ISO 16679:2015 PDF

Name: ISO 16679:2015 — Space systems — Relative motion analysis elements after LV/SC separation
SKU: ISO 16679:2015
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Space systems — Relative motion analysis elements after LV/SC separation

Название (английский):

ISO 16679:2015

Space systems — Relative motion analysis elements after LV/SC separation

Статус документа:: Действующий
Формат:: Электронный (PDF)
Количество страниц:: 10
Дата публикации:: 21 сентября 2015 г.
Издание:: ISO IS 16679 edition 1 version 1
ICS:: 49.140

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Описание (английский):

ISO 16679:2015 provides relative motion analysis elements after LV/SC separation, including analysis input, analysis principle, analysis method and analysis output. It is applicable to the mission design and verification for the prediction of relative motion after LV/SC separation. This International Standard focuses on the relative motion between the objects involved in one launch mission. It does not cover the issues about the collision avoidance between newly launched objects and on-orbit ones.

Abstract

Похожие стандарты

Упомянутые в описании и другие стандарты ISO

Overview - ISO 16679:2015 (Relative motion analysis after LV/SC separation)

ISO 16679:2015 defines the elements and procedures for performing relative motion analysis following launch vehicle (LV) and spacecraft (SC) separation. It is intended for mission design and verification to predict post‑separation relative motion between objects involved in a single launch mission. The standard explicitly focuses on intra‑mission relative motion and does not address collision avoidance with pre‑existing on‑orbit objects.

Key topics and technical requirements

Analysis inputs: required data include theoretical velocity, position and attitude of LV and each SC at separation (presented in a predetermined coordinate system), separation velocity, mass and inertia characteristics, and identified deviations (mass, thrust, impulse, attitude, etc.).

Analysis principle: safety-first approach; use established trajectory/orbit analysis practices (perturbations, astrodynamics) and explicitly cover deviations.

Analysis method - four mandatory elements:

Astrodynamics modelling: select and apply consistent coordinate reference frames (Annex C lists options such as ECEF, J2000, perigee orbital) and gravity/atmospheric/perturbation models.
Deviation analysis and identification: identify likely deviations (e.g., separation velocity, separation attitude, orbital stage mass, de‑orbit thrust/attitude).
Relative motion simulation: simulate for an agreed analysis period (no less than one orbit), generate deviation scenarios by margin, typical combinations (Annex B), or random sampling, then compute relative positions by subtracting trajectories.
Safety evaluation: determine minimum relative distance using deviation margins and compare with agreed safety distance, considering LV/SC dimensions and clearance margins.

Analysis outputs: international units, distance vs. time plots, conclusions and minimum relative distance. Annex D provides a reporting template.

Practical applications and users

Launch vehicle manufacturers and operators - to produce LV-side relative motion analyses.

Spacecraft manufacturers and operators - to evaluate collision risk post‑separation and plan maneuvers/attitude control.

Mission designers and verification teams - for mission design validation, safety margins, and acceptance criteria.

Systems and safety engineers - to define separation requirements and interface control data (ICD).

Typical applications include multi‑payload deployments, end‑stage disposal planning, and contractual exchanges of LV/SC separation analysis between parties.

ISO 16679:2015 PDF

Abstract

Похожие стандарты

Overview - ISO 16679:2015 (Relative motion analysis after LV/SC separation)

Key topics and technical requirements

Practical applications and users

Related standards

Технические детали

BS ISO 16679:2015

Space systems. Relative motion analysis elements after LV/SC separation.

BS ISO 14303:2002

Space systems. Launch-vehicle-to-spacecraft interfaces.

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