Composite airspeed indicator display for compound aircrafts

Patent metadata

Field	Value
Publication number	US-10690555-B2
Application number	US-201815892045-A
Country	US
Kind code	B2
Filing date	Feb 8, 2018
Priority date	Oct 17, 2017
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

Abstract

A torque indicator for an aircraft having a main rotor system and a translational thrust system driven by at least one engine includes a first indicator operable to display an actual torque of an engine of the aircraft relative to an engine torque limit, a second indicator operable to display an actual torque of the translational thrust system of the aircraft relative to a translational thrust system torque limit, and a third indicator operable to display an actual torque of the main rotor system of the aircraft relative to a main rotor system torque limit.

First claim

What is claimed is:

1. A torque indicator for an aircraft having a main rotor system and a translational thrust system driven by at least one engine comprising:
a first indicator operable to display an actual torque of an engine of the aircraft relative to an engine torque limit; and
a second indicator operable to display an actual torque of the translational thrust system of the aircraft relative to a translational thrust system torque limit; and
a third indicator operable to display an actual torque of the main rotor system of the aircraft relative to a main rotor system torque limit.

2. The torque indicator of claim 1 , wherein the main rotor system includes an upper rotor system and a lower rotor system, and the third indicator further comprises an indicator operable to display an actual torque of the upper rotor system and an indicator operable to display an actual torque of the lower rotor system.

3. The torque indicator of claim 1 , wherein the torque indicator is a linear gage.

4. The torque indicator of claim 1 , wherein the first indicator and the second indicator are positioned adjacent sides of the torque indicator and the third indicator is arranged at a center of the torque indicator.

5. The torque indicator of claim 1 , further comprising a fourth indicator operable to display a digital, numerical readout of the first indicator, the second indicator, and third indicator.

6. The torque indicator of claim 5 , wherein the fourth indicator is operable to display a digital numerical readout of a rotor speed of the main rotor system.

7. The torque indicator of claim 1 , further comprising a fourth indicator operable to display a digital, numerical readout of a collective applied to the main rotor system.

8. The torque indicator of claim 7 , wherein the fourth indicator is operable to additionally provide a reference collective command provided to the main rotor system.

9. The torque indicator of claim 1 , wherein a color of at least one of the first indicator, second indicator, and third indicator, changes as the actual torque approaches the torque limit.

10. The torque indicator of claim 1 , wherein the torque indicator is a portion of a multifunction display unit.

11. A method of displaying a torque of various components of an aircraft comprising:
indicating, via a first indicator, an actual torque of an engine of the aircraft relative to an engine torque limit on a torque display displaying;
indicating, via a second indicator, an actual torque of a translational thrust system of the aircraft relative to a translational thrust system torque limit on the torque display; and
indicating, via a third indicator, an actual torque of a main rotor system of the aircraft relative to a main rotor system torque limit on the torque display.

12. The method of claim 11 , wherein the torque display includes a linear gage.

13. The method of claim 11 , wherein the main rotor system includes a first rotor and a second rotor and indicating an actual torque of a main rotor system of the aircraft relative to a main rotor system torque limit on the torque display further comprises:
indicating an actual torque of the first rotor relative to the main rotor system torque limit; and
indicating an actual torque of the second rotor, separate from the first rotor, relative to the main rotor system torque limit.

14. The method of claim 11 , further comprising displaying a digital readout of at least one of the actual torque of the engine, the actual torque of the translational thrust system, and the actual torque of the main rotor system.

15. The method of claim 11 , further comprising displaying a digital readout of a rotational speed of the main rotor system.

16. The method of claim 11 , further comprising displaying an actual value of a collective of the aircraft.

17. The method of claim 11 , further comprising indicating a status of at least one of the actual torque of the engine relative to the engine torque limit, the actual torque of a translational thrust system relative to the translational thrust system torque limit, and the actual torque of a main rotor system relative to the main rotor system torque limit.

18. The method of claim 17 , wherein at least one of the first indicator, the second indicator, and the third indicator, is a first color when the actual torque of the engine is at an allowable level relative to the engine torque limit, the actual torque of a translational thrust system is at an allowable level relative to the translational thrust system torque limit, and the actual torque of a main rotor system is at an allowable level relative to the main rotor system torque limit, respectively.

19. The method of claim 17 , wherein at least one of the first indicator, the second indicator, and the third indicator, is a second color when the actual torque of the engine is approaching the engine torque limit, the actual torque of a translational thrust system is approaching the translational thrust system torque limit, and the actual torque of a main rotor system is approaching the main rotor system torque limit, respectively.

20. The method of claim 17 , wherein at least one of the first indicator, the second indicator, and the third indicator, is a second color when the actual torque of the engine equals or exceeds the engine torque limit, the actual torque of a translational thrust system equals or exceeds the translational thrust system torque limit, and the actual torque of a main rotor system equals or exceeds the main rotor system torque limit, respectively.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Adams David L
• Fimbers Kevin Ron

Classifications

• G01C23/005 Primary

  Flight directors (indicating arrangements specially adapted for rotary gyroscopes G01C19/32) · CPC title

• B64C27/08

  with two or more rotors · CPC title

• G05D1/0858

  specially adapted for vertical take-off of aircraft · CPC title

• G01L3/08 Primary

  involving optical means for indicating · CPC title

• B64D43/02

  for indicating aircraft speed or stalling conditions · CPC title