Composite airspeed indicator display for compound aircrafts

Patent metadata

Field	Value
Publication number	US-10690554-B2
Application number	US-201815891869-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

An airspeed indicator display for an aircraft having a main rotor system and a translational thrust system includes a first indicator operable to display an actual airspeed of the aircraft and a second indicator positioned adjacent the first indicator. The second indicator is operable to display an actual pitch angle of the translational thrust system.

First claim

What is claimed is:

1. An airspeed indicator display for an aircraft having a main rotor system and a translational thrust system comprising:
a first indicator operable to display an actual airspeed of the aircraft, wherein the first indicator includes a first graphical display including a first pointer; and
a second indicator positioned adjacent the first indicator, the second indicator being operable to display a second parameter associated with the translational thrust system, wherein the second indicator includes a second graphical display including a second pointer, the second pointer being located at a position offset from the first pointer.

2. The airspeed indicator of claim 1 , wherein the first indicator is a dial having a first radius and the second indicator is an arc extending about a portion of a periphery of the first indicator, the second indicator having a second radius, the second radius being larger than the first radius.

3. The airspeed indicator of claim 1 , wherein the first indicator is operable to additionally provide a reference airspeed of the aircraft.

4. The airspeed indicator of claim 1 , wherein the second parameter displayed by the second indicator is an actual pitch angle and the second indicator is operable to additionally provide a reference pitch angle of the translational thrust system.

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

6. The airspeed indicator of claim 1 , wherein the airspeed indicator is operable to display an operational status of the translational thrust system.

7. The airspeed indicator of claim 6 , wherein a color of the second indicator varies in response to an operational mode of the translational thrust system.

8. The airspeed indicator of claim 7 , wherein a first color of the second indicator indicates that the translational thrust system is operational and a second color of the second indicator indicates that the translational thrust system is non-operational.

9. The airspeed indicator of claim 8 , wherein a third color of the second indicator indicates that the translational thrust system is transforming between operational and non-operational.

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

11. A method of using an airspeed indicator comprising:
indicating an actual airspeed of the aircraft at a first gage of a first display, wherein the first gage includes a graphical display having a first pointer; and
indicating a parameter associated with a translational thrust system of the aircraft at a second gage of the first display, the second gage being positioned adjacent the first gage, wherein the second gage includes a graphical display having a second pointer, the second pointer being located at a position offset from the first pointer.

12. The method of claim 11 , wherein the parameter associated with the translational thrust system of the aircraft includes a pitch angle of a plurality of blades of the translational thrust system.

13. The method of claim 11 , wherein the parameter associated with the translational thrust system of the aircraft includes a percentage of available thrust.

14. The method of claim 11 , further comprising indicating a digital readout of the parameter associated with the translational thrust system.

15. The method of claim 14 , wherein the digital readout is arranged directly adjacent the second gage.

16. The method of claim 14 , further comprising indicating an operational status of the translational thrust system.

17. The method of claim 16 , wherein indicating an operational status of the translational thrust system includes varying a color of at least one of the second gage and the digital readout in response to the operational status of the translational thrust system.

18. The method of claim 17 , wherein when at least one of the second gage and the digital readout is a first color, a clutch operable to provide power from an engine of the aircraft to the translational thrust system is engaged.

19. The method of claim 18 , wherein when at least one of the second gage and the digital readout is a second color, the clutch is disengaged.

20. The method of claim 19 , wherein when at least one of the second gage and the digital readout is a third color, the clutch is transforming between an engaged and disengaged configuration.

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

• B64D43/02

  for indicating aircraft speed or stalling conditions · CPC title

• B64C27/22

  Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft · CPC title