Overview
ISO 15862:2009 - "Space systems - Launch-vehicle-to-spacecraft flight environments telemetry data processing" - defines minimum requirements for measuring and processing spacecraft flight environments produced by a launch vehicle. The standard specifies what environmental parameters to measure, where and how to sample them, telemetry data pre‑processing and processing methods, and the formats and content of delivered data and flight environment analysis reports. Its purpose is to verify whether flight environments exceed pre‑flight analyses and test limits and to support post‑flight failure investigation.
Key topics and technical requirements
- Measurement fields: steady‑state acceleration, low‑frequency vibration, high‑frequency vibration, acoustic noise, shock acceleration, steady‑state pressure, and temperature.
- Measurement planning: flight measurement plan must list sensor identification, type, location, orientation, units, range, frequency range, sampling rate, sensitivity and accuracy.
- Number & location of sensors: minimum sensor locations are defined (e.g., near the spacecraft/launch‑vehicle interface; longitudinal and lateral axes for accelerometers; two acoustic points inside fairing).
- Sampling and ranges: frequency ranges and minimum sampling frequencies must be agreed between spacecraft (SC) and launch vehicle (LV) agencies to avoid frequency masking.
- Pre‑processing rules: telemetry quality checks, removal of corrupted segments, pseudo‑signal rejection, zero drift elimination and mean value correction for vibration signals.
- Processing methods:
- Low‑frequency vibration → Shock Response Spectrum (SRS) and equivalent sinusoidal levels (damping ratios by agreement).
- High‑frequency vibration → Power Spectral Density (PSD) and RMS envelopes.
- Acoustic noise → 1/3‑octave or one‑octave Sound Pressure Levels (SPL).
- Shock → SRS with agreed damping; discrete phases processed.
- Steady‑state parameters and temperature → time‑history plots from lift‑off through fairing jettison/separation.
- Delivered formats: tabular summaries and plots (with specified units - time in seconds, acceleration in m/s², PSD units in m²/s⁴/Hz, SPL in dB, SRS in m/s²). Electronic or hard‑copy delivery permitted.
Applications
- Verification that in‑flight mechanical and thermal loads comply with pre‑flight analyses and environmental tests.
- Support for anomaly and failure investigations by providing validated telemetry of vibrational, acoustic and shock events (e.g., fairing jettison, stage separations, transonic and max‑Q phases).
- Planning and acceptance criteria for spacecraft qualification and mission assurance activities.
Who should use this standard
- Launch‑vehicle providers and telemetry engineers
- Spacecraft manufacturers, payload integrators and systems engineers
- Test & verification teams and environmental analysts
- Mission assurance, anomaly investigation and safety teams
Related standards
ISO 15862 is part of the ISO space systems work (ISO/TC 20/SC 14) and complements other international and industry standards for spacecraft environmental testing, telemetry formats and launch safety (refer to national/international space system standard catalogs and agency requirements for specific cross‑references).