1、APPROVED FOR PUBLIC RELEASE DISTRIBUTION IS UNLIMITED NASA TECHNICAL STANDARD NASA-STD-5005D National Aeronautics and Space Administration Approved: Washington, DC 20546-0001 Superseding NASA-STD-5005C STANDARD FOR THE DESIGN AND FABRICATION OF GROUND SUPPORT EQUIPMENT MEASUREMENT SYSTEM IDENTIFICAT
2、ION: METRIC/SI (ENGLISH) Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NASA-STD-5005D APPROVED FOR PUBLIC RELEASE DISTRIBUTION IS UNLIMITED 2 of 76 DOCUMENT HISTORY LOG Status Document Revision Approval Date Description Baseline 5-10-1996 Baseline
3、Release Revision A 5-15-2001 Incorporated numerous updates to applicable and reference documents Revision B 9-15-2003 Incorporated numerous updates to applicable and reference documents Interim C 7-20-2007 Interim Revision (General RevisionDocument Completely Rewritten) Incorporated numerous updates
4、 to applicable and reference documents, added M (2) it will not degrade the safety or reliability of the flight or ground system; and (3) it provides a cost savings that exceeds possible cost increases due to unique maintenance or logistics requirements, modifications, or an increase in the complexi
5、ty of the interfacing equipment. Vendor or contractor documentation and supporting test data should be incorporated into system control documents. 4.2 System Requirements 4.2.1 Performance Requirements In addition to performance requirements, GSE should be designed for ease of production, manufactur
6、e, construction, and inspection. GSE should be designed to minimize the complexity Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NASA-STD-5005D APPROVED FOR PUBLIC RELEASE DISTRIBUTION IS UNLIMITED 25 of 76 and frequency of maintenance. Close manuf
7、acturing tolerances should be avoided unless required by design and performance. 4.2.1.1 Design Life GSE shall be designed for the operational life specified by program or mission requirements. Engineering documentation should specify maintenance requirements to meet design life. 4.2.1.2 Contaminati
8、on from GSE GSE shall not cause degradation of or contaminate flight systems or ground systems while it is being used, checked out, serviced, or otherwise handled. 4.2.1.3 GSE Design for Access GSE design shall include access provisions for handling, servicing, calibration, maintenance, repair, and
9、replacement of components and limited-life items. GSE design should provide for ease of operation, maintenance, servicing, cleaning, and inspection of hardware and software. GSE fault detection and isolation should be considered based on criticality and cost of failures. 4.2.1.4 Interfaces a. GSE sh
10、all meet the requirements of all interfaces with flight hardware or software as specified in interface control documentation. Interfaces should be verified by test and/or analysis. GSE should be designed to reduce or eliminate the potential for a mating device (fluid, mechanical, or electrical) to b
11、e connected to the wrong interface with flight hardware. b. GSE shall be compatible with all facility interfaces. An assessment may be required to determine if it is more cost-effective to modify the facility interface or design the GSE to meet the existing facility interface. 4.2.2 Heritage GSE Her
12、itage GSE is hardware/software that has been fabricated and delivered to a previous program. GSE designs that were not fabricated are not considered Heritage GSE and must meet the requirements of this Standard. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from
13、 IHS-,-,-NASA-STD-5005D APPROVED FOR PUBLIC RELEASE DISTRIBUTION IS UNLIMITED 26 of 76 Existing GSE that was verified to meet the GSE design and fabrication requirements of a previous NASA program shall be considered acceptable for use without further verification to the requirements of this Standar
14、d, if the following conditions are met: a. Approval is obtained from the responsible program/project office. b. Waivers to GSE design and fabrication requirements from the previous NASA program are evaluated and approved by the responsible Technical Authority against the equivalent requirements in t
15、his Standard. c. Existing GSE is verified to meet the performance requirements, interfaces, operational limits, and environments for its intended application. GSE design and fabrication requirements for previous NASA programs are defined in SW-E-0002, Ground Support Equipment General Design Requirem
16、ents: Space Shuttle; KSC-DE-512-SM, Facility, System, and Equipment General Design Requirements; SSP 50004, Ground Support Equipment Design Requirements: International Space Station; or a previous version of this Standard. 4.2.3 Reliability 4.2.3.1 Redundancy When redundancy is required to satisfy f
17、ailure tolerance: a. Redundant systems, subsystems, or components shall be designed such that the failure of one will not prevent the other from performing its intended function. Physically orienting or separating redundant items should be considered to prevent propagation of failures (e.g., routing
18、 electrical cables in separate cable trays). b. Redundant systems, subsystems, or components shall be designed such that common-cause failures (e.g., contamination, common power source, etc.) do not eliminate redundancy. c. Redundant systems shall be designed such that each independent path can be t
19、ested without invalidating the system configuration. 4.2.3.2 Failure Tolerance a. GSE (except primary structure and pressure vessels, piping, and tubing in rupture mode) shall be designed such that no single failure or inadvertent operator action results in equipment or facility damage or personal i
20、njury. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NASA-STD-5005D APPROVED FOR PUBLIC RELEASE DISTRIBUTION IS UNLIMITED 27 of 76 Failure tolerance is not possible for primary structure and pressure vessels/tubing in rupture mode. Safety of these
21、systems is achieved by application of design requirements contained in this standard. GSE may be designed to terminate operations autonomously after the first failure or inadvertent operator action and in time to preclude any scenario that results in equipment or facility damage or personal injury.
22、This approach is consistent with the historical use of the term “fail-safe” by the GSE design community. b. GSE shall be designed to sustain a failure or inadvertent operator action and still perform its basic function when necessary to meet either safety or operational requirements. Purges, ground
23、special power, and launch release systems are examples of systems that interface with other systems whose loss would propagate failures. This approach is consistent with the historical use of the term “fail-operational” by the GSE design community. 4.2.3.3 Failure Propagation GSE shall be designed t
24、o prevent failures from propagating to flight systems. The design of GSE should consider how flight hardware/software failures could propagate through the GSE and affect other flight systems. 4.2.4 Environmental Conditions 4.2.4.1 Natural Environment GSE used or stored in an uncontrolled exterior en
25、vironment shall be designed to function after exposure to the natural environment at its respective geographical location as specified in NASA-HDBK-1001, Terrestrial Environment (Climatic) Criteria Handbook for Use in Aerospace Vehicle Development. Specifications in NASA-HDBK-1001 may be tailored to
26、 reflect program-defined risk and exposure times, including operation within the launch commit criteria of the vehicle. 4.2.4.2 Launch-Induced Environment a. GSE required to function during or after exposure to the launch-induced environment shall be designed to withstand the environment defined in
27、program documents. b. GSE not required to function after exposure to the launch-induced environment shall not cause damage or create a hazard to flight hardware, facilities, other GSE, personnel, or the environment. Provided by IHSNot for ResaleNo reproduction or networking permitted without license
28、 from IHS-,-,-NASA-STD-5005D APPROVED FOR PUBLIC RELEASE DISTRIBUTION IS UNLIMITED 28 of 76 4.2.4.3 Controlled Interior Environment GSE designed to function within a controlled interior environment shall be designed to the following temperature and humidity requirements: a. Nominal temperature: +15
29、C (60 F) to +27 C (80 F). b. Extreme temperature: +11 C (52 F) to +15 C (60 F) or +27 C (80 F) to +40 C (105 F) for a maximum of 1 hour. c. Humidity: nominal 55 percent, within a range of 30 percent to 70 percent. 4.2.4.4 Controlled Clean Environment Clean rooms and associated controlled environment
30、s designated as GSE shall be designed in accordance with ASTM E2217, Standard Practice for Design and Construction of Aerospace Cleanrooms and Contamination Controlled Areas. 4.2.4.5 Uncontrolled Interior Environment GSE used in an uncontrolled interior environment shall be designed to meet the most
31、 severe exterior environmental conditions for humidity and temperature anticipated at the respective geographical locations, as defined in NASA-HDBK-1001. Some uncontrolled interior environments can exceed the most severe exterior environment, i.e., an enclosed trailer in a hot (tropical or desert)
32、exterior environment. 4.2.4.6 Environmental Test Methods Environmental methods and conditions required for testing and qualification of GSE components shall be in accordance with MIL-STD-810, Environmental Engineering Considerations and Laboratory Tests. KSC-STD-164, Environmental Test Methods for G
33、round Support Equipment, Standard for, should be used as a guide to standardize practices. 4.2.4.7 Seismic Environment GSE used in Zones 3 or 4 as defined in NASA-HDBK-1001 shall be designed to resist the effects of a seismic event using the criteria and guidelines in ASCE-7, Minimum Design Loads fo
34、r Buildings and Other Structures, Chapter 15, Seismic Design Requirements for Non-Building Structures. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NASA-STD-5005D APPROVED FOR PUBLIC RELEASE DISTRIBUTION IS UNLIMITED 29 of 76 4.3 Documentation 4.3
35、.1 Drawings and Specifications Drawings and specifications required for the fabrication, construction, installation, modification, test, operation, maintenance, sustaining, and use of GSE shall be prepared in accordance with drawing practices equal to or more stringent than the engineering drawing p
36、ractices of ASME Y14.100, Engineering Drawing Practices. 4.3.2 Technical Documentation Technical documentation (e.g., manuals and reports) shall be prepared and delivered to the user of the GSE. Documentation should include applicable deliverables contained in Appendix B. 4.4 Logistics GSE design do
37、cumentation shall identify spare parts, components, materials, and items required to support construction, fabrication, installation, activation, test, verification, and operation. 4.5 Limited-Life Items a. Limited-life items shall be controlled from the date of their manufacture through their perio
38、d of operational use, including the time they are in storage. b. The status of limited-life items shall be documented. c. GSE design documentation shall identify limited-life items and provide instructions for replacement of those parts, components, and materials. Use of items with a projected lifet
39、ime that is less than the design life of the GSE for which the items are intended should be avoided whenever possible. Elapsed time or cycle indicators should be employed to accumulate operational time or cycles for limited-life items. The age of items that are installed in a non-operating mode shou
40、ld also be tracked. 4.6 Quality Assurance Documentation shall be provided by the design organization to verify compliance with this Standard (reference Appendix B). Examinations and tests are recommended to verify that all requirements of this Standard have been achieved. This may include the follow
41、ing: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NASA-STD-5005D APPROVED FOR PUBLIC RELEASE DISTRIBUTION IS UNLIMITED 30 of 76 Tests and analyses of the performance and reliability requirements. Measurement or comparison of specified physical cha
42、racteristics. Verification, with specific criteria, of workmanship. Test and inspection methods for ensuring compliance, including environmental. Conditions for performance. 4.6.1 Quality Requirements Definition Quality requirements shall be defined on the engineering drawings or in other technical
43、documents that are included in the design, fabrication, or installation contract. The design documentation should include any special processes, testing, and inspections to be conducted. 4.6.2 Testing a. Testing requirements shall be specified in engineering documentation. b. Critical components sha
44、ll undergo qualification testing to verify compliance with the applicable specifications and the ability to perform required design functions in the intended environment. 4.6.2.1 Load Test a. Structural GSE (access platforms, workstands, etc.) shall be load tested to a minimum of 125 percent of the
45、design or working load. b. Lifting devices and equipment shall be load tested in accordance with NASA-STD-8719.9, Standard for Lifting Devices and Equipment. 4.6.2.2 Metrology and Calibration Metrology and calibration of all test equipment and tools used in support of fabrication, assembly, installation, and test of GSE shall be in accordance with NPD 8730.1, Metrology and Calibration. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
