Temperature correction of vertical speed of aircraft
AssigneeAirbus Canada Managing Gp Inc.
InventorsDimitri Cuesta, Guillaume Savoie-Chiasson
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Abstract
The present disclosure provides methods and systems for correcting a vertical speed of an aircraft. An instantaneous vertical speed of the aircraft is obtained, based on inertial data from an inertial reference unit on the aircraft. A first correction is applied to the instantaneous vertical speed to generate a baro-inertial vertical speed, and a second correction is applied to the baro-inertial vertical speed based on an error between a geometric vertical speed and the baro-inertial vertical speed to obtain a temperature-corrected baro-inertial vertical speed.
Claims12
A method for correcting a vertical speed of an aircraft, the method comprising:
- obtaining an instantaneous vertical speed of the aircraft based on inertial data from an inertial reference unit on the aircraft;
- applying a first correction to the instantaneous vertical speed to generate a baro-inertial vertical speed;
- and
- applying a second correction to the baro-inertial vertical speed based on an error between a geometric vertical speed and the baro-inertial vertical speed to obtain a temperature-corrected baro-inertial vertical speed,
- wherein:
- applying the second correction to the baro-inertial vertical speed comprises applying a time-based function of the error between the geometric vertical speed and a pressure altitude vertical speed;
- the time-based function of the error is estimated as a moving-average of an instantaneous error between the geometric vertical speed and the baro-inertial vertical speed, over a given portion of time prior to a current time;
- and
- the instantaneous error corresponds to:
- Err
- inst
- =
- (
- V
- z
- ,
- Geom
- V
- z
- ,
- Press
- ·
- V
- z
- ,
- BI
- -
- V
- z
- ,
- BI
- )
- where Vz,Geom is the geometric vertical speed, Vz,Press is the pressure altitude vertical speed, and Vz,BI is the baro-inertial vertical speed.
A system for correcting a vertical speed of an aircraft, the system comprising:
- a processing unit;
- and
- a non-transitory memory communicatively coupled to the processing unit and comprising computer-readable program instructions executable by the processing unit for:
- obtaining an instantaneous vertical speed of the aircraft based on inertial data from an inertial reference unit on the aircraft;
- applying a first correction to the instantaneous vertical speed to generate a baro-inertial vertical speed;
- and
- applying a second correction to the baro-inertial vertical speed based on an error between a geometric vertical speed and the baro-inertial vertical speed to obtain a temperature-corrected baro-inertial vertical speed,
- wherein:
- applying the second correction to the baro-inertial vertical speed comprises applying a time-based function of the error between the geometric vertical speed and a pressure altitude vertical speed;
- the time-based function of the error is estimated as a moving-average of an instantaneous error between the geometric vertical speed and the baro-inertial vertical speed, over a given portion of time prior to a current time;
- and
- the instantaneous error corresponds to:
- Err
- inst
- =
- (
- V
- z
- ,
- Geom
- V
- z
- ,
- Press
- ·
- V
- z
- ,
- BI
- -
- V
- z
- ,
- BI
- )
- where Vz,Geom is the geometric vertical speed, Vz,Press is the pressure altitude vertical speed, and Vz,BI is the baro-inertial vertical speed.
Dependencies are inferred from the claim text.