Aircraft Electrical System Evaluation

• US 20080036624A1
• Filed: 10/19/2007
• Published: 02/14/2008
• Est. Priority Date: 12/19/2005
• Status: Active Grant

• Current Assignee: Astronics Advanced Electronic Systems Corporation (Astronics Corporation)
• Original Assignee: Vertical Power, Inc. (Astronics Corporation)
• Inventors: DeVries, Kevin, Ausman, Marc
• Granted Patent: US 7,796,054 B2
• Time in Patent Office: Days
• US Class Current: 340/945
• CPC Class Codes: G01D 2207/10 Displays which are primarily used in aircraft or display aircraft-specific information
• CPC Class Codes: G01D 7/00 Indicating measured values
• CPC Class Codes: G08B 21/182 Level alarms, e.g. alarms responsive to variables exceeding a threshold
• CPC Class Codes: G08B 21/185 Electrical failure alarms
• CPC Class Codes: H02J 9/061 for DC powered loads
• CPC Class Codes: H02J 9/068 Electronic means for switching from one power supply to another power supply, e.g. to avoid parallel connection

Abstract

A computer implemented function monitors the position of the magneto switch in an aircraft to provide real-time feedback of engine RPM drop during a magneto (mag) check and communicates whether parameters are within limits. The function can also monitor engine and groundspeed/airspeed data in an aircraft to verify the magneto switch is in the correct position during engine start, takeoff and flight and can provide an alert to the pilot if the switch is not in the correct position. The automated magneto check function provides an easy way to test the operation of the aircraft'"'"'s engine-driven magnetos and provides additional safety by alerting the pilot to unsafe positioning of the switch.

Claims

1. A magneto characterization system for an aircraft, comprising:

a. A magneto status sensor indicating the status of the magneto system, including which magnetos are currently operating in connection with the engine;

b. An engine operation sensor adapted to indicate the operation of the engine;

c. An analysis system adapted to compare the engine operation at each of a plurality of magneto system configurations;

d. A communication system adapted to communicate a result from the analysis system to the pilot.

2. A system as in claim 1, wherein the analysis system is adapted to compare the engine operation with one or more predetermined values.

3. A system as in claim 1, wherein the engine operation sensor comprises one or more of:

an engine RPM sensor, and an engine power output sensor.

4. A system as in claim 1, wherein the magneto system comprises first and second magnetos, and the magneto status sensor comprises a sensor indicating one of the following conditions:

neither magneto supplying power to the engine, both magnetos supplying power to the engine, only the first magneto supplying power to the engine, and only the second magneto supplying power to the engine.

5. A magneto characterization system for an aircraft having first and second magnetos, comprising:

a. An engine operation rate sensor;

b. A memory device adapted to store a signal responsive to the engine operation rate sensor;

c. A user-controllable switch mounted with the first and second magnetos such that the switch can enable the first magneto only, the second magneto only, or both the first magneto and the second magneto, or disable both magnetos.

d. A switch sensor adapted to generate a signal indicative of the position of the user-controllable switch;

e. A controller responsive to the switch sensor and the engine operation rate sensor, adapted to store in the memory device a signal indicative of the engine operation rate sensor output while the switch sensor indicates that one of the first and second magnetos is enabled, and to communicate to a pilot a relationship between (a) the engine operation rate sensor output while the switch sensor indicates that the other magneto is enabled and (b) the stored signal.

6. A system as in claim 5, further comprising a display, and wherein the controller is adapted to display the relationship to a pilot.

7. A system as in claim 5, wherein the controller receives signals from one or more aircraft systems sufficient to allow the controller to determine whether the aircraft is operating in a condition wherein operating with only one magneto enabled is not preferred, and, if the aircraft is in such a condition and the switch sensor indicates that only one magneto is enabled, then communicating an alert to a pilot.

8. A system as in claim 6, wherein the controller displays the engine operation rate sensor output corresponding to the stored signal and an indication of which magneto was enabled.

9. A system as in claim 8, wherein the controller further displays the engine operation rate sensor output while the other magneto is enabled and an indication of which magneto was enabled.

10. A system as in claim 5, wherein the controller is adapted to determine a ratio of or difference between the engine operation rate sensor outputs produced while each magneto is enabled, and to communicate that ratio or difference to a pilot.

11. A system as in claim 10, wherein the controller communicates an alert to a pilot if the ratio or difference not within a predetermined range.

12. A method of determining whether two magnetos in an aircraft are both operating acceptably, comprising:

a. Providing a system as in claim 5,

b. Accepting an indication from a pilot that a magneto check is to be performed;

c. When an indication is received from the switch sensor that only one magneto is enabled, then receiving a signal from the engine operation rate sensor and storing a value indicative of the engine operate rate;

d. When an indication is received from the switch sensor that the magneto in step c is disabled and the other magneto is enabled, then receiving a signal from the engine operation rate sensor and storing a value indicative of the engine operation rate;

e. Communicating to the pilot a relationship between the two stored values.

13. A method as in claim 12, wherein communicating a relationship comprises displaying a ratio of or difference between the two stored values.

14. A method as in claim 12, wherein communicating a relationship comprises displaying a representation of the engine operation rate sensor output correlated to an indication of the magneto enabled while that output was received.