Accession Number:

AD0613300

Title:

THEORETICAL DETERMINATION OF CRASH LOADS FOR A LOCKHEED 1649 AIRCRAFT IN A CRASH TEST PROGRAM

Descriptive Note:

Technical rept.

Corporate Author:

BOEING CO RENTON WA AIRPLANE DIV

Report Date:

1964-07-01

Pagination or Media Count:

64.0

Abstract:

Acceleration time histories in directions normal and parallel to the fuselage cabin floor are given at three positions along the length of the fuselage for impact velocities of 140, 160, 180, and 200 feet per second. It is concluded that during the initial impact at 180 feet per second, peak normal accelerations of 11, 0, and -3 times that of gravity Gs will be developed 0. 03 seconds after impact at Body Stations 180, 682, and 1176. Maximum normal and longitudinal accelerations during the 6 degree ramp crash will occur at 0.24 seconds. Maximum normal accelerations at Body Stations 180, 682, and 1176 will be -17, 8, and 35 Gs respectively. Maximum longitudinal accelerations will be 4 Gs. It is further concluded that the nose of the airplane will bend upwards 10 inches relative to the center section of the fuselage 0.14 seconds after impact. This deflection will probably be of sufficient magnitude to exceed the ultimate strength of the fuselage above the cabin floor.

Subject Categories:

  • Military Aircraft Operations
  • Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE