Pulsed deicing system
A deicing system for an aircraft may supply heat to an aircraft component in pulses. A first series of pulses may melt ice built up on the aircraft component. A second series of pulses may prevent ice from forming on the aircraft component. The length of each of the pulses in the first series of pulses may be longer than the length of each of the pulses in the second series of pulses. The pulses may be supplied by a pneumatic deicing system or an electrical deicing system.
1. A method comprising:
supplying heat to an aircraft component through a pressure regulating valve connected in series with a shutoff valve toggled by a solenoid during a first pulse, wherein the first pulse is configured to melt ice on the aircraft component;
supplying heat to the aircraft component through the pressure regulating valve connected in series with the shut off valve toggled by the solenoid during a second pulse after the first pulse, wherein the second pulse is configured to prevent ice from forming on the aircraft component,
detecting, by a full authority digital engine control system, that the pressure regulating valve is in a locked open position in response to a pressure regulating valve outlet pressure being higher than a threshold value; and
modulating, by a full authority digital engine control system, the shutoff valve between an open and closed position in response to the pressure regulating valve being in the locked open position,
wherein a length of time of the first pulse is greater than a length of time of the second pulse.
2. The method of claim 1 , wherein the heat for the first pulse and the heat for the second pulse is supplied by a pneumatic deicing system.
3. The method of claim 1 , wherein the length of time of the first pulse is between 20 and 30 seconds.
4. The method of claim 3 , wherein the length of time of the second pulse is between 5 and 15 seconds.
5. The method of claim 1 , wherein the heat for the first pulse and the heat for the second pulse is supplied by an electrical deicing system.
6. The method of claim 1 , wherein the length of time of the first pulse and the length of time of the second pulse are determined by a full authority digital electronic control.
7. The method of claim 1 , wherein a length of time between the first pulse and the second pulse is between 20-30 seconds, and wherein a length of time between the second pulse and a third pulse is between 50-120 seconds.
8. A method comprising:
supplying a plurality of deicing pulses to an aircraft component through a pressure regulating valve connected in series with a shut off valve toggled by a solenoid during a first period; and
supplying a plurality of anti-icing pulses to the aircraft component through the pressure regulating valve connected in series with the shut off valve toggled by the solenoid during a second period after the first period;
detecting, by a full authority digital engine control system, that the pressure regulating valve is in a locked open position in response to a pressure regulating valve output pressure being higher than a threshold value; and
modulating, by a full authority digital engine control system, the shutoff valve between an open and closed position in response to the pressure regulating valve being in the locked open position
wherein a length of time of each of the plurality of deicing pulses is greater than a length of time of each of the plurality of anti-icing pulses.
9. The method of claim 8 , wherein the deicing pulses comprise at least one of a different length of time, a different width, or a different frequency than the anti-icing pulses.
10. The method of claim 8 , wherein the length of time of each of the plurality of deicing pulses is between 20-30 seconds.
11. The method of claim 8 , wherein the length of time of each of the plurality of anti-icing pulses is between 5-15 seconds.
12. The method of claim 8 , wherein the aircraft component is at least one of an inlet for an aircraft nacelle, a wing leading edge, a horizontal stabilizer, or a vertical fin.