AIRCRAFT OPERATION DURING STEEP APPROACH

• US 20200130851A1
• Filed: 06/29/2017
• Published: 04/30/2020
• Est. Priority Date: 06/29/2017
• Status: Active Grant

• Current Assignee: Bombardier Incorporated
• Original Assignee: Bombardier Incorporated, C Series Aircraft Limited Partnership
• Inventors: HAMEL, Remi, LEBEGUE, Olivier, DESILETS, Valerie, BROUSSEAU, Jean, AFRIANTO, Sigit, BYRNE, Andrew J., HODGE, Eric
• Granted Patent: US 11,987,368 B2
• Time in Patent Office: Days
• CPC Class Codes: B64D 13/02 the air being pressurised
• CPC Class Codes: B64D 13/06 the air being conditioned pressurising B64D13/02
• CPC Class Codes: B64D 15/166 using pneumatic boots
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing
• CPC Class Codes: B64D 2013/0603 Environmental Control Systems
• CPC Class Codes: B64D 37/32 Safety measures not otherwise provided for, e.g. preventing explosive conditions extinguishing or preventing fires in aircraft A62C
• CPC Class Codes: G05D 1/0676 specially adapted for landing
• CPC Class Codes: G05D 1/654 Landing docking at a base station G05D1/661

Abstract

Systems and methods to facilitate a steep final approach phase of flight of an aircraft are disclosed. In one embodiment, a method for operating an aircraft during a steep approach phase of flight of the aircraft comprises operating an engine of the aircraft at an idle speed associated with the steep approach type that is lower than an idle speed associated with a non-steep approach type capable of being executed by the aircraft. The method also comprises operating an ice protection system of the aircraft during the steep approach phase of flight of the aircraft.

Claims

1. A method for operating an aircraft during a steep approach phase of flight of the aircraft, the method comprising:

operating an engine of the aircraft at a first idle speed associated with a first approach type during the steep approach phase of flight of the aircraft, the first approach type being steeper than a second approach type capable of being executed by the aircraft, the first idle speed being lower than a second idle speed associated with the second approach type capable of being executed by the aircraft; and

operating an ice protection system of the aircraft during the steep approach phase of flight of the aircraft.

2. The method as defined in claim 1, comprising supplying pressurized air extracted from the engine to the ice protection system of the aircraft during the steep approach phase of flight of the aircraft.

3. The method as defined in claim 2, comprising receiving a signal indicative of the first approach type to be executed by the aircraft and then reducing an amount of pressurized air being supplied from the engine to one or more pneumatic loads other than the ice protection system.

4. The method as defined in claim 3, wherein the one or more pneumatic loads other than the ice protection system include an environmental control system of the aircraft that is operable in a lower-flow mode of operation and a higher-flow mode of operation, the method comprises inhibiting an operation of the environmental control system in the higher-flow mode of operation during the steep approach phase of flight of the aircraft.

5. The method as defined in claim 2, wherein the aircraft comprises at least two engines and the pressurized air supplied to the ice protection system during the steep approach phase of flight of the aircraft is supplied from all engines.

6. The method as defined in claim 5, further comprising inhibiting the operation of the engine of the aircraft at the first idle speed in case of a condition causing the pressurized air to be supplied to the ice protection system from fewer than the at least two engines.

7. The method as defined in claim 2, wherein the aircraft comprises at least two engines and the method comprises inhibiting an operation of the ice protection system where pressurized air is supplied to the ice protection system from only one of the at least two engines during the steep approach phase of flight of the aircraft.

8. The method as defined in claim 1, comprising inhibiting a supply of pressurized air extracted from the engine to a fuel tank inerting system of the aircraft during the steep approach phase of flight of the aircraft.

9. The method as defined in claim 1, comprising inhibiting a supply of pressurized air extracted from the engine to a heating system for a cargo compartment of the aircraft during the steep approach phase of flight of the aircraft.

10. The method as defined in claim 1, wherein an angle of approach associated with the first approach type is equal to or greater than 4.5 degrees from horizontal.

11. A system for operating an aircraft during a steep approach phase of flight of the aircraft, the system comprising:

one or more data processors; and

non-transitory machine-readable memory storing instructions executable by the one or more data processors and configured to cause the one or more data processors to;

after receiving a signal indicative of a first approach type to be executed by the aircraft where the first approach type is steeper than a second approach type capable of being executed by the aircraft, command an engine of the aircraft to operate at a first idle speed associated with the first approach type during the steep approach phase of flight of the aircraft, the first idle speed being lower than a second idle speed associated with the second approach type capable of being executed by the aircraft; and

command an ice protection system of the aircraft to operate during the steep approach phase of flight of the aircraft.

12. The system as defined in claim 11, wherein the instructions are configured to cause the one or more data processors to command a supply of pressurized air extracted from the engine to the ice protection system of the aircraft during the steep approach phase of flight of the aircraft.

13. The system as defined in claim 12, wherein the instructions are configured to, after receiving the signal indicative of the first approach type to be executed by the aircraft, cause the one or more data processors to command a reduction in an amount of pressurized air being supplied from the engine to one or more pneumatic loads other than the ice protection system.

14. The system as defined in claim 13, wherein:

the one or more pneumatic loads include an environmental control system of the aircraft that is operable in a lower-flow mode of operation and a higher-flow mode of operation; and

the instructions are configured to cause the one or more data processors to command an inhibition of an operation of the environmental control system in the higher-flow mode of operation during the steep approach phase of flight of the aircraft.

15. The system as defined in claim 12, wherein the instructions are configured to cause the one or more data processors to command the supply pressurized air to the ice protection system from at least two engines of the aircraft during the steep approach phase of flight of the aircraft.

16. The method as defined in claim 15, wherein the instructions are configured to cause the one or more data processors to command a inhibition of the operation of the engine of the aircraft at the first idle speed in case of a condition causing the pressurized air to be supplied to the ice protection system from fewer than the at least two engines.

17. The method as defined in claim 12, wherein the instructions are configured to cause the one or more data processors to inhibit an operation of the ice protection system where pressurized air is supplied to the ice protection system from only one of at least two engines of the aircraft during the steep approach phase of flight of the aircraft.

18. The system as defined in claim 11, wherein the instructions are configured to cause the one or more data processors to inhibit a supply of pressurized air extracted from the engine to a fuel tank inerting system of the aircraft during the steep approach phase of flight of the aircraft.

19. The system as defined in claim 11, wherein the instructions are configured to cause the one or more data processors to inhibit a supply of pressurized air extracted from the engine to a heating system for the cargo compartment of the aircraft during the steep approach phase of flight of the aircraft.

20. An aircraft comprising the system as defined in claim 11.