Accession Number:

AD0261961

Title:

U. S. ARMY H-25 HELICOPTER DROP TEST

Descriptive Note:

Technical rept.

Corporate Author:

CORNELL-GUGGENHEIM AVIATION SAFETY CENTER NEW YORK

Personal Author(s):

Report Date:

1961-03-15

Pagination or Media Count:

110.0

Abstract:

This report presents the results of an exploratory, experimental study. A Piasecki Model H-25A helicopter has been employed in recreating a typical accident approximating an unsuccessful attempt to attain auto-rotation from a low altitude power failure. Relatively high 50G to 100G vertical and longitudinal accelerations have been observed for periods in the order of 10 milliseconds in an impact leaving the cabin area of the airframe reasonably intact. Failure of all seats occurred without failure of either seat belts or shoulder harness. The instrumentation and research techniques used in 1 the measurement of the impact forces and accelerations, 2 the determination of the feasibility of the utilization of on-board recorders, and 3 the evaluation of certain problems inherent in the dynamic crash testing of full-scale helicopter and VTOL aircraft were presented in an earlier preliminary report AvCIR-1-TR 124.

Subject Categories:

  • Military Aircraft Operations
  • Helicopters

Distribution Statement:

APPROVED FOR PUBLIC RELEASE