BS ISO 16679:2015 pdf download – Space systems — Relative motion analysis elements after LV/SC separation 1 Scope This International Standard provides relative motion analysis elements after LV/SC separation,ncluding 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. 2 Normative reference The following documents, in whole or in part, are normatively referenced in this document and are indispensable for its application. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. ISO 14303, Space systems — Launch-vehicle-to-spacecraft interfaces 3 Terms and definitions For the purposes of this document, the terms and definitions given in ISO 14303 and the following apply. 3.1 LV/SC separation event of disconnection between LV/SC under the control of LV 3.2 relative motion analysis analysis to predict the relative distance of spacecraft(s) to objects (end stage of LV and others generated during the separation) after the LV/SC separation 3.3 separation velocity relative speed to LV when separation is completed instantly 4 Abbreviated terms LV launch vehicle SC spacecraft ICD interface control document RMS root mean square 5 Input for analysis The following information shall be included as analysis input. a) Theoretical velocity, position, attitude of LV and (each) spacecraft at the separation moment, which shall be presented in pre-determined coordinate system. Velocity and position vectors shall be offered in the format as Vx, Vy, Vz, X, Y, Z. The potential reference frames are offered in Annex C. b) Separation velocity, mass and inertia characteristics of separation bodies. c) Deviations of LV and separation parts [mass, thrust, impulse, moment-inertial characteristics (optional), tailed-effect, etc.]. d) Manoeuvres or other operations which shall affect LV end-stage orbit, related parameters and sequences. e) Manoeuvres or other operations which shall affect SC orbit, related parameters and sequences (optional). 6 General process In actual flight, relative motion after LV/SC separation is affected by many factors, including certain operations, deviations, mission profile, etc. on both sides. However, in order to simplify collaborations in applications of launch services, LV and SC parties shall perform the following processes: a) LV conducts relative motion analysis...
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