Civil Engineering Reference
In-Depth Information
Fig. 7.7
Shock load-vs.-time curve for the impact of a Phantom II aircraft on the steel-reinforced
concrete containment of a reactor building [
10
,
32
]
Mass: 20 t
Region of impact: 7 m²
Impact velocity:
215 m/s
Mass: 20 t
Region of impact: 7 m²
Impact velocity: 215 m/s
a
= 30°
Vertical
Response Rz
Vertical
Response Rz
Horizontal response Ry
Time, ms
Time, ms
Fig. 7.8
Shock load-vs.-time-diagrams for a Phantom II aircraft according to models by Riera
[
36
,
37
] and Drittler et al. [
32
-
34
]
Rokkasho-mura against crashes of Phantom military aircraft stationed at a
U.S. airfield nearby. The experiment was run to determine the shock load-vs.-time
curve produced by the impact on a rigid concrete block. In addition, the burst
characteristics of the aircraft and the dispersion of its fuel were to be determined
(replaced by water in the test).
The Phantom II, with an impact weight of roughly 20 ton, was accelerated to
215 m/s on a straight path by a two-stage rocket propulsion system. It hit a block of
steel-reinforced concrete (7
3.66 m) which, being supported on air bearings,
was moveable nearly without any friction. Acceleration sensors installed along the
body of the Phantom allowed the speed reduction of the aircraft during the impact
to be determined. Accelerations and displacements were measured on the concrete
block. The behavior of the engine was studied by high-speed photography. Fig-
ure
7.9
shows the Phantom II hitting the target; small parts of the wings were
sheared off while the other parts of the aircraft were destroyed completely (the body
disintegrated). The water simulating fuel was distributed over only a small area.
The surface of the concrete block was damaged very little. Roughly 15 cm of
concrete were broken out of the surface of the concrete block as a result of the
impact of the engine shaft [
38
-
40
].
7
