BS ISO 16679:2015 pdf free

BS ISO 16679:2015 pdf free.Space systems – Relative motion analysis elements after LV/SC separation
The fllowing 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).
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 without taking into account Sc manoeuvre, attitude control,etc. into account,
b) SC evaluates it does not collide with LV orbital stage or other SC (for multi-SC launch mission) after separation due to its manoeuvre, attitude control, etc, based on the result of LV relative motion analysis.
The general process is described in Figure 1, where Party A represents LV and Party B represents SC.The final safety evaluation should be performed based upon LV’s and SC’s analysis. If necessary input can be offered, the aforementioned processes a) and b) can be incorporated.
The astrodynamics modelling can be achieved in different coordinate systems. One alternative centroid motion model in an Earth-fixed coordinate system is offered in Annex A for information. Motion analysis of different objects should be conducted in the same coordinate system.
Gravity, atmosphere force models and related parameters shall be dealt in accordance with the trajectory/orbit calculation.BS ISO 16679 pdf download.