Personal Projects

Radio Controlled Quadcopter Drone

Tools Used:  SolidWorks (CAD, FEA, Flow Simulation), MATLAB / Simulink (PID Flight Dynamics), Momentum Theory, Arduino, MPU6050 IMU, A2212 1000KV Motors, 30A ESCs, PDB (5V BEC), and 3S 1300mAh LiPo Power Architecture.

Overview: Designed, analyzed, and optimized a high-performance FPV quadcopter drone, iterating from initial 3D CAD modeling to advanced structural and fluid dynamic validation. The engineering focus centered on optimizing the thrust-to-weight ratio (TWR), minimizing frame mass, resolving critical stress concentrations, and establishing a stable feedback control loop using an Arduino-based flight computer, MPU6050 IMU, 30A ESCs, and a 3S LiPo power architecture.

Iteration #2- optimized the frame geometry and mass down to 0.619kg, using Rankine-Froude propulsion theory and FEA stress maps to evaluate composite materials and increase arm base thickness for structural integrity. 

MATLAB trade-off studies: Hover power analysis justified selecting a 130mm propeller operating near optimal efficiency, while geometric optimization shaved 43g (6.5%) off the frame mass to achieve a calculated 8.08 TWR.

Static Structural Analysis (Solidworks FEA)

Applied a 12.25N downward load per arm in SolidWorks Static Simulation to evaluate structural stress under peak motor thrust. Mapped von Mises stress distributions and identified critical lever-arm stress concentrations at the arm-to-center-plate junctions. Discovered a material design deficit where ABS plastic yielded a minimum Factor of Safety of 0.747 (below the target 1.5 - 2.0 margin), providing structural data to justify increasing joint fillet radii and transitioning to high-strength composite materials (ex. carbon fiber or reinforced nylon) in future iterations. 

Propeller Downwash & Trajectory Analysis (SolidWorks Flow Simulation)

Simulated fluid flow around rotating propellers in SolidWorks Flow Simulation. Visualized airflow velocity trajectories up to 96.8m/s, analyzed the downwash slipstream cone, and identified tip vortex formation (induced drag) at the blade tips.

Closed-Loop Flight Control Dynamics (MATLAB / Simulink)

Modeled a 6-Degree-of-Freedom variable-mass body plant in Simulink using your drone's physical mass (0.619kg) and thrust values (12.25N). Built and tuned a closed-loop PID controller to stabilize attitude and position step responses within 1.5 seconds during simulated atmospheric disturbances.

Finalized Quadcopter Made in real life:

• 3D Printed(PLA) Motor frame and arms

• 4x A2212 brushless motors

• 4x ESCs (Electronic Speed Controllers) with yellow casing

• Power Distribution Board (PDB)

• XT60 battery cable / pigtail

• Arduino board (Uno R3)

• MPU6050 accelerometer and gyroscope module

• Dupont jumper wires (for 5V/GND logic power)

• Silver collet propeller adapters

• 1045 / 1045R propellers (CW and CCW)

Electromechanical Linear Actuator

Tools used:  MATLAB (analytical modeling & torque equations), SOLIDWORKS (3D CAD, motion study, FEA, & buckling analysis)

Overview:  This project details the design, kinematic sizing, and structural validation of an electromechanical linear actuator engineered to raise a 10kg payload (98.1N) at a steady velocity of 3.33mm/s(200mm/min) under a motor speed of 100RPM. Using a MATLAB analytical model based on lead screw power transmission equations, the required motor torque was calculated at 0.0839N·m to overcome axial loads and thread friction. Structural integrity was validated via Solidworks Simulation, yielding a peak Von Mises stress of 4.104MPa against a 620.4MPa yield strength (Factor of Safety >150) and a primary buckling load factor of 24,722, proving negligible deformation and absolute stability under static and dynamic loading.

Finalized CAD Model

Static Structural FEA (SOLIDWORKS)

Stress Distribution & FoS: Evaluated Von Mises stress concentrations under a 10kg (98.1N) downward payload, mapping a peak stress of 4.104MPa near top plate contact zones against a material yield strength of 620.4MPa to achieve a static Factor of Safety >150.  

Deflection & Strain Limits: Confirmed minimal deformation under load, recording a maximum displacement of 5.074 x 10^-3 mm and an equivalent peak strain of 9.922 x 10^-6 across the load-bearing frame.

Solar Thermal Evacuated Tube Energy Capture System

Tools Used: SOLIDWORKS Flow Simulation (Computational Fluid Dynamics (CFD), radiative heat transfer modeling, flow trajectories, and thermal surface plots.)  MATLAB (Transient data extraction, fluid thermal gradient modeling, and kinematic velocity profiling).

Overview: Designed, modeled, and optimized an inclined solar thermal evacuated tube collector system, carrying out conjugate heat transfer and computational fluid dynamics (CFD) simulations to evaluate energy absorption performance. The engineering focus centered on coupling radiative solar heat flux with internal fluid convection, mapping transient temperature gradients along the absorber height, and validating internal manifold flow velocity profiles under converged thermal solver iterations. 

CFD Setup & Radiative Heat Transfer

• Configured internal fluid domain with conjugate solid-fluid heat transfer using copper absorber elements and glass tube outer boundaries.  

• Applied radiative boundary conditions (Radiative Surfaces - Whitebody wall) and dynamic volumetric heat generation to model solar irradiance absorption. 

*The full CAD model on the bottom includes structural frame profiles and manufacturing features. For the CFD and CHT analysis, I created a defeatured simulation geometry to extract a clean fluid domain and prevent localized mesh skewness at non-critical interfaces.

Finalized CAD Model

Landing Gear Shock Absorber Assembly: Kinematic & Structural Design

Tools Used: SOLIDWORKS (3D Parametric CAD, Multi-Body Assembly Modeling, Dynamic Mating, and Motion Simulation Setup).

Overview: Designed and modeled a heavy-duty oleo-pneumatic landing gear shock absorber assembly engineered to dissipate high kinetic energy during aircraft touchdown impact. The project focused on mechanical linkage constraints, parametric sizing of telescoping components, and assembly motion verification to ensure smooth axial stroke compression without mechanical binding.

Finalized CAD Model

Wing Flapping Mechanism: Kinematic & Structural Design

Tools Used: SOLIDWORKS (3D Parametric CAD, Multi-Linkage Assembly Modeling, Motion Study Simulation).

Overview: Designed and modeled a symmetrical dual-wing flapping mechanism engineered to convert vertical linear input displacement into synchronized rotational wing actuation. The focus centered on optimizing linkage geometry, maintaining planar alignment across multi-bar joints, and verifying smooth dynamic flapping cycles without mechanical interference.

Finalized CAD Model

Arduino Robotic Arm & Servo Motor Gripper 

Tools Used: SOLIDWORKS (3D Parametric CAD, Multi-Axis Assembly Modeling, Motion Simulation), Arduino IDE (Embedded C/C++, PWM Servo Kinematics Control), Physical Prototyping (Micro/Standard Servo Integration).

Overview: Designed and modeled a multi-axis robotic arm featuring an end-effector mechanical gripper engineered for precise spatial manipulation. The project bridges parametric mechanical design with embedded electronics, coupling dynamic linkage kinematics in CAD with physical microcontroller PWM servo integration.

Finalized CAD Model

Engine Blower Design using AUTOCAD

Tools Used: Autodesk AutoCAD

Overview: Modeled a 3D direct-drive centrifugal blower system powered by a single-cylinder engine, integrating the scroll housing, drive shaft interface, rectangular duct, and structural mounting frame to ensure proper shaft alignment and vibration stability.

Finalized CAD Model