Comparison of gauging methods for Orbital’s GEOStarTM 1 Satellites

Yendler, Boris; Molinsky, Jason; Chernikov, Sergey; Guadagnoli, Daniel

doi:10.2514/6.2014-1810

Cited by 4 publications

(2 citation statements)

References 4 publications

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“…The thermal gauging method can measure the individual tank loads in a multitank system and bipropellant systems. The TPG has been implemented for the ABS1A satellite and GEOStartm1 satellites to compare the estimations carried out by different schemes, and the thermal gauging technique was able to estimate accurately with an uncertainty of less than 1 kg [16,19]. However, the nonuniform heat distribution when heat is applied to the tanks and nonuniform distribution of propellant incorporates the temperature gradients that need to be considered as TPG assumes no temperature gradients during the quantification.…”

Section: Introductionmentioning

confidence: 99%

Mathematical Modelling of a Propellent Gauging System: A Case Study on PRISMA

2023

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Propellant gauging is crucial for a spacecraft approaching the end of its lifespan. Current gauging systems for satellites typically have an accuracy rate of a few months to a year at the end of their operational life. Therefore, it is essential to determine the appropriate gauging system for mission operations. This research focuses on modeling the propellant gauging system for PRISMA, an Earth Observation (EO) satellite of the Italian Space Agency. The analysis centers on implementing algorithms that calibrate the remaining propellant mass in the satellite tank using traditional methods such as bookkeeping (BKP) and pressure-volume-temperature (PVT). To enhance accuracy in quantification, an unconventional approach called thermal propellant gauging (TPG) has been considered. Preliminary computations were conducted using data obtained from the PRISMA thermal model to understand the calibration accuracy of the three methods. At the end of its operational life, the BKP and PVT methods exhibited error rates of 4.6% and 4.8%, respectively, in calculating the mass. In contrast, the TPG method demonstrated a significantly higher precision with an error rate of 1.86%. However, at the beginning of the satellite’s operational life, the PVT and TPG methods showed error rates of 1.0% and 1.3%, respectively, while the BKP technique reported an error rate of 0.1%. Based on these findings, it has been concluded that combining the BKP and TPG approaches yields superior results throughout the satellite’s lifespan. Furthermore, the researchers have determined the specific time duration for which each of these distinct approaches can be effectively utilized.

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Section: Introductionmentioning

confidence: 99%

Mathematical Modelling of a Propellent Gauging System: A Case Study on PRISMA

2023

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“…Thrusters parameters and efficiency of firing mode (pulse or continues) may have different values; however, these values are taken as constant. An accumulated error occurs when time increases [5].…”

Section: Introductionmentioning

confidence: 99%

A Conjoint Analysis of Propellant Budget and Maneuver Life for a Communication Satellite

2021

Sakarya University Journal of Computer and Information Sciences

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Maneuvers require velocity augmentation to control a satellite at the defined orbit. The velocity augmentation provides achieving geostationary orbit, compensating orbital perturbation, orbit dispersion correction, and any other maneuver's operations for a communication satellite. All maneuvers and propellant consumption must be taken into account in the propellant budget for successful mission management. In this study, a straightforward method was proposed to calculate satellite maneuver life or associated propellant budget for general purposes. The method provides enough accuracy for general mission planning. However, communication satellite accurate end of life estimation, especially in the last three months is vitally important and depends on many factors. According to the performance requirement of procurement's standard, the propellant budget and associated satellite maneuver's life are calculated based on the worst-case or adverse three-sigma. The worst-case calculations include allocations for inefficiencies, velocity uncertainties, dispersions resulting from thruster firings, propellant residuals, the selected thrusting, and maneuver strategies' performance. High accuracy remaining propellant estimation is necessary for a successful end of life operation and decommissioning. The cost of early deorbit because of propellant misestimation is millions of dollars. Accurate remaining propellant and associated maneuver life analysis can be performed in different methods. The most common three methods are pressure, volume, temperature (PVT), bookkeeping (BK), and thermal propellant gauging (TPG). The propellant accuracy analysis shows that the propagation of uncertainties is related to system design, tank fill ratio, propellant load accuracy, orbital maneuver's inefficiency, pressure and temperature sensors, transducers, telemetry resolution, and error in equipment test data. Comparing the methods, PVT provides accuracy between ±27.81 kg to ±38.93 kg, depending on equipment size and accuracy. BK currently provides the best estimation and the highest gauging accuracy between ±9.83 kg to ±13.76 kg. TPG provides accuracy between ±10.52 to ±14.73 kg for some cases. However, the satellite operators request ±1 kg estimation of the remaining propellant to extend the lifetime and reduce costs. The satellite manufacturers should optimize propulsiıon and attitude control subsystem design and manufacturing, including propellant management device performance, applied sensors reliability and accuracy, and tank expansion performance over a mission life.

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