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2007
DOI: 10.1017/s0373463307004134
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GNSS Receiver Autonomous Integrity Monitoring with a Dynamic Model

Abstract: Traditionally, GNSS receiver autonomous integrity monitoring (RAIM) has been based upon single epoch solutions. RAIM can be improved considerably when available dynamic information is fused together with the GNSS range measurements in a Kalman filter. However, while the Kalman filtering technique is widely accepted to provide optimal estimates for the navigation parameters of a dynamic platform, assuming the state and observation models are correct, it is still susceptible to unmodelled errors. Furthermore, si… Show more

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Cited by 37 publications
(23 citation statements)
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“…barometric altimeter, clock and Inertial Navigation System, INS) are also used [29]. [44], which will be discussed later in the V-B section. Fig.…”
Section: A Traditional Approaches For Integrity Controlmentioning
confidence: 99%
“…barometric altimeter, clock and Inertial Navigation System, INS) are also used [29]. [44], which will be discussed later in the V-B section. Fig.…”
Section: A Traditional Approaches For Integrity Controlmentioning
confidence: 99%
“…Therefore, to obtain the optimal solution, the reasonable stochastic model should be determined in real-time (Wang 2000;Moore andWang 2003, Hewitson andWang 2007;Geng and Wang 2008;Yang and Gao 2005). In this paper, without affecting the validity and efficiency of our WRA, for simplification, the covariance matrix Σ w was selected as a (6 × 6) matrix with spectral density of 0·2m 2 s − 3 as follows (Schwarz et al, 1989):…”
Section: Z E B O Z H O U a N D O T H E R S Vol 66mentioning
confidence: 99%
“…The three gyroscope and three accelerometer bias states are modeled by first order Gauss-Markov processes and the receiver clock error is modeled by a two-state ͑bias and drift͒ random process model ͑Huddle 1983; Pue 2003͒. The KF state vector has 17 elements, including position, velocity, attitude errors, accelerometer and gyroscope biases, and receiver clock bias and drift, plus 12 or more GNSS range bias states ͑Hewitson 2006; Hewitson and Wang 2007͒. Regardless of the states and error model employed, the state evolution model of the discrete EKF is described by…”
Section: Gnss/ins Integrationmentioning
confidence: 99%