Dimensionamiento conceptual y paramétrico de CubeSat Bus y payload para percepción remota óptica en VIS y NIR.
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Date
2025
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Universidad de Concepción
Abstract
La creciente disponibilidad de tecnologías espaciales comerciales (COTS) junto con los enfoques de Model Based System Engineering (MBSE), ha abierto nuevos conocimientos para el diseño, modelado y simulación de misiones CubeSats. En este contexto, el objetivo general de esta Memoria es desarrollar un modelo paramétrico conceptual actualizado que permita estimar el desempeño y los requisitos de diseño de payload ópticos para Cubesats (≥3U), considerando restricciones físicas, tecnológicas desde 2020 en adelante.
La metodología empleada integra la revisión del estado del arte en percepción remota y sistemas satelitales miniaturizados, análisis de componentes COTS a partir de bases de datos abiertas como Satsearch, implementación de ecuaciones de dimensionamiento en Python, siguiendo la estructura del CubeSat System Reference Model (CSRM).
Los resultados permitieron estimar la configuración mínima de payload óptico con resolución entre 3 y 5 metros a 600 km de altitud, considerando una distancia focal equivalente a tres veces el largo del satélite y una apertura de 9 cm. Esto fue posible mediante una simulación en FreeFlyer, en dos planos SSO de igual altitud e inclinación, pero con RAAN desfasados, usando tres estaciones terrestres (Santiago, Punta Arenas y Svalbard).
Se evaluaron escenarios variando el número de satélites y GSD de 25 y 50 m. Se selecciona 6 satélites por ser el menor tamaño de constelación que cumple con 2,07 pases/día mediante figuras de mérito como el Mean Coverage Gap y el Maximum Average Time Gap. Para comunicaciones se dimensionó el downlink en banda X (8,2 GHz) usando la empresa KSAT Lite, permitiendo tener como base de referencia una antena de 13 m para luego usar datos que nos lleven a identificar variables en la ecuación de enlace. Con una tasa de 12,5 Mbit/s se obtiene Eb/N0 ~11.15 dB, demostrando la factibilidad del enlace para el caso base.
Finalmente se concluye que la calidad de la imagen depende principalmente del diámetro de apertura del instrumento óptico del CubeSat, además, si se requiere mejor resolución espacial hay que considerar un satélite de mayores dimensiones. La comunicación en banda X (enlace descendente) permite una generación rápida de datos, pero todo dependerá de la capacidad de las estaciones terrestres para descargar datos. Aun así, el futuro es prometedor para este tipo de satélite.
The increasing availability of commercial (COTS) space technologies, along with Model Based System Engineering (MBSE) approaches, has opened up new insights for the design, modeling, and simulation of CubeSat missions. In this context, the overall objective of this paper is to develop an updated conceptual parametric model that allows estimating the performance and optical payload design requirements for CubeSats (≥3U), considering physical and technological constraints from 2020 onward. The methodology employed integrates a review of the state-of-the-art in remote sensing and miniaturized satellite systems, analysis of COTS components from open databases such as Satsearch, and implementation of sizing equations in Python, following the structure of the CubeSat System Reference Model (CSRM). The results allowed estimating the minimum optical payload configuration with a resolution between 3 and 5 meters at an altitude of 600 km, considering a focal length equivalent to three times the satellite length and an aperture of 9 cm. This was achieved through a FreeFlyer simulation in two SSO planes of equal altitude and inclination, but with phase shifted RAANs, using three ground stations (Santiago, Punta Arenas, and Svalbard). Scenarios were evaluated varying the number of satellites and GSDs of 25 and 50 m. Six satellites were selected as the smallest constellation size that meets 2.07 passes/day using figures of merit such as the Average Coverage Gap and the Maximum Average Time Gap. For communications, the X-band (8.2 GHz) downlink was sized using KSAT Lite, allowing a 13 m antenna to be used as a reference base and then using data to identify variables in the link equation. With a rate of 12.5 Mbit/s, the Eb/N0 obtained was ~11.15 dB, demonstrating the feasibility of the link for the base case. Finally, it is concluded that image quality depends primarily on the aperture diameter of the CubeSat's optical instrument. Furthermore, if higher spatial resolution is required, a larger satellite should be considered. X-band communication (downlink) allows for rapid data generation, but this will depend on the capacity of ground stations to download data. Even so, the future is promising for this type of satellite.
The increasing availability of commercial (COTS) space technologies, along with Model Based System Engineering (MBSE) approaches, has opened up new insights for the design, modeling, and simulation of CubeSat missions. In this context, the overall objective of this paper is to develop an updated conceptual parametric model that allows estimating the performance and optical payload design requirements for CubeSats (≥3U), considering physical and technological constraints from 2020 onward. The methodology employed integrates a review of the state-of-the-art in remote sensing and miniaturized satellite systems, analysis of COTS components from open databases such as Satsearch, and implementation of sizing equations in Python, following the structure of the CubeSat System Reference Model (CSRM). The results allowed estimating the minimum optical payload configuration with a resolution between 3 and 5 meters at an altitude of 600 km, considering a focal length equivalent to three times the satellite length and an aperture of 9 cm. This was achieved through a FreeFlyer simulation in two SSO planes of equal altitude and inclination, but with phase shifted RAANs, using three ground stations (Santiago, Punta Arenas, and Svalbard). Scenarios were evaluated varying the number of satellites and GSDs of 25 and 50 m. Six satellites were selected as the smallest constellation size that meets 2.07 passes/day using figures of merit such as the Average Coverage Gap and the Maximum Average Time Gap. For communications, the X-band (8.2 GHz) downlink was sized using KSAT Lite, allowing a 13 m antenna to be used as a reference base and then using data to identify variables in the link equation. With a rate of 12.5 Mbit/s, the Eb/N0 obtained was ~11.15 dB, demonstrating the feasibility of the link for the base case. Finally, it is concluded that image quality depends primarily on the aperture diameter of the CubeSat's optical instrument. Furthermore, if higher spatial resolution is required, a larger satellite should be considered. X-band communication (downlink) allows for rapid data generation, but this will depend on the capacity of ground stations to download data. Even so, the future is promising for this type of satellite.
Description
Tesis presentada para optar al título de Ingeniero/a Civil Aeroespacial.
Keywords
Satélites artificiales, Detectores ópticos, Ingeniería aeroespacial