Method and device for automatically estimating at least one speed of an aircraft
AssigneeAirbus Operations GmbH
InventorsPhilippe Goupil, Nicola Mimmo, Pierre Chevalier, Daniel Lopez Fernandez, Rémy Dayre
Life of this patent
Estimating the term…
Abstract
A device including a first data generating unit for determining at least one aerodynamic hinge moment of at least one control surface of the aircraft, a second data generating unit for determining a plurality of data and at least one external static pressure and a model of hinge moment coefficient, a computation unit for computing with the aid of these data at least one speed of the aircraft, namely a Mach number and/or a conventional speed, and a data transmission unit for providing this speed to a user system.
Claims14
A method for automatically estimating at least one speed of an aircraft, during a flight of the aircraft, the method comprising, in an automatic manner and on the aircraft:
- a) determining at least one aerodynamic hinge moment of at least one control surface of the aircraft;
- b) determining a plurality of data and at least the following data:
- a static pressure external to the aircraft;
- and
- a model of hinge moment coefficient;
- c) computing a first speed of the aircraft;
- and
- d) providing the first speed thus computed to at least one user system,
- wherein step c) comprises computing a Mach number M representing a first speed of the aircraft, with an expression as follows:
- M
- a
- =
- 1
- 2
-
- γ
-
-
- P
- s
-
- M
- 2
-
- V
- δ
- p
-
- C
- h
- in which:
- Ma is the aerodynamic hinge moment;
- γ is an adiabatic coefficient of the air;
- Ps is an external static pressure;
- Vδp represents a volume of the control surface;
- and
- Ch is the model of hinge moment coefficient, dependent on the Mach number M.
A device for automatically estimating at least one speed of an aircraft, during a flight of the aircraft, the device comprising:
- a first data generating unit configured to determine at least one aerodynamic hinge moment of at least one control surface of the aircraft;
- a second data generating unit configured to determine a plurality of data and at least the following data:
- a static pressure external to the aircraft;
- and
- a model of hinge moment coefficient;
- a computation unit configured to compute a first speed;
- and
- at least one data transmission unit configured to provide the first speed to at least one user system,
- wherein the computation unit is configured to compute a Mach number M representing a first speed of the aircraft, with an expression as follows:
- M
- a
- =
- 1
- 2
-
- γ
-
-
- P
- s
-
- M
- 2
-
- V
- δ
- p
-
- C
- h
- in which:
- Ma is the aerodynamic hinge moment;
- γ is an adiabatic coefficient of the air;
- Ps is an external static pressure;
- Vδp represents a volume of the control surface;
- and
- Ch is the model of hinge moment coefficient, dependent on the Mach number M.
Dependencies are inferred from the claim text.