Mechanical Engineering student at UVM Honors College. Specialized in non-linear Sliding Mode Control (SMC) and automated fluid systems for aerospace applications.
Controller Type
Non-linear SMC
Integrator
RK4 (0.001s)
To solve the problem of coordinated aerial lifting, I developed a control architecture for two quadcopters tethered to a single mass. Standard PID fails under the non-linear pendulous disturbances of a payload; my implementation utilizes a **Sliding Surface** for finite-time convergence.
Geometry calculated via VFormationPlanner.m to maintain tension and avoid collisions.
Includes chattering reduction using boundary layer saturation ($\phi$).
function [u, s] = compute(obj, e, e_dot) % Sliding surface: s = e_dot + lambda * e s = e_dot + obj.lambda * e; % Equivalent Control u_eq = obj.lambda * e_dot; % Switching Control (Saturation for Chattering) if abs(s) <= obj.phi sat_s = s / obj.phi; else sat_s = sign(s); end u_sw = obj.eta * sat_s; u = u_eq + u_sw; end
Rocket propellant testing traditionally involves days of lab analysis. My team engineered an autonomous sampling device to reduce cycle times to **under 2 hours** by automating the fluid extraction and measurement process for UV/Vis and particulate analysis.
CAD & Prototype
Sprint 4 Finalized Design
"Device must function without nitrogen gas supply while maintaining enclosed atmosphere to prevent contamination."
40°
Formation Angle
0.001g
Sampling Precision
2.0hr
Cycle Goal
RK4
Integrator Model