The main goal of the UP project is to develop an integrated set of simulation, analysis, test & validation tools, as well as design, develop and implement in hardware two complete Attitude and Orbit Control Subsystems – for a 1U Cubesat and a microsatellite.
PROJECT DESIGNATION | UP – Analysis, HW Implementation and Pre-Flight Validation of Nano/Microsat AOCS |
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PROJECT CODE | POCI-01-0247-FEDER-023916 |
MAIN OBJECTIVE | UP aims at performing technology maturation for Guidance, Navigation and Attitude and Orbit Control systems (GNC/ AOCS) applicable to nano-satellites (CubeSats) and micro-satellites up to 150kg, from the initial design up to the implementation, test and validation in space-compatible CPU and FPGA components. For the micro-satellite case, we have performed a preliminary co-design and performance assessment of an AOCS with Image Processing for the purposes of image stabilization using a mirror-based mechanism to guide an optical instrument for Earth Observation. |
INTERVENTION REGION | Norte |
BENEFICIARIES ENTITIES | Spin.Works |
APPROVAL DATE | 31-07-2018 |
BEGIN DATE | 17-09-2018 |
CONCLUSION DATE | 11-03-2021 |
TOTAL COST | 479.634,23 EUR |
FINANCIAL SUPPORT FROM EU | FEDER – 376.732,31 EUR |
UP’s main objective was to mature the guidance, navigation and orientation and orbit control (GNC/AOCS) technologies that Spin.Works developed throughout the years, and apply them to two case studies – a nano-satellite (CubeSats) and a micro-satellite – from the initial development phases to implementation, testing and validation on CPU and FPGA components representative of space operations.
In parallel, UP also included the preliminary co-design and performance evaluation, in the case of micro-satellites, of an AOCS system and image processing for stabilizing a mirror mechanism for an optical Earth Observation instrument.
The goals achieved with the execution of the UP project were:
– Implementation and operationalization of a software toolset in support of integrated AOCS subsystems development for generic space missions, and its immediate application to two case studies – a small Cubesat (1U or 2U), and a micro-satellite up to 150kg;
– Multidisciplinary preliminary design (orbit analysis, propulsion system, structure, energy production system, automatic piloting) of a micro-satellite equipped with a high-resolution optical camera (1m/pixel), guided by a mirror mechanism that allows optimize your final image quality;
– Demonstration of the ability to cover the entire AOCS software development cycle and hardware implementation, from requirements analysis to final testing and validation of the subsystem;
– Obtaining performance statistics applicable to AOCS sub-systems for CubeSats, and in particular image-aided AOCS sub-systems applied to Earth Observation micro-satellites with high-resolution optical instruments
A document describing the main achievements and developments carried out in UP is available here.
T. Hormigo, D. Esteves, A. Santos, G. Afonso, F. Câmara, Autonomous interplanetary mission design in a continued high operational cost scenario, 8th ESA International Conference on Astrodynamic Tools and Techniques (ICATT), June 2021
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