Design and Development of Bat-Inspired Unmanned Aerial System for Mapping and Navigation

This project aims to develop a sonar-based Unmanned Aerial System (UAS) that mimics bat behavior using ultrasonic sound to form a spatial map around the aircraft to navigate through spaces and avoid obstacles. Utilizing a quadcopter design, two stacked carbon fiber plates form the central frame with each of the four booms extending from its corners to support the propulsion system. Its foremost compartment resembles the head of a Grey Long-Eared Bat, and a speaker that sits inside the mouth to emit ultrasonic pulses. These pulses are then received by 2 microphones that sit in the bat ear, allowing for real-time mapping and navigation. By incorporating speakers and microphones, a more cost-effective method of navigating and mapping is employed as opposed to using more common and expensive equipment integrated into UAVs such as cameras and sensors. SO.2 Ultrasonic Omni Lapel Lav Microphones and a 400EP125-NBWN speaker will be integrated to allow for ultrasonic-based mapping and navigation. The microphones will connect to a microcontroller, with signal processing with an ADC (analog-digital converter) if needed. The speaker will be connected to an amplifier and is controlled by the microcontroller, using PWM (pulse width modulation). Software will process the ultrasonic inputs and will generate output signals to the flight controller. Calibration will then be conducted to ensure accurate signal reading, emission, and distance measurement. The aircraft uses custom 3D-printed components fabricated using a Stratasys F170 Fused Deposition Modeling (FDM) 3D printer. Key fabricated components include housings for the 4 Electronic-Speed-Controllers (ESC), a modular battery box, a sliding door mechanism, and the bat-shaped head and ears. Each component is designed in SolidWorks to ensure compatibility with the UAS structure, with features that optimize modularity, minimize dead weight, and reduce drag. The design accounts for space constraints and clearance requirements to fit electronic components without reducing structural integrity. To validate the durability and performance of these 3D-printed parts, a Finite Element Analysis (FEA) was conducted, which helped assess stress distribution and strength under loads. This analysis ensures the structural integrity of the UAS, showing that the design withstands all forces during flight while maintaining a lightweight design. After integrating the electronic components necessary for flight, the UAS then underwent a hover test at approximately 5 feet, and roll, pitch, and yaw were simultaneously tested through this test. Controlled 90-degree and 180-degree rotations were done to evaluate yaw performance, the UAS moved forward and backward to test pitch performance, and side-to-side to test roll performance. The UAS maintained a steady flight with minimal drift, and response times remained within the expected limits. The total flight duration was approximately one minute, with smooth transitions and a controlled landing. More rigorous testing is required to validate that the aircraft meets all its requirements.