초록 ▼

A method for pointing control of a laser communication terminal on a spacecraft may include measuring a line-of-sight (LOS) error of the laser communication terminal. The method may also include estimating a LOS error of the laser communication terminal based on measurements from a spacecraft gyro a

A method for pointing control of a laser communication terminal on a spacecraft may include measuring a line-of-sight (LOS) error of the laser communication terminal. The method may also include estimating a LOS error of the laser communication terminal based on measurements from a spacecraft gyro and a gimbal gyro onboard the spacecraft. The method may further include switching from a LOS error measurement feedback to a LOS error estimate feedback to control pointing of the laser communication terminal during a power fade condition.

대표청구항 ▼

1. A method for pointing control of a laser communication terminal onboard a spacecraft, comprising: measuring a LOS error of the laser communication terminal, wherein measuring the LOS error comprises receiving a laser beam from a remote laser communications terminal by an optical receiver, the opt

1. A method for pointing control of a laser communication terminal onboard a spacecraft, comprising: measuring a LOS error of the laser communication terminal, wherein measuring the LOS error comprises receiving a laser beam from a remote laser communications terminal by an optical receiver, the optical receiver providing a LOS error measurement;estimating a LOS error of the laser communication terminal based on measurements from a spacecraft gyro and a gimbal gyro onboard the spacecraft; andmeasuring a FSM position of a fast steering mirror that controls pointing of the laser communication terminal for communications;blending a measurement from the spacecraft gyro and a measurement from the gimbal gyro associated with a gimbal for pointing the laser communication terminal, to provide a base jitter rate of the laser communication terminal;determining a LOS error estimate of the laser communication terminal from the measured LOS error, the measured FSM position and the blended gyro measurement from the spacecraft gyro and the gimbal gyro; andswitching from a LOS error measurement feedback to a LOS error estimate feedback to control the FSM position for pointing of the laser communication terminal during a power fade condition. 2. The method of claim 1, further comprising: determining a predicted base jitter of the laser communication terminal from the blended gyro measurement of the spacecraft gyro and the gimbal gyro;determining a base jitter measurement error or residue of the laser communication terminal from the measured LOS error, the measured FSM position and the predicted base jitter;determining a base jitter estimate correction from the measurement error or residue;determining an estimated base jitter from the predicted base jitter and the base jitter estimate correction; anddetermining the LOS error estimate from the estimated base jitter and the measured FSM position. 3. The method of claim 1, further comprising: determining a base jitter position measurement from the measured LOS error and the measured FSM position;determining a base jitter rate measurement from the blended measurement from the spacecraft gyro and the gimbal gyro;determining an estimated base jitter from the base jitter position measurement and the base jitter rate measurement; anddetermining the LOS error estimate from the estimated base jitter and measured FSM position. 4. The method of claim 3, wherein determining an estimated base jitter from the base jitter position measurement and the base jitter rate measurement comprises using a Kalman filter. 5. The method of claim 1, further comprising using the LOS error estimate to generate a FSM control command for pointing control of the laser communication terminal in response to a measured signal power of a laser signal from a remote laser communication terminal being below a predetermined threshold, and wherein the measured LOS error is used to generate the FSM control command for pointing control of the laser communication terminal in response to the measured signal power from the remote laser communication terminal being greater than the predetermined threshold for a selected number of signal power measurements after the measured signal power is measured as being below the predetermined threshold. 6. The method of claim 1, further comprising: resetting a counter in response to a measured signal power of a laser signal from a remote laser communication terminal being less than a predetermined threshold;incrementing the counter each time the measured signal power is greater than the predetermined threshold;using the LOS error estimate to generate a FSM control command for pointing control of the laser communication terminal in response to the counter being less than a preset exit threshold even though the measured signal power of the laser signal received from the remote laser communication terminal is greater than the predetermined threshold; andusing the LOS error measurement to generate the FSM control command for pointing control of the laser communication terminal in response to the measured signal power of the laser signal received from the remote laser communication terminal being greater than the predetermined threshold and the counter being greater than the preset exit threshold. 7. A method for pointing control of a laser communication terminal onboard a spacecraft, comprising: determining an estimated base jitter of the laser communication terminal;measuring a LOS error of the laser communication terminal, wherein measuring the LOS error comprises receiving a laser beam from a remote laser communications terminal by an optical receiver, the optical receiver providing a LOS error measurement;measuring a FSM position of a fast steering mirror that controls pointing of the laser communication terminal for communications;measuring a signal power of a laser signal received by the laser communication terminal from a remote laser communication terminal being tracked by the laser communication terminal for communications with the remote laser communication terminal;estimating a LOS error based on the estimated base jitter of the laser communication terminal and the measured FSM position;using the LOS error estimate as a FSM error to control positioning of the fast steering mirror in response to the measured signal power of the laser signal received from the remote laser communication terminal being less than a predetermined threshold; andusing the measured LOS error as the FSM error to control positioning of the fast steering mirror in response to the measured signal power being greater than the predetermined threshold. 8. The method of claim 7, further comprising determining a base jitter or motion of the laser communication terminal by determining a base motion of the laser communication terminal using a spacecraft gyro and a gimbal gyro onboard the spacecraft. 9. The method of claim 7, further comprising determining a base jitter or motion of the laser communication terminal by measuring an angular velocity of a base motion of the laser communication terminal using measurements from the spacecraft gyro and the gimbal gyro associated with the laser communication terminal. 10. The method of claim 9, wherein determining the base jitter or motion of the laser communication terminal comprises: acquiring a spacecraft gyro measurement;acquiring a gimbal gyro measurement from a gyro coupled to a gimbal for positioning the laser communication terminal; andblending the spacecraft gyro measurement and the gimbal gyro measurement to provide a rate measurement of the base jitter or motion of the laser communication terminal. 11. The method of claim 7, further comprising: resetting a counter in response to the measured signal power being less than a predetermined threshold;incrementing the counter each time the measured signal power is greater than the predetermined threshold;using the LOS error estimate as the FSM error to control positioning of the fast steering mirror in response to the counter being less than a preset exit threshold even though the measured signal power of the laser signal received from the remote laser communication terminal is greater than the predetermined threshold; andusing the LOS error measurement as the FSM error to control positioning of the fast steering mirror in response to the measured signal power of the laser signal received from the remote laser communication terminal being greater than the predetermined threshold and the counter being greater than the preset exit threshold. 12. A system for pointing control of a laser communication terminal onboard a spacecraft, comprising: a processor in the laser communication terminal mounted onboard the spacecraft;an optical receiver in the laser communication terminal for receiving a laser beam from a remote laser communications terminal to provide a LOS error measurement;a gyro-aided fine track control module operable on the processor, the gyro-aided fine track control module comprising: a sensor fusion module adapted to blend a measurement from a spacecraft gyro and a measurement from a gimbal gyro associated with a gimbal for pointing the laser communication terminal, to provide a base jitter rate of the laser communication terminal;a LOS error estimator adapted to estimate a LOS error based on measurements from the spacecraft gyro and the gimbal gyro onboard the spacecraft, the LOS error estimator being adapted to determine an LOS error estimate from the LOS error measurement, a measured FSM position and the blended gyro measurement from the spacecraft gyro and the gimbal gyro; andswitching logic module adapted to switch from using the LOS error measurement to using the LOS error estimate to generate a FSM command for pointing control of the laser communication terminal during a power fade condition. 13. The system of claim 12, wherein the LOS error estimator comprises: a computation unit for propagating a predicted base jitter of the laser communication terminal from the blended gyro measurement of the spacecraft gyro and the gimbal gyro;a computation unit for determining a base jitter measurement error or residue from the measured LOS error, the measured FSM position and the predicted base jitter;a computation unit for determining a base jitter estimate correction from the base jitter measurement error or residue;a computation unit for determining an estimated base jitter from the predicted base jitter and the base jitter estimate correction; anda computation unit for determining the LOS error estimate from the estimated base jitter and the measured FSM position. 14. The system of claim 12, wherein the LOS error estimator comprises: a computation unit to combine the measured LOS error and the measured FSM position to provide a base jitter position measurement;a conversion unit to provide a base jitter rate measurement;a base jitter estimation filter to generate an estimated base jitter of the laser communication terminal from the base jitter position measurement, the base jitter rate measurement and an enable jitter calibration signal; anda computation unit to combine the estimated base jitter and the FSM position measurement to provide the LOS error estimate. 15. The system of claim 12, further comprising: a counter, wherein the counter is incremented each time a measured signal power of a laser signal from a remote laser communication terminal is greater than a predetermined threshold and wherein the counter is reset in response to the measured signal power being less than the predetermined threshold; anda switching arrangement, the switching arrangement comprising: means for using the LOS error estimate as the FSM error to control positioning of a fast steering mirror of the laser communication terminal in response to the counter being less than a preset exit threshold even though the measured signal power of the laser signal received from the remote laser communication terminal is greater than the predetermined threshold; andmeans for using the LOS error measurement as the FSM error to control positioning of the fast steering mirror in response to the measured signal power of the laser signal received from the remote laser communication terminal being greater than the predetermined threshold and the counter being greater than the preset exit threshold. 16. A computer program product for controlling pointing of a laser communication terminal onboard a spacecraft, the computer program product comprising: a computer readable storage medium having computer readable program code embodied therewith, the computer readable program code comprising:computer readable program code configured to measure a LOS error of the laser communication terminal, wherein the computer readable program code configured to measure the LOS error from a laser beam received from a remote laser communications terminal by an optical receiver;computer readable program code configured to estimate a LOS error of the laser communication terminal based on measurements from a spacecraft gyro and a gimbal gyro onboard the spacecraft;computer readable program code configured to blend a measurement from the spacecraft gyro and a measurement from the gimbal gyro associated with a gimbal for pointing the laser communication terminal, to provide a base jitter rate of the laser communication terminal;computer readable program code configured to determine an LOS error estimate of the laser communication terminal from the measured LOS error, a measured FSM position and the blended gyro measurement from the spacecraft gyro and the gimbal gyro; andcomputer readable program code configured to switch from a LOS error measurement feedback to a LOS error estimate feedback for controlling pointing of the laser communication terminal during a power fade condition.