Active control of soft hybrid isolation systems
Apparatus, Systems, and Methods are provided for controlling motion of a spacecraft. One apparatus includes a non-contacting actuator and a passive mechanical system coupled in parallel with one another. A system includes a payload, a bus, and a hybrid actuator including a non-contacting actuator and a passive mechanical system coupled in parallel, and coupled between the bus and the payload. The system also includes an inertial actuator configured to maneuver the bus to maintain a relative position and/or attitude of the bus with respect to the payload. One method includes receiving a signal instructing a first controller to change the position and/or attitude of a payload and utilizing a hybrid system to change the position and/or attitude of the payload. The method also includes receiving the signal at a second controller and utilizing a system to change a position and/or attitude of the bus independent of the payload.
1. A hybrid actuator for maneuvering a spacecraft payload coupled to a spacecraft bus, comprising:
a non-contacting actuator; and
a passive mechanical system coupled in parallel with the non-contacting actuator,
wherein the passive mechanical system comprises:
a first spring;
a damper coupled in series with the first spring; and
a second spring coupled in parallel with the first spring and the damper.
2. The hybrid actuator of claim 1 , wherein the non-contacting actuator comprises one of an electromagnetic actuator and an electrostatic actuator.
3. The hybrid actuator of claim 1 , wherein the non-contacting actuator comprises a voice coil.
4. A system for controlling motion of a spacecraft including a payload coupled to a bus, the system comprising:
a hybrid actuator including:
a non-contacting actuator coupled between the payload and the bus, and
a passive mechanical system coupled in parallel with the non-contacting actuator, the hybrid actuator configured to maneuver one of a position and an attitude of the payload; and
a maneuvering system coupled to the bus, and configured to maneuver the bus to substantially maintain one of a relative position and a relative attitude of the bus with respect to the payload,
wherein the passive mechanical system comprises:
a first spring;
a damper coupled in series with the first spring; and
a second spring coupled in parallel with the first spring and the damper.
5. The system of claim 4 , wherein the non-contacting actuator comprises one of an electromagnetic actuator and an electrostatic actuator.
6. The system of claim 4 , wherein the non-contacting actuator comprises a voice coil.
7. The system of claim 4 , wherein the maneuvering system comprises one of a thruster, a reaction wheel assembly, a magnetic torquer, a solar sail, and a control moment gyroscope.
8. The system of claim 4 , further comprising:
a payload sensor in communication with the hybrid actuator, and configured to determine the one of the position and the attitude; and
a relative six degrees of freedom motion sensor in communication with the maneuvering system, and configured to determine the relative motion of the bus with respect to the payload.
9. The system of claim 8 , wherein the payload sensor is one of a gyroscope, an accelerometer, a star-tracker, and a focal plane detector.
10. The system of claim 4 , wherein the hybrid actuator is configured to maneuver the payload with respect to a center of mass of the spacecraft.
11. The system of claim 10 , wherein the maneuvering system is configured to maneuver the bus with respect to the center of mass of the spacecraft.
12. The system of claim 4 , wherein the hybrid actuator further comprises at least five non-contacting actuators and at least five passive mechanical systems, and wherein:
each non-contacting actuator is coupled in parallel with a respective passive mechanical system to form a hexapod configuration; and
each non-contacting actuator and passive mechanical system is coupled between the payload and the bus.