Free-Wing Multirotor Layout for Stable Forward 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, and utilizing control surfaces to manage lift and stabilize the aircraft, reducing the need for additional stabilizing devices.
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 free to rotate around a horizontal axis rather than being fixed to the chassis. This dynamic configuration allows the wing to automatically adjust its angle of attack in response to wind conditions and flight phase, optimizing aerodynamic efficiency during takeoff, hover, and landing while reducing energy losses without requiring complex active control mechanisms
Solution Approach 2:
The free-wing configuration enables the wing to self-adjust to optimal angles based on airflow conditions without requiring active control systems. The wing automatically orients itself to minimize drag and maximize lift during different flight phases, particularly benefiting from self-adjustment during windy conditions, thereby reducing energy consumption without adding mechanical complexity
2Use of energy by moving object
If the aircraft is designed with fixed pitch angle for horizontal flight, then energy efficiency is improved, but the aircraft cannot adjust pitch for climbing or descending
Solution Approach 1:
The patent resolves this contradiction by making the wing dynamically adjustable through free rotation around a horizontal axis. This allows the wing to maintain optimal angle of attack for energy efficiency during horizontal flight while simultaneously enabling pitch adjustment for climbing and descending maneuvers, as the wing can reorient itself relative to the chassis based on flight requirements
Solution Approach 2:
The free-wing configuration provides multi-functionality by enabling the same wing structure to serve both as an energy-efficient lift generator during horizontal flight and as an adjustable aerodynamic surface for vertical maneuvers. The wing effectively performs multiple functions across different flight phases without requiring separate mechanisms for each mode
3Stability of the object's composition
If stabilization devices like gimbals are added to maintain constant horizontal angle, then camera stability is improved, but device complexity and weight increase
Solution Approach 1:
The patent extracts the stabilization function from separate mechanical devices like gimbals and integrates it into the free-wing configuration itself. The free wing naturally maintains constant pitch angle during horizontal flight through its aerodynamic properties, thereby providing inherent stabilization for mounted cameras without requiring additional complex stabilization mechanisms
Solution Approach 2:
The free-wing configuration provides self-stabilization during horizontal flight by maintaining a constant pitch angle through its aerodynamic design. This self-stabilizing property eliminates the need for external stabilization devices for cameras and other payloads, reducing both mechanical complexity and weight while maintaining stability
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 by reducing energy consumption by up to a third, improves reliability by minimizing mechanical complexity, and allows for stable horizontal flight without the need for stabilization gimbals, enabling efficient and stable operations in various flight modes.
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... enabling vertical takeoff and landing
Implementation Method 3
a fixed horizontal rotor... driven by vertical and horizontal engines
Data Source
AI summary
A multirotor aircraft that includes a chassis, three or more vertical rotors, one or more free wings and one or more fixed horizontal rotors. 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.