Accession Number:

AD0404561

Title:

CREW SEAT DESIGN CRITERIA FOR ARMY AIRCRAFT

Descriptive Note:

Technical rept.

Corporate Author:

AVIATION SAFETY ENGINEERING AND RESEARCH PHOENIX AZ

Report Date:

1963-02-01

Pagination or Media Count:

60.0

Abstract:

Strength requirements set forth in military specifications governing the design and fabrication of nonejection-type crew seats currently utilized in Army aircraft were analyzed in light of accident experience with this seat and human tolerance as presently known. The analysis revealed that the strength requirements quoted in current military specifications are considerably lower than 1 those which would be dictated by the upper limit of accelerations which can be tolerated by the occupants of the seats and 2 the accelerations and forces that are associated with Army aircraft accidents. This substantiates the observation that these seats fail under relatively moderate accident conditions, thus subjecting the occupant to further hazards, especially in increased contact injuries. On the basis of the detailed examination of current specifications, human tolerance, and impact acceleration data, it is recommended that the crew seat specifications be revised and that dynamic load f of 25G for 0.20 second plus 45G for 0.10 second, measured in the pelvic region of a suitable anthropomorphic dummy, be adopted for crew seat design in the longitudinal and lateral directions, and 25G for 0.20 second for the vertical direction. In addition, an energy absorption capability must be incorporated into the seat system to reduce the vertical accelerations, which will frequently exceed 25G, to a tolerable level.

Subject Categories:

  • Aircraft
  • Protective Equipment
  • Human Factors Engineering and Man Machine Systems

Distribution Statement:

APPROVED FOR PUBLIC RELEASE