Overview
ISO 18257:2016 - "Space systems - Semiconductor integrated circuits for space applications - Design requirements" specifies the basic design requirements and process for semiconductor integrated circuits (ICs) intended for space use. The standard defines required tasks and outputs for each design stage (architecture, logic/circuit, layout, mask, package and testing) but does not prescribe detailed circuit-level designs. It emphasizes reliability, environment adaptability and verification to ensure ICs meet space system needs.
Key topics and technical requirements
- Design process and inputs
- Convert user/mission requirements into verifiable design inputs (functional, electrical, mechanical, thermal, radiation and testability constraints).
- Typical inputs include operating frequency, power budget, interfaces, fault coverage, and space-specific constraints (radiation, vacuum thermal dissipation, charging/ESD).
- Design phases
- Architecture design: define modules, interfaces, simulation models and preliminary datasheet (see Annex A).
- Logic & circuit design: produce verified gate‑level (digital) or transistor‑level (analog) netlists with DFT considerations.
- Layout design: place-and-route with design rule checking (DRC), electrical rule checking (ERC) and layout verification.
- Mask making, packaging & testing: define mask, package structure, electrical and thermal simulation for package, and test strategies.
- Detailed requirements
- Packaging: structure, technology choices, electrical and thermal simulation and constraints.
- Reliability design: derating, fault-tolerant and redundant design, ESD/antistatic protection, low‑power design, parameter margining, EMC mitigation and radiation‑hardening considerations (SEU, SEL, SET).
- Testability: design for test (DFT), built‑in self‑test (BIST), IEEE 1149.1 boundary-scan and test access strategy.
- Normative references
Applications and users
ISO 18257:2016 is practical for:
- Space IC designers (ASIC, FPGA/PLD teams) creating components for satellites, launch vehicles and space instruments.
- Systems engineers defining component-level requirements for space missions.
- Quality & reliability engineers validating design practices for radiation, thermal vacuum and EMC robustness.
- Procurement and acceptance teams specifying design verification artifacts (datasheets, simulation reports, test plans).
Practical benefits include improved space suitability, clearer traceability from mission requirements to design outputs, and reduced risk of field failures due to environmental stresses.
Related standards
Keywords: ISO 18257:2016, space systems, semiconductor ICs, design requirements, radiation-hardened IC, reliability, IC packaging, DFT, ESD, EMC, thermal vacuum, FPGA, ASIC.
