ISO 14303:2002 pdf download

ISO 14303:2002 pdf download.Space systems -Launch-vehicle-to-spacecraft interfaces.
5.6 In-flight telemetry
A description shall be made of the type of SC data that can be transmitted to the LV ground stations via LV TM on a standard basis or as options:
dynamic, acoustic and thermal environment at the SC interface;
specific internal SC measurements.
5.7 Power supply
A general description of electrical circuits associated with the electrical power supply shall be made. Optionally, a schematic drawing of the corresponding electrical circuits may be included. The following main electrical characteristics shall be indicated, together with the tolerances:
— voltage (volts);
— current (amperes);
insulation on the SC side;
— protection on the SC side;
EMC.
5.8 Earth potential (ground) continuity
The SC requirements for electrical continuity with respect to the Earth potential (ground) shall be expressed as follows:
location of SC reference point or points;
— maximum resistance between SC metallic elements and the closest reference point;
— maximum resistance of SC interlace separation plane.
6 RFlelectromagnetic interface
6.1 General
This clause identifies the interface parameters required to define the RE interface and electromagnetic interlaces between the SC and LV. SC, LV and LV range RF emissions shall be jointly evaluated to determine compatibility and possible restrictions. For the methodology for verifying these interfaces, see clauses 9 and 10.
6.2 RF telemetry and command link
The LV contractor shall provide TM and command links between the corresponding antennae of the encapsulated SC and the SC system test equipment located in the SPF.
The link shall be enabled by RF window, pick-up antenna or other equivalent methods associated with the LV PLF. The link shall be available from the time of encapsulation of the SC on the LV until launch, except when RF transmission is limited by LV activities. The SC TM and command frequency bands shall not overlap the LV frequencies.
7.4.3 Launch windows
For SSOs, launch window constraints are driven by the local time of the SC orbit and the LV performance. Any
additional LV or launch site constraints shall be indicated.
7.5 Low Earth orbit (LEO) missions
7.5.1 Performance
The performance capability of the LV for low Earth circular orbits shall be described by means of graphs showing
the variation of the payload mass as a function of orbit altitude (see Figure C.4).
7.5.2 LV Injection accuracy
The injection accuracy of the LV into a typical low earth circular orbit shall be described in terms of orbital parameters specific to circular orbits (see 7.3.2).
As a minimum, the standard deviations (1 o-) of the typical circular orbit parameters shall be given; optionally, covariance matrix of the same parameters, or an equivalent set of LV state parameters, may be provided.
7.5.3 Launch windows
If the LV or the launch site have launch window constraints, these shall be indicated.
7.6 Escape missions
7.6.1 Performance
The performance capability of the LV for escape orbits shall be described by means of graphs showing the variation of the payload mass as a function of the square of the escape velocity, v, for typical declinations of the escape velocity with respect to the equatorial plane (see Figure C.5).
7.6.2 LV Injection accuracy
The injection accuracy of the LV into a typical escape orbit shall be described in terms of parameters specific to escape missions.
As a minimum, the standard deviations (lo-) of the typical escape orbit parameters shall be given (optionally, a covariance matrix of the same parameters, or an equivalent set of LV state parameters, may be provided):
7.6.3 Launch windows
For escape missions, launch window constraints are driven by the orientation of the escape velocity vector in inertial space and the LV performance. Any additional LV or launch site constraints shall be indicated.
7.7 Circular Earth orbit missions
7.7.1 Performance.