Method and device for estimating the mach number of an aircraft

A device for estimating the Mach number of an aircraft, comprising:

• a first measurement unit configured to measure a first static pressure Ps of ambient air in a first measurement zone of the aircraft that is located on a fuselage of the aircraft;
• a second measurement unit configured to measure a second pressure P of the ambient air, by means of at least one static pressure probe, in a second measurement zone of the aircraft, the second pressure P having a value lower than the first static pressure Ps;
• a computation unit configured to estimate a Mach number of the aircraft, using the following expression:
• M
• =
• k
• 4
• +
• 4
• ⁢
• k
• 2
• -
• k
• 2
• 2
• the parameter k bearing out the expression
• k
• =
• Z
• ⁡
• (
• 1
• -
• P
• Ps
• )
• in which Z is a parameter dependent on the position of the second measurement zone on the aircraft;
• and
• a data transmission unit configured to transmit the estimated Mach number to an user system.

An aircraft comprising a device for estimating the Mach number of an aircraft, the device comprising:

• a first measurement unit configured to measure a first static pressure Ps of ambient air in a first measurement zone of the aircraft that is located on a fuselage of the aircraft;
• a second measurement unit configured to measure a second pressure P of the ambient air, by means of at least one static pressure probe, in a second measurement zone of the aircraft, the second pressure P having a value lower than the first static pressure Ps;
• a computation unit configured to estimate a Mach number of the aircraft, using the following expression:
• M
• =
• k
• 4
• +
• 4
• ⁢
• k
• 2
• -
• k
• 2
• 2
• the parameter k bearing out the expression
• k
• =
• Z
• ⁡
• (
• 1
• -
• P
• Ps
• )
• in which L is a parameter dependent on the position of the second measurement zone on the aircraft;
• and
• a data transmission unit configured to transmit the estimated Mach number to an user system.

A device for estimating the Mach number of an aircraft, the device comprising:

• a first measurement unit configured to measure a first static pressure Ps of ambient air in a first measurement zone of the aircraft;
• a second measurement unit configured to measure a second pressure P of the ambient air, by means of at least one static pressure probe, in a second measurement zone of the aircraft, the second pressure P having a value lower than the first static pressure Ps;
• a computation unit configured to estimate a Mach number of the aircraft, using the following expression:
• M
• =
• k
• 4
• +
• 4
• ⁢
• k
• 2
• -
• k
• 2
• 2
• the parameter k bearing out the expression
• k
• =
• Z
• ⁡
• (
• 1
• -
• P
• Ps
• )
• in which Z is a parameter dependent on the position of the second measurement zone on the aircraft;
• and
• a data transmission unit configured to transmit the estimated Mach number to an user system;
• wherein the first measurement unit comprises a first and a second measurement probe configured to measure a first intermediate static pressure Ps′ and a second intermediate static pressure Ps″, said first measurement unit further comprising a computer configured to determine the first static pressure Ps by averaging the first and the second intermediate static pressures Ps′ and Ps″;
• and
• wherein the first and the second intermediate static pressures Ps′, Ps″ are measured on two respective faces of a vertical tail unit of the aircraft.