REG NASA-LLIS-0810-2000 Lessons Learned Thermal Cycling.pdf

上传人:eastlab115 文档编号:1018456 上传时间:2019-03-21 格式:PDF 页数:5 大小:19.06KB
下载 相关 举报
REG NASA-LLIS-0810-2000 Lessons Learned Thermal Cycling.pdf_第1页
第1页 / 共5页
REG NASA-LLIS-0810-2000 Lessons Learned Thermal Cycling.pdf_第2页
第2页 / 共5页
REG NASA-LLIS-0810-2000 Lessons Learned Thermal Cycling.pdf_第3页
第3页 / 共5页
REG NASA-LLIS-0810-2000 Lessons Learned Thermal Cycling.pdf_第4页
第4页 / 共5页
REG NASA-LLIS-0810-2000 Lessons Learned Thermal Cycling.pdf_第5页
第5页 / 共5页
亲,该文档总共5页,全部预览完了,如果喜欢就下载吧!
资源描述

1、Best Practices Entry: Best Practice Info:a71 Committee Approval Date: 2000-04-17a71 Center Point of Contact: GRCa71 Submitted by: Wil HarkinsSubject: Thermal Cycling Practice: As a minimum, run eight thermal cycles over the approximate temperature range for hardware that cycles in flight over ranges

2、 greater than 20oC. The last three thermal cycles should be failure free.Programs that Certify Usage: This practice has been used on ATLAS, CENTAUR, Space Electronic Rocket Tests (SERTs) 1 and 2, Communication Technology Satellite (CTS), GOES, COBE, NOAA, LANDSAT, Solar Maximum Mission.Center to Con

3、tact for Information: GRCImplementation Method: This Lesson Learned is based on Reliability Practice number PT-TE-1402, from NASA Technical Memorandum 4322A, Reliability Preferred Practices for Design and Test.Benefit:Demonstrates readiness of the hardware to operate in the intended cyclic environme

4、nt. Precipitates defects from design or manufacturing processes that could result in flight failures.Implementation Method:Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-As part of ATP, run at least eight thermal cycles over the temperature range ex

5、perienced by the hardware during storage, shipping, launch, flight, and reentry. The maximum and minimum temperatures anticipated should be exceeded by 10 degrees C. The last three thermal cycles should be failure-free.Equipment must stabilize at these limits before cycling to the opposing limit. Eq

6、uipment generally should be operated within the anticipated thermal range rather than at the thermal limits.Thermal cycling should be conducted in a vacuum if the test item is designed to operate in a vacuum.Technical Rationale:Thermal cycle modeling has shown that the general form of the thermal cy

7、cling test math model is given by Equation (1).refer to D descriptionD: Where:a71 TE = Test Effectivenessa71 F = Fraction of total failures that can be recipitated by a thermal cyclea71 Pd= Probability of detectiona71 lO= Failure rate at TOa71 N = Number of thermal cyclesa71 K = A constanta71 DT = T

8、 - TOa71 T = Operating temperature for la71 TO= Operating temperature for lOFig. 1 shows that the failures available are the sum of three parts:1. Failures detected by thermal cycle tests2. Undetected failures3. Failures not precipitatedProvided by IHSNot for ResaleNo reproduction or networking perm

9、itted without license from IHS-,-,-refer to D descriptionD Figure 1: General Form of TC Test Model For single temperature range of 50oC, the test effectiveness equation reduces to Equation (2).refer to D descriptionD Figure 2 shows a plot of Equation (2) based on a probability of detection, Pd, of 0

10、9. The equation is based on values of lOand K that were found by solving two simultaneous equations.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-refer to D descriptionD Figure 2. Test Effectiveness Plot for lT = 50oC Printed circuit boards (PCBs)

11、 are especially prone to solder joint cracking. The design is required to minimize the mechanical forces, as generated by thermal mismatch of materials or vibration, in the solder joints.References:1. GDCD BNZ 69-007, Curssell, G. M., “Atlas and Centaur Component Acceptance Test Plan,“ 1984.2. NASA

12、TMX-53731, Van Orden, R. E., “Mounting of Components to Printed Wiring Boards,“ 1968.3. Laube, R. B., “Space Vehicle Thermal Cycling Test Parameters,“ Proceeding of the Institute of Environmental Sciences, 1983.4. Nelson, C. E., “System Level Reliability Thermal Cycling,“ Proceeding of the Institute

13、 of Environment Sciences, 1983.Impact of Non-Practice: Design and manufacturing defects that could have been detected during ground testing manifest themselves during flight.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Related Practices: N/AAdditional Info: Approval Info: a71 Approval Date: 2000-04-17a71 Approval Name: Eric Raynora71 Approval Organization: QSa71 Approval Phone Number: 202-358-4738Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-

展开阅读全文
相关资源
猜你喜欢
  • DIN 65156-1989 Aerospace close tolerance steel rivets with 100 flush head shank tolerance 0 to - 0 02 mm metric series《航空航天 米制系列,钉杆公差 0 至 0 02 mm 100平头紧公差钢制铆钉》.pdf DIN 65156-1989 Aerospace close tolerance steel rivets with 100 flush head shank tolerance 0 to - 0 02 mm metric series《航空航天 米制系列,钉杆公差 0 至 0 02 mm 100平头紧公差钢制铆钉》.pdf
  • DIN 65157-1989 Aerospace steel collars metric series《航空航天 米制系列钢钉套环》.pdf DIN 65157-1989 Aerospace steel collars metric series《航空航天 米制系列钢钉套环》.pdf
  • DIN 65158-1993 Aerospace blind rivets of aluminium alloy with flat round head self-locking device《航空航天 带平圆头自锁机构的铝合金盲铆钉》.pdf DIN 65158-1993 Aerospace blind rivets of aluminium alloy with flat round head self-locking device《航空航天 带平圆头自锁机构的铝合金盲铆钉》.pdf
  • DIN 65159-1993 Aerospace blind rivets of aluminium alloy with 100 countersunk head and self-locking device《航空航天 带自锁机构的100沉头铝合金盲铆钉》.pdf DIN 65159-1993 Aerospace blind rivets of aluminium alloy with 100 countersunk head and self-locking device《航空航天 带自锁机构的100沉头铝合金盲铆钉》.pdf
  • DIN 65164-1-1997 Aerospace - Non metallic braided cable sleevings - Part 1 Dimensions masses《航空航天 非金属编织软管 第1部分 尺寸、重量》.pdf DIN 65164-1-1997 Aerospace - Non metallic braided cable sleevings - Part 1 Dimensions masses《航空航天 非金属编织软管 第1部分 尺寸、重量》.pdf
  • DIN 65164-2-2014 Aerospace - Non metallic braided cable sleevings - Part 2 Technical specification Inactive for new design《航空航天 非金属编织软管 第2部分 技术规格 不适用于新设计》.pdf DIN 65164-2-2014 Aerospace - Non metallic braided cable sleevings - Part 2 Technical specification Inactive for new design《航空航天 非金属编织软管 第2部分 技术规格 不适用于新设计》.pdf
  • DIN 65165-1-2014 Aerospace - Cockpit utility lights with adjustable light intensity and colour change Inactive for new design《航空航天 灯光强度和颜色可调的驾驶舱通用照明灯 不适用于新设计》.pdf DIN 65165-1-2014 Aerospace - Cockpit utility lights with adjustable light intensity and colour change Inactive for new design《航空航天 灯光强度和颜色可调的驾驶舱通用照明灯 不适用于新设计》.pdf
  • DIN 65165-2-2014 Aerospace - Cockpit utility lights with adjustable light intensity and colour change - Technical specification Inactive for new design《航空航天 灯光强度和颜色可调的驾驶舱通用照明灯 技术规格.pdf DIN 65165-2-2014 Aerospace - Cockpit utility lights with adjustable light intensity and colour change - Technical specification Inactive for new design《航空航天 灯光强度和颜色可调的驾驶舱通用照明灯 技术规格.pdf
  • DIN 65166-1986 Aerospace wrought aluminium alloy wedge technical specifications《航空和航天 锻造铝合金楔形材 技术规范》.pdf DIN 65166-1986 Aerospace wrought aluminium alloy wedge technical specifications《航空和航天 锻造铝合金楔形材 技术规范》.pdf
  • 相关搜索

    当前位置:首页 > 标准规范 > 国际标准 > 其他

    copyright@ 2008-2019 麦多课文库(www.mydoc123.com)网站版权所有
    备案/许可证编号:苏ICP备17064731号-1