Projects

08/2024 - 05/2025

Objectives: 

Develop a low-cost SADM with sun-tracking capabilities and 2-axis controllability. Determine the voltage generated when the solar arrays are stowed, partially deployed, and fully deployed.

Overview: 

A 1-axis and 2-axis controllable SADM was designed and assembled for $625. The SADM variants are composed of hinges, and torsion spring and motor actuators. Tests evaluated the safety of the torsion spring and effectiveness, maximum deflection of the solar panels, and effectiveness of the blocking elements to prevent unintended hinge rotation. Component, integration, and system-level testing were conducted to identify faulty sensors, calibrate components, and verify the simultaneous operation of the components. The voltage generated by the body-mounted, partially deployed, and fully deployed solar array configurations was obtained.

08/2024 - 12/2024

Objectives:

Conduct a 2D CFD analysis based on the velocity, pressure, and temperature profiles of various reentry capsule designs subjected to supersonic and hypersonic flow.

Overview: 

ANSYS Fluent was used to simulate a sphere-cone and double-cone capsule within the supersonic (M = 3) and hypersonic (M = 20) flight regimes. The CFD setup and results showing the velocity, pressure, and temperature contours are provided. Comparing the CFD setup and results with existing literature showed that the setup and results are correct.

08/2023 - 05/2024

Objectives

Develop an attitude control system to provide 3-axis rotational controllability for a 12U CubeSat. 

Overview: 

An attitude determination control system (ADCS) system was designed and manufactured to provide 3-axis rotational controllability of a 12U CubeSat based on mission objectives and requirements. Trade studies were conducted and were used to shape the initial design of the mechanical, electrical, and GNC subsystems. As the electrical subsystem and GNC subsystem designs changed, the mechanical subsystem undergone multiple design iterations to improve the overall system. Mechanical components that were designed include the magnetorquers, reaction wheel, and reaction wheel mounts. In the GNC subsystem, the gyroscope and accelerometer were calibrated to improve the ADCS's accuracy and efficiency. These two sensors were used to obtain the roll and pitch angles of the CubeSat. Lastly, freshmen mechanical and programming teams were mentored.

04/2024

Objective:

Conduct a dynamics analysis of a spacecraft via quaternions.

Overview: 

Quaternions and Euler angles were used to model the orientation of a spacecraft as it underwent a rotation sequence.

3/2024

Objective:

Model the dynamics of a swinging pendulum mounted on a moving cart by applying Newton's, Lagrange's and Kane's method.

Overview:

The governing equations of a pendulum mounted on a moving cart were derived using Newton's, Lagrange's, and Kane's method. Four numerical solvers were used to model the system and verify the solutions in MATLAB. The influence of how the cart's applied force, cart's mass, pendulum's mass, and pendulum's starting angle impact the system's behavior was analyzed. Animations were created to visualize how those parameters influence the pendulum's amplitude and the cart's position.

3/2024

Objective:

Create and use a fourth order Runge-Kutta numerical solver to model the dynamics of a chaotic pendulum. 

Overview:

The governing equations of a baby-boot (chaotic pendulum) were derived using Lagrange's method. An Runge-Kutta 4 solver was created in MATLAB and was verified to be accurate by comparing its results to other solvers. The starting position, mass, and centroid's position of each rigid body were altered to examine the system's behavior. Animations were created to obtain a greater perspective on how the system behaves when various parameters are altered.

12/2023

Objectives:

Analyze the stability and controllability of the C-5A Galaxy aircraft at sea level. Create a closed-loop autopilot system to control the aircraft's roll, heading, and pitch angles.

Overview:

The open-loop stability of the C5-A aircraft operating at sea level conditions was analyzed. An auto-pilot control system was designed to control the aircraft's roll, heading, and pitch angles.

12/2023

Objective:

Design a dual-deployment 6'' diameter model rocket capable of delivering a 4 lb payload up to 10,000 ft.

Overview:

This project shows the design and assembly of the avionics-payload bay, design of the dual deployment recovery system, and flight simulations of a level three model rocket.

10/2023

Objective:

Launch and recover a 6'' diameter model rocket, which uses a J, K, or L class motor.

Overview:

This project shows the design, assembly, simulations, launch, and recovery of a level two model rocket. The avionics bay design will be first discussed, followed by the part-level and component-level assembly of the rocket. OpenRocket simulations list the stability and flight characteristics of the rocket. Lastly, details of the recovery system and post-flight examination will be discussed.