Spacecraft Models Package 2.0
Spacecraft Models for DSim
Public Member Functions | Protected Attributes | List of all members
imu Class Reference

Rate integrating IMU model. More...

#include <imu.h>

Inherits dsim_model.

Public Member Functions

 imu (dsim_model_setup *setup)
 Constructor.
 
 ~imu ()
 Destructor.
 
void initialize_data ()
 Initialize outlets and output variables.
 
void initialization_complete ()
 Finish initialization.
 
void complete_timestep ()
 Computation done after numerical integration.
 
void initialize_timestep ()
 Computation done prior to numerical integration.
 
void rhs (double t, double jd)
 Computation done during numerical integration.
 

Protected Attributes

dsim_variable bodyRate_dsim
 Body rate input.
 
dsim_variable acceleration_dsim
 Linear acceleration input.
 
dsim_variable angularAcceleration_dsim
 Angular acceleration input.
 
dsim_variable centerOfMass_dsim
 Linear acceleration input.
 
dsim_variable angularIncrement_dsim
 Angular increment input.
 
dsim_variable acceleration_measured_dsim
 Linear acceleration input.
 
dsim_variable integratedRate_dsim
 Angular rate input.
 
dsim_variable biasAccelerometer_dsim
 Angular rate input.
 
dsim_variable biasGyro_dsim
 Angular rate input.
 
dsim_variable imuPosition_dsim
 Angular rate input.
 
dsim_variable imuBodyToIMUMatrix_dsim
 Angular rate input.
 
dsim_variable oneSigmaGyroBias_dsim
 Gyro random walk noise.
 
dsim_variable oneSigmaAccelerometerBias_dsim
 Accelerometer random walk noise.
 
dsim_variable oneSigmaGyro_dsim
 Gyro output noise.
 
dsim_variable oneSigmaAccelerometer_dsim
 Accelerometer output noise.
 
dsim_variable tauGyroBias_dsim
 Gyro bias time constant.
 
dsim_variable tauAccelerometerBias_dsim
 Accelerometer bias time constant.
 
dsim_variable omegaConstant_dsim
 Gyro constant rate.
 
dsim_variable accelerationConstant_dsim
 Accelerometer constant rate.
 
dsim_variable imuBodyToIMUMatrix_param_dsim
 Accelerometer constant rate.
 

Detailed Description

Rate integrating IMU model.

Models an inertial measurement unit with 3 orthogonal linear accelerometers and 3 rate integrating gyros. The model for both gyro and accelerometer is

omega = omega_true + bias + constant + noise dbias/dt + bias/tau = noise

The second equation is for a Markov model. If tau = infinity this is a random walk model.

Reference: Warren S. Flenniken IV, John H. Wall, David M. Bevly, "Characterization of Various IMU Error Sources and the Effect on Navigation Performance"


The documentation for this class was generated from the following files: