SUAS 2026 Development & Test

We developed a custom Ground Control Station software using Python and PyQt5 to integrate mission planning and telemetry into a single interface.

Communication with the flight controller was established via MAVSDK over TCP, enabling asynchronous monitoring of telemetry and autopilot statuses.

Autonomous flight codes were initially validated in Gazebo simulations, verifying basic commands, waypoint tracking, and area scanning behaviors.

The lap and mapping routes were combined into a single continuous waypoint sequence to streamline operations and reduce operator workload.

The mapping algorithm was configured to calculate the necessary Ground Sampling Distance and generate optimal parallel flight lines automatically.

We integrated WebODM via REST API, processing captured images incrementally so that partial orthophotos are available while the UAV remains airborne.

A manual target selection interface was developed, allowing the operator to view the generated map and manually click to define target coordinates for precise positioning.

Stable software was transferred to the main aircraft. We successfully tested the entire workflow, from manual map clicking to commanding payload release from the same interface.

We optimized mission time by measuring every individual stage, ensuring the manual targeting and deployment process maximized the total competition score within the flight window.

We selected a quadcopter configuration and began designing a three-layer modular frame to completely separate the payload mechanism from internal electronics.

Detachable motor arms were designed using carbon fiber tubes and robust metal clamps, significantly reducing transportation volume while maintaining structural rigidity.

SolidWorks Simulation was performed on the main plates under 10-15 MPa flight loads, allowing us to safely incorporate weight-reduction pockets and structural ribs.

Various payload deployment concepts were evaluated. A cross-shaped parachute system was selected for its manufacturing simplicity and reliable descent control.

A specialized servo-actuated protective cage mechanism was designed specifically to securely retain and reliably deploy the GP908 Beacon Disk.

A separate dual-door, spring-assisted payload mechanism was designed for the water bottle to ensure rapid release without the risk of incomplete deployment.

Comprehensive stress and force analyses were conducted using ANSYS. Key components were reinforced with carbon fiber to optimize the strength-to-weight ratio.

The drone was fully assembled. A structural support piece was integrated between the battery housing and legs to maximize overall frame stability.

Physical strength tests, including static load, motor thrust, and manual drop tests, were conducted to verify the reliability of the detachable connections and payload releases.

System architecture was planned. T-Motor MN5008 brushless motors were selected for their high thrust-to-weight ratio to maximize flight endurance and efficiency.

The Cube Orange Pixhawk was chosen as the flight controller for redundant IMU architecture, alongside an Arducam 5 MP Global Shutter Camera to prevent motion distortion.

A Raspberry Pi 5 was selected and integrated as the primary mission computer due to its balance of compact dimensions and computational performance for onboard tasks.

We began designing a custom modular Lithium-ion battery system, strictly ensuring each module remained under 100 Wh to comply with travel transportation limits.

Individual 1S5P battery modules were assembled using 4500 mAh cells, creating independent ~83 Wh energy blocks that are easy to maintain and replace.

Battery modules were connected in parallel and series to finalize the 6S10P architecture, providing a nominal voltage of 22.2 V and 45 Ah total capacity.

Electronic components, including the power distribution, flight controller, telemetry, and motor drivers, were tested independently on the bench for operational stability.

Full integration was achieved by mounting all electronics between the lower and middle frame plates, minimizing cable lengths and reducing wiring complexity.

Extensive manual flight tests were conducted to verify electronic stability and vibration levels, followed by the rigorous configuration and testing of RTL failsafe behaviors.