AIA/NAS 1718-2013 pdf download RELIABILITY DEMONSTRATION OF SOLID PROPELLANT ROCKET MOTORS .
Purpose
The standard specifies reliability estimation and demonstrationguidelines for solid rocket motors.
Application
The general requirements and reliability demonstration techniquesdescribed herein should be the principal basis for estimating solid rocketmotor reliability. Specific demonstration requirements may be included inthe request for proposal, work statement, or other contractual document.ASan option of the procuring activity, a specific demonstration plan for theproposed system may be prepared by the contractor as part of the reliabilityprogram plan.
This standard applies primarily to large solid rocket motorsIt may be adapted for other applications as an option of the contractor andprocuring activity.
REFERENCED DOCUMENTS
Appendix l herein lists several useful references.The currentissues of the following documents form a part of this standard practice tothe extent specified herein:
Governmental
MIL-STD-721，Definition of Effectiveness Terms
Non-Governmental
References No.l and No.13 listed in Appendix l herein.
DEFINITIONS
The definitions of MIL-STD-721 apply.
GENERAL REOUIREMENTS
Motor Demonstration
The reliability demonstration methods outlined herein encompassthe use oftest data from the following typical sources:
a.Development and continuing development tests.Preliminary flight rating tests (PFRT).b
c.Qualification tests.
d.Quality assurance tests.
e.Flight tests.
f.Applicable field and storage tests.
g.Applicable tests from other programs .
Principal Activities
Development of a solid rocket motor reliability demonstrationprogram involves four major activities.
Determining the number or subsystems compos ition.8.
Establish a declaration policy.
Establishing criteria and evaluating the successc.
or failure of all tests.
Selecting an appropriate reliability estimationd.
technique for comparison with requirements.
Subsystem Selection
The motor may be subdivided into parts, referred to as sub-systems .Determining applicability and scoring test results by subsystemsnormally provides a larger equivalent sample population than would other-wise result， The number of subsystems should be based on the functionalindependence of subassemblies, The number should be minimized due to performance interactions when subsystems are not entirely independent.Atypical solid rocket motor subsystem classification for reliability demon-stration purposes appears as follows:
Ignition subsystem (includes arming device and igniter)8.b。Loaded case subsystem (includes case, liner, insulationand propellant).
Nozzle and TVC subsystem (includes nozzle, injectantc.assembly or actuation unit, and pressurization subsystemor power supply).
Other subsystem selection may be used upon mutual agreementbetween the contractor and procuring activity.