Structures and Materials Commons^™

Payload Selection To Correlate Shielding Performance With Molecular Structure And Elemental Composition For Rosisat: The Radiation Orbital Shielding Investigation Satellite, Chase Patterson, Jacob L. Blanton, Kylie Nager

Beyond: Undergraduate Research Journal

Exposure to space weather in the Low Earth Orbit (LEO) environment poses significant challenges to both the integrity and longevity of orbital hardware, as well as the health of astronauts, driving the necessity for improved means of radiation shielding for future missions. With a 1U CubeSat formfactor, ROSISat is a planned LEO mission that aims to characterize the radiation shielding capabilities of seven candidate materials: ultra-high molecular weight polyethylene, boron nitride, carbon nanotubes, boron nitride nanotubes with polyethylene fibers, carbon fiber reinforced composite, and aerographene, as well as two control materials: aluminum 6061 and ep33. By comparing the shielding performance …

Sal-E: Responsive Space Pathfinder Mission, Adrian Serniak, Kayla Wong

College of Engineering Summer Undergraduate Research Program

The main objective of the SAL-E mission is to grow the Cal Poly CubeSat Lab’s (PolySat) capabilities in rapid spacecraft design and testing, as well as to provide the current generation of students with the opportunity to design, test, integrate, and communicate with a satellite. This summer we will mainly be focusing on aspects of spacecraft test and integration, as we prepare for our satellite handoff in the Fall. Specifically, we will be conducting satellite assembly, Thermal Vacuum Chamber (TVAC) Testing, Vibrations Testing, and software validation and testing on the flight unit satellite. Students participating in this multidisciplinary SURP will …

Characterizing Heating And Resistance Properties Of Nichrome Burn Wire To Be Used In Cubesat Actuation, Noah Moix

Mechanical Engineering Undergraduate Honors Theses

This thesis investigates the use of Nichrome 60 wire as a burn wire mechanism, commonly utilized in CubeSats and other aerospace engineering applications requiring precise, single-use release systems. The experiment focused on characterizing the thermal and resistive behavior of Nichrome 60 wire under Joule heating conditions. Four wire configurations were tested: 34-gauge and 36-gauge wires, each at lengths of 1 inch and 2 inches. Each configuration was subjected to a constant current until thermal failure occurred. During testing, real-time measurements of electrical resistance and wire temperature were recorded. This data was used to generate resistance vs. temperature profiles for each …

A Systematic Study Into The Design And Utilization Of Burn Wire As A Means Of Tensioning And Releasing Spacecraft Mechanisms Through Applied Joule Heating, Chandler Dye

Mechanical Engineering Undergraduate Honors Theses

The joule heating characteristics of Nichrome burn wires, often used as a thermal cutting device in mechanisms designed to fasten and release CubeSat deployables, are examined in the following thesis. Wires ranging from 0.125 inches to 2 inches long, and diameters of 30 Ga and 40 Ga, are investigated through analytical calculations and thermal simulations based on heat transfer due to joule heating, and through physical circuitry-based experiments. The temperature data is used to generate heating curves to predict the time it takes for Nichrome wires to fail under varying testing parameters. This research aims to catalog a series of …

Uv Space Imager Enclosure Coating, David Silva Cortez, Victor Alexander Rempel Dekhtyar, Maria L. Muñoz

Mechanical Engineering

The goal of this project is to reduce the amount of stray light entering an ultraviolet (UV) imager through absorption. This report outlines the use of ZnO nanoparticles mixed in an epoxy matrix for use in a CubeSat enclosure. Through testing, our team verified that the ZnO and epoxy coating experienced a peak absorption between 360-370 nm. The epoxy mixture with the .75% by weight ZnO nanoparticles absorbed up to 99.9 % of UV light at its peak. The effect on material properties, such as Young’s modulus and ultimate tensile strength, was also tested. Tensile tests demonstrated that adding ZnO …

Redesign Of Cubesat For Beam Charging, Kuba Preis

Industrial and Manufacturing Engineering

This paper is intended to be a study in the applications of the design freedom granted by additive manufacture in the design of a 1U CubeSat frame. The main loads experienced by a CubeSat are structural (during launch) and thermal (solar radiation). Beam charging is an emerging technology which involves charging a CubeSat using a laser beam. In this paper, a CubeSat frame was redesigned to account for the structural loads induced during launch and the thermal loads induced when beam charging. The thermal, weight, design, and structural requirements for a new CubeSat design were derived. The 1U CubeSat frame …

Deployable Antenna For Cubesat, Mackenzie Thomas Lennon, Caleb Andrew Barber, David Matthew Galves

Mechanical Engineering

This project is a proof-of-concept ground model of a large deployable antenna designed for the small space requirements of CubeSats. This small deployment module is designed to fit a 2 m by 1 m reflective antenna inside a storage volume of with the dimensions 20 cm by 20 cm x 40 cm. The reflector will be deployed to a parabolic shape with the goal of modeling the reflector necessary for high frequency communication. Because this module is designed as a proof-of-concept for the deployable parabolic reflector specifically, no electrical components will be incorporated and will just focus on the deployment …

Design, Manufacture, Dynamic Testing, And Finite Element Analysis Of A Composite 6u Cubesat, Yanina Soledad Hallak

Master's Theses

CubeSats, specially the 6U standard, is nowadays the tendency where many developers point towards. The upscaling size of the standard and payloads entail the increase of the satellite overall mass. Composite materials have demonstrated the ability to fulfill expectations like reducing structural masses, having been applied to different types of spacecraft, including small satellites.

This Thesis is focused on designing, manufacturing, and dynamic testing of a 6U CubeSat made of carbon fiber, fiberglass, and aluminum.

The main objective of this study was obtaining a mass reduction of a 6U CubeSat structure, maintaining the stiffness and strength. Considering the thermal effects …

Improving And Expanding The Capabilities Of The Poly-Picosatellite Orbital Deployer, David Pignatelli

Master's Theses

The Poly-Picosatellite Orbital Deployer (P-POD) has undergone a series of revisions over the years. The latest revision, described in this Master’s Thesis, incorporates new capabilities like EMI shielding, an inert gas purge system, and an electrical interface to the CubeSats after they are integrated into the P-POD. Additionally, some mass reduction modifications are made to the P-POD, while its overall strength is increased. The P-POD inert gas purge system successfully flew, on a previous revision P-POD. The P-POD components are analyzed to a set of dynamic loads for qualification, and successfully undergoes random vibration qualification testing. The P-POD encounters some …

Feasibility Study Into The Use Of 3d Printed Materials In Cubesat Flight Missions, Daniel Fluitt

Master's Theses

The CubeSat Program has provided access to space for many universities, private companies, and government institutions primarily due to the low cost of CubeSat satellite development. While these costs are orders of magnitude lower than similarly capable nano-satellite missions, they are still outside of the budgetary constraints of many potential developers including university and high school clubs. Using 3D printed plastics in the production of CubeSat structures and mechanisms presents a large cost savings opportunity that will allow these institutions to participate in the development of these satellites, expanding the educational and scientific impact of the CubeSat Program.

Five rapid …