REG NASA-LLIS-0788--2000 Lessons Learned Surface Charging Electrostatic Discharge Analysis.pdf

1、Best Practices Entry: Best Practice Info:a71 Committee Approval Date: 2000-04-17a71 Center Point of Contact: JPLa71 Submitted by: Wilson HarkinsSubject: Surface Charging/Electrostatic Discharge Analysis Practice: Considering the natural environment, perform spacecraft charging analyses to determine

2、that the energy that can be stored by each nonconductive surface is less than 3 mJ. Determine the feasibility of occurrence of electrostatic discharges (ESD). ESD should not be allowed to occur on surfaces near receivers/antenna operating at less than 8 GHz or on surfaces near sensitive circuits. Fo

3、r this practice to be effective, a test program to demonstrate the spacecrafts immunity to a 3 mJ ESD is required.Abstract: Preferred Practice for Design & Test. Unpredictable operational anomalies and electronic parts failure could be caused by in-flight ESD events. The consequences could be catast

4、rophic. Considering the natural environment, perform spacecraft charging analyses to determine that the energy that can be stored by each nonconductive surface is less than 3 mJ. Determine the feasibility of occurrence of electrostatic discharges (ESD). ESD should not be allowed to occur on surfaces

5、 near receivers/antenna operating at less than 8 GHz or on surfaces near sensitive circuits. For this practice to be effective, a test program to demonstrate the spacecrafts immunity to a 3 mJ ESD is required.Programs that Certify Usage: This practice has been used on the Voyager and Galileo program

6、s.Center to Contact for Information: JPLImplementation Method: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-This Lesson Learned is based on Reliability Practice number PD-AP-1301, from NASA Technical Memorandum 4322A, Reliability Preferred Practic

7、es for Design and Test.Surfaces that are conceivable electrostatic discharge (ESD) sources can be identified early in the program. Design changes such as application of a conductive coating and use of alternate materials can be implemented to eliminate or reduce the ESD risk. Preventive measures suc

8、h as the installation of RC filters on sensitive circuits also can be implemented to control the adverse ESD effects.Use a validated computer code (NASCAP or other appropriate computer code) to determine the maximum differential charging (V) of each nonconductive surface. When differential charging

9、occurs, an electric field is developed within the dielectric material. The magnitude of the electric field (E) is given by:E = V/d where d is the thickness of the dielectric material. Usually, when this electric field is greater than 2x105V/cm, ESD is likely to occur.To determine the charging level,

10、 electrical properties of the nonconductive material must be known. These properties include (but are not limited to) surface resistivity, bulk resistivity, secondary and backscatter electron emission coefficient, and photoelectron yield. For materials with unknown electrical properties, the chargin

11、g level must be determined by a ground test. In the ground test, the nonconductive surface is exposed to simulated charging environments (mission-dependent) and the resulting charging levels are measured.ESD must not be allowed to occur on surfaces near sensitive radio frequency (RF) receivers and o

12、n surfaces near sensitive circuits. For other surfaces, the energy of an ESD should be limited to 3 mJ. The ESD energy can be determined with the following equation:W = 1/2CV2where C is the capacitance of the nonconductive surface with respect to spacecraft ground. The value C depends on the geometr

13、y (area and thickness) of the nonconductive surface. The ESD energy as a function of capacitance and charging level is displayed in Figure 1. Usually, the best way to reduce the ESD energy is to limit the value of V. This usually implies the use of a more conductive material. Since the charging curr

14、ent available in the space environment is relatively low, material with resistivity of 109Ohm-cm is considered adequate for effective charge control.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-refer to D descriptionD Figure 1: ESD Energy as a Fun

15、ction of Capacitance and Voltage In an environment of energetic electrons, spacecraft surface charging can occur. Due to their high resistivities, dielectric surfaces can be charged to different potentials than the metallic surfaces (which should be at spacecraft ground potential). When the electric

16、 field that results from differential charging is sufficiently high, an ESD would occur.ESD is an intense source of electromagnetic interference (EMI). The EMI energies that can be capacitively and inductively coupled to electronic circuits are proportional to both the magnitude and rate of increase

17、 (dI/dt) of the discharge current, respectively. Under most conditions, the discharge current (I) is directly related to the energy (W) of a discharge. By minimizing the ESD energy, the magnitude of discharge current and the magnitude of ESD-induced EMI on circuits can be reduced.The typical energy

18、required to damage a sensitive IC is an order of several J. The energy required to upset a circuit is approximately 10 times less. In a typical discharge, only a fraction of the stored electrostatic energy can be coupled to a circuit. The coupling efficiency is dependent on the shielding and geometr

19、y of the spacecraft. Restricting the energy of an ESD minimizes the amount of energy available for IC damage and circuit upset, resulting in a more reliable spacecraft. In the Voyager ESD system test program, a 30 mJ discharge did not disturb spacecraft operation. However, differences in spacecraft

20、configurations and circuit protection devices (e.g., RC filters in sensitive Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-circuits) means that the “safe“ (maximum allowable) energy could be different for different spacecraft configurations. Thus,

21、3 mJ was chosen as the maximum allowable energy.Impact of Non-Practice: Unpredictable operational anomalies and electronic parts failure could be caused by in-flight ESD events. The consequences could be catastrophic.Related Practices: N/A Additional 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-,-,-