Accession Number : ADA282792


Title :   Ring Laser Gyro Resonator Design


Descriptive Note : Technical rept.


Corporate Author : AEROSPACE CORP EL SEGUNDO CA TECHNOLOGY OPERATIONS


Personal Author(s) : Chodzko, R


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a282792.pdf


Report Date : 20 Jun 1994


Pagination or Media Count : 19


Abstract : Ring laser gyroscopes (RLGS) have been used for navigation on the Atlas II launch vehicle and are scheduled for the Titan IV and Delta launch vehicles. The typical launch vehicle random-vibration environment could cause errors in measured RLG rotation rates due to vibration (tilt) of the resonator mirrors. Vibration-induced mirror tilt can create a variation in laser power due to laser beam occlusion by the intracavity mode control aperture(s). In the present work, we have analyzed the RLG resonator design theoretically and calculated pertinent parameters such as the beam diameter at the aperture, cavity mirror alignment sensitivities, and power loss due to aperture occlusion. The mirror vibration levels required to significantly affect the laser power were then calculated for typical RLG resonator geometries. It is concluded that vibration-induced bending of a typical RLG resonator structure should not cause a significant loss in laser power.


Descriptors :   *RING LASERS , *LASER GUIDANCE , *LAUNCH VEHICLES , *GYROSCOPES , MIRRORS , VIBRATION , BENDING , LASER BEAMS , NAVIGATION , RESONATORS , CAVITY RESONATORS , RANDOM VIBRATION


Subject Categories : Lasers and Masers
      Navigation and Guidance
      Unmanned Spacecraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE