Implement three-axis accelerometer
The Three-Axis Accelerometer block implements an accelerometer on each of the three axes. The ideal measured accelerations () include the acceleration in body axes at the center of gravity (), lever arm effects due to the accelerometer not being at the center of gravity, and, optionally, gravity in body axes can be removed.
where are body-fixed angular rates, are body-fixed angular accelerations and is the lever arm. The lever arm () is defined as the distances that the accelerometer group is forward, right and below the center of gravity.
The orientation of the axes used to determine the location of the accelerometer group (xacc, yacc, zacc) and center of gravity (xCG, yCG, zCG) is from the zero datum (typically the nose) to aft, to the right of the vertical centerline and above the horizontal centerline. The x-axis and z-axis of this measurement axes are opposite the body-fixed axes producing the negative signs in the lever arms for x-axis and z-axis.
Measured accelerations () output by this block contain error sources and are defined as
where is a 3-by-3 matrix of scaling factors on the diagonal and misalignment terms in the nondiagonal, and are the biases.
Optionally discretizations can be applied to the block inputs and dynamics along with nonlinearizations of the measured accelerations via a Saturation block.
Specifies the input and output units:
|Meters per second squared||Meters|
|Feet per second squared||Feet|
The location of the accelerometer group is measured from the zero datum (typically the nose) to aft, to the right of the vertical centerline and above the horizontal centerline. This measurement reference is the same for the center of gravity input. The units are in selected length units.
Select to subtract gravity from acceleration readings.
Select to apply second-order dynamics to acceleration readings.
The natural frequency of the accelerometer. The units of natural frequency are radians per second.
The damping ratio of the accelerometer. A dimensionless parameter.
The 3-by-3 matrix used to skew the accelerometer from body axes and to scale accelerations along body axes.
The three-element vector containing long-term biases along the accelerometer axes. The units are in selected acceleration units.
Specify the update rate of the accelerometer. An update rate of 0 will create a continuous accelerometer. If noise is selected and the update rate is 0, then the noise will be updated at the rate of 0.1. The units of update rate are seconds.
Update this parameter value to 0 (continuous)
Configure a fixed-step solver for the model
Do not have a Control System Toolbox™ license
you must also select the Automatically handle rate transition for data transfer check box in the Solver pane. This check box enables the software to handle rate transitions correctly.
Select to apply white noise to acceleration readings.
The scalar seeds for the Gaussian noise generator for each axis of the accelerometer.
The height of the PSD of the white noise for each axis of the accelerometer. The units are:
The six-element vector containing three minimum values and three maximum values of acceleration in each of the accelerometer axes. The units are in selected acceleration units.
|Three-element vector||Contains the actual accelerations in body-fixed axes, in selected units.|
|Three-element vector||Contains the angular rates in body-fixed axes, in radians per second.|
|Three-element vector||Contains the angular accelerations in body-fixed axes, in radians per second squared.|
|Three-element vector||Contains the location of the center of gravity, in selected units.|
|Three-element vector||Contains the gravity in body axis, in selected units.|
|Three-element vector||Contains the measured accelerations from the accelerometer, in selected units.|
Vibropendulous error and hysteresis effects are not accounted for in this block. Additionally, this block is not intended to model the internal dynamics of different forms of the instrument.
Note: This block requires the Control System Toolbox product for discrete operation (nonzero sample time).
Rogers, R. M., Applied Mathematics in Integrated Navigation Systems, AIAA Education Series, 2000.