Session
Poster Session 1
Location
Salt Palace Convention Center, Salt Lake City, UT
Abstract
The ITASAT2 mission is a key advancement in CubeSat technology, building upon the progressive development of small satellite missions at the Instituto Tecnológico de Aeronáutica (ITA). As a continuation of the ITASAT and SPORT missions, ITASAT2 consists of three 16U CubeSats in a formation flight, designed to investigate critical space weather phenomena and perform technological demonstration of geolocation and formation flight. In addition to its scientific contributions and technological demonstration, the mission incorporates technological advancements to improve CubeSat design and integration processes. The ITASAT2 project is part of the progressive evolution of CubeSat missions at ITA, simultaneously addressing space weather research and the development of innovative technological solutions. Building on the heritage of the ITASAT and SPORT missions, ITASAT2 comprises three 16U CubeSats operating in formation flight, designed to enhance studies of ionospheric plasma dynamics, small-scale plasma structures, magnetic fields, and the radiation environment. This paper presents an advanced structural concept for a CubeSat based on a Design for Assembly, Integration, and Testing (AIT) approach. The proposed design emphasizes ease of assembly, integration, testing, and, if necessary, late-stage disassembly. In particular, the structure incorporates a "flower-like" configuration, where components are mounted directly on the CubeSat's shielding, thereby accommodating a high onboard equipment density while ensuring rapid access to internal systems for repairs or component replacements following environmental testing or transportation damage. This configuration optimally allows for the assembly and integration of three satellites simultaneously, ensuring swiftness and reduced dependence on space and ground support equipment. Moreover, the AIT design facilitates direct access to individual equipment for unit testing and enables the removal of specific components with minimal or no disassembly of surrounding systems, with the wiring architecture being considered from the earliest stages of development. The results presented in this work demonstrate the versatility of the design, highlighting its potential to streamline assembly processes and improve maintainability, thereby offering a robust and flexible solution for future CubeSat missions.
Document Type
Event
Development of ITASAT-2 CubeSat's Primary Structure with AIT-Oriented Design Now
Salt Palace Convention Center, Salt Lake City, UT
The ITASAT2 mission is a key advancement in CubeSat technology, building upon the progressive development of small satellite missions at the Instituto Tecnológico de Aeronáutica (ITA). As a continuation of the ITASAT and SPORT missions, ITASAT2 consists of three 16U CubeSats in a formation flight, designed to investigate critical space weather phenomena and perform technological demonstration of geolocation and formation flight. In addition to its scientific contributions and technological demonstration, the mission incorporates technological advancements to improve CubeSat design and integration processes. The ITASAT2 project is part of the progressive evolution of CubeSat missions at ITA, simultaneously addressing space weather research and the development of innovative technological solutions. Building on the heritage of the ITASAT and SPORT missions, ITASAT2 comprises three 16U CubeSats operating in formation flight, designed to enhance studies of ionospheric plasma dynamics, small-scale plasma structures, magnetic fields, and the radiation environment. This paper presents an advanced structural concept for a CubeSat based on a Design for Assembly, Integration, and Testing (AIT) approach. The proposed design emphasizes ease of assembly, integration, testing, and, if necessary, late-stage disassembly. In particular, the structure incorporates a "flower-like" configuration, where components are mounted directly on the CubeSat's shielding, thereby accommodating a high onboard equipment density while ensuring rapid access to internal systems for repairs or component replacements following environmental testing or transportation damage. This configuration optimally allows for the assembly and integration of three satellites simultaneously, ensuring swiftness and reduced dependence on space and ground support equipment. Moreover, the AIT design facilitates direct access to individual equipment for unit testing and enables the removal of specific components with minimal or no disassembly of surrounding systems, with the wiring architecture being considered from the earliest stages of development. The results presented in this work demonstrate the versatility of the design, highlighting its potential to streamline assembly processes and improve maintainability, thereby offering a robust and flexible solution for future CubeSat missions.
