Rotatable Wing Aircraft for Hybrid Flight Mode Transition
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Solution Overview
Problem
Existing UAV designs face inefficiencies and redundancies in flight modes, as hybrid systems attempt to combine fixed-wing and rotary-wing capabilities, often requiring additional control surfaces and propulsion systems, which complicates aerodynamic efficiency and control during transitions between flight modes.
Innovation Solution
An aircraft design featuring rotatable wings with integrated servo motors and thrust motors, allowing operation in both cruising and monocopter modes by altering wing rotation and thrust direction, utilizing the same aerodynamic surfaces for lift and control, and an active control system to maintain stability and efficiency across modes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple rotors are fused onto a fixed-wing airframe to achieve hybrid flight capabilities, then the aircraft can operate in both fixed-wing and rotary-wing modes, but the device complexity increases due to additional propulsion systems and control surfaces
Solution Approach 1:
The patent applies universality by enabling the fixed-wing airframe and propulsion systems to serve dual functions. The same wings and engines that provide forward thrust during fixed-wing flight are utilized as rotors during rotary-wing operation. The control surfaces are repurposed to function both as aerodynamic control elements during cruising and as rotational control surfaces during vertical flight, eliminating the need for separate rotor assemblies and reducing overall system complexity.
Solution Approach 2:
The patent implements dynamics by making the wings and propulsion systems dynamically reconfigurable. The wings can rotate from a fixed horizontal position during fixed-wing flight to a vertical position during rotary-wing operation. The propulsion systems dynamically adjust their orientation and function based on the selected flight mode, transitioning from providing forward thrust to generating rotational lift. This dynamic reconfiguration allows a single structure to adapt to multiple flight regimes without requiring permanently fixed additional components.
2Device complexity
If propulsion systems and control surfaces are rotated between flight modes to share components, then device complexity is reduced, but aerodynamic efficiency deteriorates during transitions between modes
Solution Approach 1:
The patent applies preliminary action by pre-positioning the wings and propulsion systems in optimal configurations for each flight mode before transitions occur. During fixed-wing flight, the wings are预先 set at the correct angle of attack and the propulsion systems are positioned to provide optimal forward thrust. When transitioning to rotary-wing mode, these components are预先 rotated to vertical positions. This preliminary positioning minimizes aerodynamic disturbances during transitions and ensures that the components are already in their most efficient configurations when each mode is engaged, thereby maintaining aerodynamic efficiency while reducing complexity.
3Device complexity
If the entire aircraft is rotated to change flight modes, then component sharing is maximized, but the loss of time increases during mode transitions
Solution Approach 1:
The patent applies segmentation by dividing the rotation operation into independent segments. Rather than rotating the entire aircraft structure, only the wings and propulsion systems are rotated independently from the fuselage. This segmented approach allows the mass of the aircraft to remain stationary while the functional components are repositioned, significantly reducing the time and energy required for mode transitions. The wings can be rotated to the required position without waiting for the entire aircraft to reorient, enabling faster transitions between fixed-wing and rotary-wing modes while maintaining full component integration.
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
Enables efficient transition between cruising and hovering modes with reduced drag and increased control capabilities, achieving structural efficiency and stability in both long-range flight and agile maneuvers, while minimizing the need for additional control systems.
Implementation Method 1
each wing having an airfoil with a leading edge and a chord
Implementation Method 2
a pair of thrust motors, each of which mounted on a corresponding wing and configured to provide a thrust in a leading direction of the airfoil
Data Source
AI summary
An aircraft including: a pair of wings rotatably coupled to opposing lateral sides of the fuselage and being rotatable relative to each other; a pair of servo motors, each connected to a corresponding wing and configured to rotate the corresponding wing in two rotational directions; a pair of thrust motors, each of which mounted on a corresponding wing; and a flight controller connected to the servo motors and to the thrust motors, and configured to control each servo motor and each thrust motor, such that the aircraft can be selectively operated in a cruising mode, such that the pair of wings are in a non-permanent-rotation-state about a yawing axis which extends at least substantially through the center of gravity, and a monocopter mode, in which the pair of thrust motors provide thrust in opposite directions so that the pair of wings are in a permanent-rotation-state about the yawing axis.