Method and a device for correcting a measurement of the pressure of a gas stream flowing in an aircraft engine
View Patent ↗A method to correct a current measurement of pressure of a gas stream delivered during a mission by a sensor in the engine. The method includes: estimating a drift error affecting the sensor on the basis of a difference existing between: (1) a calibration measurement of the pressure of the gas stream as delivered by the sensor in the engine, and (2) an atmospheric pressure measurement delivered by a sensor of the aircraft presenting accuracy greater than that of the sensor in the engine; these measurements being performed while the sensor in the engine and the sensor of the aircraft are subjected to same surrounding atmospheric pressure; and subtracting the estimated drift error from the current measurement.
1. A method of correcting a current measurement of pressure of a gas stream flowing inside a turbojet engine propelling an aircraft, the measurement being delivered during a mission of the aircraft by a first sensor in the turbojet engine, the correction method comprising:
determining if a condition for estimating a drift error is satisfied;
measuring a calibration pressure of the gas stream using the first sensor in the turbojet engine if the condition for estimating the drift error is satisfied;
measuring an atmospheric pressure using a second sensor of the aircraft if the condition for estimating the drift error is satisfied, the second sensor presenting measurement accuracy greater than that of the first sensor in the turbojet engine and being disposed in the aircraft and outside of the turbojet engine;
estimating a drift error affecting the first sensor based on a difference between the calibration pressure measured using the first sensor and the atmospheric pressure measured using the second sensor;
measuring the current measurement of the pressure of the gas stream flowing inside the turbojet engine using the first sensor; and
subtracting the estimated drift error from the current measurement of the pressure of the gas stream,
wherein the condition for estimating the drift error includes a condition in which the first sensor in the turbojet engine and the second sensor in the aircraft are subjected to same surrounding atmospheric pressure.
2. A method of correcting a measurement according to claim 1 , wherein the condition for estimating the drift error is satisfied when the turbojet engine is stopped and the aircraft is stationary on the ground.
3. A method of correcting a measurement according to claim 1 , wherein the first sensor is disposed on an outer casing of the turbojet engine.
4. A method of correcting a measurement according to claim 1 , wherein the second sensor is disposed in a cockpit of the aircraft.
5. A non-transitory readable medium including computer executable instructions for executing the correction method of claim 1 when the computer executable instructions are executed by a computer.
6. A correction device for correcting a current measurement of pressure of a gas stream flowing inside a turbojet engine propelling an aircraft, the measurement being delivered during a mission of the aircraft by a sensor in the turbojet engine, the device comprising:
means for determining if a condition for estimating a drift error is satisfied;
means for measuring a calibration pressure of the gas stream using the first sensor in the turbojet engine if the condition for estimating the drift error is satisfied;
means for measuring an atmospheric pressure using a second sensor of the aircraft if the condition for estimating the drift error is satisfied, the second sensor presenting measurement accuracy greater than that of the first sensor in the turbojet engine and being disposed in the aircraft and outside of the engine;
means for estimating a drift error affecting the first sensor in the turbojet engine based on a difference between the calibration pressure measured using the first sensor and the atmospheric pressure measured using the second sensor;
measuring the current measurement of the pressure of the gas stream flowing inside the turbojet engine using the first sensor; and
means for subtracting the estimated drift error from the current measurement of the pressure of the gas stream.
7. A correction device according to claim 6 , wherein the first sensor is disposed on an outer casing of the turbojet engine.
8. A correction device according to claim 6 , wherein the second sensor is disposed in a cockpit of the aircraft.
9. A turbomachine comprising a device according to claim 6 .
10. A system for measuring pressure of a gas stream flowing inside a turbojet engine propelling an aircraft, the system comprising:
a first sensor for sensing pressure of the gas stream, the first sensor being in the turbojet engine;
a second sensor for sensing atmospheric pressure, the second sensor being in the aircraft outside the turbojet engine and presenting measurement accuracy greater than that of the first sensor;
means for triggering:
(1) a calibration measurement of the pressure of the gas stream by the first sensor, and
(2) an atmospheric pressure measurement by the second sensor;
under conditions in which the first and second sensors are subjected to same surrounding atmospheric pressure; and
a correction device according to claim 6 , configured to correct a current pressure measurement delivered during a mission of the aircraft by the first sensor and to estimate drift error affecting the first sensor on the basis of a difference existing between the atmospheric pressure measurement and the calibration measurement.