Human Powered Aircraft

The Human Powered Aircraft project focuses on designing, constructing, and testing a lightweight, pedal-powered plane capable of sustained flight. The team developed a highly efficient aircraft structure, prioritising aerodynamic performance, structural integrity, and minimal weight to enable human-powered take off and flight. Using advanced materials and manufacturing techniques like 3D printing and laser cutting, the aircraft embodies innovative engineering solutions and extensive testing to optimise flight control, lift, and stability. 

Finite Element Analysis (FEA) was performed on the spar connection to verify its ability to handle the forces applied by the connected wing sections during flight. The analysis showed minimal stress and displacement in the spar connection, confirming its strength and reliability in supporting the tapered wing sections and maintaining structural integrity under load. 

Finite Element Analysis (FEA) was conducted on the wing attachments to assess their ability to handle the forces exerted by the main wing's weight. The simulation applied a force to account for a safety margin. Results showed low maximum stress and negligible displacement , confirming that the attachments can securely support the wing under operational conditions. 

Finite Element Analysis (FEA) was conducted on the chassis to evaluate its ability to support the aircraft’s weight under realistic load conditions. The results demonstrated the chassis’s strength and stability, confirming that it can effectively withstand the forces encountered during flight. 

Finite Element Analysis (FEA) was conducted to assess the seat's strength and stability under various load conditions. The simulations demonstrated that the seat can reliably withstand both operational and heavier loads, maintaining its structural integrity and ensuring stability. These results validate the seat's robustness for use in the aircraft. 

Performance testing of different aerofoils highlighted the balance between lift and drag across various taper ratios and angles of attack. The DAE31 aerofoil emerged as the optimal choice due to its superior lift-to-drag performance, particularly at higher angles, making it ideal for efficient flight. In contrast, the FX76MP140, while offering higher lift, was excluded due to its significantly increased drag, which would compromise aerodynamic efficiency. 

HPA Rudder Testing.mp4

Rudder Testing

This video demonstrates the functionality of the rudder, designed to ensure effective yaw control for directional stability during flight. The test validates the rudder's responsiveness and ability to achieve the required deflection angles for manoeuvrability.

HPA Elevator Testing.mp4

Elevator Testing

This video showcases the testing of the elevator, responsible for pitch control to manage the aircraft’s altitude. The test confirms its capability to deliver smooth and precise deflections within the required range, ensuring stability and performance during flight.

HPA Thrust Testing.mp4

Thrust Testing

This video demonstrates the thrust testing of the aircraft prototype. The prototype is run with its propeller controlled remotely and the thrust generated is measured at the tail of the chassis. The increasing readings on the scale reflect the propeller's capability to produce sufficient thrust for flight.

HPA Final Prototype.mp4

Wing Strength Testing

The video and image above show the prototype resting on two bins, with the wings supported at each end. This setup tests the structural strength and integrity of the wings, ensuring they can withstand the forces encountered during flight without deformation or failure.