ISO 27852-2024 PDF

Full title and description

St ISO 27852-2024 — Space systems — Estimation of orbit lifetime. Third edition (2024). Specifies methods, modelling approaches and recommended resources for predicting long‑duration orbit lifetime and orbital decay for spacecraft, launch vehicle stages, upper stages and associated debris in LEO‑crossing orbits following mission completion.

Abstract

This standard defines a process for long‑duration orbit lifetime prediction for space objects in low Earth orbit and LEO‑crossing trajectories after mission end‑of‑life. It clarifies acceptable modelling approaches and sources for solar and geomagnetic activity, guidance on atmosphere model selection and inputs, methods for estimating spacecraft ballistic coefficient and recommended practices for uncertainty assessment and documentation of lifetime predictions.

General information

• Status: Published
• Publication date: 23 February 2024
• Publisher: International Organization for Standardization (ISO)
• ICS / categories: 49.140 (Space systems and operations)
• Edition / version: 3rd edition (2024)
• Number of pages: 48

Scope

ISO 27852:2024 applies to prediction of orbit lifetime (orbital decay) for spacecraft, launch vehicles, upper stages and fragments/debris in low Earth orbit and LEO‑crossing orbits after their mission phase (including possible mission extensions). It covers selection and use of atmosphere and solar/geomagnetic input models, approaches to determine ballistic coefficients, recommended data inputs, and methods to quantify and report uncertainty in long‑term lifetime estimates. It does not set operational clearance limits or collision-avoidance procedures but supports engineering assessments and end‑of‑life planning.

Key topics and requirements

• Defined process for long‑duration orbit lifetime prediction, including lifecycle and scenario definition.
• Guidance on selection and use of atmosphere models (for example empirical thermospheric density models) and how to justify model choice for different altitude regimes.
• Recommendations for solar and geomagnetic activity modelling and sources to represent long‑term variability and extremes.
• Methods for estimating the spacecraft ballistic coefficient (mass, cross‑sectional area, drag coefficient) and handling configuration / attitude uncertainties.
• Requirements for uncertainty analysis and sensitivity studies to support confidence bounds on lifetime predictions.
• Consideration of mission end‑of‑life scenarios (controlled reentry, passivation, disposal to graveyard orbits, natural decay) and how those scenarios affect lifetime estimates.
• Data and documentation practices for reproducible lifetime assessments and reporting of assumptions, inputs and model versions.

Typical use and users

Used by spacecraft and mission designers, orbital analysts, space debris mitigation planners, space agencies, launch service providers, satellite operators, insurers and regulatory bodies. Typical applications include end‑of‑life planning, compliance with debris‑mitigation requirements, risk assessment for reentry and long‑term orbital population studies.

Related standards

Commonly referenced standards and technical reports in the same domain include ISO 24113 (Space debris mitigation requirements), ISO 23312 (detailed debris mitigation requirements for spacecraft), ISO/TR 18146 (space debris mitigation design and operation guidance), ISO 19389 (conjunction data message), ISO 26900 (orbit data messages) and other ISO space systems standards addressing rendezvous, on‑orbit servicing and reentry risk. ISO 27852:2024 replaces ISO 27852:2016.

Keywords

orbit lifetime, orbital decay, LEO, atmospheric drag, ballistic coefficient, solar activity, geomagnetic activity, re‑entry, space debris mitigation, lifetime prediction, uncertainty analysis

FAQ

Q: What is this standard?

A: ISO 27852:2024 is an international standard that specifies methods and guidance for estimating the long‑term orbit lifetime (orbital decay) of spacecraft, upper stages and debris in LEO‑crossing orbits.

Q: What does it cover?

A: It covers the prediction process, selection of atmosphere and solar/geomagnetic input models, approaches for estimating ballistic coefficient, uncertainty and sensitivity analysis, and documentation practices for lifetime assessments after mission end‑of‑life.

Q: Who typically uses it?

A: Satellite and spacecraft designers, orbital analysts, space agency mission planners, satellite operators, insurers and regulators use it to support end‑of‑life planning, debris‑mitigation compliance and reentry risk assessments.

Q: Is it current or superseded?

A: Current. This is the 3rd edition, published 23 February 2024; it replaces the 2016 edition (ISO 27852:2016).

Q: Is it part of a series?

A: It is part of the family of ISO space systems and space debris standards and is commonly used together with standards such as ISO 24113 (debris mitigation), ISO 23312, ISO/TR 18146 and related orbit data messaging and conjunction reporting standards.

Q: What are the key keywords?

A: orbit lifetime, LEO, atmospheric drag, ballistic coefficient, solar activity, geomagnetic activity, reentry, space debris mitigation.