Constellation Computation Lab:

Abstract:

This project aims to balance the number of required satellites with the least amount of launches to reduce the cost of deploying the satellite constellation to orbit. The secondary objective is to offer direct connection to the maximum number of people over a 24 hour period, while also considering factors such as reducing orbital collisions and providing coverage to remote locations. The feasible constellation approaches were found using low dexterity test runs, where potential solutions were scored and costed based on a simulation of the 400 most populous cities. The results of the test runs were compared using a ratio of score to cost, and the top two constellations with the highest ratios were selected for a full 41,000 city simulation.

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Thermal Analysis of Geostationary Radiator:

Attitude Sensors and Actuators Lab:

Abstract:

This analysis focuses on the understanding and measurement of the capabilities of two attitude actuators (reaction wheel and control moment gyro) and one attitude sensor (MEMS rate gyro). The MEMS rate gyro is best at recording low-frequency angular velocities and positions. The reaction wheel measures angular velocity based on applied torques, with a momentum capability of 108 Nms. Using a bicycle wheel as a control moment gyro, the behavior follows the conservation of momentum principle. When a physical rate gyro is rotated on all axes, only the z-axis affects the wheel's behavior.

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Beam Buckling Lab:

Abstract:

The purpose of this lab is to study the buckling behavior of beams made of different materials and cross-sections and determine their maximum buckling load. The analysis will be conducted using the Euler Column method which estimates the beam's load versus displacement. Although not entirely accurate, the results provide a close approximation to real-world scenarios. It is essential to understand the buckling characteristics of a beam when designing a structure that must support a specific load.

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Aircraft Feedback Control:

Abstract:

The goal of this laboratory was to create a feedback control system for a fixed-wing aircraft via a numerical solution. This numerical solution was computed using ODE45 with the aircraft state variables to estimate a stable control system. These controls allowed for the simulation of aircraft performance given set input conditions.

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