Coaxial rotor low-speed mixing

Patent metadata

Field	Value
Publication number	US-9802694-B2
Application number	US-201514699160-A
Country	US
Kind code	B2
Filing date	Apr 29, 2015
Priority date	May 1, 2014
Publication date	Oct 31, 2017
Grant date	Oct 31, 2017

Abstract

A system and method for estimating rotor mixing commands for an aircraft includes receiving signals indicative of reference commands from one or more controllers; receiving signals indicative of airspeed and sideslip angle for the aircraft, the sideslip angle being indicative of a direction of flight for the aircraft; calculating a sine and cosine of the sideslip angle; determining gains for roll and pitch as a function of the airspeed, the determining including referencing a look-up table that indexes the gain constants with the airspeed; and determining the one or more rotor mixing commands from the determined gains, the one or more rotor mixing commands being applied synchronously to the rotors in the aircraft.

First claim

What is claimed is:

1. A method for estimating rotor mixing commands for an aircraft, comprising:
receiving signals indicative of reference commands from one or more controllers;
receiving signals from one or more sensors indicative of airspeed and sideslip angle for the aircraft, the sideslip angle being indicative of a direction of flight for the aircraft;
calculating a sine and cosine of the sideslip angle;
determining gains for roll and pitch as a function of the airspeed, the determining includes referencing a look-up table that indexes the gain with the airspeed; and
determining the one or more rotor mixing commands from the determined gain, the one or more rotor mixing commands being applied synchronously to the rotors in the aircraft.

2. The method of claim 1 , wherein the receiving of information indicative of displacement commands further comprises receiving information indicative of an unmixed roll command signal, an unmixed pitch command signal, and a yaw command signal that produce a desired flight response for the aircraft.

3. The method of claim 1 , wherein the determining of the one or more rotor mixing commands further comprises determining a mixed pitch command as a function of a differential collective to ganged pitch mixing signal.

4. The method of claim 3 , further comprising applying the differential collective to ganged pitch mixing signal for travel along a lateral axis of the aircraft.

5. The method of claim 3 , wherein the determining of the mixed pitch command further comprises summing the differential collective to ganged pitch mixing signal with an unmixed pitch command signal.

6. The method of claim 3 , further comprising determining the differential collective to ganged pitch mixing signal as a function of a yaw command signal, the sine of the sideslip angle, the airspeed, and the determines gain pitch for airspeed.

7. The method of claim 1 , wherein the determining of the one or more rotor mixing commands further comprises determining a mixed roll command as a function of a differential collective to ganged roll mixing signal.

8. The method of claim 7 , further comprising applying the differential collective to ganged roll mixing signal for travel along a longitudinal axis of the aircraft.

9. The method of claim 7 , wherein the determining of the mixed roll command further comprises summing the differential collective to ganged roll mixing signal with an unmixed roll command signal.

10. The method of claim 7 , further comprising determining the differential collective to ganged roll mixing signal as a function of a yaw command signal, the cosine of the sideslip angle, the airspeed, and the gain roll constant for airspeed.

11. A system for estimating mixing commands for an aircraft, comprising:
a processor that receives signals indicative of reference commands from one or more controllers, receives signals from one or more sensors indicative of airspeed and sideslip angle for the aircraft and determines a sine and cosine of the sideslip angle, wherein the sideslip angle being indicative of a direction of flight for the aircraft; and
a memory that indexes gain constants for roll and pitch with the airspeed;
wherein the processor determines gains for roll and pitch as a function of the airspeed; and
wherein the processor determines the one or more rotor mixing commands as a function of the determined gains and communicates the one or more rotor mixing command to a servo of a rotor system associated with the processor, the servo being displaced in response to the one or more rotor mixing commands.

12. The system of claim 11 , wherein the processor receives information indicative of an unmixed roll command signal, an unmixed pitch command signal, and a yaw command signal that produce a desired flight response for the aircraft.

13. The system of claim 11 , wherein the processor determines the one or more rotor mixing commands from a mixed pitch command as a function of a differential collective to ganged pitch mixing signal.

14. The system of claim 13 , wherein the processor determines the one or more rotor mixing commands by determining a mixed roll command as a function of a differential collective to ganged roll mixing signal.

15. The system of claim 14 , wherein the processor applies the differential collective to ganged pitch mixing signal during travel along a lateral axis of the aircraft and applies the differential collective to ganged roll mixing signal for travel along a longitudinal axis of the aircraft.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Luszcz Matthew T
• White Matthew A
• Wittmer Kenneth S

Classifications

• Y02T50/34

  Cross-Sectional Technologies · mapped topic

• B64C27/10

  arranged coaxially · CPC title

• G05D1/0858

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

• B64C27/72

  Means acting on blades · CPC title

• B64C13/16 Primary

  actuated automatically, e.g. responsive to gust detectors · CPC title