Navigation system utilizing yaw rate constraint during inertial dead reckoning
A navigation system that utilizes yaw rate constraint during inertial dead reckoning is provided. The system accumulates relative yaw measurements to produce dead reckoning mechanization update values. The system corrects for z axis drift errors.
1. A Global Navigation Satellite System (GNSS)/inertial (INS) navigation system including:
a GNSS subsystem including a GNSS antenna that receives GNSS satellite signals and a GNSS receiver that processes the GNSS satellite signals to produce GNSS measurement information;
an INS subsystem including
an inertial measurement unit (IMU) with a plurality of sensors including one or more gyroscopes that measure rotation about a z axis, the IMU being configured to produce IMU measurements for the respective sensors,
a yaw rate constraint subsystem configured to accumulate the IMU measurements of rotation about the z-axis over mechanization update intervals to produce dead reckoning mechanization update values and accumulate the values over a turn rate accumulation period and calculate a corresponding yaw rate, the yaw rate constraint subsystem being further configured to operate during a dead reckoning mode to determine at the start of a next mechanization update interval, if the calculated yaw rate exceeds a turn rate threshold, and if not, direct an INS filter to perform a zero yaw rate update,
the INS filter being configured to
process the GNSS measurement information and the IMU measurements at the start of the mechanization update interval when the GNSS/INS system is in a navigation mode,
process the IMU measurements and perform the zero yaw rate update if directed to do so at the start of the mechanization update interval when the GNSS/INS system is in the dead reckoning mode, and
process the IMU measurements over the mechanization update interval to produce one or more of INS-based position, velocity and attitude.
2. The GNSS/INTS navigation system of claim 1 wherein the turn rate threshold is associated with an intentional turn rate that corresponds to an environment in which the GNSS/INS system is operating.
3. The GNSS/INS navigation system of claim 2 wherein the turn rate accumulation period includes one or more mechanization update intervals.
4. The GNSS/INTS navigation system of claim 3 wherein the zero yaw rate update is performed using accumulated z-axis measurements from the previous mechanization update interval.
5. The GNSS/INTS navigation system of claim 4 wherein the yaw rate constraint subsystem further assigns weights to the z-axis measurements based on a level of noise observed over the previous mechanization update interval before performing the zero yaw rate update.
6. The GNSS/INTS navigation system of claim 1 wherein the INS filter is a Kalman filter and the zero yaw rate update utilizes a design matrix H with the attitude states filled, and an observation equation z and an update variance R
H 1×N =[0 0 0 . . . R l 13 e R l 23 e R l 33 e . . . 0 0 0]
z 1×1 =0.0−ΣGyro z l
R 1×1 =( 3.0*Standard Devation(ΣGyro z l )) 2
where the rotation matrix included in the design matrix H is defined by the mechanization frame of the INS filter.
7. An inertial (INS) navigation system including
an inertial measurement unit (IMU) with a plurality of sensors including one or more gyroscopes that measure rotation about a z axis, the IMU being configured to produce IMU measurements for the respective sensors,
a yaw rate constraint subsystem configured to accumulate the z-axis measurements over mechanization update intervals to produce dead reckoning mechanization update values, accumulate the values over a turn rate accumulation period and produce a yaw rate, the yaw rate constraint subsystem being further configured to determine at the start of a mechanization update interval, if the yaw rate exceeds a turn rate threshold, and if not, direct an INS filter to perform a zero yaw rate update, and
the INS filter being configured to
process the IMU measurements and perform the zero yaw rate update if directed to do so at the start of a next mechanization update interval, and
process the IMU measurements over the next mechanization update interval to produce one or more of INS-based position, velocity and attitude.
8. The INS navigation system of claim 7 wherein the turn rate threshold is associated with an intentional turn rate that corresponds to an environment in which the INS navigation system is operating.
9. The INS navigation system of claim 8 wherein the turn rate accumulation period includes one or more mechanization update intervals and the zero yaw rate update is performed using the dead reckoning mechanization update value from the previous mechanization update interval.
10. The INS navigation system of claim 7 wherein the yaw rate constraint subsystem further assigns weights to the z-axis measurements based on a level of noise in the measurements over the previous mechanization update interval before performing the zero yaw rate update.
11. The INS navigation system of claim 7 wherein the INS filter is a Kalman filter and the zero yaw rate update utilizes a design matrix H with the attitude states filled, and an observation equation z and an update variance R
H 1×N =[0 0 0 . . . R l 13 e R l 23 e R l 33 e . . . 0 0 0]
z 1×1 =0.0−ΣGyro z l
R 1×1=( 3.0*Standard Devation(ΣGyro z l )) 2
where the rotation matrix included in the design matrix H is defined by the mechanization frame of the INS filter.