초록 ▼

The invention relates to a device for determining total temperature for aircraft. This device is particularly useful in a probe, called a multifunction probe, for measuring several aerodynamic parameters such as, for example, the total pressure (Pt), the static pressure (Ps) and the total temperatur

The invention relates to a device for determining total temperature for aircraft. This device is particularly useful in a probe, called a multifunction probe, for measuring several aerodynamic parameters such as, for example, the total pressure (Pt), the static pressure (Ps) and the total temperature (TT) of an airflow surrounding the aircraft. The device includes a deiced temperature probe. To obtain the total temperature (TTcorrected) of the airflow, the temperature (TTmeasured) recorded by the temperature probe is corrected as a function of the upstream infinity parameters (M∞ , Pt∞, Ps∞) of the aircraft and of the power (P) dissipated in the probe in order to deice it.

대표청구항 ▼

The invention claimed is: 1. A device for determining a total corrected temperature (TTcorrected) of an aircraft, including a probe fixed to a skin of the aircraft, the probe comprising: means for measuring a total temperature (TTmeasured); and means for dissipating thermal power intended to preven

The invention claimed is: 1. A device for determining a total corrected temperature (TTcorrected) of an aircraft, including a probe fixed to a skin of the aircraft, the probe comprising: means for measuring a total temperature (TTmeasured); and means for dissipating thermal power intended to prevent ice from forming in the probe; means for correcting said measured total temperature (TT measured) recorded by the means for measuring a total temperature as a function of upstream infinity parameters (M∞, Pt ∞, Ps∞) and of the power (P) dissipated in the probe, in order to obtain the total corrected temperature (TT corrected) of the airflow, wherein, M∞ is a Mach number of the flow at upstream infinity, Pt∞ is a dynamic pressure at upstream infinity, Ps∞ is a static pressure at upstream infinity. 2. The device according to claim 1, wherein the means for measuring a total temperature comprise a chamber into which part of an airflow surrounding the skin of the aircraft penetrates, means for slowing down the airflow penetrating into the chamber, and a temperature sensor placed in the chamber and intended to measure the temperature of the slowed-down airflow. 3. The device according to claim 1, wherein the device includes means for measuring the static pressure (PS) of the airflow. 4. The device according to claim 1, wherein the device further includes means for measuring the total pressure (Pt) of the airflow. 5. A method for determining the total corrected temperature (TTcorrected) of an aircraft using a probe fixed to a skin of the aircraft, the probe comprising means for measuring a total temperature (TTmeasured) and means for dissipating thermal power intended to prevent ice from forming in the probe, the method comprising the steps of: correcting said measured temperature (TTmeasured) recorded by the means for measuring a total corrected temperature as a function of the upstream infinity parameters of the aircraft and of the power (P) dissipated in the probe, in order to obtain the total temperature (TTcorrected) of the airflow, wherein M∞ is a Mach number of the flow at upstream infinity, Pt∞ is a dynamic pressure at upstream infinity, Ps∞ is a static pressure at upstream infinity. 6. A method according to claim 5, comprising correcting a recovery error due to the velocity of the aircraft using a linear function of the velocity (M∞, Mloc) of the aircraft, this function being expressed in the following manner: description="In-line Formulae" end="lead" Correctionrecovery=f횞M∞+g, description="In-line Formulae" end="tail" where Correctionrecovery is a correction applied to a temperature (TTmeasured) measured by means for measuring a total temperature and representative of the recovery error, and where f and g are constants determined from experimental results obtained on the probe in question subjected to various airflow velocities in a wind tunnel. 7. A method according to claim 5, comprising correcting a deicing error due to the means for dissipating thermal power using a function of the velocity (M∞, Mloc) of the aircraft expressed as the Mach number and of the power dissipated in the probe for deicing, this function being expressed in the following manner: where Correctiondeicing is a correction applied to a temperature measured by a temperature sensor and representative of the icing error, where a and b are polynomials that are functions of Z and of M∞, Z being a reduced Mach number; and where c, d and e are constants determined from experimental results obtained on the probe relative to a wind tunnel, the polynomials a and b being expressed, for example, in the form: description="In-line Formulae" end="lead"a=k횞 (l-M∞),description="In-line Formulae" end="tail" description="In-line Formulae" end="lead"b=m횞Z -δ횞(l+n횞M∞2)-δ description="In-line Formulae" end="tail" where k, l, m and n are constants and where δ is a function of the altitude of the aircraft. 8. A method according to claim 5, wherein it consists in comprising correcting the temperature (TTmeasured) recorded by the means for measuring a total temperature (TTmeasured) as a function of a mean temperature of the probe.