PISTON ENGINE AIRCRAFT AUTOMATED PRE-FLIGHT TESTING

• US 20090259350A1
• Filed: 04/09/2008
• Published: 10/15/2009
• Est. Priority Date: 04/09/2008
• Status: Active Grant

• Current Assignee: Lycoming Engines
• Original Assignee: Lycoming Engines
• Inventors: Morris, James Paul, Schneider, Charles
• Granted Patent: US 8,131,406 B2
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems
• CPC Class Codes: F02C 9/00 Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2270/708 with comparison tables

Abstract

One embodiment is directed to a method for testing an aircraft prior to flight. The method includes receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner. The method includes, in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry. The method includes, upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry.

Claims

1. A method for testing an aircraft prior to flight, the method comprising:

receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner;

in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry; and

upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry.

2. A method as in claim 1 wherein the engine control circuitry, when controlling operation of the set of piston engines of the aircraft during flight, is arranged to control engine combustion using electronic fuel injectors to deliver fuel and spark plugs to ignite the fuel;

and wherein conducting the pre-flight test includes;

electronically communicating with a set of engine subsystems from the engine control circuitry.

3. A method as in claim 2 wherein the electronic control circuitry includes (i) a primary electronic control unit (ECU) which is arranged to control engine combustion during a normal flight mode of the electronic control circuitry, and (ii) a secondary ECU which is arranged to control engine combustion during a backup flight mode of the electronic control circuitry, the electronic control circuitry transitioning from the normal flight mode to the backup flight mode in the event of a failure of the primary ECU;

and wherein electronically communicating with the set of engine subsystems includes;

conducting a first portion of the pre-flight test on the set of engine subsystems from a channel of the primary ECU, and conducting a second portion of the pre-flight test on the set of engine subsystems from a channel of the second ECU, the second portion of the pre-flight test substantially mirroring the first portion of the pre-flight test.

4. A method as in claim 3 wherein outputting the result of the pre-flight test from the engine control circuitry includes:

automatically storing the result of the pre-flight test to a storage log residing in non-volatile memory.

5. A method as in claim 3 wherein outputting the result of the pre-flight test from the engine control circuitry includes:

varying a blinking frequency of a set of pilot viewable lamps to provide pilot feedback regarding an amount of completeness of the pre-flight test.

6. A method as in claim 3 wherein conducting the first portion of the pre-flight test includes completely carrying out a first pre-defined sequence of testing steps regardless of whether there is a failure of any testing step of the first pre-defined sequence of testing steps;

and

wherein conducting the second portion of the pre-flight test includes completely carrying out a second pre-defined sequence of testing steps regardless of whether there is a failure of any testing step of the second pre-defined sequence of testing steps.

7. A method as in claim 3 wherein conducting the first portion of the pre-flight test includes testing the set of engine subsystems to verify existence of a set of enabling conditions from the perspective of the primary ECU;

and

wherein conducting the second portion of the pre-flight test includes testing the set of engine subsystems to verify existence of the set of enabling conditions from the perspective of the secondary ECU.

8. A method as in claim 3 wherein the set of engine subsystems includes a throttle positioning subsystem having a base, a throttle, and an actuator which is arranged to angularly position the throttle relative to the base;

wherein conducting the first portion of the pre-flight test includes, from the channel of the primary ECU, (i) sending a first throttle positioning signal to the actuator of the throttle positioning subsystem, the first throttle positioning signal being arranged to move the throttle to a first predefined angular position relative to the base, and (ii) measuring whether the throttle has moved to the first predefined angular position relative to the base in response to the first throttle positioning signal; and

wherein conducting the second portion of the pre-flight test includes, from the channel of the primary ECU, (i) sending a second throttle positioning signal to the actuator of the throttle positioning subsystem, the second throttle positioning signal being arranged to move the throttle to a second predefined angular position relative to the base, and (ii) measuring whether the throttle has moved to the second predefined angular position relative to the base in response to the second throttle positioning signal.

9. A method as in claim 3 wherein the set of engine subsystems includes a spark plug signal source and a network of spark plug cables which is arranged to deliver spark plug signals from the spark plug signal source to the spark plugs;

wherein conducting the first portion of the pre-flight test includes, from the channel of the primary ECU, (i) directing the spark plug signal source to deliver a first set of spark plug signals to the spark plugs through the network, and (ii) measuring engine combustion in response to the first set of spark plug signals; and

wherein conducting the second portion of the pre-flight test includes, from the channel of the secondary ECU, (i) directing the spark plug signal source to deliver a second set of spark plug signals to the spark plugs through the network, and (ii) measuring engine combustion in response to the second set of spark plug signals.

10. A method as in claim 3 wherein the set of engine subsystems includes an adjustable propeller subsystem having a valve which controls an oil pressure, a propeller base, fin members which extend from the propeller base and which change angular pitch relative to the propeller base in response to changes in the oil pressure;

wherein conducting the first portion of the pre-flight test includes, from the channel of the primary ECU, (i) sending a first propeller pitch control signal to the valve of the throttle positioning subsystem, the first propeller pitch control signal being arranged to effectuate a change in the oil pressure to change the angular pitch of the fin members of the throttle positioning subsystem, and (ii) measuring whether the fin members have changed angular pitch relative to the propeller base in response to the change in the oil pressure; and

wherein conducting the second portion of the pre-flight test includes, from the channel of the primary ECU, (i) sending a second propeller pitch control signal to the valve of the throttle positioning subsystem, the second propeller pitch control signal being arranged to effectuate a change in the oil pressure to change the angular pitch of the fin members of the throttle positioning subsystem, and (ii) measuring whether the fin members have changed angular pitch relative to the propeller base in response to the change in the oil pressure.

11. A method as in claim 3 wherein the set of engine subsystems includes a turbo charge subsystem having a pressure control valve;

wherein conducting the first portion of the pre-flight test includes, from the channel of the primary ECU, (i) sending a first valve signal to the pressure control valve of the turbo charge subsystem, the first valve signal being arranged to move the pressure control valve between opened and closed positions, and (ii) measuring whether a pressure change has occurred in response to sending of the first valve signal to the pressure control valve of the turbo charge subsystem; and

wherein conducting the second portion of the pre-flight test includes, from the channel of the primary ECU, (i) sending a second valve signal to the pressure control valve of the turbo charge subsystem, the second valve signal being arranged to move the pressure control valve between the opened and closed positions, and (ii) measuring whether a pressure change has occurred in response to sending of the second valve signal to the pressure control valve of the turbo charge subsystem.

12. A method as in claim 3 wherein the primary ECU includes a first memory device which stores a first set of instructions and a first processor;

wherein the secondary ECU includes a second memory device which stores a second set of instructions and a second processor;

wherein conducting the first portion of the pre-flight test on the set of engine subsystems from a channel of the primary ECU includes operating the first processor in accordance with the first set of instructions; and

wherein conducting the second portion of the pre-flight test on the set of engine subsystems from a channel of the secondary ECU includes operating the second processor in accordance with the second set of instructions.

13. A method as in claim 12 wherein the first set of instructions stored in the first memory device of the primary ECU is first executable code;

wherein the second set of instructions stored in the second memory device of the secondary ECU is second executable code;

wherein operating the first processor in accordance with the first set of instructions includes the first processor executing the first executable code; and

wherein operating the second processor in accordance with the second set of instructions includes the second processor executing the second executable code.

14. An electronic aircraft control system, comprising:

an engine subsystem interface;

a communications interface; and

engine control circuitry coupled to the engine subsystem interface and the communications interface, the engine control circuitry being arranged to control operation of a set of piston engines of an aircraft during flight, the engine control circuitry being further arranged to;

receive a user signal from the communications interface, the user signal indicating that a pilot of the aircraft has directed the engine control circuitry to begin testing the aircraft in an automated manner,

in response to the user signal, conduct a pre-flight test of the aircraft through the engine subsystem interface, and

upon completion of the pre-flight test, output a result of the pre-flight test through the communications interface.

15. An electronic aircraft control system as in claim 14 wherein the engine control circuitry, when controlling operation of the set of piston engines of the aircraft during flight, is arranged to control engine combustion using electronic fuel injectors to deliver fuel and spark plugs to ignite the fuel;

and

wherein the engine control circuitry, when conducting the pre-flight test, is arranged to electronically communicate with a set of engine subsystems.

16. An electronic aircraft control system as in claim 15 wherein the electronic control circuitry includes (i) a primary electronic control unit (ECU) which is arranged to control engine combustion during a normal flight mode of the electronic control circuitry, and (ii) a secondary ECU which is arranged to control engine combustion during a backup flight mode of the electronic control circuitry, the electronic control circuitry transitioning from the normal flight mode to the backup flight mode in the event of a failure of the primary ECU;

and

wherein the electronic control circuitry, when electronically communicating with the set of engine subsystems, is arranged to (i) conduct a first portion of the pre-flight test on the set of engine subsystems from a channel of the primary ECU, and (ii) conduct a second portion of the pre-flight test on the set of engine subsystems from a channel of the second ECU, the second portion of the pre-flight test substantially mirroring the first portion of the pre-flight test.

17. An electronic aircraft control system as in claim 16 wherein the electronic control circuitry, when outputting the result of the pre-flight test, is arranged to:

automatically store the result of the pre-flight test to a storage log residing in non-volatile memory through the communications interface.

18. An electronic aircraft control system as in claim 16 wherein the electronic control circuitry, when outputting the result of the pre-flight test, is arranged to:

vary a blinking frequency of a set of pilot viewable lamps through the communications interface to provide pilot feedback regarding an amount of completeness of the pre-flight test.

19. An electronic aircraft control system as in claim 16 wherein the electronic control circuitry, when conducting the first portion of the pre-flight test, is arranged to completely carry out a first pre-defined sequence of testing steps regardless of whether there is a failure of any testing step of the first pre-defined sequence of testing steps;

and

wherein the electronic control circuitry, when conducting the second portion of the pre-flight test, is arranged to completely carry out a second pre-defined sequence of testing steps regardless of whether there is a failure of any testing step of the second pre-defined sequence of testing steps.

20. An electronic aircraft control system as in claim 16 wherein the electronic control circuitry, when conducting the first portion of the pre-flight test, is arranged to test the set of engine subsystems to verify existence of a set of enabling conditions from the perspective of the primary ECU;

and

wherein the electronic control circuitry, when conducting the second portion of the pre-flight test, is arranged to test the set of engine subsystems to verify existence of the set of enabling conditions from the perspective of the secondary ECU.