The adversary aligns operations with heightened solar/geomagnetic activity so effects resemble natural disturbances. During storms, receivers struggle with scintillation and increased noise; SEUs and resets rise; navigation and timing degrade; and operators expect anomalies. By conducting EMI, spoofing, or timing-sensitive sequences within these windows, the attacker benefits from ambient interference and plausible attribution to space weather. Telemetry gaps, link fades, or transient upsets appear consistent with the environment, delaying suspicion that a deliberate action occurred.
| ID | Name | Tiering | Description | NIST Rev5 | ISO 27001 | Onboard SV | Ground | |
| CM0085 | Electromagnetic Shielding | Spacecraft electronics are vulnerable to natural ionizing particle radiation and intentional electromagnetic threats such as high-power microwave and electromagnetic pulse effects. Both may cause transient upset or permanent damage, but they act through different physical mechanisms and require distinct protections. Conductive enclosures and associated electromagnetic protection reduce fields and induced transients from HPM or EMP, while particle-radiation shielding reduces the dose or particle environment reaching susceptible components. The spacecraft design must address particle-radiation protection and HPM or EMP protection as coordinated but separately verified requirements. Enclosure materials, geometry, penetrations, bonding, and component placement should be evaluated together so that protection against one environment does not create unacceptable mass, thermal, electrical, or secondary-radiation effects in another. Shielding is primarily a design- and integration-phase hardware control and generally cannot be increased after launch. It must be combined with component hardness assurance and electrical protection measures sufficient to meet the mission’s residual susceptibility requirements. | CP-13 PE-18 PE-19 PE-21 PE-9 | A.5.29 A.7.5 A.7.8 A.7.11 A.7.12 A.5.10 A.7.5 A.7.8 A.7.5 A.7.8 A.8.12 | ||||