초록 ▼

The disclosed embodiments concerns a system for monitoring anemobaroclinometric parameters in an aircraft, including a primary detection circuit having at least one measurement channel. The measurement channel includes a device for measuring static air pressure,a device for measuring a side-slip ang

The disclosed embodiments concerns a system for monitoring anemobaroclinometric parameters in an aircraft, including a primary detection circuit having at least one measurement channel. The measurement channel includes a device for measuring static air pressure,a device for measuring a side-slip angle of the aircraft,a device for measuring a dynamic pressure, a total air temperature and a angle of attack of the aircraft, anda data-processing device capable of determining anemobaroclinometric parameters from the measurements of static pressure, side-slip angle, dynamic pressure, total air temperature and angle of attack,a least one laser anemometer to measure at least one true airspeed parameter of the aircraft.

대표청구항 ▼

1. A system for monitoring anemobaroclinometric parameters in an aircraft, comprising a primary detection circuit comprising at least one measurement channel, the measurement channel comprising: a mechanical device for measuring static air pressure;a mechanical device for measuring a side-slip angle

1. A system for monitoring anemobaroclinometric parameters in an aircraft, comprising a primary detection circuit comprising at least one measurement channel, the measurement channel comprising: a mechanical device for measuring static air pressure;a mechanical device for measuring a side-slip angle of the aircraft,a mechanical device for measuring a dynamic pressure, a total air temperature and a angle of attack of the aircraft, anda data-processing device configured to determine anemobaroclinometric parameters from the measurements of static pressure, side-slip angle, dynamic pressure, total air temperature and angle of attack,wherein the system further comprises a least one laser anemometer to measure at least one true airspeed parameter of the aircraft, and to provide a redundant indication of at least one of static pressure, side-slip angle, dynamic pressure, total air temperature and angle of attack during flight using a non-mechanical technology, the laser anemometer being placed in a housing made in the vicinity of the external skin of the aircraft and being protected by a window ensuring the optical passage of the laser rays. 2. The system according to claim 1, wherein the laser anemometer is integrated into a secondary detection circuit. 3. The system according to claim 1, further comprising: a secondary detection circuit comprising at least one static pressure measurement device, at least one dynamic pressure measurement device, at least one processing device for processing the data supplied by the measurement devices, and whereinthe laser anemometer further comprises a circuit for monitoring the parameters. 4. The system according to claim 1, wherein the laser anemometer is integrated into a second measurement channel of the primary detection circuit. 5. The system according to claim 4, wherein the primary detection circuit comprises a third measurement channel similar to the first measurement channel. 6. The system according to claim 4, wherein the primary detection circuit has a third measurement channel integrating a second laser anemometer.