The whole Cubesat functionality depends on the integrity of its subsystems. For that reason, it is very important that the structure subsystem is built to be robust and reliable to ensure the protection of all other subsystems integrated within.
The goal is to develop a high performance Cubesat structure with the use of new materials, like composite materials. The use of composite materials for primary structure increases the strength and reduces the weight of existing Cubesat structures increasing at the same time the payload capacity.
Interplanetary missions require more robust and reliable structures so a Cubesat manufactured with composite materials could be the solution for those exploratory missions. One of the keys of a composite structure is the design in order to reduce manufacturing cost and stress concentration, especially on interference with other components.
The results of study on alternative structures designs for Cubesat, shows that one solid wall composite Cubesat design can stand up to 25g loads with a temperature range of -55°C (-67° F) to 90°C (194° F). Additionally, the vibration simulation results show a minimum vibration mode of 157.6 Hz. All of that was achieved with a weight of 183 grams.
Table of Contents
- Chapter 1. Introduction
- 1.1 CubeSat missions
- 1.1.1 Poly Picosatellite Orbital Deployer (P-POD)
- 1.1.2 CubeSat
- 1.2 Project objectives
- Chapter 2. Background
- 2.1 Missions
- 2.1.1 NASA Missions
- 2.1.2 ESA Missions
- 2.2 Structures
- 2.2.1 Kit CubeSat Structures
- 2.2.2 Custom Made CubeSat Structures
- 2.3 Requirements
- 2.3.1 Analysis Requirements
- Chapter 3. Alternative Cubesat structure
- 3.1 Introduction and Background
- 3.2 Additional requirements
- 3.3 Materials
- 3.3.1 Metallic materials
- 3.3.2 Nonmetallic materials
- 3.3.3 Material evaluation
- 3.4 Manufacture processes
- 3.4.1 Metallic Materials
- 3.4.2 Non-Metallic Materials
- 3.4.3 Joint Methods
- 3.5 Conceptual Study
- 3.6 Design Concept
- 3.6.1 Internal Columns
- 3.6.2 Shear panels
- 3.6.3 Shear angles
- 3.6.4 Rails
- 3.6.5 Feet Blocks
- 3.6.6 Assembly process
- 3.6.7 Payload interface
- 3.7 Finite Element Model
- 3.7.1 Finite element validation
- 3.7.2 Load Cases
- 3.7.3 Static Analysis
- 3.7.4 Vibration Analysis
- 3.8 Summary Results
- Chapter 4. Conclusions and Future works
Objectives and Key Themes
The objective of this project was to develop a high-performance CubeSat structure using composite materials to increase strength, reduce weight, and enhance payload capacity. The study aimed to explore alternative structural designs that would be robust and reliable enough for interplanetary missions while also reducing manufacturing costs and stress concentration.
- Development of a robust and lightweight CubeSat structure.
- Exploration of composite materials for CubeSat construction.
- Optimization of structural design to reduce manufacturing costs and stress concentrations.
- Evaluation of the structural performance under static and vibration loads.
- Assessment of the suitability of the design for interplanetary missions.
Chapter Summaries
Chapter 1. Introduction: This chapter introduces the concept of CubeSats and their missions, focusing on the importance of a robust and reliable structure for the successful operation of all integrated subsystems. It also outlines the project's objectives, which center around developing a high-performance CubeSat structure using advanced materials and design principles. The chapter lays the groundwork for the subsequent chapters by establishing the context and goals of the research.
Chapter 2. Background: This chapter provides a comprehensive overview of existing CubeSat missions (both NASA and ESA), various structural designs (kit and custom-made), and relevant requirements for CubeSat structures. It establishes a foundation for understanding the existing technological landscape and the challenges in designing a more advanced structure. The chapter systematically presents the context within which the proposed alternative structure design will be evaluated, covering established missions, designs, and specifications.
Chapter 3. Alternative Cubesat structure: This chapter presents the core of the research, detailing the proposed alternative CubeSat structure design using composite materials. It explores different materials, manufacturing processes, and joint methods, ultimately culminating in a detailed conceptual design. The design is then validated through finite element analysis, including static and vibration simulations, to demonstrate its robustness and suitability for demanding missions. The chapter meticulously explains the design choices, manufacturing techniques, and analytical processes employed to achieve the project's goals.
Keywords
CubeSat, Structure, Composite Materials, Static Analysis, Vibration Analysis, Finite Element Analysis, Interplanetary Missions, Lightweight Structures, Robustness, Reliability.
CubeSat Structure Design using Composite Materials: Frequently Asked Questions
What is the main focus of this document?
This document provides a comprehensive overview of a project focused on designing a high-performance CubeSat structure using composite materials. It includes a table of contents, project objectives, key themes, chapter summaries, and keywords. The core of the project involves developing a lightweight, robust structure suitable for demanding missions, including interplanetary travel.
What are the key objectives of the CubeSat structure project?
The primary objectives are to develop a robust and lightweight CubeSat structure using composite materials, explore the use of these materials in CubeSat construction, optimize the design to minimize costs and stress concentrations, evaluate the structure's performance under various loads (static and vibration), and assess its suitability for interplanetary missions.
What are the key themes explored in this project?
The key themes revolve around the design, analysis, and validation of a novel CubeSat structure. This includes material selection (metallic and non-metallic composites), manufacturing processes, finite element analysis (FEA) techniques (static and vibration analysis), and the overall goal of creating a structure that is both lightweight and robust enough for challenging space missions.
What chapters are included, and what is their content?
The document is structured into four chapters: Chapter 1 (Introduction) introduces CubeSats and the project's objectives; Chapter 2 (Background) provides context on existing missions and structures; Chapter 3 (Alternative CubeSat structure) details the proposed design, material selection, manufacturing processes, FEA, and results; and Chapter 4 (Conclusions and Future works) summarizes findings and outlines future research directions.
What types of analysis were conducted on the proposed CubeSat structure?
Finite Element Analysis (FEA) was used extensively to validate the design. Specifically, static and vibration analyses were performed to assess the structure's response to various load cases, ensuring its robustness and reliability under the stresses of spaceflight.
What materials were considered for the CubeSat structure?
Both metallic and non-metallic composite materials were evaluated for their suitability in the CubeSat structure. The selection process considered factors such as strength-to-weight ratio, manufacturing feasibility, and overall cost-effectiveness.
What are the advantages of using composite materials in CubeSat construction?
The use of composite materials offers several advantages, including increased strength and stiffness, reduced weight, improved payload capacity, and potentially lower manufacturing costs compared to traditional materials. This is crucial for maximizing the capabilities of a CubeSat within its size and weight constraints.
What is the significance of this research for interplanetary missions?
The development of a lightweight yet robust CubeSat structure is particularly relevant for interplanetary missions. The reduced weight translates to lower launch costs, while the enhanced strength and reliability ensure the successful operation of the spacecraft during the challenging conditions of interplanetary travel.
What are the key words associated with this project?
The key words summarizing this research include: CubeSat, Structure, Composite Materials, Static Analysis, Vibration Analysis, Finite Element Analysis, Interplanetary Missions, Lightweight Structures, Robustness, and Reliability.
- Quote paper
- Gustavo Cotta Vallina (Author), 2014, Alternative structure design for Cubesat, Munich, GRIN Verlag, https://www.hausarbeiten.de/document/284992
