Attitude and Heading Reference Systems

	The LCR-92 µAHRS® is a state-of-the art attitude and heading reference system. Angular rates are measured by three fiber-optic gyros in a strap-down configuration and heading and attitude are determined. Accordingly, the functions of a heading gyro, attitude gyro and turn gyro are integrated in a single, low-volume unit. The system has been selected for the NASA T-38 and the T-6A JPATS trainer aircraft, is standard equipment on the Pilatus PC 12, as well as other applications. The system is also standard equipment for helicopter programmes such as the Sikorsky S-76 and S-92, MD900 Explorer and Bell 412. The µAHRS® product family was extended with the LCR-93 µAHRS®. In addition to the fiber-optic gyros, this attitude and heading reference system contains a 3-axis, silicon accelerometer using micro-mechanical technology. In addition to an improvement of the attitude accuracy, acceleration data as well as barometric altitude and vertical speed are available. The LCR-93 is standard equipment on the Cessna Excel and Learjet 31 and 45 business jets, as well as on the Pilatus PC-9 trainer aircraft. A special version, integrated with GPS, delivers ground speed data for presentation on a Head-Up Display.
	The LTR-97 µAHRS® attitude and heading reference system was developed specifically for the civil airliner market as a replacement for conventional, mechanical gyro systems. The long-life, fiber-optic gyros result in a significant reduction in operating costs.
All members of the µAHRS® family are certified by the LBA and FAA in accordance with TSO C4c, C5e and C6d.Over 3000 µAHRS® are currently in use world-wide.

 

Flight Control and Stabilisation Systems

µFORS Gyroscope This single-axis, fiber-optic gyro is intended for use in a multitude of applications. It delivers fully-compensated angular rates or angular increments over a serial interface. The sensors can be used to measure angular rates or increments or as a heading gyro in diverse applications, such as for the stabilisation of missiles, airborne sensor systems, or land vehicle systems. Over 8000 gyros are currently in use world-wide.

The accelerometer B-290 Triad has been developed for applications in Attitude Heading Reference Systems and Inertial Measurement Units. It consist of three all-silicon micro-mechanical accelerometers with analog and digital electronics and interfaces in a small housing. Sensor data are scaled and fully temperature compensated. B-290 Triads are available with different measurement ranges.

Inertial Measurement Units (IMU)

		The EF-2000 IMU is a quadruplex-redundant sensor system within the flight control system of the Eurofighter. Gyros and accelerometers are used in a skewed-axis, strap-down configuration, this configuration requiring half the quantity of sensors than that which is required for a conventional, non-skewed configuration. This realises significant savings in weight and volume.
	FOG IMU The new FOG IMU's are modular and consist of three mFORS gyros, a B-290 accelerometer triad, a processor module, and a power supply. Their low weight, high accuracy, and ease of customisation to fulfil specific requirements make them suitable for a number of applications. Applications include various types of guided weapons (air-to-air, air-to-ground).

 

Computers

	The Flight Control Data Concentrator FCDC is a computer used for compressing and analysing status and failure data in flight-control systems. It is used on the Airbus A-318, A-319, A-320 and A-321 aircrafts.
	Seat Sequencer LISS LITEF has developed the control computer for the ejection seat of the Eurofighter under contract from Martin-Baker. High reliability and integrity achieved with a redundant architecture and the implementation of accelerometers and air-data sensors are the distinguishing features of this computer.

---

Top