New players have entered the space economy in recent years. It is primarily private companies that are altering the paradigm of the current business model. This is what is becoming known as NewSpace. The new players' goal is to privatise access to space and provide services in order to create a completely new economy based on space applications, with a particular emphasis on green solutions. The new launch service companies hold an important place among the new start-ups. They are the primary source of pollution in the Earth's environment from the space sector. The Orion Space System was created as a spin-off from Sirius Space Services in order to democratise and standardise access to reusable solutions for launchers operating at Guiana Space Center. The thesis focuses on the recovery solution developed for microlaunchers, which envisions a passive ballistic reentry with in-air capture under parachutes. A case study on Sirius 1's first stage is used to analyse the results. To determine the feasibility of the proposed solution, an accurate evaluation of the re-entry trajectory is required. This research is also necessary for the precise planning of the maritime recovery operations. A Python code is developed to define the loads acting on the stage during the ballistic reentry on Earth and to design the trajectory to follow. All of the simplified models studied in order to simulate the stage's behaviour in the real world are included in the software. The results are presented in the form of a Monte Carlo analysis of the relevant quantities for a reentry vehicle. Once the best strategy to follow during the reentry trajectory has been determined, a GNC loop is created in Matlab Simulink to complete the task. As actuators, on/off thruster pods placed at the top of the stage are used in the proposed solution. The navigation block with sensor model and full state estimator, the guidance logic, and the controller model based on LQR state feedback control combined with a PWPF modulator are all presented. A Monte Carlo analysis in a relevant scenario is used to test the robustness of the loop.
Negli ultimi anni nuovi attori stanno entrando nella space economy. Questi sono principalmente compagnie che vogliono cambiare il paradigma dell'attuale modello di business. L'obiettivo è quello di privatizzare l'accesso allo spazio e fornire servizi per creare un'economia completamente nuova attorno alle applicazioni spaziali, con un focus particolare sulle soluzioni verdi. Tra le nuove start-up un posto importante lo occupano quelle dedicate ai servizi di lancio. Queste aziende sono le principali fonti di inquinamento ambientale terrestre del settore spaziale. Orion Space System è nata come una branca di Sirius Space Services per democratizzare e standardizzare l'accesso a soluzioni riutilizzabili per i lanciatori che operano in Guyana Francese. Il focus della tesi è sulla soluzione di recupero progettata per microlanciatori, che prevede un rientro balistico e successivamente un aggancio in aria del paracadute. I risultati sono stati analizzati grazie a un caso studio sul primo stadio del Sirius 1. La soluzione proposta prevede un'accurata valutazione della traiettoria di rientro per determinare la fattibilità. Il suo studio è inoltre fondamentale per avere una pianificazione delle operazioni marittime di recupero. Un codice in python è stato sviluppato per definire i carichi agenti sullo stadio durante il rientro balistico sulla terra e per disegnare la traiettoria da seguire. Nel software sono presenti tutti i modelli semplificati studiati per simulare in maniera preliminare il comportamento dello stadio nella realtà. Una volta definita, grazie a questa analisi, la strategia migliore da seguire durante il rientro, un anello di controllo completo è stato sviluppato per eseguire il compito. La soluzione proposta presenta come attuatori dei thrusters on/off posizionati in cima allo stadio. Il blocco della Navigation con i modelli dei sensori e l'osservatore agli stati, la logica di guida, e il controllo basato su un regolatore quadratico lineare (LQR) in combinazione con un modulatore PWPF sono presentati nel dettaglio. La robustezza del controllo è stata testata con un'analisi Monte Carlo in ambiente rilevante.
Feasibility Analysis on the Re-Entry Trajectory of a Microlauncher First Stage
Pozzoli, Matteo
2021/2022
Abstract
New players have entered the space economy in recent years. It is primarily private companies that are altering the paradigm of the current business model. This is what is becoming known as NewSpace. The new players' goal is to privatise access to space and provide services in order to create a completely new economy based on space applications, with a particular emphasis on green solutions. The new launch service companies hold an important place among the new start-ups. They are the primary source of pollution in the Earth's environment from the space sector. The Orion Space System was created as a spin-off from Sirius Space Services in order to democratise and standardise access to reusable solutions for launchers operating at Guiana Space Center. The thesis focuses on the recovery solution developed for microlaunchers, which envisions a passive ballistic reentry with in-air capture under parachutes. A case study on Sirius 1's first stage is used to analyse the results. To determine the feasibility of the proposed solution, an accurate evaluation of the re-entry trajectory is required. This research is also necessary for the precise planning of the maritime recovery operations. A Python code is developed to define the loads acting on the stage during the ballistic reentry on Earth and to design the trajectory to follow. All of the simplified models studied in order to simulate the stage's behaviour in the real world are included in the software. The results are presented in the form of a Monte Carlo analysis of the relevant quantities for a reentry vehicle. Once the best strategy to follow during the reentry trajectory has been determined, a GNC loop is created in Matlab Simulink to complete the task. As actuators, on/off thruster pods placed at the top of the stage are used in the proposed solution. The navigation block with sensor model and full state estimator, the guidance logic, and the controller model based on LQR state feedback control combined with a PWPF modulator are all presented. A Monte Carlo analysis in a relevant scenario is used to test the robustness of the loop.| File | Dimensione | Formato | |
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https://hdl.handle.net/10589/197637