초록 ▼

The invention relates to a system to control the deceleration of an aircraft during the taxiing phase on a landing strip, the system has a detector of the current position of the aircraft on the strip, and of the current speed of the aircraft on the strip, a calculator receiving position and speed v

The invention relates to a system to control the deceleration of an aircraft during the taxiing phase on a landing strip, the system has a detector of the current position of the aircraft on the strip, and of the current speed of the aircraft on the strip, a calculator receiving position and speed values from the detector, to define, as a function of the desired final speed of the aircraft at the so-called final position on the strip, a deceleration set-point modification time, after the current time, and a new deceleration set-point to apply from the modification time, to reach the final position at the desired speed.

대표청구항 ▼

The invention claimed is: 1. System to control deceleration of an aircraft during taxiing phase on a landing strip, the system comprising: acquisition means of a current position of the aircraft on the landing strip, acquisition means of a current speed of the aircraft on the landing strip, calcula

The invention claimed is: 1. System to control deceleration of an aircraft during taxiing phase on a landing strip, the system comprising: acquisition means of a current position of the aircraft on the landing strip, acquisition means of a current speed of the aircraft on the landing strip, calculation means of a deceleration set-point modification time, after a time of impact of the aircraft on the landing strip, and a new deceleration set-point to apply from said modification time, to reach a final position, which corresponds to an exit junction of the landing strip, at a desired final speed, which is not nil, receiving position and speed values from the acquisition means, and accounting for said desired final speed of the aircraft in said final position. 2. System according to claim 1, comprising continuous acquisition means of the current position and current speed of the aircraft, and continuous calculation means of a new deceleration value. 3. System according to claim 1, wherein the current position acquisition means comprise a GPS (global positioning system) type system. 4. System according to claim 1, wherein the current speed acquisition means comprise an IRS (inertial reference system) type speed measurement system specific to the aircraft. 5. System according to claim 1, wherein the calculation means comprise a neural network computer. 6. Braking equipment for an aircraft equipped with a control system according to claim 1. 7. Braking equipment according to claim 6, comprising an anti-blocking system connected between the calculation means and a wheel braking system on the aircraft. 8. Method to control deceleration of an aircraft running on a landing strip, between at least a current position of the aircraft occupied at a current time, at which said aircraft has a current speed, and a final position, which corresponds to an exit junction of the landing strip, at which the aircraft must have a determined final position and a final speed, which is not nil, wherein a deceleration set-point modification time, after time of impact of the aircraft on the landing strip, and a new deceleration set-point applied from said set-point modification time, are determined as a function of the current position, the current speed and the final speed, in order to reach the final position at the final speed. 9. Method according to claim 8, wherein the current position and speed of the aircraft are measured continuously, and wherein a new deceleration value is defined continuously. 10. Method according to claim 9, wherein a deceleration modification time is also defined, when the deceleration set-point is not yet applied.