Dilution Of Precision (navigation)

Dilution of precision (DOP), or geometric dilution of precision (GDOP), is a term used in satellite navigation and geomatics engineering to specify the error propagation as a mathematical effect of navigation satellite geometry on positional measurement precision.

Introduction

The concept of dilution of precision (DOP) originated with users of the Loran-C navigation system. The idea of geometric DOP is to state how errors in the measurement will affect the final state estimation. This can be defined as:

:$\operatorname = \frac$

Conceptually you can geometrically imagine errors on a measurement resulting in the $\Delta ( \text )$ term changing. Ideally small changes in the measured data will not result in large changes in output location. The opposite of this ideal is the situation where the solution is very sensitive to measurement errors. The interpretation of this formula is shown in the figure to the right, showing two possible scenarios with acceptable and poor GDOP.

With the wide adoption of satellite navigation systems, the term has come into much wider usage. Neglecting ionospheric and tropospheric effects, the signal from navigation satellites has a fixed precision. Therefore, the relative satellite-receiver geometry plays a major role in determining the precision of estimated positions and times. Due to the relative geometry of any given satellite to a receiver, the precision in the pseudorange of the satellite translates to a corresponding component in each of the four dimensions of position measured by the receiver (i.e., $x$, $y$, $z$, and $t$). The precision of multiple satellites in view of a receiver combine according to the relative position of the satellites to determine the level of precision in each dimension of the receiver measurement. When visible navigation satellites are close together in the sky, the geometry is said to be weak and the DOP value is high; when far apart, the geometry is strong and the DOP value is low. Consider two overlapping rings, or annuli, of different centres. If they overlap at right angles, the greatest extent of the overlap is much smaller than if they overlap in near parallel. Thus a low DOP value represents a better positional precision due to the wider angular separation between the satellites used to calculate a unit's position. Other factors that can increase the effective DOP are obstructions such as nearby mountains or buildings.

DOP can be expressed as a number of separate measurements:
; HDOP: Horizontal dilution of precision
; VDOP: Vertical dilution of precision
; PDOP: Position (3D) dilution of precision
; TDOP: Time dilution of precision
; GDOP: Geometric dilution of precision

These values follow mathematically from the positions of the usable satellites. Signal receivers allow the display of these positions (''skyplot'') as well as the DOP values.

The term can also be applied to other location systems that employ several geographical spaced sites. It can occur in electronic-counter-counter-measures ( electronic warfare) when computing the location of enemy emitters ( radar jammers and radio communications devices). Using such an interferometry technique can provide certain geometric layout where there are degrees of freedom that cannot be accounted for due to inadequate configurations.

The effect of geometry of the satellites on position error is called geometric dilution of precision (GDOP) and it is roughly interpreted as ratio of position error to the range error. Imagine that a square pyramid is formed by lines joining four satellites with the receiver at the tip of the pyramid. The larger the volume of the pyramid, the better (lower) the value of GDOP; the smaller its volume, the worse (higher) the value of GDOP will be. Similarly, the greater the number of satellites, the better the value of GDOP.

Interpretation

The DOP factors are functions of the diagonal elements of the covariance matrix of the parameters, expressed either in a global or a local geodetic frame.

Computation

As a first step in computing DOP, consider the unit vectors from the receiver to satellite $i$:
:$\begin &\left(\frac, \frac, \frac\right), & R_i &= \sqrt \end$

where $x, y, z$ denote the position of the receiver and $x_i, y_i, z_i$ denote the position of satellite i. Formulate the matrix, A, which (for 4 pseudorange measurement residual equations) is:
:$A = \begin \frac & \frac & \frac & 1 \\ \frac & \frac & \frac & 1 \\ \frac & \frac & \frac & 1 \\ \frac & \frac & \frac & 1 \end$

The first three elements of each row of ''A'' are the components of a unit vector from the receiver to the indicated satellite. The last element of each row refers to the partial derivative of pseudorange w.r.t. receiver's clock bias.
Formulate the matrix, ''Q'', as the covariance matrix resulting from the least-squares normal matrix:
:$Q = \left( A^\mathsf A \right)^$

In general:
: $Q = \left(J_\mathsf^\mathsf \left(J_ C_ J_^\mathsf\right)^J_\right)^$

where $J_$ is the Jacobian of the sensor measurement residual equations $f_\left(\underline, \underline\right) = 0$, with respect to the unknowns, $\underline$; $J_$ is the Jacobian of the sensor measurement residual equations with respect to the measured quantities $\underline$, and $C_$ is the correlation matrix for noise in the measured quantities.

For the preceding case of 4 range measurement residual equations: $\underline = (x, y, z, \tau)^\mathsf$, $\underline = \left(\tau_, \tau_, \tau_, \tau_\right)^\mathsf$, $\tau = ct$, $\tau_ = ct_$, $R_ = , \tau_ - \tau, = \sqrt$, $f_\left(\underline, \underline\right) = \sqrt - \sqrt$, $J_ = A$, $J_ = -I$ and the measurement noises for the different $\tau _$ have been assumed to be independent which makes $C_ = I$.

This formula for Q arises from applying best linear unbiased estimation to a linearized version of the sensor measurement residual equations about the current solution $\Delta\underline = -Q*\left(J_^\mathsf\left(J_C_J_^\mathsf\right)^f\right)$, except in the case of B.L.U.E. $C_$ is a noise covariance matrix rather than the noise correlation matrix used in DOP, and the reason DOP makes this substitution is to obtain a relative error. When $C_$ is a noise covariance matrix, $Q$ is an estimate of the matrix of covariance of noise in the unknowns due to the noise in the measured quantities. It is the estimate obtained by the ''first-order second moment'' (F.O.S.M.) uncertainty quantification technique which was state of the art in the 1980s. In order for the F.O.S.M. theory to be strictly applicable, either the input noise distributions need to be Gaussian or the measurement noise standard deviations need to be small relative to rate of change in the output near the solution. In this context, the second criteria is typically the one that is satisfied.

This (i.e. for the 4 time of arrival/range measurement residual equations) computation is in accordance with where the weighting matrix,
$P = \left(J_C_J_^\mathsf\right)^$ happens to simplify down to the identity matrix.

Note that P only simplifies down to the identity matrix because all the sensor measurement residual equations are time of arrival (pseudo range) equations. In other cases, for example when trying to locate someone broadcasting on an international distress frequency, $P$ would not simplify down to the identity matrix and in that case there would be a "frequency DOP" or FDOP component either in addition to or in place of the TDOP component. (Regarding "in place of the TDOP component": Since the clocks on the legacy International Cospas-Sarsat Programme LEO satellites are much less accurate than GPS clocks, discarding their time measurements would actually increase the geolocation solution accuracy.)

The elements of $Q$ are designated as:
:$Q = \begin \sigma_x^2 & \sigma_ & \sigma_ & \sigma_ \\ \sigma_ & \sigma_^2 & \sigma_ & \sigma_ \\ \sigma_ & \sigma_ & \sigma_^2 & \sigma_ \\ \sigma_ & \sigma_ & \sigma_ & \sigma_^2 \end$

PDOP, TDOP, and GDOP are given by:Section 1.4.9 of ''Principles of Satellite Positioning''

:$\begin \operatorname &= \sqrt\\ \operatorname &= \sqrt\\ \operatorname &= \sqrt\\ &= \sqrt\\ \end$

Notice GDOP is the square root of the trace of the $Q$ matrix.

The horizontal and vertical dilution of precision,
:$\begin \operatorname &= \sqrt \\ \operatorname &= \sqrt \end$,
are both dependent on the coordinate system used. To correspond to the local east-north-up coordinate system,

EDOP^2 x x x
x NDOP^2 x x
x x VDOP^2 x
x x x TDOP^2

and the derived dilutions:
:$\begin \operatorname &= \sqrt \\ \operatorname &= \sqrt \\ \operatorname &= \sqrt \end$

See also

* Circular error probable
* GNSS positioning calculation

References

Further reading

DOP Factors

manually calculating GDOP

HDOP AND GPS HORIZONTAL POSITION ERRORS

* Article on DOP and Trimble's program:
Determining Local GPS Satellite Geometry Effects On Position Accuracy

* Notes & GIF image on manually calculating GDOP
Geographer's Craft
* GPS Errors & Estimating Your Receiver's Accuracy

* GPS Accuracy, Errors & Precision
Radio-Electronics.com

{{DEFAULTSORT:Dilution Of Precision (Gps)
Satellite navigation