Resonant Actuator Linkage for Stable Large-Angle Deflection
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Solution Overview
Problem
Existing actuator devices face challenges in achieving a high efficiency and stable operation, particularly in terms of the deflection angle ratio between movable portions and the need for stable resonance responses.
Innovation Solution
The actuator device is designed with specific configurations of connection portions and natural angular frequencies that satisfy certain equations, ensuring a large deflection angle ratio and suppressing unnecessary resonance, thereby enhancing efficiency and stability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a tilt rotor mechanism is used to achieve both vertical and horizontal flight, then flight versatility is improved, but device complexity increases
Solution Approach 1:
The aircraft is divided into modular components: a central body, detachable rotor assemblies, and separate propulsion units. This segmentation allows the same basic platform to be configured for different flight modes (vertical takeoff, horizontal flight, transition) by reconfiguring or detaching specific modules, thereby achieving versatility without permanently increasing overall system complexity.
Solution Approach 2:
The rotor assembly incorporates dynamic positioning mechanisms that allow the rotor to tilt and rotate between different orientations. This dynamic capability enables the single rotor structure to perform multiple functions (vertical lift, horizontal propulsion, transition modes) without requiring separate fixed structures for each flight mode, resolving the complexity-versatility tradeoff.
2Reliability
If multiple rotors are used for vertical takeoff and landing, then flight reliability is improved, but device complexity increases
Solution Approach 1:
Multiple rotor functions are merged into a single integrated rotor assembly that can operate in different configurations. The rotor system combines vertical lift capability with horizontal propulsion capability in one unified structure, reducing the number of separate rotor systems needed while maintaining reliability through redundant control mechanisms within the single assembly.
Solution Approach 2:
The rotor assembly is designed as a universal component that performs multiple functions: vertical lift generation, horizontal propulsion, and transition between flight modes. This multi-functionality eliminates the need for separate specialized rotors for different flight phases, thereby improving reliability through standardized components while reducing overall device complexity.
3Adaptability or versatility
If a tilting mechanism is added to enable rotor angle adjustment, then flight versatility is improved, but manufacturing precision requirements increase
Solution Approach 1:
The tilting mechanism incorporates localized adjustment features at critical points of the rotor assembly rather than requiring precision throughout the entire structure. By concentrating precision requirements to specific local areas (such as hinge points and mounting interfaces) while using more tolerant designs in other areas, the mechanism achieves the necessary angular adjustment capability without excessively high overall manufacturing precision requirements.
Data Source
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AI summary
An actuator device includes a support portion; a first movable portion; a second movable portion; a first connection portion that connects the first movable portion and the second movable portion to each other such that the first movable portion is swingable around a first axis; a second connection portion that connects the second movable portion and the support portion to each other such that the first movable portion is swingable around the first axis by vibrating the second movable portion; and a drive unit that applies a drive force to the second movable portion. Two natural angular frequencies ω1 and ω2 (where ω1 < ω2) for vibration of the first movable portion and the second movable portion around the first axis satisfy one of the following equation (1) and equation (2) and do not satisfy the other, [Equation 1] 0<1−ω1ωii2≤0.2 [Equation 2] 0<ω2ωii2−1≤0.2 In the above equations, ωii = (ki/ji)1/2, ki is a torsional spring constant of the first connection portion around the first axis, and ji is an inertia moment of the first movable portion around the first axis.