UAVs

UAV conversion from gas to electric and restoration 

The focus of the UAV Restructuring project was to establish groundwork for future UAV teams. The red plane was restored to flying conditions utilizing a DA100 gas engine. The white plane was retrofitted with an equivalent electric motor to the previously installed BT-86 Fuji gas engine along with an FPV camera for surveillance purposes. Both of these planes serve as the launchpad for future teams. This project was supported by AeroSpace Corporation.

Thermal Mapping UAV 

A lightweight, 3D-printed thermal-mapping UAV engineered for wildfire surveillance, this platform integrates an IR camera, GPS, and long-range telemetry to monitor remote terrain. Built from heatresistant ASA, reinforced with carbon-fiber rods, and validated through structural and aerodynamic testing, it’s designed for rugged field conditions. With extended battery life, hand-launch deployment, and reliable long-range data transmission, it offers a practical, cost-effective solution for detecting emerging hotspots across California’s wildfire-prone regions.

Disposable UAV: Light Duty Quadcopter 

The purpose of this project is to design and develop a quadcopter capable of fully autonomous flight using a waypoint-based navigation system. By integrating a flight-control module, the UAV is programmed to follow predetermined routes and complete missions with minimal human involvement. An FPV camera was added to provide real-time visual monitoring during flight, supporting mission oversight and operational awareness. Overall, the project aims to establish a reliable and adaptable platform for future advancements in autonomous aerial capabilities.

Design and development of a Low-cost UAV powered by turbo jet engine 

Charlie is a twenty-pound carbon fiber UAV powered by a 30-pound-force turbo jet engine, capable of carrying a ten-pound payload. Four layers of two twill carbon fiber formed the main bottom layer of her NACA 2412 air foil using a plastered 3d printed mold/ Seven Burch wood ribs were manufactured with a CNC to form her lateral support as well as structural reinforcement for the wind flaps. The carbon fiber lay also formed her D-box spar by wrapping the layup around a 3d printed lip that seconded as a gluing surface. The spar was limited by its manufacturing geometry so a gradient focus reinforcement of eight and six layers of carbon fiber spread form the center of her fuselage.

Composite UAV

The development of composite UAVs (Unmanned Aerial Vehicles) addresses the need for efficient, durable, and versatile aerial systems in industries like agriculture, surveillance, and disaster response. Traditional drones made from metal or plastic face limitations in weight, strength, and environmental resistance, reducing efficiency and cumbersome fabrication process. This project seeks to propose a low-cost fabrication process to fabricate a composite UAV.

Composite UAV Mold Development 

Using an off-the-shelf UAV, this project focuses on designing and constructing molds for UAV towards the path of final fabrication and assembly. To achieve this, non-destructive methods were employed to conduct various tests and create molds from the foam UAV. A 3D scan of the original UAV was used to develop a CAD model, which was then subjected to Ansys simulations to verify flight characteristics and performance. Followed by that high performance molds were developed to fabricate the UAV

Characterization and optimization of Turbojet engine for UAV 

This project aimed to evaluate the thermal and thrust properties of various fuels, including kerosene, diesel, Jet A, and E85, to determine the most suitable option to incorporate into a composite UAV. Using a 50 lbf turbojet engine, the team modified the test stand and installed thermocouples to measure temperatures at multiple points on the turbojet engine. The collected data provided valuable insights into performance, helping the UAV team understand what to expect when installing the turbojet engine onto their composite UAV.

Camber Line Morphing wing UAV 

This project details the design, development, and testing of a camber line morphing wing. The aim is to improve aerodynamic efficiency by eliminating hinged control surfaces, potentially reducing fuel burn by creating less drag. Simulations and tests were conducted to optimize the design. The project created a scalable prototype for future applications where more degrees of morphing can be added