REG NASA-LLIS-0773--2000 Lessons Learned Design Practice to Control Interference from Electrostatic Discharge (ESD).pdf

《REG NASA-LLIS-0773--2000 Lessons Learned Design Practice to Control Interference from Electrostatic Discharge (ESD).pdf》由会员分享，可在线阅读，更多相关《REG NASA-LLIS-0773--2000 Lessons Learned Design Practice to Control Interference from Electrostatic Discharge (ESD).pdf（4页珍藏版）》请在麦多课文档分享上搜索。

1、Best Practices Entry: Best Practice Info:a71 Committee Approval Date: 2000-04-11a71 Center Point of Contact: JPLa71 Submitted by: Wilson HarkinsSubject: Design Practice to Control Interference from Electrostatic Discharge (ESD) Practice: Minimize the adverse effects of electrostatic discharge (ESD)

2、on spacecraft by implementing the following three design practices:1. Make all external surfaces of the spacecraft electrically conductive and grounded to the main structure.2. Provide all internal metallic elements and other conductive elements with an “ESD conductive“ path to the main structure.3.

3、 Enclose all sensitive circuitry in an electrically conductive enclosure- a “Faraday cage“.Abstract: Preferred Practice for Design from NASA Technical Memorandum 4322A, NASA Reliability Preferred Practices for Design and Test.Minimize the adverse effects of electrostatic discharge (ESD) on spacecraf

4、t by implementing the following three design practices:1. Make all external surfaces of the spacecraft electrically conductive and grounded to the main structure.2. Provide all internal metallic elements and other conductive elements with an “ESD conductive“ path to the main structure.3. Enclose all

5、 sensitive circuitry in an electrically conductive enclosure- a “Faraday cage“.The first two practices should dissipate most electric charges before a difference in potential can become high enough to cause an ESD. If a discharge occurs, the third practice lowers the coupling to sensitive circuits,

6、reducing the probability or severity of the interference.All external dielectric surfaces such as windows, radomes and solar panels are coated to make them slightly conductive without destroying their transparency to optical/IR/RF radiation. Cost and performance trade-offs must be made in order to s

7、elect suitable materials for each application. The conductive layer should be less than 109ohms per square and connected to structural ground.All internal metallic elements, greater than 3 cm2in area or 25 cm in length, including unused wires in cables, connectors, circuit board traces, spot shields

8、, and other conductive elements, have a conductive path to ground with a resistance less than 100 MW. Small metallic objects ( 3 cm2) may be ungrounded if grounding is not practical.Each metallic layer of thermal blankets is grounded to the main structure.All external metallic components are electri

9、cally connected to the common ground of the main structure.All electronics are enclosed in a Faraday cage shielded enclosure. External cabling outside of the Faraday cage are shielded by means of overshields with 360 degree backshells at the Faraday cage Provided by IHSNot for ResaleNo reproduction

10、or networking permitted without license from IHS-,-,-entry. Sensitive circuits should use independent, balanced wiring with each lead and its return twisted together.Filter all circuits coming into the Faraday cage; low-pass filters and transient suppressors are typical, but digital logic discrimina

11、tors have also been used. Avoid the possibility of high differential voltages between components by connecting all conductive materials to a common ground.In the case of large structures, such as Space Station, surface charging can be controlled by use of an external ionizing plasma source.Since it

12、is impractical to duplicate the space plasma environment, testing for ESD resorts to resistance measurement on one hand and circuit immunity to artificial discharges on the other hand. The requirements for each of these conditions depend on the spacecraft charging conditions anticipated for the part

13、icular orbit that the spacecraft will occupy.All spacecraft designers must consider space charging in the spacecraft design. Space charging arises when materials are immersed in an energetic space plasma. Different materials with different surface resistivities produce voltage gradients which can bu

14、ild up until the voltage breakdown limit is exceeded. When this occurs, a discharge is produced which causes transients in electrical circuitry and degradation or redeposition of material.References1. Purvis, C., Garrett, H., Whittlesey, A., Stevens, N. (1984), “Design Guidelines for Assessing and C

15、ontrolling Spacecraft Charging Effects,“ NASA Technical Paper 2361. (This paper has an extensive bibliography.)2. Surface Charging/ESD Analysis, Reliability Preferred Practice No. PD-AP-13013. Thick Dielectric Charging/Internal Electrostatic Discharge (Draft), Reliability Preferred Guideline No. PD-

16、AP-1316Impact of Non-Practice: ESD events can cause transient voltage spikes on sensitive circuits which can corrupt data, produce false commands, or cause system failure. Degradation of surface material can result from arcing or redeposition of material on other surfaces if precautions are not obse

17、rved.Related Practices: N/AAdditional Info: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Approval Info: a71 Approval Date: 2000-04-11a71 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-,-,-