| Name of the Spacecraft | Tipology of the Spacecraft | COSPAR ID | SATCAT id | Date of the Event | Status at the time of the event | Consequence | Notes/Details | Sources |
| Anik E1 | Satellite | 1991-067A | | 20-Jan-1994 | Active | Temporary failure | Two geostationary satellites of the same type suffered similar problems likely caused by a space weather event. In both cases, the momentum wheel control circuitry is thought to have been disabled by an electrostatic discharge, resulting in a loss of control. The control was later re-established. | http://sat-nd.com/failures/ |
| | | | | | | | https://space.skyrocket.de/doc_sdat/anik-e.htm. https://agupubs.onlinelibrary.wiley.com/doi/full/10.1029/2012SW000811 |
| Anik E2 | Satellite | 1991-026A | | ⬆️ | Active | Temporary failure | ⬆️ | |
| MAR-ECS-1 (MARECSA) | Satellite | 1981-122A | 13010 | 33322 | Active | End of mission. | Complete failure of the satellite due to serious damage to its solar panels. | Bedingfield, K.L. & Leach, R.D., Spacecraft System Failures and Anomalies Attributed to the Natural Space Environment. National Aeronautics and Space Administration Marshall Space Flight Center. August 1996. p. 6 |
| Telstar 401 | Satellite | 1993-077A | 22927 | 9-Oct-1994 | Active | Temporary failure | One hour service distruption due to electrostatic discharge and stabilization briefly lost. | The Space Review, Airclaims, October 25, 1994, p. ATLAS 5/D Bedingfield, K.L. & Leach, R.D., Spacecraft System Failures and Anomalies Attributed to the Natural Space Environment. National Aeronautics and Space Administration Marshall Space Flight Center. August 1996. |
| BS-3A | Satellite | 1990-077A | | 34387 | Active | Temporary failure | 60 minutes telemetry outage due to an electrostatic discharge | “Mobile Satellite Reports,” Vol. 15, No. 12, June 21,1991 The Space Review, Airclaims, September 21, 1994, p. N&H 4/B. |
| GMS-4 (Himawari 4) | Satellite | 1989-070A | 20217 | Jan-1991 and Jul-1991 | Active | Temporary failure | Visible Infrared Spin Scan Radiometer changes in state due to electrostatic discharges | Spacecraft Anomaly Database, Version. ANOM5I, National Geophysical Data Center, Solar-Terrestrial Physics Division, Boulder CO, March 1994. |
| Intelsat 511 | Satellite | 1985-055A | 15873 | Aug-1993 | Active | Temporary failure | Attitude control system distruption and uncommanded status changes due to electrostatic charging events | Spacecraft Anomaly Database, Version. ANOM5I, National Geophysical Data Center, Solar-Terrestrial Physics Division, Boulder CO, March 1994. |
| Intelsat 510 | Satellite | 1985-025A | 15629 | Aug-1993 | Active | Temporary failure | Attitude control system distruption and uncommanded status changes due to electrostatic charging events | Spacecraft Anomaly Database, Version. ANOM5I, National Geophysical Data Center, Solar-Terrestrial Physics Division, Boulder CO, March 1994. |
| AMPTE/CCE | Satellite | 1984-088A | | 30997 | Active | Temporary failure | Data modulation lost due to a phantom command caused by spacecraft electrostatic charging. Operating procedures changed in order to keep the satellite operational. | Shockley, Edward, F., Orbital Anomalies in Goddard Spacecraft 1984, Assurance Requirements Office, Office of Flight Assurance, NASA Goddard Space Flight Center, September 1985. |
| GOES-6 | Satellite | 1983-041A | 14050 | 27-Sep-1986 | Active | Temporary failure | Uncommanded shift in its Visible Infrared Spin Scan Radiometer Atmospheric Sounder (VAS) Earth window due to electrostatic discharge. Due to the same reason the satellite experienced on March 17, 1986 an automatic recalibration of its X-ray scan. | Spacecraft Anomaly Database, Version. ANOM5I, National Geophysical Data Center, Solar-Terrestrial Physics Division, Boulder CO, March 1994. Elsen, William, G., Orbital Anomalies in Goddard Spacecraft for CY 1986, Assurance Requirements Office, Office of Flight Assurance, NASA Goddard Space Flight Center, April 1987. |
| GOES-4 | Satellite | 1980-074A | 11964 | 29674 | Active | Severe failure. | The mirror used with the Visible Spin Scan Radiometer- Atmospheric Sounder (VAS), the principle instrument on the spacecraft, suffered phantom commands that began a sudden, undesired repositioning making it impossible to track the Earth’s weather until a new series of commands was issued by controllers on Earth. This happened because a portion of the VAS second stage radiation cooler was ungrounded and built up potential from the surrounding plasma until it discharged, creating a large electromagnetic pulse. This pulse created large current surges that flowed along the wiring to the VAS. This kind of anomaly was recurrent and lead, on November 25, 1982 to the complete fail of the system. The satellite was decomissioned. | Farthing, Winifred, H., Brown, James, P., and Bryant, William, C., Differential Spacecraft Charging on the Geostationary Operational Environmental Satellites, NASA Technical Memorandum 83908, Goddard Space Flight Center, Greenbelt Maryland, March 1982. |
| Meteosat-F1 | Satellite | | | 1977-1980 | Active | Temporary failure | 150 anomalies due to electrostatic discharges. The second satellite of Meteosat constellations (Meteosat-2) was modified in order to solve some of these issues and also was equipped with electrons measurement instrumentation. | Hodge, D., and Leverington, D., “Investigation of Electrostatic Discharge Phenomena on the Meteosat Spacecraft,” ESA Journal, Vol. 13, 1979, p. 101- 113 |
| DSCS-2 (9431) | Satellite | 1971-095A | | 2-Jun-1973 | Active | End of mission | Failed because power to its communications subsystem was suddenly interrupted. The review board found that the failure was due to a high energy discharge caused by spacecraft charging as a result of a geomagnetic substorm. | Inouye, George, T., “Spacecraft Charging Anomalies on the DSCS II Launch 2 Satellites,” Proceedings of the Spacecraft Charging Technology Conference, NASA Lewis Research Center, February, 1977, p. 829-852. |
| TSS (Tethered Satellite System) | Satellite | | | 34755 | Active | End of mission | The satellite was developed to study the electrodynamics of tethers that might be used to generate power in space. The 20-kilometre cable was made by kevlar, nomex, copper wire and a teflon sheath. After five hours the tether snapped. It was eroded by an electrical discharge into the ambient plasma. | Harland, David M. & Lorenz, Ralph D., Space Systems Failures. Springer-Praxis, 2005. P.274 |