Abstract: Disclosed is a method and apparatus for validating a two-way satellite communication system in an aircraft. The two-way satellite communication system may include a network access unit, a modem, and a satellite antenna assembly. A satellite link emulator may be disposed proximate the aircraft. A validation controller may initiate a validation test of the two-way satellite communication system using the satellite link emulator, including receiving, at the satellite link emulator, a transmitted uplink signal from the satellite antenna assembly, and transmitting, using the satellite link emulator, a downlink signal to the satellite antenna assembly in response to the received uplink signal. A pass/fail indication may be determined based on operation of the network access unit, the modem, and the satellite antenna assembly during the validation test.

Abstract: Disclosed is a method and apparatus for validating a two-way satellite communication system in an aircraft. The two-way satellite communication system may include a network access unit, a modem, and a satellite antenna assembly. A satellite link emulator may be disposed proximate the aircraft. A validation controller may initiate a validation test of the two-way satellite communication system using the satellite link emulator, including receiving, at the satellite link emulator, a transmitted uplink signal from the satellite antenna assembly, and transmitting, using the satellite link emulator, a downlink signal to the satellite antenna assembly in response to the received uplink signal. A pass/fail indication may be determined based on operation of the network access unit, the modem, and the satellite antenna assembly during the validation test.

Abstract: A craft (e.g., an aircraft, a spacecraft, a watercraft, a vehicle such as an automotive vehicle or a rail vehicle, or any suitable mobile platform) may incorporate a first inertial measurement unit. A calibration unit incorporating a second inertial measurement unit may be mounted to the craft with a mount point. One or more first inertial measurements may be received from the first inertial measurement unit and the second inertial measurement unit. One or more antenna pointing controller calibration parameters may be determined based at least in part on the first inertial measurement(s) and the second inertial measurement(s). An antenna pointing controller may be configured with the determined calibration parameters and may control a steerable antenna subsystem mounted with the mount point utilizing the determined calibration parameters. The mount point may be keyed such that inertial measurements with the mounted calibration unit are applicable to the mounted steerable antenna subsystem.

Abstract: A craft (e.g., an aircraft, a spacecraft, a watercraft, a vehicle such as an automotive vehicle or a rail vehicle, or any suitable mobile platform) may incorporate a first inertial measurement unit. A calibration unit incorporating a second inertial measurement unit may be mounted to the craft with a mount point. One or more first inertial measurements may be received from the first inertial measurement unit and the second inertial measurement unit. One or more antenna pointing controller calibration parameters may be determined based at least in part on the first inertial measurement(s) and the second inertial measurement(s). An antenna pointing controller may be configured with the determined calibration parameters and may control a steerable antenna subsystem mounted with the mount point utilizing the determined calibration parameters. The mount point may be keyed such that inertial measurements with the mounted calibration unit are applicable to the mounted steerable antenna subsystem.