The problem
An airborne payload changes how the whole vehicle behaves. Center of gravity, mass distribution, and vibration affect flight stability and imaging, while the release mechanism must operate predictably under flight loads.
My contribution
- Co-led mechanical integration of the approximately 11 kg carbon-fiber coaxial octocopter.
- Owned mechanical design and integration of the payload, gimbal, and servo-actuated release system.
- Addressed center-of-gravity, vibration, and mass-distribution challenges through iterative redesign and flight testing.
Requirements that shape the design
Design development
Integrate the payload architecture
Coordinate payload, gimbal, and release packaging within the aircraft.
Resolve system interactions
Address center-of-gravity and vibration behavior through mechanical redesign.
Test in flight
Use flight testing to evaluate and refine the integrated system’s stability and reliability.
Engineering decisions
The mechanical architecture affects both flight and payload performance. Integration work considers the position and support of each subsystem, with mass distribution and vibration treated as vehicle-level design constraints.
Build & integration
I owned the payload, gimbal, and servo-actuated release integration while co-leading broader mechanical integration of the carbon-fiber aircraft.
Validation
Iterative redesign and flight testing guided improvements to stability and reliability. The project also focused on repeatable release operation and imaging stability; detailed release rates and vibration measurements are not published here.
Outcome
Integrated payload, gimbal, and release hardware on an approximately 11 kg coaxial octocopter, with mechanical decisions informed by flight behavior and system-level constraints.
Next iteration
Add flight-test imagery, payload packaging views, and measured release or vibration data where available.