Method and device for monitoring a deviation of a first rotational speed of a first drive unit for an aircraft from a second rotational speed of an at least second drive unit for an aircraft

Patent metadata

Field	Value
Publication number	US-10202199-B2
Application number	US-201715807299-A
Country	US
Kind code	B2
Filing date	Nov 8, 2017
Priority date	Nov 17, 2016
Publication date	Feb 12, 2019
Grant date	Feb 12, 2019

Abstract

A method and a device for monitoring a deviation of a first rotational speed of a first drive unit for an aircraft from a second rotational speed of an at least second drive unit of an aircraft. The monitoring of the deviation of the first rotational speed of the first drive unit from the second rotational speed of the at least second drive unit is carried out as a function of a comparison of a detection of a first event of the first drive unit to a detection of a second event of the at least second drive unit.

First claim

What is claimed is:

1. A method for monitoring a deviation of a first rotational speed of a first drive unit for an aircraft from a second rotational speed of an at least second drive unit for an aircraft, the method comprising:
detecting a first event of the first drive unit and detecting a second event of the at least second drive unit;
comparing the detection of the first event to the detection of the second event; and
monitoring the deviation of the first rotation speed of the first drive unit from the second rotational speed of the second drive unit as a function of the comparison.

2. The method as recited in claim 1 , further comprising:
incrementing a value of a counter when the first event of the first drive unit is detected; and
decrementing the value of the counter when the second event of the at least second drive unit is detected.

3. The method as recited in claim 2 , wherein the value of the counter is incremented and decremented in whole numbers.

4. The method as recited in claim 1 , wherein the first event is a firing of a cylinder of an engine of the first drive unit, and the second event is a firing of a cylinder of an engine of the at least second drive unit.

5. The method as recited in claim 1 , wherein the first event is a signal of a position sensor of the first drive unit, and the second event is a signal of a position sensor of the at least second drive unit.

6. The method as recited in claim 2 , wherein an adaptation of the deviation of the first rotational speed of the first drive unit from the second rotational speed of the at least second drive unit of the aircraft is carried out as a function of a comparison of the value of the counter to a predefinable threshold value.

7. The method as recited in claim 2 , wherein the deviation of the first rotational speed of the first drive unit from the second rotational speed of the at least second drive unit is adapted when the value of the counter exceeds or falls below a predefinable threshold value.

8. The method as recited in claim 2 , wherein a control unit of the first drive unit recognizes and stores an error when the value of the counter exceeds or falls below a predefinable threshold value, and a corresponding signal is transmitted from the control unit of the first drive unit to a control unit of the at least second drive unit via a CAN connection, and the signal is received and stored by the second control unit of the at least second drive unit.

9. The method as recited in claim 2 , wherein a phase position between a propeller of the first drive unit and a propeller of the at least second drive unit is determined as a function of a time difference that is ascertained between the first event of the first drive unit and a successive, similar second event of the at least second drive unit.

10. The method as recited in claim 9 , further comprising:
detecting, by a position sensor of the propeller of the first drive unit that the propeller of the first drive unit exceeds or falls below a predefinable reference position, and detecting, by a position sensor of the propeller of the second drive unit that the propeller of the second drive unit exceeds or falls below a predefinable reference position;
transmitting, by the position sensors, a corresponding signal to a respective control unit, as a function of the exceeding or falling below the reference position with the aid of a CAN connection; and
receiving and storing, by the respective control units, the corresponding signals.

11. The method as recited in claim 1 , wherein the first drive unit and the at least second drive unit are each made up of at least one of: an engine, an electronic engine control unit (EECU), an autonomous, full authority digital engine controller (FADEC), a propeller that is connected to the engine, a propeller speed controller that controls a rotational speed of the propeller, and a position sensor of the propeller.

12. The method as recited in claim 1 , wherein a control unit of the first drive unit is a master control unit, and a control unit of the at least second drive unit is a slave control unit.

13. A non-transitory electronic memory medium on which is stored a computer program for monitoring a deviation of a first rotational speed of a first drive unit for an aircraft from a second rotational speed of an at least second drive unit for an aircraft, the computer program, when executed by a control unit, causing the control unit to perform:
detecting a first event of the first drive unit and detecting a second event of the at least second drive unit;
comparing the detection of the first event to the detection of the second event; and
monitoring the deviation of the first rotation speed of the first drive unit from the second rotational speed of the second drive unit as a function of the comparison.

14. A control unit for monitoring a deviation of a first rotational speed of a first drive unit for an aircraft from a second rotational speed of an at least second drive unit for an aircraft, the control unit configured to:
detect a first event of the first drive unit and detect a second event of the at least second drive unit;
compare the detection of the first event to the detection of the second event; and
monitor the deviation of the first rotation speed of the first drive unit from the second rotational speed of the second drive unit as a function of the comparison.

Assignees

• Bosch Gmbh Robert

Inventors

• Widmer Martin

Classifications

• B64C11/50

  Phase synchronisation between multiple propellers · CPC title

• F02D25/02

  to synchronise speed · CPC title

• B64D31/12 Primary

  for equalising or synchronising power plants · CPC title

• B64D31/06 Primary

  actuated automatically · CPC title