Engineering Design Handbook - Helicopter Engineering, Part by ARMY MATERIEL COMMAND ALEXANDRIA VA


This 1976 quantity, the second one element of a three-part sequence, is meant to set forth particular layout criteria for military helicopters, to set up qualification standards, and to supply technical assistance to helicopter designers in either the and in the military. This guide offers with the evolution of the automobile from an authorized initial layout configuration. due to this part of the advance, the layout is defined in adequate aspect to allow building and qualification of the helicopter as being in compliance with all appropriate necessities, together with the licensed approach specification. layout requisites for all car subsystems are incorporated.

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Extra info for Engineering Design Handbook - Helicopter Engineering, Part Two - Detail Design:

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Thus, A represents aluminum, F rare earth, H thorium, K zirconium, L lithium, M manganese, Q silver, T tin, and Z zinc. By this designation, AZ91C is identified as an alloy of magnesium containing 9% 2-5 aluininutn. 1 % zinc. and having ;I "C" variation. The heiit-treat and temper designations for magtiesiutii virtually are identical to those for aluminum. The temper designations used are those in ASTM 8206. There are four groups of magnesium casting alloys. The Mg-A and Mg-Z binary systems ;ire designed for use at temperatures below 300°1-'and are of loirer cost.

17-20 17-20 17-22 17-22 17-23 17-23 APPENDIX A EXAMPLE OF A PRELIMINARY HEATING, COOLING, AND VENTILATION ANALYSIS HEATING A N D VENTILATION ANALYSIS .................. A- 1 A- 1 DESIGN REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . 1 DESIGN ASSUMPTIONS . . . . . . . . . . . . . . . . . . . . . . . 2 HEAT LOSSES . . . . . . . . . . . . . . . . . .

The metal can be press- or hammer-forged at temperatures ranging from 2300" down to 1500°F. Forging is completed at relatively low temperatures. The objective is to refine the grain structure, thereby enhancing the strength and toughness of the steel. A minimum reduction of 25% in thickness during the final forging cycle is recommended t o produce optimum mechanical properties in the finished product. Hot bending, hot drawing, and hot spinning are accomplished at I500"-1800"t. Cold-forming operations are performed on the annealed material.

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