Altitude and acceleration command altitude hold algorithm for rotorcraft with large center of gravity range

• US 8,694,182 B2
• Filed: 04/03/2007
• Issued: 04/08/2014
• Est. Priority Date: 04/03/2007
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Cherepinsky, Igor
• Primary Examiner(s): Keith, Jack W.
• Assistant Examiner(s): MUSTAFA, IMRAN K
• Application Number:
  US11/695,707
• Publication Number:
  US 20080249672A1
• Time in Patent Office: 2,562 Days
• Field of Search: 701/3, 701/4, 701/7, 701/220, 244/17.11, 244/17.13, 244/76.R, 244/177, 244/178, 244/223, 318/628
• US Class Current: 701/7
• CPC Class Codes: B64C 19/00 Aircraft control not otherwise provided for
• CPC Class Codes: G05D 1/0858 specially adapted for vertical take-off of aircraft

Abstract

A flight control system includes an Acceleration and Attitude Command/Velocity Hold mode (AACVH) algorithm which blends attitude commands with acceleration commands. This blending determines a trim attitude for a given rotorcraft flight condition.

Claims

1. A flight control system for a rotary wing rotorcraft comprising:

a cyclic controller; and

a microprocessor with an attitude model, an acceleration model and an Attitude and Acceleration Command/Velocity Hold (AACVH) algorithm, said microprocessor in communication with said cyclic controller, said AACVH algorithm operable to blend an attitude command from said attitude model with an acceleration command from said acceleration model to determine a trim attitude for a given rotorcraft hover flight condition such that said collective cyclic controller returns must be returned to a neutral position to achieve said hover flight condition, said neutral position is a center detent position for said cyclic controller;

wherein said AACVH algorithm holds constant attitude and holds constant acceleration in response to said cyclic controller being held out of said center detent position.

2. The system as recited in claim 1, wherein said trim attitude is defined as an attitude where first derivatives of a primary velocity state and a primary attitude state are zero.

3. The system as recited in claim 1, further comprising a sensor system which senses measured rotorcraft attitude and a measured rotorcraft velocity and acceleration in communication with said Attitude and Acceleration Command/Velocity Hold microprocessor for use by said AACVH algorithm.

4. The system as recited in claim 1, wherein said Attitude and Acceleration Command/Velocity Hold AACVH algorithm generates an output to a model following controller.

5. The system as recited in claim 1, wherein said neutral position equates to said trim attitude for the rotorcraft.

6. The system as recited in claim 1, wherein said AACVH algorithm varies rotorcraft attitude over a long term but not over a short term.

7. The system as recited in claim 6, wherein said AACVH algorithm requires the rotorcraft to hold attitude over said short term but adjusts said rotorcraft attitude over the long term to be at a deceleration level so that as the rotorcraft approaches said hover flight condition such that said cyclic controller is returned to said center detent position with the rotorcraft at a proper attitude to hold said hover flight condition.

8. The system as recited in claim 7, wherein said short term is between 15-30 seconds.