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Journal Article

Numerical Analysis of Blast Protection Improvement of an Armored Vehicle Cab by Composite Armors and Anti-Shock Seats

Abstract The objective of this article is to evaluate the effects of different blast protective modules to military vehicle structures and occupants. The dynamic responses of the V-shape integral basic armor, the add-on honeycomb sandwich structure module, and the anti-shock seat-dummy system were simulated and analyzed. The improvements of occupant survivability by different protective modules were compared using occupant injury criteria. The integral armored cab can maintain the integrity of the cab body structure. The add-on honeycomb sandwich armor reduces the peak structural deformation and velocity of the cab floor by 34.9% and 47.4%, respectively, compared with the cab with integral armors only. The integral armored cab with the anti-shock seat or the honeycomb sandwich structures reduces the occupant shock responses below the injury criteria. For different blast threat intensities, the selection of appropriate protective modules can meet protection requirements.

Temperature Measuring Devices Nomenclature

This SAE Aerospace Recommended Practice (ARP) defines the nomenclature of temperature measuring devices. General temperature measurement related terms are defined first, followed by nomenclature specific to temperature measuring devices, particularly thermocouples.

Emergency Warning Device and Emergency Warning Device Protective Container

This SAE Standard provides test procedures and performance requirements for emergency warning devices (triangular shape), without self-contained energy sources, that are designed to be carried in motor vehicles and used to warn approaching traffic of the presence of a stopped vehicle, except for devices designed to be permanently affixed to the vehicle, and provides test procedures and performance requirements for protective containers for such emergency warning devices.
Technical Paper

Transport Airplane Fuselage Section Longitudinal Impact Test

A transport airplane fuselage section with a full complement of cabin seats and anthropomorphic test dummies was longitudinally impact tested at a condition that approached the ultimate strength of the airframe protective shell structure. Airframe structural responses, seat/floor reaction loads, and the interactive effects of secondary impacts between multiple cabin seat rows were investigated. The scope and conduct of the test are presented together with some preliminary analyses of the test results.
Technical Paper

Crash Impact Characteristics of Helicopter Composite Structures

This paper describes the results of a research program to investigate the crash impact behavior of helicopter composite structures designed to meet the U.S. Army’s crashworthiness requirements specified in MIL-STD-1290. The program included design, fabrication, and crash testing of two full-scale composite helicopter cabin sections. The drop test conditions for the two cabin sections were representative of the 42 ft/s vertical crash impact velocity requirement specified in MIL-STD-1290 assuming the landing gear had slowed the aircraft from 42 ft/s to 30 ft/s prior to fuselage contact. Roll attitudes of 0° (flat) and 20° were used in the two cabin drop tests.

Operator Enclosure Pressurization System Test Procedure

This SAE Recommended Practice establishes a uniform test procedure for evaluating performance of operator enclosure pressurization systems for construction, general-purpose industrial, agricultural, forestry, and specialized mining machinery as categorized in SAE J1116 for off-road, self-propelled work machines. The purpose of this document is to outline a procedure which will provide a uniform measurement of operator enclosure pressurization.