David P Lockard

US Patent:

20120153086, Jun 21, 2012

Filed:

Dec 15, 2011

Appl. No.:

13/326779

Inventors:

Mehdi R. Khorrami - Norfolk VA, US
David P. Lockard - Hampton VA, US
James B. Moore - Yorktown VA, US
Ji Su - Yorktown VA, US
Travis L. Turner - Yorktown VA, US
John C. Lin - Seaford VA, US
Karen M. Taminger - Yorktown VA, US
Seun K. Kahng - Poquoson VA, US
Scott A. Verden - Hampton VA, US

Assignee:

United States of America as represented by the Administrator of the National Aeronautics and Spac - Washington DC

International Classification:

B64C 9/16

US Classification:

244216

Abstract:

A system is provided for reducing aeroacoustic noise generated by an aircraft having wings equipped with trailing-edge flaps. The system includes a plurality of elastically deformable structures. Each structure is coupled to and along one of the side edges of one of the trailing-edge flaps, and is coupled to a portion of one of the wings that is adjacent to the one of the side edges. The structures elastically deform when the trailing-edge flaps are deployed away from the wings.

US Patent:

20120261517, Oct 18, 2012

Filed:

Apr 18, 2012

Appl. No.:

13/449807

Inventors:

Travis L. Turner - Yorktown VA, US
Mehdi R. Khorrami - Norfolk VA, US
David P. Lockard - Hampton VA, US
Martin J. McKenney - Virginia Beach VA, US
Raymond D. Atherley - Norfolk VA, US
Reggie T. Kidd - Hampton VA, US

Assignee:

U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration - Washington DC

International Classification:

B64C 3/50
B64C 13/16

US Classification:

244203, 244214

Abstract:

A multi-element airfoil system includes an airfoil element having a leading edge region and a skin element coupled to the airfoil element. A slat deployment system is coupled to the slat and the skin element, and is capable of deploying and retracting the slat and the skin element. The skin element substantially fills the lateral gap formed between the slat and the airfoil element when the slat is deployed. The system further includes an uncoupling device and a sensor to remove the skin element from the gap based on a critical angle-of-attack of the airfoil element. The system can alternatively comprise a trailing edge flap, where a skin element substantially fills the lateral gap between the flap and the trailing edge region of the airfoil element. In each case, the skin element fills a gap between the airfoil element and the deployed flap or slat to reduce airframe noise.

US Patent:

20120097791, Apr 26, 2012

Filed:

Oct 20, 2011

Appl. No.:

13/277859

Inventors:

Travis L. Turner - Yorktown VA, US
Reggie T. Kidd - Hampton VA, US
David P. Lockard - Hampton VA, US
Mehdi R. Khorrami - Norfolk VA, US
Craig L. Streett - Virginia Beach VA, US
Douglas Leo Weber - Hayes VA, US

Assignee:

U.S.A as represented by the Administrator of the National Aeronautics and Space Administration - Washington DC

International Classification:

B64C 1/40
B64C 3/50

US Classification:

244 1 N, 244214

Abstract:

A slat cove filler is utilized to reduce airframe noise resulting from deployment of a leading edge slat of an aircraft wing. The slat cove filler is preferably made of a super elastic shape memory alloy, and the slat cove filler shifts between stowed and deployed shapes as the slat is deployed. The slat cove filler may be configured such that a separate powered actuator is not required to change the shape of the slat cove filler from its deployed shape to its stowed shape and vice-versa. The outer contour of the slat cove filler preferably follows a profile designed to maintain accelerating flow in the gap between the slat cove filler and wing leading edge to provide for noise reduction.

US Patent:

20210237850, Aug 5, 2021

Filed:

Apr 5, 2021

Appl. No.:

17/222604

Inventors:

- Washington DC, US
Scott E. Brynildsen - Yorktown VA, US
John W. Mulvaney - Yorktown VA, US
Albert R. Allen - Yorktown VA, US
David P. Lockard - Hampton VA, US
Craig L. Streett - Fairfax VA, US
Mehdi R. Khorrami - Norfolk VA, US

International Classification:

B64C 9/24
B64C 9/02
B64C 9/08

Abstract:

Methods, systems and devices of the various embodiments may provide slat-cove fillers configured to reduce leading-edge slat noise on aircraft, such as transport aircraft.

US Patent:

20190112029, Apr 18, 2019

Filed:

Oct 12, 2018

Appl. No.:

16/158595

Inventors:

- WASHINGTON DC, US
James B. Moore - Yorktown VA, US
David L. Long - Newport News VA, US
Henry H. Haskin - Victor MT, US
Albert R. Allen - Yorktown VA, US
David P. Lockard - Hampton VA, US
Craig L. Streett - Virginia Beach VA, US
Mehdi R. Khorrami - Norfolk VA, US

International Classification:

B64C 9/02
B64C 3/50
B64C 9/34
B64C 9/24

Abstract:

Wing structure that includes slat-cove fillers configured to reduce leading-edge slat noise on aircraft, such as transport aircraft.

US Patent:

20160137284, May 19, 2016

Filed:

Jan 25, 2016

Appl. No.:

15/005338

Inventors:

- Washington DC, US
Reggie T. Kidd - Hampton VA, US
David P. Lockard - Hampton VA, US
Mehdi R. Khorrami - Norfolk VA, US
Craig L. Streett - Virginia Beach VA, US
Douglas Leo Weber - Hayes VA, US

International Classification:

B64C 3/48
B64C 9/24

Abstract:

A slat cove filler is utilized to reduce airframe noise resulting from deployment of a leading edge slat of an aircraft wing. The slat cove filler is preferably made of a super elastic shape memory alloy, and the slat cove filler shifts between stowed and deployed shapes as the slat is deployed. The slat cove filler may be configured such that a separate powered actuator is not required to change the shape of the slat cove filler from its deployed shape to its stowed shape and vice-versa. The outer contour of the slat cove filler preferably follows a profile designed to maintain accelerating flow in the gap between the slat cove filler and wing leading edge to provide for noise reduction.