Autorotating Aerial Device Flap Control for Trajectory and Descent Speed
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Solution Overview
Problem
Existing autorotating aerial devices lack effective control over trajectory direction and descent speed, especially in varying environmental conditions, and often require complex packaging and high-cost manufacturing.
Innovation Solution
An autorotating aerial device with a housing member, an actuator, and a controller that adjusts the angle of attack of a flap portion on the wing member to switch between diving and autorotating modes, enabling improved control of trajectory direction and descent speed.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If conventional hard-landing deployment is used, then sensor delivery is simple, but manufacturing cost is high and flight path flexibility is poor
Solution Approach 1:
The patent applies dynamics by making the wing member's flap portion adjustable during flight. The actuator changes the flap angle dynamically, allowing the device to transition between autorotating mode (for flexible, slow descent) and diving mode (for fast, direct descent). This dynamic adjustment resolves the contradiction by enabling both flight path flexibility and cost-effective sensor deployment without requiring ruggedized sensors.
2Reliability
If parachute or guided parafoil arrest device is used, then sensor delivery is controlled, but packaging complexity increases and canopy must not collapse
Solution Approach 1:
The patent employs a disposable autorotating aerial device that eliminates the need for reusable parachutes or parafoils. The device is designed for single-use deployment, with no complex canopy structures that could collapse. The wing member with adjustable flap provides sufficient control for reliable sensor delivery, and the entire device can be discarded after use, simplifying packaging and eliminating the reliability issues associated with canopy collapse.
3Adaptability or versatility
If autorotating device with controllable vertical fin is used, then trajectory control is attempted, but weather resistance is poor and technical difficulties arise
Solution Approach 1:
The patent improves weather resistance while maintaining trajectory control by dynamically adjusting the flap angle on the wing member. Unlike fixed vertical fin designs that struggle in varying weather, this system can adapt its aerodynamic characteristics in real-time. The actuator modifies the flap position to compensate for weather conditions, enabling reliable trajectory control across diverse environmental conditions while maintaining the autorotating deployment advantage.
4Ease of manufacture
If autorotating device with integrated electro-mechanical structure is used, then manufacturing is low-cost and easy, but trajectory control is lacking
Solution Approach 1:
The patent resolves this contradiction by adding a dynamic flap adjustment mechanism to the cost-effective autorotating device. The actuator-controlled flap portion enables trajectory control capabilities while maintaining the simplicity and low manufacturing cost of the integrated electro-mechanical structure. The device retains its ease of manufacture through modular design, where the added actuator and flap control system integrate seamlessly with the existing autorotating mechanism.
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 device achieves improved control of trajectory direction and descent speed in various environmental conditions, including vertical descent, diving, quick recovery, and soft landing, while being lightweight and cost-effective.
Implementation Method 1
an autorotating aerial device, method of forming the autorotating aerial device and an autorotating aerial system
Implementation Method 2
a wing member coupled to the actuator, the wing member comprising a main wing portion and a flap portion adjustable with respect to the main wing portion
Implementation Method 3
the controller is configured to control the actuator to switch the autorotating aerial device between a diving mode of operation and an autorotating mode of operation based on adjusting an angle of attack of the flap portion
Implementation Method 4
switch the autorotating aerial device between a diving mode of operation and an autorotating mode of operation
Data Source
AI summary
Disclosed herein is are systems, devices, and methods for an autorotating aerial device which includes a housing member having disposed thereon an actuator and a controller configured to control the actuator. The device also includes a wing member coupled to the actuator, the wing member including a main wing portion and a flap portion adjustable with respect to the main wing portion. The controller is configured to control the actuator to switch the autorotating aerial device between a diving mode of operation and an autorotating mode of operation based on adjusting an angle of attack of the flap portion, the angle of attack being with respect to a lateral axis along the main wing portion.