Novel Algorithm for Tracking LEO Satellites Using Doppler Frequency Shift Technique

Rouzegar, Hossein; Nasirian, Mehrzad; Ghanbarisabagh, Mohammad

doi:10.1007/s11277-017-4291-3

Cited by 11 publications

(6 citation statements)

References 3 publications

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Section: Introductionmentioning

confidence: 99%

“…Another way to obtain initial data for USS prediction models is to measure of the orbit parameters for its pass over the UGS using the telemetry or command radio signals [13][14][15][16]. The measured parameters for the UGS are the time and the Doppler shift of the frequency of the received radio signal [16][17][18]. In paper [13], a general method for determining the satellite orbit was proposed, based on improving approximations for the initial components of position and velocity by means of successive differential corrections from Doppler observations.…”

Section: Introductionmentioning

confidence: 99%

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Orbit Determination Methods For LEO Satellites From Probabilistic Analysis, Circular Motion Model And Single Pass Doppler Measurements

Спиридонов

Saetchnikov

Ушаков

et al. 2021

2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)

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The Doppler m easurements o f the telemetry radio signals nanosatellite CubeBel-1 for a single pass over the Belarusian State University ground station w ere carried out. Two methods for orbit determ ination of a small satellite are considered. The first m ethod is based on the SGP4 m odel and requires additional information from the NORAD TLE catalog o f the satellite orbital parameters. An unknown sm all satellite is identified using the NORAD TLE catalog based on a probabilistic estimation o f the elevation angle and the Doppler frequency shift o f receiving telemetry signals. The second method is based on processing experim ental measurements o f the Doppler frequency of the telemetry radio signals and Keplerian circular motion m odel for the sm all satellite. It does not require additional information from the NORAD database o f satellite orbital parameters.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Orbit Determination Methods For LEO Satellites From Probabilistic Analysis, Circular Motion Model And Single Pass Doppler Measurements

Спиридонов

Saetchnikov

Ушаков

et al. 2021

2021 IEEE 8th International Workshop on Metrology for AeroSpace (MetroAeroSpace)

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“…An alternative way to obtain initial data for predictive models of the motion of a USSC is to determine the orbit based on measurements of the characteristics of radio signals of a telemetric or command radio link, which simplifies the hardware implementation and the cost of the measuring system [13,14]. The measured parameters for a budgetary ground receiving station (GRS) are the time and the Doppler frequency shift of the received radio signal [15].…”

Section: Introductionmentioning

confidence: 99%

Determination of the Orbit of an Unknown Ultra-Small Spacecraft Based on the Circular Perturbed Motion Model and Measurements of the Doppler Frequency Shift

et al. 2020

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In this work, the determination of the orbit of an unknown ultra-small spacecraft based on Doppler measurements of the telemetry signal frequency is studied. The reception and processing of telemetry radio signals was carried out by the ground station of the Belarusian State University. In the model of perturbed circular motion, the radio signals of a small satellite were processed and the parameters of its orbit were determined. Based on a probabilistic estimate of the elevation angle and Doppler frequency shift of an ultra-small spacecraft from 10-20 measurements, a set of orbital parameters is determined for the estimated time of receiving telemetry signals. For antenna systems, the dynamics of changes in the elevation angle, azimuth, and Doppler frequency shift of telemetry radio signals for the next flights of an unknown ultra-small spacecraft was predicted. The calculated absolute errors in predicting the elevation angle, azimuth, and Doppler frequency shift did not exceed 3 • , 3 • and 250 Hz, respectively, which is sufficient for successful telemetry reception and decoding. Using the NORAD database of orbital parameters, the Chinese nanosatellite LUOJIA-1 01 of the Cubesat (6U) format (number 43485 in the NORAD system) was identified.

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“…To achieve the objectives of almost all formation flying missions, attitude coordination plays a vital role (Bondhus et al, 2005; Paita et al, 2016; Rouzegar et al, 2017). It includes keeping the antennas or imaging cameras on the target accurately for all the satellites in a formation, adjusting the satellite attitude/orbit for rendezvous and debris removal applications (Paita, 2017; Wang and Xue, 2018).…”

Section: Introductionmentioning

confidence: 99%

Vibration suppression and attitude control for the formation flight of flexible satellites by optimally tuned on-off state-dependent Riccati equation approach

Rouzegar

Khosravi

Sarhadi

2020

Transactions of the Institute of Measurement and Control

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In this paper, vibration suppression and attitude control for the formation flight of flexible satellites using optimally tuned on-off SDRE (state-dependent Riccati equation) approach is discussed. A formation consisting of flexible satellites has highly nonlinear dynamics and the corresponding satellites are subject to vibrations as well as uncertainties due to the practical conditions. Vibrations that are mainly caused by flexible modes of the satellites disorganize the coordination and hinder the formation stability as well as decreasing its performance and lifetime. Hence, flexibility should be considered in formation model and the coordination control needs to address such challenges. Owing to capabilities of SDRE approach for nonlinear systems, it is used as the coordination control. Satellites are assumed to be equipped with thrusters as their actuators which requires the control to be applied as on-off pulses. To this end, an algorithm is suggested to efficiently convert SDRE control into on-off pulses. For optimal tuning of the controller, the particle swarm optimization (PSO) algorithm is employed. Stability of the system has also been analyzed via a Lyapunov-based approach utilizing the region of attraction concept. The proposed on-off SDRE approach has shown to effectively suppress the vibrations in the presence of uncertainties leading to the accurate coordination of the whole formation while consuming less energy. Simulation results show the capability, efficiency, robustness and stability of the suggested approach.

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Novel Algorithm for Tracking LEO Satellites Using Doppler Frequency Shift Technique

Cited by 11 publications

References 3 publications

Orbit Determination Methods For LEO Satellites From Probabilistic Analysis, Circular Motion Model And Single Pass Doppler Measurements

Orbit Determination Methods For LEO Satellites From Probabilistic Analysis, Circular Motion Model And Single Pass Doppler Measurements

Determination of the Orbit of an Unknown Ultra-Small Spacecraft Based on the Circular Perturbed Motion Model and Measurements of the Doppler Frequency Shift

Vibration suppression and attitude control for the formation flight of flexible satellites by optimally tuned on-off state-dependent Riccati equation approach

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