Simultaneous spacecraft orbit estimation and control based on GPS measurements via extended Kalman filter

Habib, Tamer Mekky

doi:10.1016/j.ejrs.2012.11.002

Cited by 7 publications

(4 citation statements)

References 9 publications

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“…Such kind of data fusion is commonly known as 'orbital filter'. Several research papers describe the use of orbital filter for LEO, such as Zhou (2004), Chiaradia et al (2000), Choi et al (2010) and Habib (2013).…”

Section: Introductionmentioning

confidence: 99%

GPS-based orbital filter to reach the moon

et al. 2015

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Nowadays, global navigation satellite systems (GNSSs) are used for many new applications that go further than the original goal of providing position, velocity and timing for land, maritime and air applications. In particular, GNSS receivers have been adopted as main navigation system for several low Earth orbits (LEOs) missions, increasing the autonomy of the hosting spacecraft, reducing the networking operation costs. Accordingly, they result in an attractive solution even for higher Earth orbits. However, although many studies have shown that GNSS observations can also be obtained at altitudes above the GNSS constellations by using high sensitivity receivers, the use of these signals is still challenging because of their very weak power and the poor relative geometry between the receiver and the transmitters. In this paper, we describe the implementation of an orbital filter specifically designed for moon missions, which aims to improve the navigation performance achievable when using GNSS observations.

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Section: Introductionmentioning

confidence: 99%

GPS-based orbital filter to reach the moon

et al. 2015

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“…Orbital filters are widely used to improve the accuracy of the navigation solution provided by GNSS receivers. This is documented in Chiaradia et al (2000), Habib (2013), Pardal et al (2009) and many others. All of them use a Kalman Filter estimator for the positioning of a satellite in LEO.…”

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confidence: 70%

GNSS-based Orbital Filter for Earth Moon Transfer Orbits

et al. 2015

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Numerous applications, not only Earth-based, but also space-based, have strengthened the interest of the international scientific community in using Global Navigation Satellite Systems (GNSSs) as navigation systems for space missions that require good accuracy and low operating costs. Indeed, already successfully used in Low Earth Orbits (LEOs), GNSSbased navigation systems can maximise the autonomy of a spacecraft while reducing the burden and the costs of ground operations. That is why GNSS is also attractive for applications in higher Earth orbits up to the Moon, such as in Moon Transfer Orbits (MTOs). However, the higher the altitude the receiver is above the GNSS constellations, the poorer and the weaker are the relative geometry and the received signal powers, respectively, leading to a significant navigation accuracy reduction. In order to improve the achievable GNSS performance in MTOs, we consider in this paper an adaptive orbital filter that fuses the GNSS observations with an orbital forces model. Simulation results show a navigation accuracy significantly higher than that attainable individually by a standalone GNSS receiver or by means of a pure orbital propagation.

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“…An estimation and identification of parameters and control variables of electricmotor-driven motion system can be found in [31]. In space science, Habib used an extended Kalman filter to estimate the spacecraft position and velocity, and then applied a PD controller to control the system [32].…”

Section: B Literature Reviewmentioning

confidence: 99%

A Control Theoretic Approach to Simultaneously Estimate Average Value of Time and Determine Dynamic Price for High-Occupancy Toll Lanes

Wang

Jin

Yin

2021

IEEE Trans. Intell. Transport. Syst.

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The dynamic pricing problem of a freeway corridor with high-occupancy toll (HOT) lanes was formulated and solved based on a point queue abstraction of the traffic system [1]. However, existing pricing strategies cannot guarantee that the closed-loop system converges to the optimal state, in which the HOT lanes' capacity is fully utilized but there is no queue on the HOT lanes, and a well-behaved estimation and control method is quite challenging and still elusive.This paper attempts to fill the gap by making three fundamental contributions: (i) to present a simpler formulation of the point queue model based on the new concept of residual capacity, (ii) to propose a simple feedback control theoretic approach to estimate the average value of time and calculate the dynamic price, and (iii) to analytically and numerically prove that the closed-loop system is stable and guaranteed to converge to the optimal state, in either Gaussian or exponential manners.

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Simultaneous spacecraft orbit estimation and control based on GPS measurements via extended Kalman filter

Cited by 7 publications

References 9 publications

GPS-based orbital filter to reach the moon

GPS-based orbital filter to reach the moon

GNSS-based Orbital Filter for Earth Moon Transfer Orbits

A Control Theoretic Approach to Simultaneously Estimate Average Value of Time and Determine Dynamic Price for High-Occupancy Toll Lanes

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