MIL-STD-1798C
5.3 (Task lll) Design Analyses and Development Tests.
Analyses and development tests shall be performed to support the Design Control Activity and to verify that the specific performance, function, and integrity requirements have been met. The early definition of design objectives; the specification of subsystem design environments and usage; the identification of critical design failure modes; component and part functional criticality; and recommendations for materials selection and characterization, design analysis, development testing, and manufacturing process controls are accomplished as part of Task III.
These tasks should be conducted using methods which have been verified on prior Programs or which will be verified during system/component development. Development analysis and test shall address all appropriate natural and induced environmental conditions to which the equipment will be exposed in service.
5.3.1 Manufacturing and quality assessment.
An assessment of the manufacturing and quality system shall be conducted to ensure the OEM manufacturing and quality systems can consistently produce components able to meet all specification requirements throughout the ground and flight operation. The assessment shall also include inspection capability and repairability as required to be consistent with damage- tolerance actions. The timing of this assessment should be after the Program Office is satisfied the specific component design is stable.
5.3.2 Design analyses.
Design analyses shall include, but are not limited to, the elements detailed in the subparagraphs which follow.
5.3.2.1 Load analyses.
These analyses are used to define the magnitude and distribution of significant static, dynamic, and repeated loads which the equipment encounters when operated within the envelope established by the specific system requirements and detailed design criteria. This analysis involves identifying the internal and external operating load sources, as well as inertial effects imposed by accelerations, decelerations, angular velocities, external air loads, and gyroscopic moments. Where applicable, the loads analysis shall include the effects of temperature and system installation (e.g., dynamic response and deformation of the airframe or support structure). Repeated load sources imposed by the airframe shall be included, as applicable. When applicable, these analyses shall address flight and ground operation, as well as maintenance, storage, and transportation.
5.3.2.2 Design stress/environment spectra development.
This analysis shall be used to develop the design stress/environment spectra for individual system elements. The design stress/environment spectra shall characterize the repeated operating loads, pressures, thermal cycles, vibration, acoustics, and chemicals in a format which accounts for the primary functional duty cycle and usage of the equipment. The intent is to develop a spectrum that characterizes the significant usage events which may affect primary failure modes (e.g., fatigue, cracking, stress, corrosion, cracking, wear, etc.) which the system elements will experience based on the design service life and usage. This spectra shall be used to assist in material selection, component sizing, and performance/life verification.
5.3.2.3 Performance and function sizing analyses.
Analyses shall be conducted to support sizing, configuration development, and to verify specific performance requirements.
33
For Parts Inquires call Parts Hangar, Inc (727) 493-0744
© Copyright 2015 Integrated Publishing, Inc.
A Service Disabled Veteran Owned Small Business