Method of and system for one-engine-inoperative training in aircraft with dissimilar engines

Patent metadata

Field	Value
Publication number	US-12488702-B2
Application number	US-202117378980-A
Country	US
Kind code	B2
Filing date	Jul 19, 2021
Priority date	Jul 19, 2021
Publication date	Dec 2, 2025
Grant date	Dec 2, 2025

Abstract

A method of simulating an aircraft one-engine inoperative (“OEI”) event includes operating a supplemental power unit (“SPU”) at a first SPU power level less than an SPU contingency power rating, operating a primary engine at a first primary-engine power level, reducing the primary-engine power level to less than the first primary-engine power level, and maintaining a sum of the primary-engine power level and the SPU power level at a power level substantially equal to the SPU contingency power rating.

First claim

What is claimed is:

1 . A method of simulating a one-engine inoperative (“OEI”) event in a multi-engine aircraft that does not employ identical engines, the method comprising:
operating a supplemental power unit (“SPU”) at a first SPU power level less than an SPU contingency power rating, wherein the SPU contingency power rating is a power level after which the SPU must be inspected to assess a need for an overhaul of the SPU;
operating a primary engine at a first primary-engine power level;
simulating the OEI inoperative event by reducing the primary-engine power level to less than the first primary-engine power level; and
maintaining a sum of the primary-engine power level and the SPU power level at a power level substantially equal to the SPU contingency power rating.

2 . The method of claim 1 , wherein the first SPU power level is a power level at which the SPU can be operated continuously without damage.

3 . The method of claim 1 , wherein the first SPU power level is a non-zero power level.

4 . The method of claim 1 , wherein the first SPU power level is zero.

5 . The method of claim 1 , comprising operating the SPU at a second SPU power level greater than the first SPU power level and less than the SPU contingency power rating.

6 . The method of claim 1 , comprising operating the SPU at a second SPU power level less than the first SPU power level.

7 . A system for simulating an aircraft one-engine inoperative (“OEI”) event in a multi-engine aircraft that does not employ identical engines, the system comprising:
a supplemental power unit (“SPU”) operable at a first SPU power level less than an SPU contingency power rating, wherein the SPU contingency power rating is a power level after which the SPU must be inspected to assess a need for an overhaul of the SPU;
a primary engine operable at a first primary-engine power level;
a flight control system (“FCS”) that controls the SPU and the primary engine, wherein the FCS is operable to:
simulate the OEI inoperative event by reducing the primary-engine power level to less than the first primary-engine power level; and
maintain a sum of the primary-engine power level and the SPU power level at a power level substantially equal to the SPU contingency power rating.

8 . The system of claim 7 , wherein the first SPU power level is a power level at which the SPU can be operated continuously without damage.

9 . The system of claim 7 , wherein the first SPU power level is a non-zero power level.

10 . The system of claim 7 , wherein the first SPU power level is zero.

11 . The system of claim 7 , wherein the SPU is operable at a second SPU power level greater than the first SPU power level and less than the SPU contingency power rating.

12 . The system of claim 7 , wherein the SPU is operable at a second SPU power level less than the first SPU power level.

13 . A computer-program product comprising a non-transitory computer-usable medium having computer-readable program code embodied therein, the computer-readable program code adapted to be executed to implement a method comprising:
operating a supplemental power unit (“SPU”) of a multi-engine aircraft that does not employ identical engines at a first SPU power level less than an SPU contingency power rating, wherein the SPU contingency power rating is a power level after which the SPU must be inspected to assess a need for an overhaul of the SPU; operating a primary engine of the multi-engine aircraft at a first primary-engine power level; simulating the OEI inoperative event by reducing the primary-engine power level to less than the first primary-engine power level; and maintaining a sum of the primary-engine power level and the SPU power level at a power level substantially equal to the SPU contingency power rating.

14 . The computer-program product of claim 13 , wherein the first SPU power level is a power level at which the SPU can be operated continuously without damage.

15 . The computer-program product of claim 13 , wherein the first SPU power level is a non-zero power level.

16 . The computer-program product of claim 13 , wherein the first SPU power level is zero.

17 . The computer-program product of claim 13 , the method comprising operating the SPU at a second SPU power level greater than the first SPU power level and less than the SPU contingency power rating.

Assignees

• Bell Textron Inc
• Textron Innovations Inc

Inventors

• Acee Aaron Alexander
• Mosig Timothy Mcclellan
• Seifert Michael

Classifications

• G09B9/08 Primary

  for teaching control of aircraft, e.g. Link trainer · CPC title

• B64D31/12

  for equalising or synchronising power plants · CPC title

• B64C27/12

  Rotor drives · CPC title

• B64C27/006

  Safety devices · CPC title

• G09B9/18 Primary

  Condition of engine or fuel supply · CPC title