Optical alignment system and method
An optical system for aligning various avionics sensors and displays includes an aircraft having a nose section, a forward fuselage section, and an aft fuselage section, and at least one of a sensor, a display, a sensor substitute, and a display substitute. A laser is attached to a side of the aft section of the fuselage, and is directed toward a corresponding laser target on a laser target board. The laser target board is mounted on a frame and is positioned a distance away from the aircraft, and includes a plurality of laser targets. Between the laser target board and the laser is a reference plate which includes an aperture through which a beam from the laser passes. With the laser aligned with its respective laser target, the relative position of the sensor, display, sensor substitute, or display substitute is determined relative to known positions on the aircraft.
1. An optical alignment system, comprising:
an aircraft having a nose section, a forward fuselage section, and an aft fuselage section;
at least one of a sensor, a sensor substitute, a display, and a display substitute;
at least one laser;
a laser target board mounted to a frame, the target board having a plurality of laser targets; and
a reference plate having an aperture;
wherein the laser target board is positioned a distance away from the nose section of the aircraft generally along a longitudinal centerline of the aircraft,
wherein a first laser is attached to a first side of the aft fuselage section of the aircraft and directed toward a first target located on the target board, and
wherein the reference plate is attached normal to a first side of the forward fuselage section of the aircraft such that a beam from the first laser passes through the aperture.
2. The alignment system of claim 1 , wherein the at least one of a sensor, a sensor substitute, a display, and a display substitute is located within the nose section of the aircraft.
3. The alignment system of claim 1 , wherein the at least one of a sensor, a sensor substitute, a display, and a display substitute is located within a cockpit of the aircraft.
4. The alignment system of claim 1 , wherein a height of the laser target board is adjustable.
5. The alignment system of claim 1 , wherein at least the first laser and the is attached to the fuselage via a gimbal mount.
6. The alignment system of claim 1 comprising a display or display substitute, wherein the display or display substitute is configured for aligning components of a Head-Up-Display.
7. The alignment system of claim 1 , wherein the at least one of a sensor and a sensor substitute includes an optical alignment tool directed toward a target located on the laser target board.
8. The alignment system of claim 7 , wherein the optical alignment tool includes at least one of a bore sighting scope and a laser.
9. The alignment system of claim 1 , wherein the laser target board includes a plurality of laser targets.
10. An optical alignment method for an aircraft having a nose section, a forward fuselage section, and an aft fuselage section, the method comprising:
providing at least one of a sensor, a display, a sensor substitute, or a display substitute; at least one laser, a laser target board mounted to a frame, the target board having a plurality of laser targets, and a reference plate having an aperture;
positioning the laser target board a known distance away from the nose section of the aircraft along a longitudinal centerline of the aircraft;
attaching a first laser to a first side of the aft fuselage section of the aircraft and directing the first laser toward a first target located on the target board;
attaching the reference plate to a first side of the forward fuselage section of the aircraft such that a beam from the first laser passes through the first aperture;
determining the distance from the target board to a reference location on a first side of the aircraft,
determining a position of the at least one sensor, display, sensor substitute, or display substitute relative to a reference position of the aircraft.
11. The alignment method of claim 10 , wherein the position of the at least one of a sensor and sensor substitute is an angular position, and a total angular tolerance window for the angular position is +/−1.5 milliradians in pitch, roll, and yaw.
12. The alignment method of claim 10 , further comprising adjusting a height of the laser target board.
13. The alignment method of claim 10 , further comprising placing at least one of a sensor and a sensor substitute within an interior of the aircraft and directing the at least one of a sensor and a sensor substitute towards a target on the laser target board.
14. The alignment method of claim 13 , wherein the at least one of a display and a display substitute is configured for aligning a Head-Up-Display system.
15. The alignment method of claim 10 , wherein the at least one of a sensor and a sensor substitute is located in the nose section of the aircraft.