Active isolation for seeker optics
An optical system configured to counteract vibrations due to a munitions launch includes a cylindrical optical lens stack. The system also includes an accelerometer attached to the lens stack and connected to a control system and power supply. The system further includes a mechanical actuator attached to the lens stack and connected to a control system and power supply. The mechanical actuator is a piezoelectric actuator.
1. An optical system configured to counteract deformation and/or vibration due to a munition launch and/or flight acceleration, the system comprising:
a power supply;
a control system;
a cylindrical optical lens stack;
a cylindrical holder attached to and surrounding the optical lens stack;
a piezoelectric cylinder attached to and surrounding the cylindrical holder and connected to both the control system and the power supply,
wherein the control system actuates the piezoelectric cylinder to counteract the deformation and/or the vibration of the optical lens stack caused by the munition launch and/or the flight acceleration.
2. The system of claim 1 , wherein the piezoelectric cylinder comprises an accelerometer.
3. The system of claim 1 , wherein the piezoelectric cylinder comprises a mechanical actuator.
4. The system of claim 2 , wherein the accelerometer has a sheer stress film sensor on an outside surface of the accelerometer.
5. The system of claim 2 , wherein the accelerometer is a piezoresistive accelerometer.
6. The system of claim 1 , wherein the piezoelectric cylinder comprises both an accelerometer and a mechanical actuator.
7. The system of claim 3 , further comprising:
a cylindrical accelerometer attached to and surrounding the piezoelectric cylinder.
8. The system of claim 7 , wherein the control system actuates the piezoelectric cylinder based on signals received from the cylindrical accelerometer so as to actuate the piezoelectric cylinder to counteract the deformation and/or vibration of the optical lens stack caused by the munition launch and/or the flight accelerations.
9. The system of claim 1 , wherein the optical lens stack operates at wavelengths from infrared to visible.
10. The system of claim 1 , wherein the system is included in a missile seeker system.
11. A method of forming an optical system configured to counteract deformation and/or vibration due to a munition launch and/or flight accelerations, the method comprising:
forming a multi-lens cylindrical optical lens stack in a cylindrical holder;
inserting the optical lens stack in a piezoelectric cylinder
connecting the piezoelectric cylinder to both a control system and a power supply;
actuating, via the control system, the piezoelectric cylinder to counteract the deformation and/or the vibration of the optical lens stack caused by the munition launch and/or the flight accelerations.
12. The method of claim 11 , further comprising:
sensing vibrations with an accelerometer.
13. The method of claim 12 , wherein the accelerometer is a piezoresistive accelerometer.
14. The method of claim 12 , wherein the accelerometer is a sheer stress film sensor.
15. The method of claim 12 , wherein the accelerometer is the piezoelectric cylinder.
16. The method of claim 12 , further comprising:
generating a signal by the accelerometer, wherein actuating, via the control system, of the piezoelectric cylinder is based on the signal generated by the accelerometer.
17. The method of claim 13 wherein a signal from the piezoresistive accelerometer is inverted and amplified by the control system and sent to the piezoelectric cylinder to counteract the deformation and/or the vibration of the optical lens stack caused by the munition launch and/or the flight accelerations to minimize deformation of the optical lens stack.
18. The method of claim 14 , wherein a signal from the sheer stress film sensor is inverted and amplified by the control system and sent to the piezoelectric cylinder to counteract the deformation and/or the vibration of the optical lens stack caused by the munition launch and/or the flight accelerations to minimize deformation of the optical stack.
19. The method of claim 11 , wherein a signal from the piezoelectric cylinder is inverted and amplified and used to actuate the piezoelectric cylinder to counteract the deformation and/or the vibration of the optical lens stack caused by the munition launch and/or the flight accelerations to minimize deformation of the optical lens stack.
20. The method of claim 11 , wherein the optical system is included in a missile seeker system.