Mark R Larson

US Patent:

56810911, Oct 28, 1997

Filed:

Jun 15, 1995

Appl. No.:

8/490796

Inventors:

Mark Larson - Pembroke Pines FL
Michael Oleson - Ft. Lauderdale FL

Assignee:

Aircraft Modular Products, Inc. - Miami FL

International Classification:

A47C 702

US Classification:

29745221

Abstract:

An aircraft seat pan assembly to be mounted on an aircraft seat foundation including a pair of spaced side rail supports and a pair of spaced apart cross supports disposed in spanning relating between the side rail supports, the seat pan assembly including a seat panel with a primary surface, a pair of opposite side edges, a front edge, and a rear edge. The side edges and front edge of the seat panel are structured to be secured directly to the side rail supports and a front cross support of the seat foundation in generally planar relation thereto, and a rear edge of the seat panel is structured to be secured to the rear cross support in a generally elevated, spaced apart position there above such that a quantity of a downward spine load exerted on the seat panel will be absorbed at the connection between the rear edge and the rear cross support. Accordingly, the panel will resist the downward spine load thereon to a satisfaction of FAA guidelines with a minimum initial stroking distance between the primary surface of the seat panel and any underlying seat frame portions being maintained.

US Patent:

59044071, May 18, 1999

Filed:

Oct 28, 1997

Appl. No.:

8/958947

Inventors:

Mark Larson - Pembroke Pines FL
Michael Oleson - Ft. Lauderdale FL

Assignee:

Aircraft Modular Products, Inc. - Miami FL

International Classification:

A47C7/02

US Classification:

29745221

Abstract:

An aircraft seat pan assembly to be mounted on an aircraft seat foundation including a pair of spaced side rail supports and a pair of spaced apart cross supports disposed in spanning relating between the side rail supports, the seat pan assembly including a seat panel with a primary surface, a pair of opposite side edges, a front edge, and a rear edge. The side edges and front edge of the seat panel are structured to be secured directly to the side rail supports and a front cross support of the seat foundation in generally planar relation thereto, and a rear edge of the seat panel is structured to be secured to the rear cross support in a generally elevated, spaced apart position there above such that a quantity of a downward spine load exerted on the seat panel will be absorbed at the connection between the rear edge and the rear cross support. Accordingly, the panel will resist the downward spine load thereon to a satisfaction of FAA guidelines with a minimum initial stroking distance between the primary surface of the seat panel and any underlying seat frame portions being maintained.

US Patent:

58365478, Nov 17, 1998

Filed:

Apr 8, 1996

Appl. No.:

8/630009

Inventors:

Roger Koch - Miami Shores FL
Ronald Grilliot - Plantation FL
Mark Larson - Pembroke Pines FL

Assignee:

Aircraft Modular Products, Inc. - Miami FL

International Classification:

B60N 242
B60R 21055
B64D 2504
B64D 2500

US Classification:

244122R

Abstract:

An attenuated aircraft seat back assembly for use on an aircraft passenger seat of the type which includes a seat back frame with a front side and a rear side, the attenuated assembly comprising a mount assembly structured to be secured at the rear side of the seat back frame, preferably at an upper end thereof, and an impact absorbent, generally rigid material panel fixedly secured thereto. The mount assembly is structured to securely maintain the rigid material panel in a generally parallel orientation relative to the seat back frame, and spaced apart from the seat back frame by a predetermined distance. The rigid material panel, which is sized and configured to shield an upper region of the seat back frame, is substantially lightweight and includes a honeycomb interior core structured and disposed to substantially resist the force of a direct impact thereto, while still yielding sufficiently so that an object impacting the rigid material panel will have a Head Injury Criteria (HIC) value which is acceptable under current Federal Aviation Administration regulations. Preferably, an energy absorbent, resilient material panel is adhered to a front face of the rigid material panel, and together have a combined thickness of generally about two inches, while being spaced apart from the seat back frame in assembled form so as to minimize an overall thickness of the assembly.