Deceleration to hover modulation

Patent metadata

Field	Value
Publication number	US-9308985-B2
Application number	US-201414251133-A
Country	US
Kind code	B2
Filing date	Apr 11, 2014
Priority date	Apr 11, 2014
Publication date	Apr 12, 2016
Grant date	Apr 12, 2016

Abstract

A system and method for controlling a deceleration profile of an aircraft, includes a processor and memory that receives a signal indicative of a deceleration command; receives signals indicative of a sensed velocity and a commanded heading rate; determines a commanded velocity in response to the receiving of the deceleration command and the commanded heading rate; determines an estimated deceleration command as a function of the commanded velocity; and determines an actual deceleration command in response to the determining of the estimated deceleration command.

First claim

What is claimed is:

1. A method for controlling a deceleration profile of an aircraft, comprising:
determining the deceleration profile to obtain a hover condition at a commanded location; and
adjusting the deceleration profile in a continuous manner by manual input from a pilot, wherein adjusting comprises:
receiving, with a processor, a signal indicative of a deceleration command;
receiving with the processor, signals indicative of a sensed velocity and a commanded heading rate;
determining, with the processor, a commanded velocity in response to the receiving of the deceleration command and the commanded heading rate;
determining, with the processor, an estimated deceleration command as a function of the commanded velocity; and
determining, with the processor, an actual deceleration command in response to the determining of the estimated deceleration command.

2. The method of claim 1 , wherein the receiving of the deceleration command further comprises receiving longitudinal and lateral deceleration commands.

3. The method of claim 1 , wherein the determining of the commanded velocity further comprises determining a commanded longitudinal velocity and a commanded lateral velocity.

4. The method of claim 3 , further comprising determining a longitudinal velocity error signal indicative of a difference between the commanded longitudinal velocity and a sensed longitudinal velocity.

5. The method of claim 4 , further comprising determining a longitudinal commanded gain ratio as a function of the longitudinal velocity error signal and a total velocity magnitude.

6. The method of claim 5 , further comprising determining a lateral commanded gain ratio as a function of the lateral velocity error signal and a total velocity magnitude.

7. The method of claim 6 , further comprising determining the estimated deceleration command as a function of the total velocity magnitude.

8. The method of claim 3 , further comprising determining a lateral velocity error signal indicative of a difference between the commanded lateral velocity and a sensed lateral velocity.

9. The method of claim 1 , further comprising determining a commanded acceleration in response to the receiving of the deceleration command.

10. The method of claim 9 , further comprising determining a second error value indicative of a difference between the commanded acceleration and a sensed acceleration.

11. The method of claim 1 , further comprising determining a Translational Rate Command response wherein controller deflection correlates to steady state velocity.

12. A system for controlling a deceleration profile of an aircraft, comprising
a propeller comprising a plurality of blades, wherein the propeller is associated with a sensor;
a processor; and
memory having instructions stored thereon that, when executed by the processor, cause the system to:
determine the deceleration profile to obtain a hover condition at a commanded location, wherein the deceleration profile is adjustable in a continuous manner by manual input from a pilot;
receive a signal indicative of a deceleration command;
receive signals indicative of a sensed velocity and a commanded heading rate;
determine a commanded velocity in response to the receiving of the deceleration command and the commanded heading rate;
determine an estimated deceleration command as a function of the commanded velocity; and
determine an actual deceleration command in response to the determining of the estimated deceleration command.

13. The system of claim 12 , wherein the processor is configured to receive longitudinal and lateral deceleration commands.

14. The system of claim 12 , wherein the processor is configured to determine a commanded longitudinal velocity and a commanded lateral velocity.

15. The system of claim 14 , wherein the processor is configured to determine a longitudinal velocity error signal indicative of a difference between the commanded longitudinal velocity and a sensed longitudinal velocity.

16. The system of claim 15 , wherein the processor is configured to determine a longitudinal commanded gain ratio as a function of the longitudinal velocity error signal and a total velocity magnitude.

17. The system of claim 14 , wherein the processor is configured to determine a lateral velocity error signal indicative of a difference between the commanded lateral velocity and a sensed lateral velocity.

18. The system of claim 17 , wherein the processor is configured to determine a lateral commanded gain ratio as a function of the lateral velocity error signal and a total velocity magnitude.

19. The system of claim 12 , wherein the processor is configured to determine a commanded acceleration in response to the receiving of the deceleration command.

20. The system of claim 19 , wherein the processor is configured to determine a second error value indicative of a difference between the commanded acceleration and a sensed acceleration.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Kubik Stephen
• Faynberg Alex
• Mcculley Stephen C
• Rucci John P
• Corry Christiaan P
• Pavelka Edward

Classifications

• G05D1/102

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

• G05D13/62

  characterised by the use of electric means, e.g. use of a tachometric dynamo, use of a transducer converting an electric value into a displacement {(electric motor control H02P)} · CPC title

• B64C13/503 Primary

  Fly-by-Wire · CPC title

• G05D1/0202

  specially adapted to aircraft · CPC title

• G05D13/02

  Details · CPC title