Fiber-reinforced, composite, structural member exhibiting non-linear strain-to-failure and method of making same

A helicopter landing gear, comprising:

• a pair of skids;
• and
• one or more cross members extending between the pair of skids, the one or more cross members comprising:
• a plurality of layers of fiber-reinforced, organic matrix, composite material in which adjacent layers are bonded to one another, the plurality of layers having:
• a first, innermost layer comprising reinforcing fibers oriented generally at 90 degrees with respect to a loading direction of the structural member;
• a second layer disposed on the first layer, the second layer comprising reinforcing fibers oriented generally at ±25 degrees with respect to the loading direction of the structural member;
• a third layer disposed on the second layer, the third layer comprising reinforcing fibers oriented generally at 90 degrees with respect to the loading direction of the structural member;
• a fourth layer disposed on the third layer, the fourth layer comprising reinforcing fibers oriented generally at ±30 degrees with respect to the loading direction of the structural member;
• a fifth layer disposed on the fourth layer, the fifth layer comprising reinforcing fibers oriented generally at 90 degrees with respect to the loading direction of the structural member;
• and
• a sixth layer disposed on the fifth layer, the sixth layer comprising reinforcing fibers oriented generally at ±45 degrees with respect to the loading direction of the structural member;
• wherein the one or more cross members are configured to exhibit non-linear stress-strain responses when mechanically loaded to failure.