Accession Number : ADA294041

Title :   Evaluating the Potential for Rotation and Loss of Flight Helmets From Inertia and Impact Loads

Descriptive Note : Final rept.

Corporate Author : ARMY AEROMEDICAL RESEARCH LAB FORT RUCKER AL

Personal Author(s) : Bruckart, James E. ; Haley, Joseph L., Jr.

PDF Url : ADA294041

Report Date : MAR 1995

Pagination or Media Count : 16

Abstract : In severe helicopter accidents, flight helmets rotate or sometimes come off the head, triggering wearer injury. This study evaluates rotation potential for new flight helmets. Current and prototype flight helmets (SPH-4B and two versions of the HGU-56) were subjected to three tests. First, rotation was measured with up to a 50-pound upward pull at the rear edge of the helmet on a medium-size headform. Second, angular displacement was measured with a 30-pound force at the side of the helmet. Third, the helmet was placed on a Hybrid II headform and Hybrid III neck, then mounted on a pendulum test device. The freefalling pendulum was decelerated to produce 16 to 20 G peak acceleration at the neck. Angular displacement of the helmet versus time was measured with high-speed video. The upward pull tests produced 18 to 33 degrees of helmet rotation. Sideward loads produced 13 to 21 degrees of rotation. The pendulum test produced up to 45 degrees forward and up to 25 degrees rearward displacement.

Descriptors :   *INERTIA, *LOSSES, *AVIATION SAFETY, *FLIGHT HELMETS, TEST AND EVALUATION, ANGLES, IMPACT, EDGES, LOADS(FORCES), DISPLACEMENT, PILOTS, PROTOTYPES, TEST EQUIPMENT, HELICOPTERS, WOUNDS AND INJURIES, VIDEO SIGNALS, ROTATION, PULL TESTS, HELMETS, ACCIDENTS, PENDULUMS, NECK(ANATOMY).

Subject Categories : Protective Equipment
      Military Aircraft Operations

Distribution Statement : APPROVED FOR PUBLIC RELEASE