ROBERT HAROLD HAMMER
Pilots at 110 Ave, Kirkland, WA
License number
Washington A0764348
Issued Date
Jul 2015
Expiration Date
Jul 2017
Category
Airmen
Type
Authorized Aircraft Instructor
Address
Address
4723 110Th Ave NE, Kirkland, WA 98033
Professional information
Hybrid Composite Structures
US Patent:
4344995, Aug 17, 1982
Filed:
Sep 15, 1980
Appl. No.:
6/187247
Inventors:
Robert H. Hammer - Kirkland WA
Assignee:
The Boeing Company - Seattle WA
International Classification:
B32B 312, B32B 2302, B32B 310
US Classification:
428 61
Abstract:
A graphite containing composite structure having a fastener area for joining the composite to other structures terminates the graphite reinforced laminate adjacent to the fastener area. Kevlar reinforced laminates abut the graphite laminate and extend over the fastener area and are further reinforced with Kevlar laminates that overlap the graphite then extend over the fastener area.
Method Of Making Wing Box Cover Panel
US Patent:
4749155, Jun 7, 1988
Filed:
Sep 30, 1985
Appl. No.:
6/781776
Inventors:
Robert H. Hammer - Kirkland WA
Raymond E. Pearson - Redmond WA
Raymond E. Pearson - Redmond WA
Assignee:
The Boeing Company - Seattle WA
International Classification:
B64C 320, B64C 324
US Classification:
244123
Abstract:
A plurality of channel-shaped members (12) are positioned longitudinally along the inner surface of an outer skin (6). Each member (12) has a web (14) and two flanges (16). Members (12) are positioned laterally contiguously to each other so that, when outer skin (6) and members (12) are cured together, webs (14) form an inner skin portion (8) and adjacent flanges (16) form blade stiffeners (10). A generally L-shaped member (22) is positioned to extend longitudinally along the inner surface of outer skin (6) adjacent to each side edge of skin (6), with one leg (26) of member (22) contiguous to a modified flange (16') of channel-shaped member (12'). When outer skin (6) and members (12,12',22) are cured together, leg (26) and flange (16') form a spar chord (20). Reinforcing fibers in skin (6,8) resist torsional shear. Reinforcing fibers in stiffeners (10) and spar chords (20) resist bending loads.