MIL-STD-2131A

LAUNCHER, EJECTION, GUIDED MISSILE AIRCRAFT, GENERAL DESIGN CRITERIA FOR

contributor author	NAVY - AS - Naval Air Systems Command
date accessioned	2017-09-04T15:49:16Z
date available	2017-09-04T15:49:16Z
date copyright	33588
date issued	1991
identifier other	QDKWDAAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/52202
description abstract	The purpose of this document is to provide guidelines for establishing general criteria for the design, development, construction, maintenance and testing of an ejection launcher. This standard is applicable to all missile suspension systems. However, it is assumed that all new missile developments will employ a 14-inch or 30-inch missile suspension system as defined in MIL-A-8591. The launcher shall provide for the carriage, service and power ejection release of an airborne guided missile with either a nuclear or conventional warhead from tactical aircraft in flight. Intended Use: The intended use of this standard is to provide guidelines for establishing criteria for the design, development, construction, maintenance, and testing of an ejection launcher.
language	English
title	MIL-STD-2131A	num
title	LAUNCHER, EJECTION, GUIDED MISSILE AIRCRAFT, GENERAL DESIGN CRITERIA FOR	en
type	standard
page	40
status	Active
tree	NAVY - AS - Naval Air Systems Command:;1991
contenttype	fulltext
subject keywords	Captive flight loads
subject keywords	Clearances
subject keywords	Interfaces