Kalman filter

For statistics and control theory, Kalman filtering, also known as linear quadratic estimation (LQE), is an algorithm that uses a series of measurements observed over time, including statistical noise and other inaccuracies, and produces estimates of unknown variables that tend to be more accurate than those based on a single measurement alone, by estimating a joint probability distribution over the variables for each timeframe. The filter is named after Rudolf E. Kálmán, who was one of the primary developers of its theory.

The Kalman filter keeps track of the estimated state of the system and the variance or uncertainty of the estimate. The estimate is updated using a state transition model and measurements. ${\displaystyle {\hat {x}}_{k\mid k-1}}$ denotes the estimate of the system's state at time step k before the k-th measurement y_k has been taken into account; ${\displaystyle P_{k\mid k-1}}$ is the corresponding uncertainty.

This digital filter is sometimes termed the Stratonovich–Kalman–Bucy filter because it is a special case of a more general, nonlinear filter developed somewhat earlier by the Soviet mathematician Ruslan Stratonovich.^[1][2][3][4] In fact, some of the special case linear filter's equations appeared in papers by Stratonovich that were published before summer 1961, when Kalman met with Stratonovich during a conference in Moscow.^[5]

Kalman filtering^[6] has numerous technological applications. A common application is for guidance, navigation, and control of vehicles, particularly aircraft, spacecraft and ships positioned dynamically.^[7] Furthermore, Kalman filtering is a concept much applied in time series analysis used for topics such as signal processing and econometrics. Kalman filtering is also one of the main topics of robotic motion planning and control^[8][9] and can be used for trajectory optimization.^[10] Kalman filtering also works for modeling the central nervous system's control of movement. Due to the time delay between issuing motor commands and receiving sensory feedback, the use of Kalman filters^[11] provides a realistic model for making estimates of the current state of a motor system and issuing updated commands.^[12]

The algorithm works by a two-phase process having a prediction phase and an update phase. For the prediction phase, the Kalman filter produces estimates of the current state variables, along with their uncertainties. Once the outcome of the next measurement (necessarily corrupted with some error, including random noise) is observed, these estimates are updated using a weighted average, with more weight being given to estimates with greater certainty. The algorithm is recursive. It can operate in real time, using only the present input measurements and the state calculated previously and its uncertainty matrix; no additional past information is required.

Optimality of Kalman filtering assumes that errors have a normal (Gaussian) distribution. In the words of Rudolf E. Kálmán: "In summary, the following assumptions are made about random processes: Physical random phenomena may be thought of as due to primary random sources exciting dynamic systems. The primary sources are assumed to be independent gaussian random processes with zero mean; the dynamic systems will be linear."^[13] Though regardless of Gaussianity, if the process and measurement covariances are known, the Kalman filter is the best possible linear estimator in the minimum mean-square-error sense. ^[14] It is a common misconception (perpetuated in the literature) that the Kalman filter cannot be rigorously applied unless all noise processes are assumed to be Gaussian.^[15]

Extensions and generalizations of the method have also been developed, such as the extended Kalman filter and the unscented Kalman filter which work on nonlinear systems. The basis is a hidden Markov model such that the state space of the latent variables is continuous and all latent and observed variables have Gaussian distributions. Kalman filtering has been used successfully in multi-sensor fusion,^[16] and distributed sensor networks to develop distributed or consensus Kalman filtering.^[17]

History

The filtering method is named for Hungarian émigré Rudolf E. Kálmán, although Thorvald Nicolai Thiele^[18][19] and Peter Swerling developed a similar algorithm earlier. Richard S. Bucy of the Johns Hopkins Applied Physics Laboratory contributed to the theory, causing it to be known sometimes as Kalman–Bucy filtering. Kalman was inspired to derive the Kalman filter by applying state variables to the Wiener filtering problem.^[20]Stanley F. Schmidt is generally credited with developing the first implementation of a Kalman filter. He realized that the filter could be divided into two distinct parts, with one part for time periods between sensor outputs and another part for incorporating measurements.^[21] It was during a visit by Kálmán to the NASA Ames Research Center that Schmidt saw the applicability of Kálmán's ideas to the nonlinear problem of trajectory estimation for the Apollo program resulting in its incorporation in the Apollo navigation computer.^[22]: 16

This Kalman filtering was first described and developed partially in technical papers by Swerling (1958), Kalman (1960) and Kalman and Bucy (1961).

The Apollo computer used 2k of magnetic core RAM and 36k wire rope [...]. The CPU was built from ICs [...]. Clock speed was under 100 kHz [...]. The fact that the MIT engineers were able to pack such good software (one of the very first applications of the Kalman filter) into such a tiny computer is truly remarkable.

— Interview with Jack Crenshaw, by Matthew Reed, TRS-80.org (2009) [1]

Kalman filters have been vital in the implementation of the navigation systems of U.S. Navy nuclear ballistic missile submarines, and in the guidance and navigation systems of cruise missiles such as the U.S. Navy's Tomahawk missile and the U.S. Air Force's Air Launched Cruise Missile. They are also used in the guidance and navigation systems of reusable launch vehicles and the attitude control and navigation systems of spacecraft which dock at the International Space Station.^[23]

Overview of the calculation

Kalman filtering uses a system's dynamic model (e.g., physical laws of motion), known control inputs to that system, and multiple sequential measurements (such as from sensors) to form an estimate of the system's varying quantities (its state) that is better than the estimate obtained by using only one measurement alone. As such, it is a common sensor fusion and data fusion algorithm.

Noisy sensor data, approximations in the equations that describe the system evolution, and external factors that are not accounted for, all limit how well it is possible to determine the system's state. The Kalman filter deals effectively with the uncertainty due to noisy sensor data and, to some extent, with random external factors. The Kalman filter produces an estimate of the state of the system as an average of the system's predicted state and of the new measurement using a weighted average. The purpose of the weights is that values with better (i.e., smaller) estimated uncertainty are "trusted" more. The weights are calculated from the covariance, a measure of the estimated uncertainty of the prediction of the system's state. The result of the weighted average is a new state estimate that lies between the predicted and measured state, and has a better estimated uncertainty than either alone. This process is repeated at every time step, with the new estimate and its covariance informing the prediction used in the following iteration. This means that Kalman filter works recursively and requires only the last "best guess", rather than the entire history, of a system's state to calculate a new state.

The measurements' certainty-grading and current-state estimate are important considerations. It is common to discuss the filter's response in terms of the Kalman filter's gain. The Kalman gain is the weight given to the measurements and current-state estimate, and can be "tuned" to achieve a particular performance. With a high gain, the filter places more weight on the most recent measurements, and thus conforms to them more responsively. With a low gain, the filter conforms to the model predictions more closely. At the extremes, a high gain (close to one) will result in a more jumpy estimated trajectory, while a low gain (close to zero) will smooth out noise but decrease the responsiveness.

When performing the actual calculations for the filter (as discussed below), the state estimate and covariances are coded into matrices because of the multiple dimensions involved in a single set of calculations. This allows for a representation of linear relationships between different state variables (such as position, velocity, and acceleration) in any of the transition models or covariances.

Example application

As an example application, consider the problem of determining the precise location of a truck. The truck can be equipped with a GPS unit that provides an estimate of the position within a few meters. The GPS estimate is likely to be noisy; readings 'jump around' rapidly, though remaining within a few meters of the real position. In addition, since the truck is expected to follow the laws of physics, its position can also be estimated by integrating its velocity over time, determined by keeping track of wheel revolutions and the angle of the steering wheel. This is a technique known as dead reckoning. Typically, the dead reckoning will provide a very smooth estimate of the truck's position, but it will drift over time as small errors accumulate.

For this example, the Kalman filter can be thought of as operating in two distinct phases: predict and update. In the prediction phase, the truck's old position will be modified according to the physical laws of motion (the dynamic or "state transition" model). Not only will a new position estimate be calculated, but also a new covariance will be calculated as well. Perhaps the covariance is proportional to the speed of the truck because we are more uncertain about the accuracy of the dead reckoning position estimate at high speeds but very certain about the position estimate at low speeds. Next, in the update phase, a measurement of the truck's position is taken from the GPS unit. Along with this measurement comes some amount of uncertainty, and its covariance relative to that of the prediction from the previous phase determines how much the new measurement will affect the updated prediction. Ideally, as the dead reckoning estimates tend to drift away from the real position, the GPS measurement should pull the position estimate back toward the real position but not disturb it to the point of becoming noisy and rapidly jumping.

Technical description and context

The Kalman filter is an efficient recursive filter estimating the internal state of a linear dynamic system from a series of noisy measurements. It is used in a wide range of engineering and econometric applications from radar and computer vision to estimation of structural macroeconomic models,^[24][25] and is an important topic in control theory and control systems engineering. Together with the linear-quadratic regulator (LQR), the Kalman filter solves the linear–quadratic–Gaussian control problem (LQG). The Kalman filter, the linear-quadratic regulator, and the linear–quadratic–Gaussian controller are solutions to what arguably are the most fundamental problems of control theory.

In most applications, the internal state is much larger (has more degrees of freedom) than the few "observable" parameters which are measured. However, by combining a series of measurements, the Kalman filter can estimate the entire internal state.

For the Dempster–Shafer theory, each state equation or observation is considered a special case of a linear belief function and the Kalman filtering is a special case of combining linear belief functions on a join-tree or Markov tree. Additional methods include belief filtering which use Bayes or evidential updates to the state equations.

A wide variety of Kalman filters exists by now: Kalman's original formulation - now termed the "simple" Kalman filter, the Kalman–Bucy filter, Schmidt's "extended" filter, the information filter, and a variety of "square-root" filters that were developed by Bierman, Thornton, and many others. Perhaps the most commonly used type of very simple Kalman filter is the phase-locked loop, which is now ubiquitous in radios, especially frequency modulation (FM) radios, television sets, satellite communications receivers, outer space communications systems, and nearly any other electronic communications equipment.

Underlying dynamic system model

Kalman filtering is based on linear dynamic systems discretized in the time domain. They are modeled on a Markov chain built on linear operators perturbed by errors that may include Gaussian noise. The state of the target system refers to the ground truth (yet hidden) system configuration of interest, which is represented as a vector of real numbers. At each discrete time increment, a linear operator is applied to the state to generate the new state, with some noise mixed in, and optionally some information from the controls on the system if they are known. Then, another linear operator mixed with more noise generates the measurable outputs (i.e., observation) from the true ("hidden") state. The Kalman filter may be regarded as analogous to the hidden Markov model, with the difference that the hidden state variables have values in a continuous space as opposed to a discrete state space as for the hidden Markov model. There is a strong analogy between the equations of a Kalman Filter and those of the hidden Markov model. A review of this and other models is given in Roweis and Ghahramani (1999)^[26] and Hamilton (1994), Chapter 13.^[27]

In order to use the Kalman filter to estimate the internal state of a process given only a sequence of noisy observations, one must model the process in accordance with the following framework. This means specifying the matrices, for each time-step k, following:

• F_k, the state-transition model;
• H_k, the observation model;
• Q_k, the covariance of the process noise;
• R_k, the covariance of the observation noise;
• and sometimes B_k, the control-input model as described below; if B_k is included, then there is also
• u_k, the control vector, representing the controlling input into control-input model.

 

Model underlying the Kalman filter. Squares represent matrices. Ellipses represent multivariate normal distributions (with the mean and covariance matrix enclosed). Unenclosed values are vectors. For the simple case, the various matrices are constant with time, and thus the subscripts are not used, but Kalman filtering allows any of them to change each time step.

The Kalman filter model assumes the true state at time k is evolved from the state at (k − 1) according to

${\displaystyle \mathbf {x} _{k}=\mathbf {F} _{k}\mathbf {x} _{k-1}+\mathbf {B} _{k}\mathbf {u} _{k}+\mathbf {w} _{k}}$ 

where

• F_k is the state transition model which is applied to the previous state x_k−1;
• B_k is the control-input model which is applied to the control vector u_k;
• w_k is the process noise, which is assumed to be drawn from a zero mean multivariate normal distribution, ${\displaystyle {\mathcal {N}}}$ , with covariance, Q_k: ${\displaystyle \mathbf {w} _{k}\sim {\mathcal {N}}\left(0,\mathbf {Q} _{k}\right)}$ .

At time k an observation (or measurement) z_k of the true state x_k is made according to

${\displaystyle \mathbf {z} _{k}=\mathbf {H} _{k}\mathbf {x} _{k}+\mathbf {v} _{k}}$ 

where

• H_k is the observation model, which maps the true state space into the observed space and
• v_k is the observation noise, which is assumed to be zero mean Gaussian white noise with covariance R_k: ${\displaystyle \mathbf {v} _{k}\sim {\mathcal {N}}\left(0,\mathbf {R} _{k}\right)}$ .

The initial state, and the noise vectors at each step {x₀, w₁, ..., w_k, v₁, ... ,v_k} are all assumed to be mutually independent.

Many real-time dynamic systems do not exactly conform to this model. In fact, unmodeled dynamics can seriously degrade the filter performance, even when it was supposed to work with unknown stochastic signals as inputs. The reason for this is that the effect of unmodeled dynamics depends on the input, and, therefore, can bring the estimation algorithm to instability (it diverges). On the other hand, independent white noise signals will not make the algorithm diverge. The problem of distinguishing between measurement noise and unmodeled dynamics is a difficult one and is treated as a problem of control theory using robust control.^[28][29]

Details

The Kalman filter is a recursive estimator. This means that only the estimated state from the previous time step and the current measurement are needed to compute the estimate for the current state. In contrast to batch estimation techniques, no history of observations and/or estimates is required. In what follows, the notation ${\displaystyle {\hat {\mathbf {x} }}_{n\mid m}}$  represents the estimate of ${\displaystyle \mathbf {x} }$  at time n given observations up to and including at time m ≤ n.

The state of the filter is represented by two variables:

• ${\displaystyle \mathbf {x} _{k\mid k}}$ , the a posteriori state estimate mean at time k given observations up to and including at time k;
• ${\displaystyle \mathbf {P} _{k\mid k}}$ , the a posteriori estimate covariance matrix (a measure of the estimated accuracy of the state estimate).

The algorithm structure of the Kalman filter resembles that of Alpha beta filter. The Kalman filter can be written as a single equation; however, it is most often conceptualized as two distinct phases: "Predict" and "Update". The predict phase uses the state estimate from the previous timestep to produce an estimate of the state at the current timestep. This predicted state estimate is also known as the a priori state estimate because, although it is an estimate of the state at the current timestep, it does not include observation information from the current timestep. In the update phase, the innovation (the pre-fit residual), i.e. the difference between the current a priori prediction and the current observation information, is multiplied by the optimal Kalman gain and combined with the previous state estimate to refine the state estimate. This improved estimate based on the current observation is termed the a posteriori state estimate.

Typically, the two phases alternate, with the prediction advancing the state until the next scheduled observation, and the update incorporating the observation. However, this is not necessary; if an observation is unavailable for some reason, the update may be skipped and multiple prediction procedures performed. Likewise, if multiple independent observations are available at the same time, multiple update procedures may be performed (typically with different observation matrices H_k).^[30][31]

Predict

Predicted (a priori) state estimate	${\displaystyle {\hat {\mathbf {x} }}_{k\mid k-1}=\mathbf {F} _{k}\mathbf {x} _{k-1\mid k-1}+\mathbf {B} _{k}\mathbf {u} _{k}}$
Predicted (a priori) estimate covariance	${\displaystyle {\hat {\mathbf {P} }}_{k\mid k-1}=\mathbf {F} _{k}\mathbf {P} _{k-1\mid k-1}\mathbf {F} _{k}^{\textsf {T}}+\mathbf {Q} _{k}}$

Update

Innovation or measurement pre-fit residual	${\displaystyle {\tilde {\mathbf {y} }}_{k}=\mathbf {z} _{k}-\mathbf {H} _{k}{\hat {\mathbf {x} }}_{k\mid k-1}}$
Innovation (or pre-fit residual) covariance	${\displaystyle \mathbf {S} _{k}=\mathbf {H} _{k}{\hat {\mathbf {P} }}_{k\mid k-1}\mathbf {H} _{k}^{\textsf {T}}+\mathbf {R} _{k}}$
Optimal Kalman gain	${\displaystyle \mathbf {K} _{k}={\hat {\mathbf {P} }}_{k\mid k-1}\mathbf {H} _{k}^{\textsf {T}}\mathbf {S} _{k}^{-1}}$
Updated (a posteriori) state estimate	${\displaystyle {\hat {\mathbf {x} }}_{k\mid k}={\hat {\mathbf {x} }}_{k\mid k-1}+\mathbf {K} _{k}{\tilde {\mathbf {y} }}_{k}}$
Updated (a posteriori) estimate covariance	${\displaystyle \mathbf {P} _{k|k}=\left(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k}\right){\hat {\mathbf {P} }}_{k|k-1}}$
Measurement post-fit residual	${\displaystyle {\tilde {\mathbf {y} }}_{k\mid k}=\mathbf {z} _{k}-\mathbf {H} _{k}{\hat {\mathbf {x} }}_{k\mid k}}$

The formula for the updated (a posteriori) estimate covariance above is valid for the optimal K_k gain that minimizes the residual error, in which form it is most widely used in applications. Proof of the formulae is found in the derivations section, where the formula valid for any K_k is also shown.

A more intuitive way to express the updated state estimate (${\displaystyle {\hat {\mathbf {x} }}_{k\mid k}}$ ) is:

${\displaystyle {\hat {\mathbf {x} }}_{k\mid k}=(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k}){\hat {\mathbf {x} }}_{k\mid k-1}+\mathbf {K} _{k}\mathbf {z} _{k}}$ 

This expression reminds us of a linear interpolation, ${\displaystyle x=(1-t)(a)+t(b)}$  for ${\displaystyle t}$  between [0,1]. In our case:

• ${\displaystyle t}$  is the matrix ${\displaystyle \mathbf {K} _{k}\mathbf {H} _{k}}$  the takes values from ${\displaystyle 0}$  (high error in the sensor) to ${\displaystyle I}$  or a projection (low error).
• ${\displaystyle a}$  is the internal state ${\displaystyle {\hat {\mathbf {x} }}_{k\mid k-1}}$  estimated from the model.
• ${\displaystyle b}$  is the internal state ${\displaystyle \mathbf {H} _{k}^{-1}\mathbf {z} _{k}}$  estimated from the measurement, assuming ${\displaystyle \mathbf {H} _{k}}$  is nonsingular.

This expression also resembles the alpha beta filter update step.

Invariants

If the model is accurate, and the values for ${\displaystyle {\hat {\mathbf {x} }}_{0\mid 0}}$  and ${\displaystyle \mathbf {P} _{0\mid 0}}$  accurately reflect the distribution of the initial state values, then the following invariants are preserved:

${\displaystyle {\begin{aligned}\operatorname {E} [\mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k\mid k}]&=\operatorname {E} [\mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k\mid k-1}]=0\\\operatorname {E} [{\tilde {\mathbf {y} }}_{k}]&=0\end{aligned}}}$ 

where ${\displaystyle \operatorname {E} [\xi ]}$  is the expected value of ${\displaystyle \xi }$ . That is, all estimates have a mean error of zero.

Also:

${\displaystyle {\begin{aligned}\mathbf {P} _{k\mid k}&=\operatorname {cov} \left(\mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k\mid k}\right)\\\mathbf {P} _{k\mid k-1}&=\operatorname {cov} \left(\mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k\mid k-1}\right)\\\mathbf {S} _{k}&=\operatorname {cov} \left({\tilde {\mathbf {y} }}_{k}\right)\end{aligned}}}$ 

so covariance matrices accurately reflect the covariance of estimates.

Estimation of the noise covariances Q_k and R_k

Practical implementation of a Kalman Filter is often difficult due to the difficulty of getting a good estimate of the noise covariance matrices Q_k and R_k. Extensive research has been done to estimate these covariances from data. One practical method of doing this is the autocovariance least-squares (ALS) technique that uses the time-lagged autocovariances of routine operating data to estimate the covariances.^[32][33] The GNU Octave and Matlab code used to calculate the noise covariance matrices using the ALS technique is available online using the GNU General Public License.^[34] Field Kalman Filter (FKF), a Bayesian algorithm, which allows simultaneous estimation of the state, parameters and noise covariance has been proposed.^[35] The FKF algorithm has a recursive formulation, good observed convergence, and relatively low complexity, thus suggesting that the FKF algorithm may possibly be a worthwhile alternative to the Autocovariance Least-Squares methods.

Optimality and performance

It follows from theory that the Kalman filter provides an optimal state estimation in cases where a) the model matches the real system perfectly, b) the entering noise is "white" (uncorrelated) and c) the covariances of the noise are known exactly. Correlated noise can also be treated using Kalman filters.^[36] Several methods for the noise covariance estimation have been proposed during past decades, including ALS, mentioned in the section above. After the covariances are estimated, it is useful to evaluate the performance of the filter; i.e., whether it is possible to improve the state estimation quality. If the Kalman filter works optimally, the innovation sequence (the output prediction error) is a white noise, therefore the whiteness property of the innovations measures filter performance. Several different methods can be used for this purpose.^[37] If the noise terms are distributed in a non-Gaussian manner, methods for assessing performance of the filter estimate, which use probability inequalities or large-sample theory, are known in the literature.^[38][39]

Example application, technical

 

  Truth;   filtered process;   observations.

Consider a truck on frictionless, straight rails. Initially, the truck is stationary at position 0, but it is buffeted this way and that by random uncontrolled forces. We measure the position of the truck every Δt seconds, but these measurements are imprecise; we want to maintain a model of the truck's position and velocity. We show here how we derive the model from which we create our Kalman filter.

Since ${\displaystyle \mathbf {F} ,\mathbf {H} ,\mathbf {R} ,\mathbf {Q} }$  are constant, their time indices are dropped.

The position and velocity of the truck are described by the linear state space

${\displaystyle \mathbf {x} _{k}={\begin{bmatrix}x\\{\dot {x}}\end{bmatrix}}}$ 

where ${\displaystyle {\dot {x}}}$  is the velocity, that is, the derivative of position with respect to time.

We assume that between the (k − 1) and k timestep, uncontrolled forces cause a constant acceleration of a_k that is normally distributed with mean 0 and standard deviation σ_a. From Newton's laws of motion we conclude that

${\displaystyle \mathbf {x} _{k}=\mathbf {F} \mathbf {x} _{k-1}+\mathbf {G} a_{k}}$ 

(there is no ${\displaystyle \mathbf {B} u}$  term since there are no known control inputs. Instead, a_k is the effect of an unknown input and ${\displaystyle \mathbf {G} }$  applies that effect to the state vector) where

${\displaystyle {\begin{aligned}\mathbf {F} &={\begin{bmatrix}1&\Delta t\\0&1\end{bmatrix}}\\[4pt]\mathbf {G} &={\begin{bmatrix}{\frac {1}{2}}{\Delta t}^{2}\\[6pt]\Delta t\end{bmatrix}}\end{aligned}}}$ 

so that

${\displaystyle \mathbf {x} _{k}=\mathbf {F} \mathbf {x} _{k-1}+\mathbf {w} _{k}}$ 

where

${\displaystyle {\begin{aligned}\mathbf {w} _{k}&\sim N(0,\mathbf {Q} )\\\mathbf {Q} &=\mathbf {G} \mathbf {G} ^{\textsf {T}}\sigma _{a}^{2}={\begin{bmatrix}{\frac {1}{4}}{\Delta t}^{4}&{\frac {1}{2}}{\Delta t}^{3}\\[6pt]{\frac {1}{2}}{\Delta t}^{3}&{\Delta t}^{2}\end{bmatrix}}\sigma _{a}^{2}.\end{aligned}}}$ 

The matrix ${\displaystyle \mathbf {Q} }$  is not full rank (it is of rank one if ${\displaystyle \Delta t\neq 0}$ ). Hence, the distribution ${\displaystyle N(0,\mathbf {Q} )}$  is not absolutely continuous and has no probability density function. Another way to express this, avoiding explicit degenerate distributions is given by

${\displaystyle \mathbf {w} _{k}\sim \mathbf {G} \cdot N\left(0,\sigma _{a}^{2}\right).}$ 

At each time phase, a noisy measurement of the true position of the truck is made. Let us suppose the measurement noise v_k is also distributed normally, with mean 0 and standard deviation σ_z.

${\displaystyle \mathbf {z} _{k}=\mathbf {Hx} _{k}+\mathbf {v} _{k}}$ 

where

${\displaystyle \mathbf {H} ={\begin{bmatrix}1&0\end{bmatrix}}}$ 

and

${\displaystyle \mathbf {R} =\mathrm {E} \left[\mathbf {v} _{k}\mathbf {v} _{k}^{\textsf {T}}\right]={\begin{bmatrix}\sigma _{z}^{2}\end{bmatrix}}}$ 

We know the initial starting state of the truck with perfect precision, so we initialize

${\displaystyle {\hat {\mathbf {x} }}_{0\mid 0}={\begin{bmatrix}0\\0\end{bmatrix}}}$ 

and to tell the filter that we know the exact position and velocity, we give it a zero covariance matrix:

${\displaystyle \mathbf {P} _{0\mid 0}={\begin{bmatrix}0&0\\0&0\end{bmatrix}}}$ 

If the initial position and velocity are not known perfectly, the covariance matrix should be initialized with suitable variances on its diagonal:

${\displaystyle \mathbf {P} _{0\mid 0}={\begin{bmatrix}\sigma _{x}^{2}&0\\0&\sigma _{\dot {x}}^{2}\end{bmatrix}}}$ 

The filter will then prefer the information from the first measurements over the information already in the model.

Asymptotic form

For simplicity, assume that the control input ${\displaystyle \mathbf {u} _{k}=\mathbf {0} }$ . Then the Kalman filter may be written:

${\displaystyle {\hat {\mathbf {x} }}_{k\mid k}=\mathbf {F} _{k}{\hat {\mathbf {x} }}_{k-1\mid k-1}+\mathbf {K} _{k}[\mathbf {z} _{k}-\mathbf {H} _{k}\mathbf {F} _{k}{\hat {\mathbf {x} }}_{k-1\mid k-1}].}$ 

A similar equation holds if we include a non-zero control input. Gain matrices ${\displaystyle \mathbf {K} _{k}}$  evolve independently of the measurements ${\displaystyle \mathbf {z} _{k}}$ . From above, the four equations needed for updating the Kalman gain are as follows:

${\displaystyle {\begin{aligned}\mathbf {P} _{k\mid k-1}&=\mathbf {F} _{k}\mathbf {P} _{k-1\mid k-1}\mathbf {F} _{k}^{\textsf {T}}+\mathbf {Q} _{k},\\\mathbf {S} _{k}&=\mathbf {H} _{k}\mathbf {P} _{k\mid k-1}\mathbf {H} _{k}^{\textsf {T}}+\mathbf {R} _{k},\\\mathbf {K} _{k}&=\mathbf {P} _{k\mid k-1}\mathbf {H} _{k}^{\textsf {T}}\mathbf {S} _{k}^{-1},\\\mathbf {P} _{k|k}&=\left(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k}\right)\mathbf {P} _{k|k-1}.\end{aligned}}}$ 

Since the gain matrices depend only on the model, and not the measurements, they may be computed offline. Convergence of the gain matrices ${\displaystyle \mathbf {K} _{k}}$  to an asymptotic matrix ${\displaystyle \mathbf {K} _{\infty }}$  applies for conditions established in Walrand and Dimakis.^[40] Simulations establish the number of steps to convergence. For the moving truck example described above, with ${\displaystyle \Delta t=1}$ . and ${\displaystyle \sigma _{a}^{2}=\sigma _{z}^{2}=\sigma _{x}^{2}=\sigma _{\dot {x}}^{2}=1}$ , simulation shows convergence in ${\displaystyle 10}$  iterations.

Using the asymptotic gain, and assuming ${\displaystyle \mathbf {H} _{k}}$  and ${\displaystyle \mathbf {F} _{k}}$  are independent of ${\displaystyle k}$ , the Kalman filter becomes a linear time-invariant filter:

${\displaystyle {\hat {\mathbf {x} }}_{k}=\mathbf {F} {\hat {\mathbf {x} }}_{k-1}+\mathbf {K} _{\infty }[\mathbf {z} _{k}-\mathbf {H} \mathbf {F} {\hat {\mathbf {x} }}_{k-1}].}$ 

The asymptotic gain ${\displaystyle \mathbf {K} _{\infty }}$ , if it exists, can be computed by first solving the following discrete Riccati equation for the asymptotic state covariance ${\displaystyle \mathbf {P} _{\infty }}$ :^[40]

${\displaystyle \mathbf {P} _{\infty }=\mathbf {F} \left(\mathbf {P} _{\infty }-\mathbf {P} _{\infty }\mathbf {H} ^{\textsf {T}}\left(\mathbf {H} \mathbf {P} _{\infty }\mathbf {H} ^{\textsf {T}}+\mathbf {R} \right)^{-1}\mathbf {H} \mathbf {P} _{\infty }\right)\mathbf {F} ^{\textsf {T}}+\mathbf {Q} .}$ 

The asymptotic gain is then computed as before.

${\displaystyle \mathbf {K} _{\infty }=\mathbf {P} _{\infty }\mathbf {H} ^{\textsf {T}}\left(\mathbf {R} +\mathbf {H} \mathbf {P} _{\infty }\mathbf {H} ^{\textsf {T}}\right)^{-1}.}$ 

Additionally, a form of the asymptotic Kalman filter more commonly used in control theory is given by

${\displaystyle {\displaystyle {\hat {\mathbf {x} }}_{k+1}=\mathbf {F} {\hat {\mathbf {x} }}_{k}+\mathbf {B} \mathbf {u} _{k}+\mathbf {\overline {K}} _{\infty }[\mathbf {z} _{k}-\mathbf {H} {\hat {\mathbf {x} }}_{k}],}}$ 

where

${\displaystyle {\overline {\mathbf {K} }}_{\infty }=\mathbf {F} \mathbf {P} _{\infty }\mathbf {H} ^{\textsf {T}}\left(\mathbf {R} +\mathbf {H} \mathbf {P} _{\infty }\mathbf {H} ^{\textsf {T}}\right)^{-1}.}$ 

This leads to an estimator of the form

${\displaystyle {\displaystyle {\hat {\mathbf {x} }}_{k+1}=(\mathbf {F} -{\overline {\mathbf {K} }}_{\infty }\mathbf {H} ){\hat {\mathbf {x} }}_{k}+\mathbf {B} \mathbf {u} _{k}+\mathbf {\overline {K}} _{\infty }\mathbf {z} _{k},}}$ 

Derivations

The Kalman filter can be derived as a generalized least squares method operating on previous data.^[41]

Deriving the posteriori estimate covariance matrix

Starting with our invariant on the error covariance P_k | k as above

${\displaystyle \mathbf {P} _{k\mid k}=\operatorname {cov} \left(\mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k\mid k}\right)}$ 

substitute in the definition of ${\displaystyle {\hat {\mathbf {x} }}_{k\mid k}}$ 

${\displaystyle \mathbf {P} _{k\mid k}=\operatorname {cov} \left[\mathbf {x} _{k}-\left({\hat {\mathbf {x} }}_{k\mid k-1}+\mathbf {K} _{k}{\tilde {\mathbf {y} }}_{k}\right)\right]}$ 

and substitute ${\displaystyle {\tilde {\mathbf {y} }}_{k}}$ 

${\displaystyle \mathbf {P} _{k\mid k}=\operatorname {cov} \left(\mathbf {x} _{k}-\left[{\hat {\mathbf {x} }}_{k\mid k-1}+\mathbf {K} _{k}\left(\mathbf {z} _{k}-\mathbf {H} _{k}{\hat {\mathbf {x} }}_{k\mid k-1}\right)\right]\right)}$ 

and ${\displaystyle \mathbf {z} _{k}}$ 

${\displaystyle \mathbf {P} _{k\mid k}=\operatorname {cov} \left(\mathbf {x} _{k}-\left[{\hat {\mathbf {x} }}_{k\mid k-1}+\mathbf {K} _{k}\left(\mathbf {H} _{k}\mathbf {x} _{k}+\mathbf {v} _{k}-\mathbf {H} _{k}{\hat {\mathbf {x} }}_{k\mid k-1}\right)\right]\right)}$ 

and by collecting the error vectors we get

${\displaystyle \mathbf {P} _{k\mid k}=\operatorname {cov} \left[\left(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k}\right)\left(\mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k\mid k-1}\right)-\mathbf {K} _{k}\mathbf {v} _{k}\right]}$ 

Since the measurement error v_k is uncorrelated with the other terms, this becomes

${\displaystyle \mathbf {P} _{k\mid k}=\operatorname {cov} \left[\left(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k}\right)\left(\mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k\mid k-1}\right)\right]+\operatorname {cov} \left[\mathbf {K} _{k}\mathbf {v} _{k}\right]}$ 

by the properties of vector covariance this becomes

${\displaystyle \mathbf {P} _{k\mid k}=\left(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k}\right)\operatorname {cov} \left(\mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k\mid k-1}\right)\left(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k}\right)^{\textsf {T}}+\mathbf {K} _{k}\operatorname {cov} \left(\mathbf {v} _{k}\right)\mathbf {K} _{k}^{\textsf {T}}}$ 

which, using our invariant on P_k | k−1 and the definition of R_k becomes

${\displaystyle \mathbf {P} _{k\mid k}=\left(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k}\right)\mathbf {P} _{k\mid k-1}\left(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k}\right)^{\textsf {T}}+\mathbf {K} _{k}\mathbf {R} _{k}\mathbf {K} _{k}^{\textsf {T}}}$ 

This formula (sometimes known as the Joseph form of the covariance update equation) is valid for any value of K_k. It turns out that if K_k is the optimal Kalman gain, this can be simplified further as shown below.

Kalman gain derivation

The Kalman filter is a minimum mean-square error estimator. The error in the a posteriori state estimation is

${\displaystyle \mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k\mid k}}$ 

We seek to minimize the expected value of the square of the magnitude of this vector, ${\displaystyle \operatorname {E} \left[\left\|\mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k|k}\right\|^{2}\right]}$ . This is equivalent to minimizing the trace of the a posteriori estimate covariance matrix ${\displaystyle \mathbf {P} _{k|k}}$ . By expanding out the terms in the equation above and collecting, we get:

${\displaystyle {\begin{aligned}\mathbf {P} _{k\mid k}&=\mathbf {P} _{k\mid k-1}-\mathbf {K} _{k}\mathbf {H} _{k}\mathbf {P} _{k\mid k-1}-\mathbf {P} _{k\mid k-1}\mathbf {H} _{k}^{\textsf {T}}\mathbf {K} _{k}^{\textsf {T}}+\mathbf {K} _{k}\left(\mathbf {H} _{k}\mathbf {P} _{k\mid k-1}\mathbf {H} _{k}^{\textsf {T}}+\mathbf {R} _{k}\right)\mathbf {K} _{k}^{\textsf {T}}\\[6pt]&=\mathbf {P} _{k\mid k-1}-\mathbf {K} _{k}\mathbf {H} _{k}\mathbf {P} _{k\mid k-1}-\mathbf {P} _{k\mid k-1}\mathbf {H} _{k}^{\textsf {T}}\mathbf {K} _{k}^{\textsf {T}}+\mathbf {K} _{k}\mathbf {S} _{k}\mathbf {K} _{k}^{\textsf {T}}\end{aligned}}}$ 

The trace is minimized when its matrix derivative with respect to the gain matrix is zero. Using the gradient matrix rules and the symmetry of the matrices involved we find that

${\displaystyle {\frac {\partial \;\operatorname {tr} (\mathbf {P} _{k\mid k})}{\partial \;\mathbf {K} _{k}}}=-2\left(\mathbf {H} _{k}\mathbf {P} _{k\mid k-1}\right)^{\textsf {T}}+2\mathbf {K} _{k}\mathbf {S} _{k}=0.}$ 

Solving this for K_k yields the Kalman gain:

${\displaystyle {\begin{aligned}\mathbf {K} _{k}\mathbf {S} _{k}&=\left(\mathbf {H} _{k}\mathbf {P} _{k\mid k-1}\right)^{\textsf {T}}=\mathbf {P} _{k\mid k-1}\mathbf {H} _{k}^{\textsf {T}}\\\Rightarrow \mathbf {K} _{k}&=\mathbf {P} _{k\mid k-1}\mathbf {H} _{k}^{\textsf {T}}\mathbf {S} _{k}^{-1}\end{aligned}}}$ 

This gain, which is known as the optimal Kalman gain, is the one that yields MMSE estimates when used.

Simplification of the posteriori error covariance formula

The formula used to calculate the a posteriori error covariance can be simplified when the Kalman gain equals the optimal value derived above. Multiplying both sides of our Kalman gain formula on the right by S_kK_k^T, it follows that

${\displaystyle \mathbf {K} _{k}\mathbf {S} _{k}\mathbf {K} _{k}^{\textsf {T}}=\mathbf {P} _{k\mid k-1}\mathbf {H} _{k}^{\textsf {T}}\mathbf {K} _{k}^{\textsf {T}}}$ 

Referring back to our expanded formula for the a posteriori error covariance,

${\displaystyle \mathbf {P} _{k\mid k}=\mathbf {P} _{k\mid k-1}-\mathbf {K} _{k}\mathbf {H} _{k}\mathbf {P} _{k\mid k-1}-\mathbf {P} _{k\mid k-1}\mathbf {H} _{k}^{\textsf {T}}\mathbf {K} _{k}^{\textsf {T}}+\mathbf {K} _{k}\mathbf {S} _{k}\mathbf {K} _{k}^{\textsf {T}}}$ 

we find the last two terms cancel out, giving

${\displaystyle \mathbf {P} _{k\mid k}=\mathbf {P} _{k\mid k-1}-\mathbf {K} _{k}\mathbf {H} _{k}\mathbf {P} _{k\mid k-1}=(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k})\mathbf {P} _{k\mid k-1}}$ 

This formula is computationally cheaper and thus nearly always used in practice, but is only correct for the optimal gain. If arithmetic precision is unusually low causing problems with numerical stability, or if a non-optimal Kalman gain is deliberately used, this simplification cannot be applied; the a posteriori error covariance formula as derived above (Joseph form) must be used.

Sensitivity analysis

The Kalman filtering equations provide an estimate of the state ${\displaystyle {\hat {\mathbf {x} }}_{k\mid k}}$  and its error covariance ${\displaystyle \mathbf {P} _{k\mid k}}$  recursively. The estimate and its quality depend on the system parameters and the noise statistics fed as inputs to the estimator. This section analyzes the effect of uncertainties in the statistical inputs to the filter.^[42] In the absence of reliable statistics or the true values of noise covariance matrices ${\displaystyle \mathbf {Q} _{k}}$  and ${\displaystyle \mathbf {R} _{k}}$ , the expression

${\displaystyle \mathbf {P} _{k\mid k}=\left(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k}\right)\mathbf {P} _{k\mid k-1}\left(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k}\right)^{\textsf {T}}+\mathbf {K} _{k}\mathbf {R} _{k}\mathbf {K} _{k}^{\textsf {T}}}$ 

no longer provides the actual error covariance. In other words, ${\displaystyle \mathbf {P} _{k\mid k}\neq E\left[\left(\mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k\mid k}\right)\left(\mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k\mid k}\right)^{\textsf {T}}\right]}$ . In most real-time applications, the covariance matrices that are used in designing the Kalman filter are different from the actual (true) noise covariances matrices.^{[citation needed]} This sensitivity analysis describes the behavior of the estimation error covariance when the noise covariances as well as the system matrices ${\displaystyle \mathbf {F} _{k}}$  and ${\displaystyle \mathbf {H} _{k}}$  that are fed as inputs to the filter are incorrect. Thus, the sensitivity analysis describes the robustness (or sensitivity) of the estimator to misspecified statistical and parametric inputs to the estimator.

This discussion is limited to the error sensitivity analysis for the case of statistical uncertainties. Here the actual noise covariances are denoted by ${\displaystyle \mathbf {Q} _{k}^{a}}$  and ${\displaystyle \mathbf {R} _{k}^{a}}$  respectively, whereas the design values used in the estimator are ${\displaystyle \mathbf {Q} _{k}}$  and ${\displaystyle \mathbf {R} _{k}}$  respectively. The actual error covariance is denoted by ${\displaystyle \mathbf {P} _{k\mid k}^{a}}$  and ${\displaystyle \mathbf {P} _{k\mid k}}$  as computed by the Kalman filter is referred to as the Riccati variable. When ${\displaystyle \mathbf {Q} _{k}\equiv \mathbf {Q} _{k}^{a}}$  and ${\displaystyle \mathbf {R} _{k}\equiv \mathbf {R} _{k}^{a}}$ , this means that ${\displaystyle \mathbf {P} _{k\mid k}=\mathbf {P} _{k\mid k}^{a}}$ . While computing the actual error covariance using ${\displaystyle \mathbf {P} _{k\mid k}^{a}=E\left[\left(\mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k\mid k}\right)\left(\mathbf {x} _{k}-{\hat {\mathbf {x} }}_{k\mid k}\right)^{\textsf {T}}\right]}$ , substituting for ${\displaystyle {\widehat {\mathbf {x} }}_{k\mid k}}$  and using the fact that ${\displaystyle E\left[\mathbf {w} _{k}\mathbf {w} _{k}^{\textsf {T}}\right]=\mathbf {Q} _{k}^{a}}$  and ${\displaystyle E\left[\mathbf {v} _{k}\mathbf {v} _{k}^{\textsf {T}}\right]=\mathbf {R} _{k}^{a}}$ , results in the following recursive equations for ${\displaystyle \mathbf {P} _{k\mid k}^{a}}$  :

${\displaystyle \mathbf {P} _{k\mid k-1}^{a}=\mathbf {F} _{k}\mathbf {P} _{k-1\mid k-1}^{a}\mathbf {F} _{k}^{\textsf {T}}+\mathbf {Q} _{k}^{a}}$ 

and

${\displaystyle \mathbf {P} _{k\mid k}^{a}=\left(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k}\right)\mathbf {P} _{k\mid k-1}^{a}\left(\mathbf {I} -\mathbf {K} _{k}\mathbf {H} _{k}\right)^{\textsf {T}}+\mathbf {K} _{k}\mathbf {R} _{k}^{a}\mathbf {K} _{k}^{\textsf {T}}}$ 

While computing ${\displaystyle \mathbf {P} _{k\mid k}}$ , by design the filter implicitly assumes that ${\displaystyle E\left[\mathbf {w} _{k}\mathbf {w} _{k}^{\textsf {T}}\right]=\mathbf {Q} _{k}}$  and ${\displaystyle E\left[\mathbf {v} _{k}\mathbf {v} _{k}^{\textsf {T}}\right]=\mathbf {R} _{k}}$ . The recursive expressions for ${\displaystyle \mathbf {P} _{k\mid k}^{a}}$  and ${\displaystyle \mathbf {P} _{k\mid k}}$  are identical except for the presence of ${\displaystyle \mathbf {Q} _{k}^{a}}$  and ${\displaystyle \mathbf {R} _{k}^{a}}$  in place of the design values ${\displaystyle \mathbf {Q} _{k}}$  and ${\displaystyle \mathbf {R} _{k}}$  respectively. Researches have been done to analyze Kalman filter system's robustness.^[43]

Square root form

One problem with the Kalman filter is its numerical stability. If the process noise covariance Q_k is small, round-off error often causes a small positive eigenvalue of the state covariance matrix P to be computed as a negative number. This renders the numerical representation of P indefinite, while its true form is positive-definite.

Positive definite matrices have the property that they have a triangular matrix square root P = S·S^T. This can be computed efficiently using the Cholesky factorization algorithm, but more importantly, if the covariance is kept in this form, it can never have a negative diagonal or become asymmetric. An equivalent form, which avoids many of the square root operations required by the matrix square root yet preserves the desirable numerical properties, is the U-D decomposition form, P = U·D·U^T, where U is a unit triangular matrix (with unit diagonal), and D is a diagonal matrix.

Between the two, the U-D factorization uses the same amount of storage, and somewhat less computation, and is the most commonly used square root form. (Early literature on the relative efficiency is somewhat misleading, as it assumed that square roots were much more time-consuming than divisions,^[44]: 69 while on 21st-century computers they are only slightly more expensive.)

Efficient algorithms for the Kalman prediction and update steps in the square root form were developed by G. J. Bierman and C. L. Thornton.^[44][45]

The L·D·L^T decomposition of the innovation covariance matrix S_k is the basis for another type of numerically efficient and robust square root filter.^[46] The algorithm starts with the LU decomposition as implemented in the Linear Algebra PACKage (LAPACK). These results are further factored into the L·D·L^T structure with methods given by Golub and Van Loan (algorithm 4.1.2) for a symmetric nonsingular matrix.^[47] Any singular covariance matrix is pivoted so that the first diagonal partition is nonsingular and well-conditioned. The pivoting algorithm must retain any portion of the innovation covariance matrix directly corresponding to observed state-variables H_k·x_k|k-1 that are associated with auxiliary observations in y_k. The l·d·l^t square-root filter requires orthogonalization of the observation vector.^[45][46] This may be done with the inverse square-root of the covariance matrix for the auxiliary variables using Method 2 in Higham (2002, p. 263).^[48]

Parallel form

The Kalman filter is efficient for sequential data processing on central processing units (CPUs), but in its original form it is inefficient on parallel architectures such as graphics processing units (GPUs). It is however possible to express the filter-update routine in terms of an associative operator using the formulation in Särkkä (2021).^[49] The filter solution can then be retrieved by the use of a prefix sum algorithm which can be efficiently implemented on GPU.^[50] This reduces the computational complexity from ${\displaystyle O(N)}$  in the number of time steps to ${\displaystyle O(\log(N))}$ .

Relationship to recursive Bayesian estimation

The Kalman filter can be presented as one of the simplest dynamic Bayesian networks. The Kalman filter calculates estimates of the true values of states recursively over time using incoming measurements and a mathematical process model. Similarly, recursive Bayesian estimation calculates estimates of an unknown probability density function (PDF) recursively over time using incoming measurements and a mathematical process model.^[51]

In recursive Bayesian estimation, the true state is assumed to be an unobserved Markov process, and the measurements are the observed states of a hidden Markov model (HMM).

 

hidden markov model

Because of the Markov assumption, the true state is conditionally independent of all earlier states given the immediately previous state.

${\displaystyle p(\mathbf {x} _{k}\mid \mathbf {x} _{0},\dots ,\mathbf {x} _{k-1})=p(\mathbf {x} _{k}\mid \mathbf {x} _{k-1})}$ 

Similarly, the measurement at the k-th timestep is dependent only upon the current state and is conditionally independent of all other states given the current state.

${\displaystyle p(\mathbf {z} _{k}\mid \mathbf {x} _{0},\dots ,\mathbf {x} _{k})=p(\mathbf {z} _{k}\mid \mathbf {x} _{k})}$ 

Using these assumptions the probability distribution over all states of the hidden Markov model can be written simply as:

${\displaystyle p\left(\mathbf {x} _{0},\dots ,\mathbf {x} _{k},\mathbf {z} _{1},\dots ,\mathbf {z} _{k}\right)=p\left(\mathbf {x} _{0}\right)\prod _{i=1}^{k}p\left(\mathbf {z} _{i}\mid \mathbf {x} _{i}\right)p\left(\mathbf {x} _{i}\mid \mathbf {x} _{i-1}\right)}$ 

However, when a Kalman filter is used to estimate the state x, the probability distribution of interest is that associated with the current states conditioned on the measurements up to the current timestep. This is achieved by marginalizing out the previous states and dividing by the probability of the measurement set.

This results in the predict and update phases of the Kalman filter written probabilistically. The probability distribution associated with the predicted state is the sum (integral) of the products of the probability distribution associated with the transition from the (k − 1)-th timestep to the k-th and the probability distribution associated with the previous state, over all possible ${\displaystyle x_{k-1}}$ .

${\displaystyle p\left(\mathbf {x} _{k}\mid \mathbf {Z} _{k-1}\right)=\int p\left(\mathbf {x} _{k}\mid \mathbf {x} _{k-1}\right)p\left(\mathbf {x} _{k-1}\mid \mathbf {Z} _{k-1}\right)\,d\mathbf {x} _{k-1}}$ 

The measurement set up to time t is

${\displaystyle \mathbf {Z} _{t}=\left\{\mathbf {z} _{1},\dots ,\mathbf {z} _{t}\right\}}$ 

The probability distribution of the update is proportional to the product of the measurement likelihood and the predicted state.

${\displaystyle p\left(\mathbf {x} _{k}\mid \mathbf {Z} _{k}\right)={\frac {p\left(\mathbf {z} _{k}\mid \mathbf {x} _{k}\right)p\left(\mathbf {x} _{k}\mid \mathbf {Z} _{k-1}\right)}{p\left(\mathbf {z} _{k}\mid \mathbf {Z} _{k-1}\right)}}}$ 

The denominator

${\displaystyle p\left(\mathbf {z} _{k}\mid \mathbf {Z} _{k-1}\right)=\int p\left(\mathbf {z} _{k}\mid \mathbf {x} _{k}\right)p\left(\mathbf {x} _{k}\mid \mathbf {Z} _{k-1}\right)\,d\mathbf {x} _{k}}$ 

is a normalization term.

The remaining probability density functions are

${\displaystyle {\begin{aligned}p\left(\mathbf {x} _{k}\mid \mathbf {x} _{k-1}\right)&={\mathcal {N}}\left(\mathbf {F} _{k}\mathbf {x} _{k-1},\mathbf {Q} _{k}\right)\\p\left(\mathbf {z} _{k}\mid \mathbf {x} _{k}\right)&={\mathcal {N}}\left(\mathbf {H} _{k}\mathbf {x} _{k},\mathbf {R} _{k}\right)\\p\left(\mathbf {x} _{k-1}\mid \mathbf {Z} _{k-1}\right)&={\mathcal {N}}\left({\hat {\mathbf {x} }}_{k-1},\mathbf {P} _{k-1}\right)\end{aligned}}}$ 

The PDF at the previous timestep is assumed inductively to be the estimated state and covariance. This is justified because, as an optimal estimator, the Kalman filter makes best use of the measurements, therefore the PDF for ${\displaystyle \mathbf {x} _{k}}$  given the measurements ${\displaystyle \mathbf {Z} _{k}}$  is the Kalman filter estimate.

Marginal likelihood

Related to the recursive Bayesian interpretation described above, the Kalman filter can be viewed as a generative model, i.e., a process for generating a stream of random observations z = (z₀, z₁, z₂, ...). Specifically, the process is

1. Sample a hidden state ${\displaystyle \mathbf {x} _{0}}$  from the Gaussian prior distribution ${\displaystyle p\left(\mathbf {x} _{0}\right)={\mathcal {N}}\left({\hat {\mathbf {x} }}_{0\mid 0},\mathbf {P} _{0\mid 0}\right)}$ .
2. Sample an observation ${\displaystyle \mathbf {z} _{0}}$  from the observation model ${\displaystyle p\left(\mathbf {z} _{0}\mid \mathbf {x} _{0}\right)={\mathcal {N}}\left(\mathbf {H} _{0}\mathbf {x} _{0},\mathbf {R} _{0}\right)}$ .
3. For ${\displaystyle k=1,2,3,\ldots }$ , do
   1. Sample the next hidden state ${\displaystyle \mathbf {x} _{k}}$  from the transition model ${\displaystyle p\left(\mathbf {x} _{k}\mid \mathbf {x} _{k-1}\right)={\mathcal {N}}\left(\mathbf {F} _{k}\mathbf {x} _{k-1}+\mathbf {B} _{k}\mathbf {u} _{k},\mathbf {Q} _{k}\right).}$ 
   2. Sample an observation ${\displaystyle \mathbf {z} _{k}}$  from the observation model ${\displaystyle p\left(\mathbf {z} _{k}\mid \mathbf {x} _{k}\right)={\mathcal {N}}\left(\mathbf {H} _{k}\mathbf {x} _{k},\mathbf {R} _{k}\right).}$ 

This process has identical structure to the hidden Markov model, except that the discrete state and observations are replaced with continuous variables sampled from Gaussian distributions.

In some applications, it is useful to compute the probability that a Kalman filter with a given set of parameters (prior distribution, transition and observation models, and control inputs) would generate a particular observed signal. This probability is known as the marginal likelihood because it integrates over ("marginalizes out") the values of the hidden state variables, so it can be computed using only the observed signal. The marginal likelihood can be useful to evaluate different parameter choices, or to compare the Kalman filter against other models using Bayesian model comparison.

It is straightforward to compute the marginal likelihood as a side effect of the recursive filtering computation. By the chain rule, the likelihood can be factored as the product of the probability of each observation given previous observations,

${\displaystyle p(\mathbf {z} )=\prod _{k=0}^{T}p\left(\mathbf {z} _{k}\mid \mathbf {z} _{k-1},\ldots ,\mathbf {z} _{0}\right)}$ ,

and because the Kalman filter describes a Markov process, all relevant information from previous observations is contained in the current state estimate ${\displaystyle {\hat {\mathbf {x} }}_{k\mid k-1},\mathbf {P} _{k\mid k-1}.}$  Thus the marginal likelihood is given by

${\displaystyle {\begin{aligned}p(\mathbf {z} )&=\prod _{k=0}^{T}\int p\left(\mathbf {z} _{k}\mid \mathbf {x} _{k}\right)p\left(\mathbf {x} _{k}\mid \mathbf {z} _{k-1},\ldots ,\mathbf {z} _{0}\right)d\mathbf {x} _{k}\\&=\prod _{k=0}^{T}\int {\mathcal {N}}\left(\mathbf {z} _{k};\mathbf {H} _{k}\mathbf {x} _{k},\mathbf {R} _{k}\right){\mathcal {N}}\left(\mathbf {x} _{k};{\hat {\mathbf {x} }}_{k\mid k-1},\mathbf {P} _{k\mid k-1}\right)d\mathbf {x} _{k}\\&=\prod _{k=0}^{T}{\mathcal {N}}\left(\mathbf {z} _{k};\mathbf {H} _{k}{\hat {\mathbf {x} }}_{k\mid k-1},\mathbf {R} _{k}+\mathbf {H} _{k}\mathbf {P} _{k\mid k-1}\mathbf {H} _{k}^{\textsf {T}}\right)\\&=\prod _{k=0}^{T}{\mathcal {N}}\left(\mathbf {z} _{k};\mathbf {H} _{k}{\hat {\mathbf {x} }}_{k\mid k-1},\mathbf {S} _{k}\right),\end{aligned}}}$ 

i.e., a product of Gaussian densities, each corresponding to the density of one observation z_k under the current filtering distribution ${\displaystyle \mathbf {H} _{k}{\hat {\mathbf {x} }}_{k\mid k-1},\mathbf {S} _{k}}$ . This can easily be computed as a simple recursive update; however, to avoid numeric underflow, in a practical implementation it is usually desirable to compute the log marginal likelihood ${\displaystyle \ell =\log p(\mathbf {z} )}$  instead. Adopting the convention ${\displaystyle \ell ^{(-1)}=0}$ , this can be done via the recursive update rule

${\displaystyle \ell ^{(k)}=\ell ^{(k-1)}-{\frac {1}{2}}\left({\tilde {\mathbf {y} }}_{k}^{\textsf {T}}\mathbf {S} _{k}^{-1}{\tilde {\mathbf {y} }}_{k}+\log \left|\mathbf {S} _{k}\right|+d_{y}\log 2\pi \right),}$ 

where ${\displaystyle d_{y}}$  is the dimension of the measurement vector.^[52]

An important application where such a (log) likelihood of the observations (given the filter parameters) is used is multi-target tracking. For example, consider an object tracking scenario where a stream of observations is the input, however, it is unknown how many objects are in the scene (or, the number of objects is known but is greater than one). For such a scenario, it can be unknown apriori which observations/measurements were generated by which object. A multiple hypothesis tracker (MHT) typically will form different track association hypotheses, where each hypothesis can be considered as a Kalman filter (for the linear Gaussian case) with a specific set of parameters associated with the hypothesized object. Thus, it is important to compute the likelihood of the observations for the different hypotheses under consideration, such that the most-likely one can be found.

Information filter

In cases where the dimension of the observation vector y is bigger than the dimension of the state space vector x, the information filter can avoid the inversion of a bigger matrix in the Kalman gain calculation at the price of inverting a smaller matrix in the prediction step, thus saving computing time. In the information filter, or inverse covariance filter, the estimated covariance and estimated state are replaced by the information matrix and information vector respectively. These are defined as:

${\displaystyle {\begin{aligned}\mathbf {Y} _{k\mid k}&=\mathbf {P} _{k\mid k}^{-1}\\{\hat {\mathbf {y} }}_{k\mid k}&=\mathbf {P} _{k\mid k}^{-1}{\hat {\mathbf {x} }}_{k\mid k}\end{aligned}}}$ 

Similarly the predicted covariance and state have equivalent information forms, defined as:

${\displaystyle {\begin{aligned}\mathbf {Y} _{k\mid k-1}&=\mathbf {P} _{k\mid k-1}^{-1}\\{\hat {\mathbf {y} }}_{k\mid k-1}&=\mathbf {P} _{k\mid k-1}^{-1}{\hat {\mathbf {x} }}_{k\mid k-1}\end{aligned}}}$ 

as have the measurement covariance and measurement vector, which are defined as:

${\displaystyle {\begin{aligned}\mathbf {I} _{k}&=\mathbf {H} _{k}^{\textsf {T}}\mathbf {R} _{k}^{-1}\mathbf {H} _{k}\\\mathbf {i} _{k}&=\mathbf {H} _{k}^{\textsf {T}}\mathbf {R} _{k}^{-1}\mathbf {z} _{k}\end{aligned}}}$ 

The information update now becomes a trivial sum.^[53]

${\displaystyle {\begin{aligned}\mathbf {Y} _{k\mid k}&=\mathbf {Y} _{k\mid k-1}+\mathbf {I} _{k}\\{\hat {\mathbf {y} }}_{k\mid k}&={\hat {\mathbf {y} }}_{k\mid k-1}+\mathbf {i} _{k}\end{aligned}}}$ 

The main advantage of the information filter is that N measurements can be filtered at each time step simply by summing their information matrices and vectors.

${\displaystyle {\begin{aligned}\mathbf {Y} _{k\mid k}&=\mathbf {Y} _{k\mid k-1}+\sum _{j=1}^{N}\mathbf {I} _{k,j}\\{\hat {\mathbf {y} }}_{k\mid k}&={\hat {\mathbf {y} }}_{k\mid k-1}+\sum _{j=1}^{N}\mathbf {i} _{k,j}\end{aligned}}}$ 

To predict the information filter the information matrix and vector can be converted back to their state space equivalents, or alternatively the information space prediction can be used.^[53]

December 15, 2023