Satellite orientation system
Embodiments of the present invention include a two-stage blending filter that blends the measurements from two angular sensors to form a single superior high bandwidth measurement for improved disturbance rejection in a satellite systems for increased accuracy in satellite pointing, orientation, and attitude control. Embodiments of the present invention can include a satellite system including a first sensor including or defining a first measurement bandwidth; a first filter connected to the first sensor; a second sensor including or defining a second measurement bandwidth; a second filter connected to the second sensor; and a third filter connected to the first filter and the second filter. The third filter blend the first signal and the second signal into a third signal; and transmit the third signal to a flight controller configured to adjust an orientation of the satellite, a satellite subsystem, or both, relative to a target in response to the third signal.
1. A satellite system comprising:
a first angle sensor comprising a first measurement bandwidth;
a first filter connected to the first sensor;
a second angle sensor comprising a second measurement bandwidth;
a second filter connected to the second sensor;
a third filter connected to the first filter and the second filter, the third filter configured to:
receive a first signal from the first filter comprising a first bandwidth range;
receive a second signal from the second filter comprising a second bandwidth range;
blend the first signal and the second signal into a third signal; and
transmit the third signal to a flight controller configured to adjust an orientation of the satellite, a satellite subsystem, or both, relative to a target in response to the third signal.
2. The satellite system of claim 1 , wherein the first sensor comprises a Coriolis vibratory gyro.
3. The satellite system of claim 2 , wherein the first measurement bandwidth comprises a range between DC and a first high frequency value.
4. The satellite system of claim 3 , wherein the second sensor comprises a magneto-hydro dynamometer.
5. The satellite system of claim 4 , wherein the second measurement bandwidth comprises a range comprising a second high frequency value greater than the first high frequency value.
6. The satellite system of claim 5 , wherein the first filter comprises a lowpass filter configured to suppress high frequency noise from the first sensor.
7. The satellite system of claim 6 , wherein the second filter comprises a high pass filter configured to suppress low frequency noise from the second sensor.
8. The satellite system of claim 7 , wherein the third filter comprises an H-infinity filter.
9. The satellite system of claim 1 , further comprising an actuator connected to the flight controller and configured to orient the satellite, the satellite subsystem, or both, in response to a command from the flight controller.
10. A satellite orientation system comprising:
an actuator configured to orient the satellite, a satellite subsystem, or both;
a blending filter comprising:
a first filter connected to a first sensor;
a second filter connected to a second sensor;
a third filter connected to the first filter and the second filter, the third filter configured to:
receive a first signal from the first filter comprising a first bandwidth range;
receive a second signal from the second filter comprising a second bandwidth range;
blend the first signal and the second signal into a third signal; and
a flight controller connected to the blending filter and the actuator, the flight controller configured to command the actuator to adjust an orientation of the satellite, a satellite subsystem, or both, relative to a target in response to the third signal.
11. The system of claim 10 , further comprising a first sensor comprising a Coriolis vibratory gyro comprising a first measurement bandwidth.
12. The system of claim 11 , wherein the first measurement bandwidth comprises a range between DC and a first high frequency value.
13. The system of claim 12 , wherein the first filter comprises a lowpass filter configured to suppress high frequency noise from the first sensor.
14. The system of claim 10 , wherein the second sensor comprises a magneto-hydro dynamometer comprising a second measurement bandwidth.
15. The system of claim 14 , wherein the second measurement bandwidth comprises a range comprising a second high frequency value greater than the first high frequency value.
16. The system of claim 15 , wherein the second filter comprises a high pass filter configured to suppress low frequency noise from the second sensor.
17. The system of claim 10 , wherein the third filter comprises an H-infinity filter.
18. A satellite orientation system comprising:
an actuator configured to orient the satellite, a satellite subsystem, or both;
a Coriolis vibratory gyro comprising a first measurement bandwidth;
a first filter connected to the Coriolis vibratory gyro;
a magneto-hydro dynamometer comprising a second measurement bandwidth;
a second filter connected to the magneto-hydro dynamometer;
an H-infinity blending filter connected to the first filter and the second filter, configured to:
receive a first signal from the first filter comprising a first bandwidth range;
receive a second signal from the second filter comprising a second bandwidth range;
blend the first signal and the second signal into a third signal; and
a flight controller connected to the H-infinity blending filter and the actuator, the flight controller configured to command the actuator to adjust an orientation of the satellite, a satellite subsystem, or both, relative to a target in response to the third signal.
19. The system of claim 18 , wherein:
the first measurement bandwidth measurement comprises a first bandwidth range between DC and a first high frequency value; and
the second bandwidth measurement comprises a range comprising a second high frequency value greater than the first high frequency value.
20. The system of claim 18 , wherein:
the first filter comprises a lowpass filter configured to suppress high frequency noise from the Coriolis vibratory gyro; and
the second filter comprises a high pass filter configured to suppress low frequency noise from the magneto-hydro dynamometer.