Flapping-Wing Linkage Assembly for Stable Hover and Maneuverability
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Solution Overview
Problem
Conventional rotary wing micro air vehicles (MAVs) lack the maneuverability, gust tolerance, and aerodynamic performance of biologically-inspired flapping-wing systems, which are essential for tasks like infrastructure inspection, surveillance, and search and rescue operations, due to their susceptibility to aerodynamic disturbances and noise levels.
Innovation Solution
A hover-capable flapping-wing aircraft design featuring a support frame, motor, pair of wings, and linkage assembly that translates motor torque into flapping motion, along with yaw and pitch actuation assemblies for control, utilizing lightweight composites and micro-electronics to achieve biomimetic flight capabilities similar to hummingbirds.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional rotary wing systems are used, then the aircraft can achieve stable flight, but maneuverability and gust tolerance are degraded
Solution Approach 1:
The patent implements dynamic flapping motion of wings instead of static rotary blades, allowing the aircraft to adapt its aerodynamic characteristics in real-time. The wings can change angle, amplitude, and frequency of flapping to optimize performance for different flight conditions, achieving both stability and maneuverability
Solution Approach 2:
The flapping wings generate lift through periodic upstroke and downstroke motions. This periodic action creates instantaneous lift direction changes that enable superior maneuverability and gust rejection compared to continuous rotary motion, while maintaining stable hover capability
2Adaptability or versatility
If flapping-wing systems are used, then maneuverability and gust tolerance are improved, but device complexity increases
Solution Approach 1:
The patent combines multiple functions into the linkage assembly: the same mechanism that drives wing flapping also controls pitch, roll, and yaw moments through coordinated actuation of links. This integration reduces overall system complexity compared to having separate control systems for each function
Solution Approach 2:
The linkage assembly serves multiple purposes: generating flapping motion, controlling wing pitch angle, adjusting stroke amplitude, and providing aerodynamic control surfaces. This multi-functionality reduces the number of separate components needed, managing complexity while achieving superior maneuverability
3Device complexity
If conventional rotors are used, then the structure is simpler, but aerodynamic performance degrades at low Reynolds number
Solution Approach 1:
The patent changes the operational parameters of the wings by varying flapping frequency, amplitude, and angle of attack dynamically. This allows the wings to operate efficiently across different Reynolds number regimes, maintaining superior aerodynamic performance where conventional rotors degrade
Solution Approach 2:
The wings utilize composite material construction with varying stiffness properties along the span. This allows the wings to maintain structural integrity while enabling flexible deformation during flapping, optimizing aerodynamic performance at low Reynolds numbers without excessive complexity
4Object-generated harmful factors
If flapping-wing systems are used, then noise levels are reduced, but manufacturing complexity increases
Solution Approach 1:
The patent employs flexible wing membranes or thin shell structures that naturally dampen mechanical vibrations and reduce noise generation during flapping. This passive noise reduction approach achieves quiet operation without adding active noise control systems, managing manufacturing complexity
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 enhances maneuverability, gust tolerance, and reduces noise, enabling efficient hovering and agile flight in various conditions, with improved lift production and stability, making it suitable for diverse civilian and military missions.
Implementation Method 1
a linkage assembly coupled to the support frame and configured to translate an output torque of the motor into flapping motion of the wings, wherein the linkage assembly comprises a first link coupled to a rotational output of the motor, a second link pivotably coupled to the first link at a first pivot joint, a third link pivotably coupled to the second link at a second pivot joint, and a fourth link pivotably coupled to the support frame and slidably coupled to the third link
Implementation Method 2
a pair of wings coupled to the support frame... configured to translate an output torque of the motor into flapping motion of the wings... enabling efficient hovering and agile flight
Data Source
AI summary
A flapping-wing aircraft includes a support frame, a motor coupled to the support frame, a pair of wings coupled to the support frame, and a linkage assembly coupled to the support frame and configured to translate an output torque of the motor into flapping motion of the wings, wherein the linkage assembly includes a first link coupled to a rotational output of the motor, a second link pivotably coupled to the first link at a first pivot joint, a third link pivotably coupled to the second link at a second pivot joint, and a fourth link pivotably coupled to the support frame and slidably coupled to the third link, and wherein the fourth link is coupled to a first wing of the pair of wings.