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NASA (General)
NASA Commissioned Guideline Report on the Use of COTS Plastic Microcircuits in NASA Space Flight Hardware (DRAFT)
NASA Commissioned Guideline Report on the Use of COTS Plastic Microcircuits in NASA Space Flight Hardware (DRAFT - SEPT. 30, 2004). Commercial Off-The-Shelf Plastic Encapsulated Microcircuits (COTS PEMs) are now being evaluated by the US DOD agencies, European Space Agency, and the National Aeronautical Space Agency, among others. For many years these agencies would not use COTS PEMs in their military and space hardware because of their reliability risk and even safety concerns. Today this is all changing and these same agencies are attempting to find ways to reduce the risk and at the same time reduce some of the development costs. The main drivers to use COTS are the lower procurement cost, more performance and functionality, and reduced size and weight. To this end NASA has also embarked on an ambitious path to gather real time data and evidence on COTS PEMs that will lead to more understanding and knowledge of COTS quality and reliability. NASA has spent three years of planning, testing, and analyzing COTS PEMs, under the NEPP Program, and has identified many of the quality and reliability risks associated with COTS PEMs if used in a demanding reliability application and in a radiation hostile environment. The nature of COTS is, of course, ongoing change to meet the needs of a demanding and competitive commercial market. Therefore, to stay abreast, the work must continue by NASA to refine all the information gathered and add new information as it becomes available. This NASA guideline and report shares NASA’s recent experiences with COTS PEMs reliability (non-radiation), gives examples of risk based on the data gathered and analysis, and makes recommendations that NASA believes will help steer the NASA design community and Project Managers to use COTS PEMs with confidence and minimum risk.
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NASA Commissioned Guideline Report on the Use of COTS Plastic Microcircuits in NASA Space Flight Hardware (DRAFT - SEPT. 30, 2004). Commercial Off-The-Shelf Plastic Encapsulated Microcircuits (COTS PEMs) are now being evaluated by the US DOD agencies, European Space Agency, and the National Aeronautical Space Agency, among others. For many years these agencies would not use COTS PEMs in their military and space hardware because of their reliability risk and even safety concerns. Today this is all changing and these same agencies are attempting to find ways to reduce the risk and at the same time reduce some of the development costs. The main drivers to use COTS are the lower procurement cost, more performance and functionality, and reduced size and weight. To this end NASA has also embarked on an ambitious path to gather real time data and evidence on COTS PEMs that will lead to more understanding and knowledge of COTS quality and reliability. NASA has spent three years of planning, testing, and analyzing COTS PEMs, under the NEPP Program, and has identified many of the quality and reliability risks associated with COTS PEMs if used in a demanding reliability application and in a radiation hostile environment. The nature of COTS is, of course, ongoing change to meet the needs of a demanding and competitive commercial market. Therefore, to stay abreast, the work must continue by NASA to refine all the information gathered and add new information as it becomes available. This NASA guideline and report shares NASA’s recent experiences with COTS PEMs reliability (non-radiation), gives examples of risk based on the data gathered and analysis, and makes recommendations that NASA believes will help steer the NASA design community and Project Managers to use COTS PEMs with confidence and minimum risk.
NASA DC-8 AIRBORNE LABORATORY EXPERIMENTER HANDBOOK (JUNE 2002)
DC-8 AIRBORNE LABORATORY EXPERIMENTER HANDBOOK., Since August 1987, NASA has been operating A Douglas DC-8-72 Aircraft (NASA 817) for research activities in earth, atmospheric, and space sciences. This aircraft, extensively modified as a flying laboratory, is based at Dryden Flight Research Center (DFRC), Edwards, California. It is operated for the benefit of researchers whose proposals have been previously approved by NASA Headquarters. Airborne laboratory flights may be operated out of DFRC or from deployment sites worldwide, according to the research requirements. The purpose of this handbook is to acquaint prospective DC-8 researchers with the aircraft and its capabilities. The handbook also contains procedures for obtaining approval to fly experiments, outlines requirements for equipment design and installation, and identifies the personnel and facilities that are available at DFRC for supporting research activities in the DC-8 airborne laboratory. This handbook is managed and revised from time to time by the DFRC Airborne Science Directorate. Therefore, before arranging for experiments it is advisable to review the web site listed below, then contact the DFRC Airborne Science Directorate or your assigned mission manager for a current issue. For information about the overall DFRC Airborne Science Program, including aircraft schedules and Airborne Science flight request procedures, and for an electronic version of this and other experimenter handbooks, look on the World Wide Web at: http://www.dfrc.nasa.gov/airsci/.
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DC-8 AIRBORNE LABORATORY EXPERIMENTER HANDBOOK., Since August 1987, NASA has been operating A Douglas DC-8-72 Aircraft (NASA 817) for research activities in earth, atmospheric, and space sciences. This aircraft, extensively modified as a flying laboratory, is based at Dryden Flight Research Center (DFRC), Edwards, California. It is operated for the benefit of researchers whose proposals have been previously approved by NASA Headquarters. Airborne laboratory flights may be operated out of DFRC or from deployment sites worldwide, according to the research requirements. The purpose of this handbook is to acquaint prospective DC-8 researchers with the aircraft and its capabilities. The handbook also contains procedures for obtaining approval to fly experiments, outlines requirements for equipment design and installation, and identifies the personnel and facilities that are available at DFRC for supporting research activities in the DC-8 airborne laboratory. This handbook is managed and revised from time to time by the DFRC Airborne Science Directorate. Therefore, before arranging for experiments it is advisable to review the web site listed below, then contact the DFRC Airborne Science Directorate or your assigned mission manager for a current issue. For information about the overall DFRC Airborne Science Program, including aircraft schedules and Airborne Science flight request procedures, and for an electronic version of this and other experimenter handbooks, look on the World Wide Web at: http://www.dfrc.nasa.gov/airsci/.
NASA ER-2 AIRBORNE LABORATORY EXPERIMENTER HANDBOOK (AUG 2002)
NASA ER-2 AIRBORNE LABORATORY EXPERIMENTER HANDBOOK (AUG 2002)., The purpose of this handbook is to acquaint prospective ER-2 researchers with the aircraft and its capabilities. The contents of this book should be considered guidelines, and Lockheed or NASA can provide additional detail or clarification on any area. The handbook also contains procedures for obtaining approval to fly experiments, outlines requirements for equipment design and installation, and identifies the personnel and facilities that are available at DFRC for supporting research activities. This handbook is revised from time to time. Therefore, before arranging for experiments it is advisable to contact the Dryden Airborne Science Directorate for a current issue. For information about the overall Dryden Airborne Science Program, including aircraft schedules and Airborne Science Flight Request procedures, and for an electronic version of this and other experimenter handbooks, look on the World Wide Web at: http://www.dfrc.nasa.gov/airsci/.
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NASA ER-2 AIRBORNE LABORATORY EXPERIMENTER HANDBOOK (AUG 2002)., The purpose of this handbook is to acquaint prospective ER-2 researchers with the aircraft and its capabilities. The contents of this book should be considered guidelines, and Lockheed or NASA can provide additional detail or clarification on any area. The handbook also contains procedures for obtaining approval to fly experiments, outlines requirements for equipment design and installation, and identifies the personnel and facilities that are available at DFRC for supporting research activities. This handbook is revised from time to time. Therefore, before arranging for experiments it is advisable to contact the Dryden Airborne Science Directorate for a current issue. For information about the overall Dryden Airborne Science Program, including aircraft schedules and Airborne Science Flight Request procedures, and for an electronic version of this and other experimenter handbooks, look on the World Wide Web at: http://www.dfrc.nasa.gov/airsci/.
NASA Fault Tree Handbook with Aerospace Applications
Fault Tree Handbook with Aerospace Applications. NASA Project Coordinators: Dr. Michael Stamatelatos, NASA Headquarters Office of Safety and Mission Assurance Mr. J. Caraballo, NASA Langley Research Center Authors: NASA Dr. Michael Stamatelatos, NASA HQ, OSMA Lead Author: Dr. William Vesely, SAIC Contributing Authors (listed in alphabetic order): Dr. Joanne Dugan, University of Virginia Mr. Joseph Fragola, SAIC Mr. Joseph Minarick III, SAIC Mr. Jan Railsback, NASA JSC.
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1.1
Fault Tree Handbook with Aerospace Applications. NASA Project Coordinators: Dr. Michael Stamatelatos, NASA Headquarters Office of Safety and Mission Assurance Mr. J. Caraballo, NASA Langley Research Center Authors: NASA Dr. Michael Stamatelatos, NASA HQ, OSMA Lead Author: Dr. William Vesely, SAIC Contributing Authors (listed in alphabetic order): Dr. Joanne Dugan, University of Virginia Mr. Joseph Fragola, SAIC Mr. Joseph Minarick III, SAIC Mr. Jan Railsback, NASA JSC.
NASA Metrology - Calibration and Measurement Processes Guidelines
This publication is intended to assist in meeting the metrology requirements for National Aeronautics and Space Administration Quality Assurance handbooks by system cord ractors.
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This publication is intended to assist in meeting the metrology requirements for National Aeronautics and Space Administration Quality Assurance handbooks by system cord ractors.
NASA Mission Design Process: An Engineering Guide to the Conceptual Design, Mission Analysis, and Definition Phases
NASA Mission Design Process: An Engineering Guide to the Conceptual Design, Mission Analysis, and Definition Phases. This guide is to be used as a starting point for developing and executing a plan for conducting a mission design study, i.e., defining the mission and then designing the system(s), required to conduct the specific mission.
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NASA Mission Design Process: An Engineering Guide to the Conceptual Design, Mission Analysis, and Definition Phases. This guide is to be used as a starting point for developing and executing a plan for conducting a mission design study, i.e., defining the mission and then designing the system(s), required to conduct the specific mission.
NASA Probabilistic Risk Assessment Procedures Guide for NASA Managers and Practitioners
NASA Probabilistic Risk Assessment (PRA) Procedures Guide for NASA Managers and Practitioners. This PRA Procedures Guide is neither a textbook nor a sourcebook of PRA methods and techniques for the subject matter. It is the recommended approach and procedures, based on the experience of the authors, of how PRA should be performed for aerospace applications. It therefore serves two purposes: 1. To complement the training material taught in the PRA course for practitioners and, together with the Fault Tree Handbook, to provide PRA methodology documentation. 2. To assist aerospace PRA practitioners in selecting an analysis approach that is best suited for their applications.
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1.1
NASA Probabilistic Risk Assessment (PRA) Procedures Guide for NASA Managers and Practitioners. This PRA Procedures Guide is neither a textbook nor a sourcebook of PRA methods and techniques for the subject matter. It is the recommended approach and procedures, based on the experience of the authors, of how PRA should be performed for aerospace applications. It therefore serves two purposes: 1. To complement the training material taught in the PRA course for practitioners and, together with the Fault Tree Handbook, to provide PRA methodology documentation. 2. To assist aerospace PRA practitioners in selecting an analysis approach that is best suited for their applications.
NASA Program/Project Life Cycle Process Flow
NASA Program/Project Life Cycle Process Flow. A Wall Chart that provides a graphical, time-phased overview of the NASA Mission Design Process in terms of Conceptual Design, Mission, Analysis, and Definition Phases
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NASA Program/Project Life Cycle Process Flow. A Wall Chart that provides a graphical, time-phased overview of the NASA Mission Design Process in terms of Conceptual Design, Mission, Analysis, and Definition Phases
NASA Reliability Centered Maintenance Guide For Facilities and Collateral Equipment
Reliability Centered Maintenance (RCM) is the process that is used to determine the most effective approach to maintenance. It involves identifying actions that, when taken, will reduce the probability of failure and which are the most cost effective. It seeks the optimal mix of Condition-Based Actions, other Time- or Cycle-Based actions, or a Run-to-Failure approach, as shown in Figure 1-1. The principal features of each strategy are shown below their block in Figure 1-1. RCM is an ongoing process that gathers data from operating systems performance and uses this data to improve design and future maintenance. These maintenance strategies, rather than being applied independently, are integrated to take advantage of their respective strengths in order to optimize facility and equipment operability and efficiency while minimizing life-cycle costs. The elements of RCM are developed in Chapter 2 and the maintenance strategies are defined and discussed in Chapter 3. Reliability Centered Maintenance
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Reliability Centered Maintenance (RCM) is the process that is used to determine the most effective approach to maintenance. It involves identifying actions that, when taken, will reduce the probability of failure and which are the most cost effective. It seeks the optimal mix of Condition-Based Actions, other Time- or Cycle-Based actions, or a Run-to-Failure approach, as shown in Figure 1-1. The principal features of each strategy are shown below their block in Figure 1-1. RCM is an ongoing process that gathers data from operating systems performance and uses this data to improve design and future maintenance. These maintenance strategies, rather than being applied independently, are integrated to take advantage of their respective strengths in order to optimize facility and equipment operability and efficiency while minimizing life-cycle costs. The elements of RCM are developed in Chapter 2 and the maintenance strategies are defined and discussed in Chapter 3. Reliability Centered Maintenance
NASA SCHEDULE MANAGEMENT HANDBOOK (14 OCT 2006) - DRAFT
NASA SCHEDULE MANAGEMENT HANDBOOK (14 OCT 2006) - DRAFT. The purpose of schedule management is to provide the framework for time-phasing, coordination, and communicating the necessary tasks within a work effort. The intent is to improve schedule management by providing recommended concepts, processes, and techniques used within the Agency and private industry. The intended function of this handbook is two-fold: first, to provide guidance for meeting the scheduling requirements contained in NPR 7120.5; and second, to describe the schedule management approach and the recommended best practices for carrying out this project control function. The handbook will be updated as needed, to enhance efficient and effective schedule management across the Agency. The guidance provided within this document is applicable to contractors, international partners, academic institutions, public and private research laboratories, and internal Agency organizations involved in support of carrying out NASA programs and projects. It is acknowledged that most, if not all, the above external organizations will have their own internal schedule management documents. Issues that arise from conflicting schedule guidance will be resolved on a case by case basis as contracts and partnering relationships are established.
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NASA SCHEDULE MANAGEMENT HANDBOOK (14 OCT 2006) - DRAFT. The purpose of schedule management is to provide the framework for time-phasing, coordination, and communicating the necessary tasks within a work effort. The intent is to improve schedule management by providing recommended concepts, processes, and techniques used within the Agency and private industry. The intended function of this handbook is two-fold: first, to provide guidance for meeting the scheduling requirements contained in NPR 7120.5; and second, to describe the schedule management approach and the recommended best practices for carrying out this project control function. The handbook will be updated as needed, to enhance efficient and effective schedule management across the Agency. The guidance provided within this document is applicable to contractors, international partners, academic institutions, public and private research laboratories, and internal Agency organizations involved in support of carrying out NASA programs and projects. It is acknowledged that most, if not all, the above external organizations will have their own internal schedule management documents. Issues that arise from conflicting schedule guidance will be resolved on a case by case basis as contracts and partnering relationships are established.
NASA STYLE - FULL GUIDE (NOVEMBER 2006)
NASA STYLE - FULL GUIDE (NOVEMBER 2006). The goal of this Style Guide is to establish a clear, consistent and unique visual identity for NASA. The visual identity builds on NASA’s brand by combining the most recognized existing elements—our name and insignia—with progressive elements and messages. Uniform graphic elements and messages provide the framework for establishing a visual identity. In turn, designers can use this architecture to create materials that enhance public knowledge of NASA’s work. Issued under the authority of 14 CFR 1221, this guide sets out the prime elements needed to produce approved NASA communications material. The fi rst section defi nes the basic elements of the NASA visual identity and discusses its usage. The remainder of the guide explores how to combine and incorporate the basic elements into the agency’s print, Web and media communications.
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NASA STYLE - FULL GUIDE (NOVEMBER 2006). The goal of this Style Guide is to establish a clear, consistent and unique visual identity for NASA. The visual identity builds on NASA’s brand by combining the most recognized existing elements—our name and insignia—with progressive elements and messages. Uniform graphic elements and messages provide the framework for establishing a visual identity. In turn, designers can use this architecture to create materials that enhance public knowledge of NASA’s work. Issued under the authority of 14 CFR 1221, this guide sets out the prime elements needed to produce approved NASA communications material. The fi rst section defi nes the basic elements of the NASA visual identity and discusses its usage. The remainder of the guide explores how to combine and incorporate the basic elements into the agency’s print, Web and media communications.
NASA Work Breakdown Structure Reference Guide (MAY 1994)
NASA Work Breakdown Structure Reference Guide (MAY 1994). The work breakdown structure (WBS) is an effective tool in managing NASA programs and projects. It assists both NASA and contractors in fulfilling management responsibilities. In accordance with NASA Handbook 7120.5, Management of Major System Programs and Projects, a WBS is mandatory for major system acquisitions and major projects, and will be used for other projects when practical. A WBS is required when performance measurement is applied to a contract. The purpose of this WBS reference guide is to support the completion of program and project objectives within budget and schedule constraints. This reference guide can be used for various work efforts including research, development, construction, test and evaluation, and operations. The products of these work efforts may be hardware, software, data, or service elements (alone or in combination).
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NASA Work Breakdown Structure Reference Guide (MAY 1994). The work breakdown structure (WBS) is an effective tool in managing NASA programs and projects. It assists both NASA and contractors in fulfilling management responsibilities. In accordance with NASA Handbook 7120.5, Management of Major System Programs and Projects, a WBS is mandatory for major system acquisitions and major projects, and will be used for other projects when practical. A WBS is required when performance measurement is applied to a contract. The purpose of this WBS reference guide is to support the completion of program and project objectives within budget and schedule constraints. This reference guide can be used for various work efforts including research, development, construction, test and evaluation, and operations. The products of these work efforts may be hardware, software, data, or service elements (alone or in combination).
NASA-GB-001-94, Software Measurement Guidebook
NASA-GB-001-94, Software Measurement Guidebook. This document is a product of the NASA Software Program, an Agency-wide program to promote continual improvement of software engineering within NASA. The goals and strategies for this program are documented in the NASA Software Strategic Plan, July 13, 1995. Additional information is available from the NASA Software IV&V facility on the World Wide Web at site http://www.ivv.nasa.gov/
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NASA-GB-001-94
NASA-GB-001-94, Software Measurement Guidebook. This document is a product of the NASA Software Program, an Agency-wide program to promote continual improvement of software engineering within NASA. The goals and strategies for this program are documented in the NASA Software Strategic Plan, July 13, 1995. Additional information is available from the NASA Software IV&V facility on the World Wide Web at site http://www.ivv.nasa.gov/
NASA-GB-1740.13, SOFTWARE SAFETY GUIDEBOOK
This NASA Software Safety Guidebook was prepared by the NASA Glenn Research Center, Office of Safety Assurance Technologies, under a Center Software Initiative Proposal (CSIP) task for the National Aeronautics and Space (NASA NASA-GB-1740.13, SOFTWARE SAFETY GUIDEBOOK. The NASA Software Safety Standard NASA-STD-8719.13A [1] prepared by NASA HQ addresses the “who, what, when and why” of Software Safety Analyses. This Software Safety Guidebook addresses the “how to”.
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NASA GB-1740.13
This NASA Software Safety Guidebook was prepared by the NASA Glenn Research Center, Office of Safety Assurance Technologies, under a Center Software Initiative Proposal (CSIP) task for the National Aeronautics and Space (NASA NASA-GB-1740.13, SOFTWARE SAFETY GUIDEBOOK. The NASA Software Safety Standard NASA-STD-8719.13A [1] prepared by NASA HQ addresses the “who, what, when and why” of Software Safety Analyses. This Software Safety Guidebook addresses the “how to”.
NASA-GB-8719.13, NASA SOFTWARE SAFETY GUIDEBOOK
NASA-GB-8719.13, NASA SOFTWARE SAFETY GUIDE. This document has been issued to make available to software safety practitioners a guidebook for assessing software systems for software’s contribution to safety and techniques for analyzing and applying appropriate safety techniques and methods to software. Software developers and software safety engineers are the primary focus; however, software assurance (SA) engineers, project managers, system engineers, and system safety engineers will also find this guidebook useful. This guidebook cancels NASA-GB-1740.13-96, NASA Guidebook for Safety Critical Software Analysis and Development.
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NASA-GB-8719.13
NASA-GB-8719.13, NASA SOFTWARE SAFETY GUIDE. This document has been issued to make available to software safety practitioners a guidebook for assessing software systems for software’s contribution to safety and techniques for analyzing and applying appropriate safety techniques and methods to software. Software developers and software safety engineers are the primary focus; however, software assurance (SA) engineers, project managers, system engineers, and system safety engineers will also find this guidebook useful. This guidebook cancels NASA-GB-1740.13-96, NASA Guidebook for Safety Critical Software Analysis and Development.
NASA-GB-A302, SOFTWARE FORMAL INSPECTIONS GUIDEBOOK
SOFTWARE FORMAL INSPECTIONS GUIDEBOOK. The Software Formal Inspections Guidebook is designed to support the inspection process of software developed by and forNASA. This document provides information on how to implement a recommended and proven method for conducting formal inspections of NASA software. This Guidebook is a companion document to NASA Standard 2202-93, Software Formal Inspections Standard, approved April 1993, which provides the rules, procedures, and specific requirements for conducting software formal inspections. Application of the Formal Inspections Standard is optional to NASA program or project management. In cases where program or project management decide to use the formal inspections method, this Guidebook provides additional information on how to establish and implement the process.
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NASA-GB-A302
SOFTWARE FORMAL INSPECTIONS GUIDEBOOK. The Software Formal Inspections Guidebook is designed to support the inspection process of software developed by and forNASA. This document provides information on how to implement a recommended and proven method for conducting formal inspections of NASA software. This Guidebook is a companion document to NASA Standard 2202-93, Software Formal Inspections Standard, approved April 1993, which provides the rules, procedures, and specific requirements for conducting software formal inspections. Application of the Formal Inspections Standard is optional to NASA program or project management. In cases where program or project management decide to use the formal inspections method, this Guidebook provides additional information on how to establish and implement the process.
NASA-SPEC-5004A, WELDING OF AEROSPACE GROUND SUPPORT EQUIPMENT AND RELATED NONCONVENTIONAL STRUCTURES
NASA-SPEC-5004A, WELDING OF AEROSPACE GROUND SUPPORT EQUIPMENT AND RELATED NONCONVENTIONAL STRUCTURES. This specification was developed to establish uniform engineering practices and methods and to ensure the inclusion of essential criteria in the welding of ground support equipment (GSE) used by or for NASA. The specification was prepared by the intercenter committee on materials and processes and approved by the Engineering Management Council (EMC). This specification is applicable to GSE that supports space vehicle or payload programs or projects and to critical nonconventional facilities, where applicable. This specification establishes preferred practices for the welding of GSE used by or for NASA programs and projects. This specification is recommended for the design of nonflight hardware used to support the operations of receiving, transportation, handling, assembly, inspection, test, checkout, service, and launch of space vehicles and payloads at NASA launch, landing, or retrieval sites. These criteria and practices may be used for items used at the manufacturing, development, and test sites upstream of the launch, landing, or retrieval sites.
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NASA-SPEC-5004
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A
NASA-SPEC-5004A, WELDING OF AEROSPACE GROUND SUPPORT EQUIPMENT AND RELATED NONCONVENTIONAL STRUCTURES. This specification was developed to establish uniform engineering practices and methods and to ensure the inclusion of essential criteria in the welding of ground support equipment (GSE) used by or for NASA. The specification was prepared by the intercenter committee on materials and processes and approved by the Engineering Management Council (EMC). This specification is applicable to GSE that supports space vehicle or payload programs or projects and to critical nonconventional facilities, where applicable. This specification establishes preferred practices for the welding of GSE used by or for NASA programs and projects. This specification is recommended for the design of nonflight hardware used to support the operations of receiving, transportation, handling, assembly, inspection, test, checkout, service, and launch of space vehicles and payloads at NASA launch, landing, or retrieval sites. These criteria and practices may be used for items used at the manufacturing, development, and test sites upstream of the launch, landing, or retrieval sites.
NASA/CR 194428, A USERS MANUAL FOR DEVELOPING COST ESTIMATING RELATIONSHIPS - VOL. 1 (AUG 1996)
NASA/CR 194428, A USERS MANUAL FOR DEVELOPING COST ESTIMATING RELATIONSHIPS - VOL. 1 (AUG 1996)., This Cost Estimating Relationship(CER) development project was initiated by the National Aeronautics and Space Administration's(NASA)Lewis Research Center (LeRC)in Cleveland, Ohio. NASA sponsored the project to support on-going cost analysis activities at LeRC. The primary study focus areas are to collect pertinent cost estimating research data and to assist in the development of cost estimating relationships. Hopefully, useful planning estimate level CER's will be developed by NASA and Boeing analysts from this project data for future air-breathing aircraft propulsion systems and microgravity space systems.
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CR-19442
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NASA/CR 194428, A USERS MANUAL FOR DEVELOPING COST ESTIMATING RELATIONSHIPS - VOL. 1 (AUG 1996)., This Cost Estimating Relationship(CER) development project was initiated by the National Aeronautics and Space Administration's(NASA)Lewis Research Center (LeRC)in Cleveland, Ohio. NASA sponsored the project to support on-going cost analysis activities at LeRC. The primary study focus areas are to collect pertinent cost estimating research data and to assist in the development of cost estimating relationships. Hopefully, useful planning estimate level CER's will be developed by NASA and Boeing analysts from this project data for future air-breathing aircraft propulsion systems and microgravity space systems.
NASA/CR-2002-211839, SEE Design Guide and Requirements for Electrical Deadfacing (JUL 2002)
NASA/CR-2002-211839, Berki, J.M. and Sargent, N.B., SEE Design Guide and Requirements for Electrical Deadfacing (JUL 2002), George C. Marshall Space Flight Center , Marshall Space Flight Center, AL 35812, National Aeronautics and Space Administration, Washington, DC 20546-0001, July, 2002, pp. 72,
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CR-2002-211839
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NASA/CR-2002-211839, Berki, J.M. and Sargent, N.B., SEE Design Guide and Requirements for Electrical Deadfacing (JUL 2002), George C. Marshall Space Flight Center , Marshall Space Flight Center, AL 35812, National Aeronautics and Space Administration, Washington, DC 20546-0001, July, 2002, pp. 72,
NASA/CR-4740, CONTAMINATION CONTROL ENGINEERING DESIGN GUIDELINES (MAY 1996)
NASA/CR-4740, CONTAMINATION CONTROL ENGINEERING DESIGN GUIDELINES. This report describes work accomplished under contract NAS5-32876 from the NASA Goddard Space Flight Center as part of the NASA Space Environment Effects Program.
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CR-4740
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NASA/CR-4740, CONTAMINATION CONTROL ENGINEERING DESIGN GUIDELINES. This report describes work accomplished under contract NAS5-32876 from the NASA Goddard Space Flight Center as part of the NASA Space Environment Effects Program.
NASA/CR-4784, NASA CONTRACTOR REPORT 4784, DESIGN GUIDELINES FOR SHIELDING EFFECTIVENESS, CURRENT CARRYING CAPABILITY, AND THE ENHANCEMENT OF CONDUCTI
NASA/CR-4784, NASA CONTRACTOR REPORT 4784, DESIGN GUIDELINES FOR SHIELDING EFFECTIVENESS, CURRENT CARRYING CAPABILITY, AND THE ENHANCEMENT OF CONDUCTIVITY OF COMPOSITE MATERIALS (AUG 1997)., These guidelines address the electrical properties of composite materials which may have an effect on electromagnetic compatibility (EMC). The main topics of the guidelines include the electrical shielding, fault current return, and lightning protection capabilities of composite materials. These guidelines concentrate on the composites that are somewhat conductive but may require enhancement to be adequate for EMC purposes. These composites primarily consist of graphite reinforced polymers.
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CR-4784
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NASA/CR-4784, NASA CONTRACTOR REPORT 4784, DESIGN GUIDELINES FOR SHIELDING EFFECTIVENESS, CURRENT CARRYING CAPABILITY, AND THE ENHANCEMENT OF CONDUCTIVITY OF COMPOSITE MATERIALS (AUG 1997)., These guidelines address the electrical properties of composite materials which may have an effect on electromagnetic compatibility (EMC). The main topics of the guidelines include the electrical shielding, fault current return, and lightning protection capabilities of composite materials. These guidelines concentrate on the composites that are somewhat conductive but may require enhancement to be adequate for EMC purposes. These composites primarily consist of graphite reinforced polymers.
NASA/TM-102179, SELECTION OF WIRES AND CIRCUIT PROTECTIVE DEVICES FOR STS ORBITER VEHICLE PAYLOAD ELECTRICAL CIRCUITS
NASA TM-102179, SELECTION OF WIRES AND CIRCUIT PROTECTIVE DEVICES FOR STS ORBITER VEHICLE PAYLOAD ELECTRICAL CIRCUITS. This document has been prepared by the JSC Engineering Directorate, Orbiter Electrical Wiring and Installation Subsystem to aid in the electrical design of payloads to be carried aboard the Space Transportation System (STS) Orbiter vehicle. It will guide designers in selecting wire sizes and associated protective devices that are acceptable by JSC for Orbiter-borne payloads. Although the information presented is generally applicable to generic aerospace applications, it is limited in scope and is primarily intended to serve the purpose noted above. Therefore, only the ambient pressures and temperatures are addressed that are normally experienced by an Orbiter-borne payload during ground checkout and while inside the Orbiter payload bay. Part numbers and parameters for various protective devices in the appendix are also Orbiter-specific. If the designers choose to use other than "Orbiter-approved" parts they may easily find corresponding values for their specific device which can be substituted for values listed in the tables and used in their calculations. Many circuits and installations in a design will have more than one configuration that can fulfill all essential safety and reliability needs. This document does not establish requirements, but establishes guidelines form which deviations can be evaluated. Users will be required to identify for individual evaluation only those circuits that do not meet or that exceed the limits established in this document. The result of following this guide will be the delivery of a payload for flight in the Orbiter that will not conflict with the wiring and circuit protection requirements imposed by the Orbiter Payload Safety Panel. A design that is acceptable, based on these guidelines, must still be evaluated by the JSC Materials Branch for insulation compatibility. Data used in this document is derived from Eagle Engineering's report, "Wire Size Determination for Aerospace Applications."
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TM-102179
Rev. Num:
-
NASA TM-102179, SELECTION OF WIRES AND CIRCUIT PROTECTIVE DEVICES FOR STS ORBITER VEHICLE PAYLOAD ELECTRICAL CIRCUITS. This document has been prepared by the JSC Engineering Directorate, Orbiter Electrical Wiring and Installation Subsystem to aid in the electrical design of payloads to be carried aboard the Space Transportation System (STS) Orbiter vehicle. It will guide designers in selecting wire sizes and associated protective devices that are acceptable by JSC for Orbiter-borne payloads. Although the information presented is generally applicable to generic aerospace applications, it is limited in scope and is primarily intended to serve the purpose noted above. Therefore, only the ambient pressures and temperatures are addressed that are normally experienced by an Orbiter-borne payload during ground checkout and while inside the Orbiter payload bay. Part numbers and parameters for various protective devices in the appendix are also Orbiter-specific. If the designers choose to use other than "Orbiter-approved" parts they may easily find corresponding values for their specific device which can be substituted for values listed in the tables and used in their calculations. Many circuits and installations in a design will have more than one configuration that can fulfill all essential safety and reliability needs. This document does not establish requirements, but establishes guidelines form which deviations can be evaluated. Users will be required to identify for individual evaluation only those circuits that do not meet or that exceed the limits established in this document. The result of following this guide will be the delivery of a payload for flight in the Orbiter that will not conflict with the wiring and circuit protection requirements imposed by the Orbiter Payload Safety Panel. A design that is acceptable, based on these guidelines, must still be evaluated by the JSC Materials Branch for insulation compatibility. Data used in this document is derived from Eagle Engineering's report, "Wire Size Determination for Aerospace Applications."
NASA/TM-106313, DESIGN FOR RELIABILITY: NASA RELIABILITY PREFERRED PRACTICES FOR DESIGN AND TEST (OCT 94)
NASA/TM-106313, DESIGN FOR RELIABILITY: NASA RELIABILITY PREFERRED PRACTICES FOR DESIGN AND TEST (OCT 94)., This tutorial summarizes reliability experience from both NASA and industry and reflects engineering practices that support current and future civil space programs. These practices were collected from various NASA field centers and were reviewed by a committee of senior technical representatives from the participating centers (members are listed at the end). The material for this tutorial was taken from the publication issued by the NASA Reliability and Maintainability Steering Committee (NASA Reliability Preferred Practices for Design and Test. NASA TM-4322, 1991). Reliability must be an integral part of the systems engineering process. Although both disciplines must be weighed equally with other technical and programmatic demands, the application of sound reliability principles will be the key to the effectiveness and affordability of America's space program. Our space programs have shown that reliability efforts must focus on the design characteristics that affect the frequency of failure. Herein, we emphasize that these identified design characteristics must be controlled by applying conservative engineering principles.
Ident. Num:
TM-106313
Rev. Num:
-
NASA/TM-106313, DESIGN FOR RELIABILITY: NASA RELIABILITY PREFERRED PRACTICES FOR DESIGN AND TEST (OCT 94)., This tutorial summarizes reliability experience from both NASA and industry and reflects engineering practices that support current and future civil space programs. These practices were collected from various NASA field centers and were reviewed by a committee of senior technical representatives from the participating centers (members are listed at the end). The material for this tutorial was taken from the publication issued by the NASA Reliability and Maintainability Steering Committee (NASA Reliability Preferred Practices for Design and Test. NASA TM-4322, 1991). Reliability must be an integral part of the systems engineering process. Although both disciplines must be weighed equally with other technical and programmatic demands, the application of sound reliability principles will be the key to the effectiveness and affordability of America's space program. Our space programs have shown that reliability efforts must focus on the design characteristics that affect the frequency of failure. Herein, we emphasize that these identified design characteristics must be controlled by applying conservative engineering principles.
NASA/TM-106943 (NASA TECHNICAL MEMORANDUM 106943) PRELOADED JOINT ANALYSIS METHODOLOGY FOR SPACE FLIGHT SYSTEMS (DEC 1995)
NASA/TM-106943 (NASA TECHNICAL MEMORANDUM 106943) PRELOADED JOINT ANALYSIS METHODOLOGY FOR SPACE FLIGHT SYSTEMS (DEC 1995)., This report is a compilation of some of the most basic equations governing simple preloaded joint systems and discusses the more common modes of failure associated with such hardware. It is intended to provide the mechanical designer with the tools necessary for designing a basic bolted joint. Although the information presented is intended to aid in the engineering of space flight structures, the fundamentals are equally applicable to other forms of mechanical design.
Ident. Num:
TM-106943
Rev. Num:
-
NASA/TM-106943 (NASA TECHNICAL MEMORANDUM 106943) PRELOADED JOINT ANALYSIS METHODOLOGY FOR SPACE FLIGHT SYSTEMS (DEC 1995)., This report is a compilation of some of the most basic equations governing simple preloaded joint systems and discusses the more common modes of failure associated with such hardware. It is intended to provide the mechanical designer with the tools necessary for designing a basic bolted joint. Although the information presented is intended to aid in the engineering of space flight structures, the fundamentals are equally applicable to other forms of mechanical design.
NASA/TM-108542, TECHNICAL MEMORANDUM 108542 TESTING FOR RANDOM LIMIT LOAD VERSUS STATIC LIMIT LOAD
NASA/TM-108542, TECHNICAL MEMORANDUM 108542 TESTING FOR RANDOM LIMIT LOAD VERSUS STATIC LIMIT LOAD (SEPT 1997)., A study completed in 1993 by the Marshall Space Flight Center (MSFC) Random Loads/Criteria Issues Team concluded, after an extensive literature search, that almost no analytical or empirical documentation exists on the subject of the relationship between random limit load (stress) and static limit load (stress). The consensus of the team was that it is a complex subject and requires a carefully planned effort to produce an effective, yet practical, solution. In addition, no amount of analysis or planning will ever completely solve the problem of the dynamic-to-static limit load relationship. It is paramount that ample validation testing be accomplished so a database of hardware response can be built.
Ident. Num:
TM-108542
Rev. Num:
-
NASA/TM-108542, TECHNICAL MEMORANDUM 108542 TESTING FOR RANDOM LIMIT LOAD VERSUS STATIC LIMIT LOAD (SEPT 1997)., A study completed in 1993 by the Marshall Space Flight Center (MSFC) Random Loads/Criteria Issues Team concluded, after an extensive literature search, that almost no analytical or empirical documentation exists on the subject of the relationship between random limit load (stress) and static limit load (stress). The consensus of the team was that it is a complex subject and requires a carefully planned effort to produce an effective, yet practical, solution. In addition, no amount of analysis or planning will ever completely solve the problem of the dynamic-to-static limit load relationship. It is paramount that ample validation testing be accomplished so a database of hardware response can be built.
NASA/TM-1999-209734 , Lightning Protection Guidelines for Aerospace Vehicles (MAY 1999)
NASA/TM-1999-209734 , Lightning Protection Guidelines for Aerospace Vehicles (MAY 1999). Atmospheric electricity must be considered in the design, transportation, and operation of aerospace vehicles. Inadequately protected aerospace vehicles can be upset, damaged, or destroyed by a direct lightning stroke to the vehicle or launch support equipment before or after launch.1–3 Damage can also result from current induced in the vehicle from changing electric fields produced by a nearby lightning stroke. The effect of the atmosphere as an insulator and conductor of high-voltage electricity at various atmospheric pressures must also be considered. Improperly designed high-voltage systems aboard the vehicle can arc or break down at low atmospheric pressure.
Ident. Num:
TM-209734
Rev. Num:
-
NASA/TM-1999-209734 , Lightning Protection Guidelines for Aerospace Vehicles (MAY 1999). Atmospheric electricity must be considered in the design, transportation, and operation of aerospace vehicles. Inadequately protected aerospace vehicles can be upset, damaged, or destroyed by a direct lightning stroke to the vehicle or launch support equipment before or after launch.1–3 Damage can also result from current induced in the vehicle from changing electric fields produced by a nearby lightning stroke. The effect of the atmosphere as an insulator and conductor of high-voltage electricity at various atmospheric pressures must also be considered. Improperly designed high-voltage systems aboard the vehicle can arc or break down at low atmospheric pressure.
NASA/TM-1999-209734, Lightning Protection Guidelines (May 1999)
NASA/TM-1999-209734, Lightning Protection Guidelines for Aerospace Vehicles (MAY 1999). Atmospheric electricity must be considered in the design, transportation, and operation of aero- space vehicles. Inadequately protected aerospace vehicles can be upset, damaged, or destroyed by a direct lightning stroke to the vehicle or launch support equipment before or after launch.1–3 Damage can also result from current induced in the vehicle from changing electric fields produced by a nearby lightning stroke. The effect of the atmosphere as an insulator and conductor of high-voltage electricity at various atmospheric pressures must also be considered. Improperly designed high-voltage systems aboard the vehicle can arc or break down at low atmospheric pressure.
Ident. Num:
TM-1999-209734
Rev. Num:
-
NASA/TM-1999-209734, Lightning Protection Guidelines for Aerospace Vehicles (MAY 1999). Atmospheric electricity must be considered in the design, transportation, and operation of aero- space vehicles. Inadequately protected aerospace vehicles can be upset, damaged, or destroyed by a direct lightning stroke to the vehicle or launch support equipment before or after launch.1–3 Damage can also result from current induced in the vehicle from changing electric fields produced by a nearby lightning stroke. The effect of the atmosphere as an insulator and conductor of high-voltage electricity at various atmospheric pressures must also be considered. Improperly designed high-voltage systems aboard the vehicle can arc or break down at low atmospheric pressure.
NASA/TM-2006-214323, Experimental Observations for Determining the Maximum Torque Values to Apply to Composite Components Mechanically Joined with Fas
NASA/TM-2006-214323, Thomas, F.P., Experimental Observations for Determining the Maximum Torque Values to Apply to Composite Components Mechanically Joined With Fasteners (Feb 2006)., (MSFC Center Director’s Discretionary Fund Final Report, Project No. 03–13), Prepared by the Spacecraft and Vehicle Systems Department, Engineering Directorate, February 2006, pp. 36 (Aerospace structures utilize innovative, lightweight composite materials for exploration activities. These structural components, due to various reasons including size limitations, manufacturing facilities, contractual obligations, or particular design requirements, will have to be joined. The common methodologies for joining composite components are the adhesively bonded and mechanically fastened joints and, in certain instances, both methods are simultaneously incorporated into the design. Guidelines and recommendations exist for engineers to develop design criteria and analyze and test composites. However, there are no guidelines or recommendations based on analysis or test data to specify a torque or torque range to apply to metallic mechanical fasteners used to join composite components. Utilizing the torque tension machine at NASA’s Marshall Space Flight Center, an initial series of tests were conducted to determine the maximum torque that could be applied to a composite specimen. Acoustic emissions were used to nondestructively assess the specimens during the tests and thermographic imaging after the tests.
Ident. Num:
TM-2006-214323
Rev. Num:
-
NASA/TM-2006-214323, Thomas, F.P., Experimental Observations for Determining the Maximum Torque Values to Apply to Composite Components Mechanically Joined With Fasteners (Feb 2006)., (MSFC Center Director’s Discretionary Fund Final Report, Project No. 03–13), Prepared by the Spacecraft and Vehicle Systems Department, Engineering Directorate, February 2006, pp. 36 (Aerospace structures utilize innovative, lightweight composite materials for exploration activities. These structural components, due to various reasons including size limitations, manufacturing facilities, contractual obligations, or particular design requirements, will have to be joined. The common methodologies for joining composite components are the adhesively bonded and mechanically fastened joints and, in certain instances, both methods are simultaneously incorporated into the design. Guidelines and recommendations exist for engineers to develop design criteria and analyze and test composites. However, there are no guidelines or recommendations based on analysis or test data to specify a torque or torque range to apply to metallic mechanical fasteners used to join composite components. Utilizing the torque tension machine at NASA’s Marshall Space Flight Center, an initial series of tests were conducted to determine the maximum torque that could be applied to a composite specimen. Acoustic emissions were used to nondestructively assess the specimens during the tests and thermographic imaging after the tests.
NASA/TM-4322, NASA TECHNICAL MEMORANDUM 4322, NASA RELIABILITY PREFERRED PRACTICES FOR DESIGN AND TEST (SEP 1991)
NASA/TM-4322, NASA TECHNICAL MEMORANDUM 4322, NASA RELIABILITY PREFERRED PRACTICES FOR DESIGN AND TEST (SEP 1991). This manual summarizes reliability experience from both NASA and industry, and is intended to reflect engineering principles to support current and future civil space programs. The information represents the best technical advice that NASA has to offer on reliability design and test practices. Topics covered include reliability practices, including design criteria, test procedures, and analytical techniques that have been applied to previous space flight programs; and reliability guidelines, including techniques currently applied to space flight projects, where sufficient information exists to certify that the technique will contribute to mission success
Ident. Num:
TM-4322
Rev. Num:
-
NASA/TM-4322, NASA TECHNICAL MEMORANDUM 4322, NASA RELIABILITY PREFERRED PRACTICES FOR DESIGN AND TEST (SEP 1991). This manual summarizes reliability experience from both NASA and industry, and is intended to reflect engineering principles to support current and future civil space programs. The information represents the best technical advice that NASA has to offer on reliability design and test practices. Topics covered include reliability practices, including design criteria, test procedures, and analytical techniques that have been applied to previous space flight programs; and reliability guidelines, including techniques currently applied to space flight projects, where sufficient information exists to certify that the technique will contribute to mission success
NASA/TM-4511 (NASA TECHNICAL MEMORANDUM 4511) TERRESTRIAL ENVIRONMENT (CLIMATIC) CRITERIA GUIDELINES FOR USE IN AEROSPACE VEHICLE DEVELOPMENT (AUG 199
NASA/TM-4511 (NASA TECHNICAL MEMORANDUM 4511) TERRESTRIAL ENVIRONMENT (CLIMATIC) CRITERIA GUIDELINES FOR USE IN AEROSPACE VEHICLE DEVELOPMENT (AUG 1993)., Guidelines on terrestrial environment data specifically applicable in the development of design requirements specifications for NASA aerospace vehicles and associated equipment development are provided. The primary geographic areas encompassed are the John F. Kennedy Space Center, FL; Vandenberg AFB, CA; Edwards AFB, CA; Michoud Assembly Facility, New Orleans, LA; John C. Stennis Space Center, MS; Lyndon B. Johnson Space Center, Houston, TX; and the White Sands Missile Range, NM. In addition, a section was included to provide information on the general distribution of natural environmental extremes in the conterminous United States that may be needed to specify design criteria in the transportation of space vehicle subsystems and components. A summary of climatic extremes for worldwide operational needs is also included. Although not considered as a specific vehicle design criterion, a section on atmospheric attenuation was added since sensors on certain Earth orbital experiment missions are influenced by the Earth's atmosphere. The latest available information on probable climatic extremes is presented and supersedes information presented in TM X-64589, TM X-64757, TM X-78118, and TM-82473. Information is included on atmospheric chemistry, seismic criteria, and on a mathematical model to predict atmospheric dispersion of aerospace engine exhaust cloud rise and growth. There is also a section on atmospheric cloud phenomena. The information is recommended for use in the development of aerospace vehicle and associated equipment design and operational criteria, unless otherwise stated in contract work specifications. The environmental data are primarily limited to information below 90 km.
Ident. Num:
NASA-TP-4511
Rev. Num:
-
NASA/TM-4511 (NASA TECHNICAL MEMORANDUM 4511) TERRESTRIAL ENVIRONMENT (CLIMATIC) CRITERIA GUIDELINES FOR USE IN AEROSPACE VEHICLE DEVELOPMENT (AUG 1993)., Guidelines on terrestrial environment data specifically applicable in the development of design requirements specifications for NASA aerospace vehicles and associated equipment development are provided. The primary geographic areas encompassed are the John F. Kennedy Space Center, FL; Vandenberg AFB, CA; Edwards AFB, CA; Michoud Assembly Facility, New Orleans, LA; John C. Stennis Space Center, MS; Lyndon B. Johnson Space Center, Houston, TX; and the White Sands Missile Range, NM. In addition, a section was included to provide information on the general distribution of natural environmental extremes in the conterminous United States that may be needed to specify design criteria in the transportation of space vehicle subsystems and components. A summary of climatic extremes for worldwide operational needs is also included. Although not considered as a specific vehicle design criterion, a section on atmospheric attenuation was added since sensors on certain Earth orbital experiment missions are influenced by the Earth's atmosphere. The latest available information on probable climatic extremes is presented and supersedes information presented in TM X-64589, TM X-64757, TM X-78118, and TM-82473. Information is included on atmospheric chemistry, seismic criteria, and on a mathematical model to predict atmospheric dispersion of aerospace engine exhaust cloud rise and growth. There is also a section on atmospheric cloud phenomena. The information is recommended for use in the development of aerospace vehicle and associated equipment design and operational criteria, unless otherwise stated in contract work specifications. The environmental data are primarily limited to information below 90 km.
NASA/TM-4628 (NASA TECHNICAL MEMORANDUM 4628), RECOMMENDED TECHNIQUES FOR EFFECTIVE MAINTAINABILITY (DEC 1994)
NASA/TM-4628 (NASA TECHNICAL MEMORANDUM 4628), RECOMMENDED TECHNIQUES FOR EFFECTIVE MAINTAINABILITY (DEC 1994)., Recommended Techniques for Effective Maintainability. This memo provides guidance towards continuous improvement of the life cycle development process within NASA.
Ident. Num:
TM 4628
NASA/TM-4628 (NASA TECHNICAL MEMORANDUM 4628), RECOMMENDED TECHNIQUES FOR EFFECTIVE MAINTAINABILITY (DEC 1994)., Recommended Techniques for Effective Maintainability. This memo provides guidance towards continuous improvement of the life cycle development process within NASA.
NASA/TM-86556, LUBRICATION HANDBOOK FOR THE SPACE INDUSTRY (PART A: SOLID LUBRICANTS; PART Bl: LIQUID LUBRICANTS) (DEC 1985)
NASA/TM-86556, LUBRICATION HANDBOOK FOR THE SPACE INDUSTRY (PART A: SOLID LUBRICANTS; PART Bl: LIQUID LUBRICANTS) (DEC 1985)., This handbook is intended to provide a ready reference for many of the solid and liquid lubricants used in the space industry. Lubricants and lubricant properties are arranged systematically so that designers, engineers, and maintenance personnel can conveniently locate data needed for their work. This handbook is divided into two major parts (A and B). Part A is a compilation of solid lubricant suppliers information on chemical and physical property of data of more than 250 solid lubricants, bonded solid lubricants, dispersions, and composites. Part B is a compilation of chemical and physical property data of more then 250 liquid lubricants, greases, oils, compounds, and fluids. The listed materials cover a broad spectrum from manufacturing and ground support to hardware applications of spacecraft.
Ident. Num:
TM-86556
Rev. Num:
-
NASA/TM-86556, LUBRICATION HANDBOOK FOR THE SPACE INDUSTRY (PART A: SOLID LUBRICANTS; PART Bl: LIQUID LUBRICANTS) (DEC 1985)., This handbook is intended to provide a ready reference for many of the solid and liquid lubricants used in the space industry. Lubricants and lubricant properties are arranged systematically so that designers, engineers, and maintenance personnel can conveniently locate data needed for their work. This handbook is divided into two major parts (A and B). Part A is a compilation of solid lubricant suppliers information on chemical and physical property of data of more than 250 solid lubricants, bonded solid lubricants, dispersions, and composites. Part B is a compilation of chemical and physical property data of more then 250 liquid lubricants, greases, oils, compounds, and fluids. The listed materials cover a broad spectrum from manufacturing and ground support to hardware applications of spacecraft.
NASA/TM-X-64755 (REV. A), GUIDELINES FOR THE SELECTION AND APPLICATION OF TANTALUM ELECTROLYTIC CAPACITORS IN HIGHLY RELIABLE EQUIPMENT (31 JAN 1978)
NASA/TM-X-64755 (REV. A), GUIDELINES FOR THE SELECTION AND APPLICATION OF TANTALUM ELECTROLYTIC CAPACITORS IN HIGHLY RELIABLE EQUIPMENT (31 JAN 1978)., This document supersedes NASA TM X-64755, dated February 1, 1973. It presents guidelines for the selection and application of three types of tantalum electrolytic capacitors in current use at MSFC in the design of electrical and electronic circuits for space flight missions. In addition, the guidelines supplement requirements of existing Military Specifications used in the procurement of capacitors. A need exists for guidelines to assist designers in preventing some of the recurring, serious problems experienced with tantalum electrolytic capacitors in the recent past. The three types of capacitors covered by these guidelines are: solid (CSB09 and 13), wet foil (CLR25, 27, 35, and 37), and tantalum cased wet slug (CLR79).
Ident. Num:
NASA/TM-X-64755
Rev. Num:
A
NASA/TM-X-64755 (REV. A), GUIDELINES FOR THE SELECTION AND APPLICATION OF TANTALUM ELECTROLYTIC CAPACITORS IN HIGHLY RELIABLE EQUIPMENT (31 JAN 1978)., This document supersedes NASA TM X-64755, dated February 1, 1973. It presents guidelines for the selection and application of three types of tantalum electrolytic capacitors in current use at MSFC in the design of electrical and electronic circuits for space flight missions. In addition, the guidelines supplement requirements of existing Military Specifications used in the procurement of capacitors. A need exists for guidelines to assist designers in preventing some of the recurring, serious problems experienced with tantalum electrolytic capacitors in the recent past. The three types of capacitors covered by these guidelines are: solid (CSB09 and 13), wet foil (CLR25, 27, 35, and 37), and tantalum cased wet slug (CLR79).
NASA/TM-X-73305 (NASA TECHNICAL MEMORANDUM TM X-73305), ASTRONAUTICS STRUCTURES MANUAL (VOLUME 1) (AUG 1975)
NASA/TM-X-73305 (NASA TECHNICAL MEMORANDUM TM X-73305), ASTRONAUTICS STRUCTURES MANUAL (VOLUME 1) (AUG 1975). This document (Volumes 1, II, and III) presents a compilation of industry-wide methods in aerospace strength analysis that can be carried out by hand, that are general enough in scope to cover most structures encountered, and that are sophisticaed enough to give accurant estimates of the actual strength expected.
Ident. Num:
TM X -73305
Rev. Num:
-
NASA/TM-X-73305 (NASA TECHNICAL MEMORANDUM TM X-73305), ASTRONAUTICS STRUCTURES MANUAL (VOLUME 1) (AUG 1975). This document (Volumes 1, II, and III) presents a compilation of industry-wide methods in aerospace strength analysis that can be carried out by hand, that are general enough in scope to cover most structures encountered, and that are sophisticaed enough to give accurant estimates of the actual strength expected.
NASA/TP-104645 (NASA TECHNICAL MEMORANDUM 104645) THE PI-MODE OF PROJECT MANAGEMENT (APR 1997)
NASA/TP-104645 (NASA TECHNICAL MEMORANDUM 104645) THE PI-MODE OF PROJECT MANAGEMENT (APR 1997). The PI-Mode is NASA's new approach to project management. It responds to the Agency's new policy to develop scientific missions that deliver the highest quality science for a fixed cost. It also attempts to provide more research opportunities by reducing project development times and increasing the number of launches per year. In order to accomplish this, the Principal Investigator is placed at the helm of the project, with full responsibility over all aspects of the mission, including instrument and spacecraft development, as well as mission operations and data analysis. This paper intends to study the PI-Mode to determine the strengths and weaknesses of such a new project management technique. It also presents an analysis of its possible impact on the scientific community and its relations with industry, NASA, and other institutions.
Ident. Num:
TM-104645
Rev. Num:
-
NASA/TP-104645 (NASA TECHNICAL MEMORANDUM 104645) THE PI-MODE OF PROJECT MANAGEMENT (APR 1997). The PI-Mode is NASA's new approach to project management. It responds to the Agency's new policy to develop scientific missions that deliver the highest quality science for a fixed cost. It also attempts to provide more research opportunities by reducing project development times and increasing the number of launches per year. In order to accomplish this, the Principal Investigator is placed at the helm of the project, with full responsibility over all aspects of the mission, including instrument and spacecraft development, as well as mission operations and data analysis. This paper intends to study the PI-Mode to determine the strengths and weaknesses of such a new project management technique. It also presents an analysis of its possible impact on the scientific community and its relations with industry, NASA, and other institutions.
NASA/TP-104823 (NASA TECHNICAL MEMORANDUM 104823) GUIDE FOR OXYGEN HAZARDS ANALYSES ON COMPONENTS AND SYSTEMS (OCT 1996)
NASA/TP-104823 (NASA TECHNICAL MEMORANDUM 104823) GUIDE FOR OXYGEN HAZARDS ANALYSES ON COMPONENTS AND SYSTEMS (OCT 1996)., The objective of this test plan is to describe the White Sands Test Facility oxygen hazards analysis to be performed on components and systems before oxygen is introduced and is recommended before implementing the oxygen component qualification procedure. The plan describes the NASA Johnson Space Center White Sands Test Facility method consistent with the ASTM documents for analyzing the hazards of components and systems exposed to an oxygen-enriched environment. The oxygen hazards analysis is a useful tool for oxygen-system designers, system engineers, and facility managers. Problem areas can be pinpointed before oxygen is introduced into the system, preventing damage to hardware and possible injury or loss of life.
Ident. Num:
TM-104823
Rev. Num:
-
NASA/TP-104823 (NASA TECHNICAL MEMORANDUM 104823) GUIDE FOR OXYGEN HAZARDS ANALYSES ON COMPONENTS AND SYSTEMS (OCT 1996)., The objective of this test plan is to describe the White Sands Test Facility oxygen hazards analysis to be performed on components and systems before oxygen is introduced and is recommended before implementing the oxygen component qualification procedure. The plan describes the NASA Johnson Space Center White Sands Test Facility method consistent with the ASTM documents for analyzing the hazards of components and systems exposed to an oxygen-enriched environment. The oxygen hazards analysis is a useful tool for oxygen-system designers, system engineers, and facility managers. Problem areas can be pinpointed before oxygen is introduced into the system, preventing damage to hardware and possible injury or loss of life.
NASA/TP-1998-207194, PROBABILITY AND STATISTICS IN AEROSPACE ENGINEERING
NASA/TP-1998-207194, PROBABILITY AND STATISTICS IN AEROSPACE ENGINEERING. Statistics is the science of the collection, organization, analysis, and interpretation of numerical data, especially the analysis of population characteristics by inference from sampling. In engineering work this includes such different tasks as predicting the reliability of space launch vehicles and subsystems, lifetime analysis of spacecraft system components, failure analysis, and tolerance limits. A common engineering definition of statistics states that statistics is the science of guiding decisions in the face of uncertainties. An earlier definition was statistics is the science of making decisions in the face of uncertainties, but the verb making has been moderated to guiding.
Ident. Num:
TP-1998-207194
Rev. Num:
-
NASA/TP-1998-207194, PROBABILITY AND STATISTICS IN AEROSPACE ENGINEERING. Statistics is the science of the collection, organization, analysis, and interpretation of numerical data, especially the analysis of population characteristics by inference from sampling. In engineering work this includes such different tasks as predicting the reliability of space launch vehicles and subsystems, lifetime analysis of spacecraft system components, failure analysis, and tolerance limits. A common engineering definition of statistics states that statistics is the science of guiding decisions in the face of uncertainties. An earlier definition was statistics is the science of making decisions in the face of uncertainties, but the verb making has been moderated to guiding.
NASA/TP-1999-20373M, SPACECRAFT ENVIRONMENTS INTERACTIONS SPACE RADIATION AND ITS EFFECTS ON ELECTRONICS SYSTEMS
NASA/TP-1999-20373M, SPACECRAFT ENVIRONMENTS INTERACTIONS SPACE RADIATION AND ITS EFFECTS ON ELECTRONICS SYSTEMS.
Ident. Num:
TP-1999-20373M
Rev. Num:
-
NASA/TP-1999-20373M, SPACECRAFT ENVIRONMENTS INTERACTIONS SPACE RADIATION AND ITS EFFECTS ON ELECTRONICS SYSTEMS.
NASA/TP-2000-207428, Reliability and Maintainability (RMA) Training
NASA/TP-2000-207428, Reliability and Maintainability (RMA) Training. Edited by Vincent R. Lalli Glenn Henry Siemens Michael Ratheon Research A. Malec Stromberg-Carlson, H. Packard Engineers and Constructors, Cleveland, Ohio Albuquerque, New Mexico Center, Cleveland, Ohio. National Space Aeronautics Administration and Glenn Research Center
Ident. Num:
TP-2000-20728
NASA/TP-2000-207428, Reliability and Maintainability (RMA) Training. Edited by Vincent R. Lalli Glenn Henry Siemens Michael Ratheon Research A. Malec Stromberg-Carlson, H. Packard Engineers and Constructors, Cleveland, Ohio Albuquerque, New Mexico Center, Cleveland, Ohio. National Space Aeronautics Administration and Glenn Research Center
NASA/TP-2003-212244, PEM-INST-001: Instructions for Plastic Encapsulated Microcircuit (PEM) Selection, Screening, and Qualification
NASA/TP-2003-212244, PEM-INST-001: Instructions for Plastic Encapsulated Microcircuit (PEM) Selection, Screening, and Qualification. This document establishes a system of product assurance for PEMs in order to invoke the GSFC PEM policy. It is based partly on existing qualification system for military and aerospace components, experience accumulated by the parts engineering community, and practices or guidelines established by high-reliability electronics industry.
Ident. Num:
NASA/TP-2003-212244
Rev. Num:
-
NASA/TP-2003-212244, PEM-INST-001: Instructions for Plastic Encapsulated Microcircuit (PEM) Selection, Screening, and Qualification. This document establishes a system of product assurance for PEMs in order to invoke the GSFC PEM policy. It is based partly on existing qualification system for military and aerospace components, experience accumulated by the parts engineering community, and practices or guidelines established by high-reliability electronics industry.
NASA/TP-2003-212257, STATISTICAL EVALUATION AND IMPROVEMENT OF METHODS FOR COMBINING RANDOM AND HARMONIC LOADS (FEB 2003)
NASA/TP-2003-212257, Brown, A.M. and McGhee, D.S., Statistical Evaluation and Improvement of Methods for Combining Random and Harmonic Loads, George C. Marshall Space Flight Center , Marshall Space Flight Center, AL 35812, National Aeronautics and Space Administration, Washington, DC 20546-0001, February 2003, pp. 32., Structures in many environments experience both random and harmonic excitation. A variety of closed-form techniques has been used in the aerospace industry to combine the loads resulting from the two sources. The resulting combined loads are then used to design for both yield/ultimate strength and high-cycle fatigue capability. This Technical Publication examines the cumulative distribution percentiles obtained using each method by integrating the joint probability density function of the sine and random components. A new Microsoft Excel spreadsheet macro that links with the software program Mathematica to calculate the combined value corresponding to any desired percentile is then presented along with a curve fit to this value. Another Excel macro that calculates the combination using Monte Carlo simulation is shown. Unlike the traditional techniques, these methods quantify the calculated load value with a consistent percentile. Using either of the presented methods can be extremely valuable in probabilistic design, which requires a statistical characterization of the loading. Additionally, since the CDF at high probability levels is very flat, the design value is extremely sensitive to the predetermined percentile; therefore, applying the new techniques can substantially lower the design loading without losing any of the identifed structural reliability.
Ident. Num:
TP-2003-212257
Rev. Num:
-
NASA/TP-2003-212257, Brown, A.M. and McGhee, D.S., Statistical Evaluation and Improvement of Methods for Combining Random and Harmonic Loads, George C. Marshall Space Flight Center , Marshall Space Flight Center, AL 35812, National Aeronautics and Space Administration, Washington, DC 20546-0001, February 2003, pp. 32., Structures in many environments experience both random and harmonic excitation. A variety of closed-form techniques has been used in the aerospace industry to combine the loads resulting from the two sources. The resulting combined loads are then used to design for both yield/ultimate strength and high-cycle fatigue capability. This Technical Publication examines the cumulative distribution percentiles obtained using each method by integrating the joint probability density function of the sine and random components. A new Microsoft Excel spreadsheet macro that links with the software program Mathematica to calculate the combined value corresponding to any desired percentile is then presented along with a curve fit to this value. Another Excel macro that calculates the combination using Monte Carlo simulation is shown. Unlike the traditional techniques, these methods quantify the calculated load value with a consistent percentile. Using either of the presented methods can be extremely valuable in probabilistic design, which requires a statistical characterization of the loading. Additionally, since the CDF at high probability levels is very flat, the design value is extremely sensitive to the predetermined percentile; therefore, applying the new techniques can substantially lower the design loading without losing any of the identifed structural reliability.
NASA/TP-2006-214203, LOGISTICS LESSONS LEARNED IN NASA SPACE FLIGHT
NASA/TP-2006-214203, LOGISTICS LESSONS LEARNED IN NASA SPACE FLIGHT. This report first summarizes current logistics practices for the Space Shuttle Program (SSP) and the International Space Station (ISS) and examines the practices of manifesting, stowage, inventory tracking, waste disposal, and return logistics. The key findings of this examination are that while the current practices do have many positive aspects, there are also several shortcomings. These shortcomings include a high-level of excess complexity, redundancy of information/lack of a common database, and a large human-in-the-loop component.
Ident. Num:
TP-2006-214203
Rev. Num:
-
NASA/TP-2006-214203, LOGISTICS LESSONS LEARNED IN NASA SPACE FLIGHT. This report first summarizes current logistics practices for the Space Shuttle Program (SSP) and the International Space Station (ISS) and examines the practices of manifesting, stowage, inventory tracking, waste disposal, and return logistics. The key findings of this examination are that while the current practices do have many positive aspects, there are also several shortcomings. These shortcomings include a high-level of excess complexity, redundancy of information/lack of a common database, and a large human-in-the-loop component.
NASA/TP-2361, Design Guidelines for Assessing and Controlling Spacecraft Charging Effects
NASA/TP-2361, NASA TECHNICAL PAPER, Design Guidelines for Assessing and Controlling Spacecraft Charging Effects. This document is to be regarded as a guide to good design practices for assessing and controlling charging effects. It is not a NASA or Air Force mandatory requirement unless specifically included in project specifications. It is expected, however, that this document, revised as experience may indicate, will provide uniform design practices for all space vehicles.
Ident. Num:
TP-2361
Rev. Num:
-
NASA/TP-2361, NASA TECHNICAL PAPER, Design Guidelines for Assessing and Controlling Spacecraft Charging Effects. This document is to be regarded as a guide to good design practices for assessing and controlling charging effects. It is not a NASA or Air Force mandatory requirement unless specifically included in project specifications. It is expected, however, that this document, revised as experience may indicate, will provide uniform design practices for all space vehicles.
NASA/TP-3642, Working on the Boundaries: Philosophies and Practices of the Design Process
NASA Technical Paper TP-3642, Working on the Boundaries: Philosophies and Practices of the Design Process. The design process is a blend of classical procedures and evolving philosophical principles and practices in the ever-changing and challenging environments of customer expectations, new technologies, and constraining economics. An engineering product builds on those consistent and proven practices and philosophies selected in the design process. This report endeavors to identify and illuminate a few recurring design process principles published, experienced, and observed that lead to successful aerospace products.
Ident. Num:
TP-3642
Rev. Num:
-
NASA Technical Paper TP-3642, Working on the Boundaries: Philosophies and Practices of the Design Process. The design process is a blend of classical procedures and evolving philosophical principles and practices in the ever-changing and challenging environments of customer expectations, new technologies, and constraining economics. An engineering product builds on those consistent and proven practices and philosophies selected in the design process. This report endeavors to identify and illuminate a few recurring design process principles published, experienced, and observed that lead to successful aerospace products.
NHB 5300.4 (1C), RELIABILITY AND QUALITY ASSURANCE PUBLICATION INSPECTION SYSTEM PROVISIONS FOR AERONAUTICAL AND SPACE SYSTEM MATERIAL, PARTS, COMPONENTS AND SERVICES (JUL 1971) [SUPERSEDING NPC 200-3]
NHB 5300.4 (1C), RELIABILITY AND QUALITY ASSURANCE PUBLICATION INSPECTION SYSTEM PROVISIONS FOR AERONAUTICAL AND SPACE SYSTEM MATERIAL, PARTS, COMPONENTS AND SERVICES (JUL 1971) [SUPERSEDING NPC 200-3]., This publication establishes general requirements for inspection systems to ensure the required high quality of materials, parts, components and services for NASA aeronautical and space systems.
Ident. Num:
NHB 5300.4 (1C)
Rev. Num:
-
NHB 5300.4 (1C), RELIABILITY AND QUALITY ASSURANCE PUBLICATION INSPECTION SYSTEM PROVISIONS FOR AERONAUTICAL AND SPACE SYSTEM MATERIAL, PARTS, COMPONENTS AND SERVICES (JUL 1971) [SUPERSEDING NPC 200-3]., This publication establishes general requirements for inspection systems to ensure the required high quality of materials, parts, components and services for NASA aeronautical and space systems.
NHB 5300.4(3A-1), REQUIREMENTS FOR SOLDERED ELECTRICAL CONNECTIONS (DEC 1976)
NHB 5300.4(3A-1), REQUIREMENTS FOR SOLDERED ELECTRICAL CONNECTIONS (DEC 1976)., In order to maintain the high standards of the NASA soldering programs, this publication: Prescribes NASA's requirements for hand and machine soldering for reliable electrical connections. Describes and incorporates basic considerations necessary to ensure reliable soldered connections. Appendix C provides design guidelines to avoid solder cracking and solder-copper separation problems. Establishes the supplier's responsibility to train and certify personnel. Provides for supplier documentation of those fabrication and inspection procedures to be used for NASA work, including supplier innovations and changes in technology. Provides expanded and improved visual workmanship standards in Appendix B.
Ident. Num:
NHB 5300.4(3A-1)
Rev. Num:
-
NHB 5300.4(3A-1), REQUIREMENTS FOR SOLDERED ELECTRICAL CONNECTIONS (DEC 1976)., In order to maintain the high standards of the NASA soldering programs, this publication: Prescribes NASA's requirements for hand and machine soldering for reliable electrical connections. Describes and incorporates basic considerations necessary to ensure reliable soldered connections. Appendix C provides design guidelines to avoid solder cracking and solder-copper separation problems. Establishes the supplier's responsibility to train and certify personnel. Provides for supplier documentation of those fabrication and inspection procedures to be used for NASA work, including supplier innovations and changes in technology. Provides expanded and improved visual workmanship standards in Appendix B.
RAPID PROTOTYPING CAPABILITY (RPC) GUIDELINES (10/16/2007)
RAPID PROTOTYPING CAPABILITY (RPC) GUIDELINES. The purpose of this document is to describe the Rapid Prototyping process necessary for conducting experiments that utilize NASA Earth-science research results in candidate configurations for potential Integrated System Solutions (ISS, Figure 1). NASA Earth-science research results include current and planned Earth observing measurements and systems, computer model projections, data handling systems, analytical tools and networks, and other capabilities developed through NASA’s R&A Program, Earth Science Division, Science Mission Directorate. Utilizing the guidelines presented in this document, in collaboration with NASA’s Applied Sciences Program National Applications focus area Program Managers, a Rapid Prototyping Capability (RPC) Experiment can be proposed for consideration that aligns with a partnering agency’s priority decision support tools. The Experiment Team should read this document before filling in the RPC Experiment Plan Submission Form.
Ident. Num:
NO NUMBER
Rev. Num:
-
RAPID PROTOTYPING CAPABILITY (RPC) GUIDELINES. The purpose of this document is to describe the Rapid Prototyping process necessary for conducting experiments that utilize NASA Earth-science research results in candidate configurations for potential Integrated System Solutions (ISS, Figure 1). NASA Earth-science research results include current and planned Earth observing measurements and systems, computer model projections, data handling systems, analytical tools and networks, and other capabilities developed through NASA’s R&A Program, Earth Science Division, Science Mission Directorate. Utilizing the guidelines presented in this document, in collaboration with NASA’s Applied Sciences Program National Applications focus area Program Managers, a Rapid Prototyping Capability (RPC) Experiment can be proposed for consideration that aligns with a partnering agency’s priority decision support tools. The Experiment Team should read this document before filling in the RPC Experiment Plan Submission Form.
