.
3Use of energy by moving object
If vertical rotors are used for both lift and forward movement, then the configuration is simple, but energy consumption increases during horizontal flight
Solution Approach 1:
The patent segments the propulsion functions by dedicating vertical rotors specifically to lift generation and a separate horizontal rotor to forward movement. This functional segmentation allows each rotor type to operate at optimal efficiency for its designated purpose. During horizontal flight, the horizontal rotor provides thrust while the vertical rotors maintain lift, reducing the energy consumption that would occur if vertical rotors had to provide both functions simultaneously.
Solution Approach 2:
The patent implements multi-functionality through the free-rotating wing design that can adapt its orientation to work effectively with different rotor configurations. The wing's ability to rotate freely allows it to function as an efficient lifting surface during horizontal flight when the horizontal rotor is active, while also providing aerodynamic support during vertical flight phases. This universal adaptability enables the system to optimize energy consumption across different flight modes without requiring additional components.
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 energy efficiency, reduces mechanical complexity, and improves reliability by allowing the aircraft to maintain a stable pitch angle during horizontal flight, eliminating the need for stabilization devices and minimizing energy consumption, while maintaining agility and control.
Implementation Method 1
a free wing that can rotate freely around its longitudinal axis, thus providing the aircraft with lift during horizontal flight
Implementation Method 2
three or more vertical rotors...produce thrust which is larger than the aircraft's weight and enable it to take off and land vertically
Implementation Method 3
one or more fixed horizontal rotors...push or pull the aircraft forward
Data Source
Figure 1a~1b
Figure 1c~1d
Figure 1e~1f
AI summary
A multirotor aircraft that includes a chassis, three or more vertical rotors, one or more free wings and on ore more fixed horizontal rotor. The free wing is attached to the chassis by an axial connection so that the angle of the free wing is changed relative to the chassis according the flow of air over the free wing. The fixed horizontal rotor enables the multirotor aircraft to lower and climb while flying forward at a stable horizontal pitch of the chassis.