The Standby Altitude Sensor Unit (ALTSU) for the fixed wing Jaguar platform is used as a Line Replaceable Unit (LRU) for the Auto Pilot project which measures the static pressure and feeds this data to the Auto Pilot Computer.
The Pressure Sensor Unit (PSU) for the fixed wing Jaguar platform is used as an LRU that measures and distributes static pressure and differential pressure in form of DC voltages. When connected to a temperature probe, the unit generates proportional DC voltage. From these parameters, various aerodynamic parameters are calculated.
Air Data Interface Unit (ADIU), formally known as Air Data and Attitude Heading Reference System (ADAHRS) provide basic flight parameters to Engine and Flight Integrated System (EFIS) for displaying those parameters on EFIS independently of main navigation sensor (IN sensor).
In the event of failure of IN sensor, it acts as a GET-YOU-HOME system for providing basic navigation parameters to EFIS for safely return to destination point. The system shall replace conventional electro mechanical flight instruments.
The Navigation Sensor Unit (NSU) is a part of AHRS/GPS navigation System (GNS) of the Indian Air Force Hawk Aircraft. The AHRS/GPS Navigation system shall compute attitude, heading, slip angle, velocity, position and direct steering data (range, bearing and track angle error) and shall display these information, when they are valid, on the Head Down Flight Display (HDFD). Based on the functionality, NSU will be treated as safety critical item of the Aircraft.
The Air Data Computer is a device which measures the static and differential pressures. When connected to a temperature probe (by others) it gets input as impact temperature. From these three parameters various aerodynamic (Air Data) parameters can be calculated. The Air Data Computer has built in features for self tests to check the hardware and software integrity.
The Air Data unit is used for helicopter which has aerodynamically compensated, combined Pitot-Static probes mounted on the fuselage to sense the dynamic and static air pressure experienced by the helicopter in the flight. The ADU is pneumatically connected to the Pitot-Static probe and electrically connected to an Outside Air Temperature (OAT) probe mounted on the Helicopter fuselage. The ADU has provision for selecting pre programmed SEC laws by pin programming to enable correction of air data parameters based on the Helicopter configuration.
