Inertial Navigation and Control Assembly (INCA) And Redundant Rate Gyro Unit (RRGU)
Overview
Primary guidance and control of the Atlas V launch vehicle is provided by the integrated single fault-tolerant Inertial Navigation and Control Assembly (INCA) navigation and flight control assembly. INCA inertial instruments include five single axis Honeywell Ring Laser Gyros that measure vehicle body attitude changes and five Honeywell QA3000 single axis accelerometers to measure changes in vehicle body velocities that are integrated to provide an inertial navigation solution.
Angular rate information for first stage stabilization is provided by the Rate Gyro Assembly (RGA) unit featuring triply redundant pitch and yaw rate sensors. The INCA and RRGU are derived from a decades-long successful heritage of over 58 successful Atlas V missions.
INCA inertial instruments include five single axis Honeywell Ring Laser Gyros that measure vehicle body attitude changes and five Honeywell QA3000 single axis accelerometers to measure changes in vehicle body velocities that are integrated to provide an inertial navigation solution.
Angular rate information for first stage stabilization is provided by the Rate Gyro Assembly (RGA) unit featuring triply redundant pitch and yaw rate sensors. The INCA and RRGU are derived from a decades-long successful heritage of over 58 successful Atlas V missions.
Angular rate information for first stage stabilization is provided by the Rate Gyro Assembly (RGA) unit featuring triply redundant pitch and yaw rate sensors. The INCA and RRGU are derived from a decades-long successful heritage of over 58 successful Atlas V missions.
INCA inertial instruments include five single axis Honeywell Ring Laser Gyros that measure vehicle body attitude changes and five Honeywell QA3000 single axis accelerometers to measure changes in vehicle body velocities that are integrated to provide an inertial navigation solution.
Angular rate information for first stage stabilization is provided by the Rate Gyro Assembly (RGA) unit featuring triply redundant pitch and yaw rate sensors. The INCA and RRGU are derived from a decades-long successful heritage of over 58 successful Atlas V missions.
