Sensitivity of an extended Kalman filter 2. variation in the observation error levels, observation rates, and types of observations

Cicci, David A.; Ballard, Gary H.

doi:10.1016/0096-3003(94)90120-1

“…Orbit determination with measurements provided by a constellation of satellites is considered in [26] and [27]. The tracking and data relay satellite system (TDRSS) uses satellites in geostationary orbits to track satellites in lowEarth orbit (LEO), while the global positioning system (GPS) uses a constellation of satellites with pseudorange measurements, that is, range measurements with clock differentials, to determine the location of the user.…”

mentioning

confidence: 99%

Spacecraft tracking using sampled-data Kalman filters

Teixeira

¹

,

Santillo

²

,

Erwin

³

et al. 2008

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T he problem of estimating the state of a dynamical system based on limited measurements arises in many applications. For the case of a linear system with known dynamics and Gaussian noise, the classical Kalman filter (KF) provides the optimal solution [1], [2]. However, state estimation for nonlinear systems remains a challenging problem of intense research interest. Optimal nonlinear filters [3] are often infinite dimensional and thus are difficult to implement [4]. Within a deterministic setting, nonlinear observers are available for systems of special structure [5], [6]. Except for systems of special structure, however, approximate filters are usually implemented in practice.Two main approaches are available for approximate nonlinear filtering. The first approach is based on analytically or numerically linearizing the nonlinear dynamics and

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“…Unlike the study in [20,21], which considers either angle (two observations per satellite), angle and range (three observations per satellite), and angle, range, and range rate (four observations per satellite), we consider the case in which only range measurements are available (one observation per satellite). In addition, the sample rate in [20] was chosen to be 33 Hz, while we are interested in the ability to track under time-sparse measurements, available on a scale of only minutes or perhaps hours.…”

Section: Introductionmentioning

confidence: 99%

“…Orbit estimation with measurements provided by a constellation of satellites is considered in [20,21]. One scenario (TDRSS) considers the use of observing satellites in circular, equatorial, geosynchronous orbits to track satellites in low-Earth orbit, while another scenario (GPS) involves the use of a constellation of satellites with pseudo-range measurements (range measurements with clock error biases) to determine the location of the user.…”

Section: Introductionmentioning

confidence: 99%

Spacecraft Trajectory Estimation Using a Sampled-Data Extended Kalman Filter with Range-Only Measurements

Erwin

¹

,

Santillo

²

,

Bernstein

³

2006

Proceedings of the 45th IEEE Conference on Decision and Control

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)Air Force Research Laboratory AFRL/VSSV Space Vehicles 3550 Aberdeen Ave SE SPONSOR/MONITOR'S REPORTKirtland AFB, NM 87117-5776 NUMBER(S) DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTESSubmitted to 2006 American Control Conference, Minneapolis, MN. Government Purpose Rights ABSTRACTDetermining the trajectory of a body orbiting the Earth is a fundamental task in astrodynamics. In this paper we use a sampled-data extended Kalman Filter to estimate the trajectory of a target satellite when only range measurements are available from a constellation of orbiting spacecraft. We consider the ability of the filter to acquire the target satellite under time-sparse measurements, and to estimate the eccentricity and inclination of the target satellite's orbit. Our goal is to quantify tradeoffs among acquisition time, tracking accuracy, and measurement sample rate. In addition, when the orbits of the observing spacecraft are all equatorial, it is found that inclination maneuvers of the target satellite are unobservable. Abstract-Determining the trajectory of a body orbiting the Earth is a fundamental task in astrodynamics. In this paper we use a sampled-data extended Kalman filter to estimate the trajectory of a target satellite when only range measurements are available from a constellation of orbiting spacecraft. We consider the ability of the filter to acquire the target satellite under time-sparse measurements, and to estimate the eccentricity and inclination of the target satellite's orbit. Our goal is to quantify tradeoffs among acquisition time, tracking accuracy, and measurement sample rate. In addition, when the orbits of the observing spacecraft are all equatorial, it is found that inclination maneuvers of the target satellite are unobservable. SUBJECT TERMS

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“…As in [20,21], we employ the sampled-data (continuousdiscrete) extended Kalman filter [2, p. 188]. This extended Kalman filter involves continuous-time propagation of the state estimate as well as the pseudo-error covariance between measurements and data updates.…”

Section: Introductionmentioning

confidence: 99%

Spacecraft Trajectory Estimation Using a Sampled-Data Extended Kalman Filter with Range-Only Measurements

Erwin¹,

Bernstein²

2005

1

0

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)Air Force Research Laboratory AFRL/VSSV Space Vehicles 3550 Aberdeen Ave SE SPONSOR/MONITOR'S REPORTKirtland AFB, NM 87117-5776 NUMBER(S) DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTESSubmitted to 2006 American Control Conference, Minneapolis, MN. Government Purpose Rights ABSTRACTDetermining the trajectory of a body orbiting the Earth is a fundamental task in astrodynamics. In this paper we use a sampled-data extended Kalman Filter to estimate the trajectory of a target satellite when only range measurements are available from a constellation of orbiting spacecraft. We consider the ability of the filter to acquire the target satellite under time-sparse measurements, and to estimate the eccentricity and inclination of the target satellite's orbit. Our goal is to quantify tradeoffs among acquisition time, tracking accuracy, and measurement sample rate. In addition, when the orbits of the observing spacecraft are all equatorial, it is found that inclination maneuvers of the target satellite are unobservable. Abstract-Determining the trajectory of a body orbiting the Earth is a fundamental task in astrodynamics. In this paper we use a sampled-data extended Kalman filter to estimate the trajectory of a target satellite when only range measurements are available from a constellation of orbiting spacecraft. We consider the ability of the filter to acquire the target satellite under time-sparse measurements, and to estimate the eccentricity and inclination of the target satellite's orbit. Our goal is to quantify tradeoffs among acquisition time, tracking accuracy, and measurement sample rate. In addition, when the orbits of the observing spacecraft are all equatorial, it is found that inclination maneuvers of the target satellite are unobservable. SUBJECT TERMS

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Sensitivity of an extended Kalman filter 2. variation in the observation error levels, observation rates, and types of observations

Cited by 3 publications

References 1 publication

Spacecraft tracking using sampled-data Kalman filters

Spacecraft tracking using sampled-data Kalman filters

Spacecraft Trajectory Estimation Using a Sampled-Data Extended Kalman Filter with Range-Only Measurements

Spacecraft Trajectory Estimation Using a Sampled-Data Extended Kalman Filter with Range-Only Measurements

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