C&L Racing Steering and Suspension Christian Lau, Lorelai Lanning Project Mentor(s): Charles Pringle, PE; Jeunghwan “John” Choi, PhD
The objective of this project is to design, build, test, and produce an off-road RC Baja vehicle that can compete in the ASME RC Baja event. The goal was to make a system that is both light and strong enough to maintain its functionality effectively on rough terrain. The suspension and steering systems are essential components to keep the vehicle stable, structurally sound, and under precise control. Engineering principles from statics, dynamics, and mechanics of materials were applied to analyze key components such as control arms, shock towers, and steering elements. Calculations were performed to ensure that design requirements were met, including achieving a 180° turn within a 3-foot radius, limiting suspension deflection during a 1-meter drop, and maintaining acceptable stress and deflection limits for structural components. The final design incorporates an independent double wishbone front suspension and a solid rear axle to balance performance, simplicity, and reliability. Manufacturing methods included a combination of manual machining 6061 aluminum and 3D-Printing using PLA to optimize cost, fabrication time, and structural performance. Testing procedures, including drop tests, turning radius evaluations, and load-deflection testing using an Instron machine, were developed to validate the design against performance requirements. The results of the design and analysis indicate that the RC Baja vehicle meets the required engineering criteria and can withstand the demands of off-road competition. The project demonstrates the successful integration of engineering analysis, design optimization, and manufacturing processes to produce a functional and competitive RC Baja system. Presentation Type: Poster Presentation (May 21, 9:30am–3:00pm) Keywords : RC Baja, Suspension, Steering SOURCE Form ID: 36 The engineering problem addressed in this project was the safe, effective ejection and recovery of a satellite payload from a model rocket during its descent. The objective was to design a mechanism capable of ejecting a small rectangular prism-shaped satellite from a rocket tube. Current models often deploy payloads during fuselage separation, which is 10,000 ft AGL, but this project specifically focuses on deployment at 500 ft AGL during the descent phase to avoid high-altitude retrieval issues and radio frequency limitations. The system protects sensitive sensors from takeoff vibrations while ensuring the payload remains removable without tools for easy inspection. The engineering method utilized a spring- loaded deployment mechanism integrated into the rocket's middle body tube section. Initial designs involving side-door ejections were abandoned due to structural concern. The final method employs dual compression springs and solenoid latches to trigger ejection. Manufacturing processes included laser cutting 14-gauge aluminum for the payload walls and 3D printing internal components to avoid Faraday cage effects on wireless signals. Statics, dynamics, and mechanics of materials analyses were performed to ensure the assembly could withstand 40Gs of force at takeoff. Results from initial evaluations and performance predictions indicated that the design was flight ready. The deployment system utilized springs with a constant of 30 lbf/in to ensure reliable ejection even if the rocket was inverted. Testing in a vertical jig and high-speed videography at 240 FPS was used to verify the final ejection velocity of at least 0.5 m/s and trigger latency of less than 1 second. Presentation Type: Poster Presentation (May 21, 9:30am–3:00pm) Keywords: IREC, Rocket Payload, Deployment Mechanism, CubeSat, Satellite SOURCE Form ID: 25 IREC Rocket Payload: Deployment System Jace Leensvaart, Armando Nungaray, Jairus Philips Project Mentor(s): Charles Pringle, PE; Jeunghwan “John” Choi, PhD
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