FRACTURE CONTROL REQUIREMENTS FOR COMPOSITE AND BONDED VEHICLE AND PAYLOAD STRUCTURES
|Publication Date:||29 June 2006|
This document provides the fracture control requirements for composite and bonded structures used in the construction of MSFC manned vehicle and payload hardware. The scope includes manned launch, retrieval, transfer, and landing vehicles, space habitats, and payloads or experiments that are launched, retrieved, stored, or operated during any portion of a manned spaceflight mission.
Fiber reinforced polymer matrix composites, sandwich construction (bonded metallic and nonmetallic), and bonds between metallic or composite parts fall within the scope of this document.
Metal and ceramic matrix structures, foam, flexible inflatable structures, liquid-fueled rocket engines, and solid propellants are specifically excluded. Also, fracture control of metallic parts/structures are not specifically covered by this document, but where metallics are used in conjunction with composites or bonds, all the provisions of this document shall be met.
The purpose of this document is to provide a minimum set of fracture control requirements to be used in designing and assessing composite and bonded structures.
This document applies to in-house and contract activities and should be cited in program and contract documents as a technical requirement. All prime contractors and subcontractors performing activities to the requirements of this document shall be on-site audited and approved by NASA as to their quality management system and process controls as specified herein. With the prior approval of the MSFC Fracture Control Board (FCB), individual provisions of this document may be tailored based on application specific experience and sufficient technical rationale.
This document is applicable to all new, used, or repaired flight hardware that is within its scope.