a. The effect of the parts packaging in the radiation shielding model shall be assessed as follows:
1. Place the target point inside the package, located on top or inside the active region of the volume
NOTE The objective is to get the best possible estimate of the deposited dose at die level, the target point. The active region is typically a silicon chip.
2. For hybrid devices containing several sensitive dies, use one target point per die.
NOTE The reason is that the calculated dose level can vary significantly depending on the die location.
3. For situations where the total ionising dose from X-ray or g-ray fields is the largest contribution, assess the influence of local high-Z materials and include it in the calculations.
NOTE Example of high-Z materials are gold contacts or tungsten silicide layers and vias.
a. The effect of the equipment in the radiation shielding model shall be assessed as follows:
1. Include in the equipment model (at least) the subsystem enclosure and printed circuit boards (PCBs), unless
(a) worst-case calculations in which they are excluded show the component can tolerate the environment to within the RDM, and
(b) it is demonstrated that the enclosure and PCB materials do not lead to radiation enhancement.
2. Either surround the target points by the actual parts package model, or use a worst case parts package.
NOTE Example of worst case parts package is an aluminium sphere with a thickness of 0,6 mm.
3. In order to get a better estimate of the radiation level, include in the model any passive element providing shielding to active elements.
NOTE Example of passive elements that can provide shielding are transformers, capacitors, and connectors.
a. The effect of the spacecraft in the radiation shielding model shall be assessed as follows:
1. Include in the spacecraft radiation model a representation of the structure and the boxes for equipments.
2. Include in the model the material, as follows:
(a) Where the dominant material used in the spacecraft is aluminium, or material of similar Z, model the spacecraft as aluminium boxes of the thickness having the size of actual enclosures, containing a reduced density of aluminium to provide the equivalent mass of the actual contents.
(b) Otherwise, model the spacecraft with the precise material and contents as for the actual subsystem.
3. Approximate the walls of the satellite to those of an aluminium box providing the equivalent areal mass.
4. Assess the shielding afforded by the satellite structure for an internal subsystem either by:
(a) Using a worst-case calculation, and assuming normal incidence of radiation on each of the faces of the satellite box, or
(b) Perform a sector shielding analysis for each subsystem location to better determine the shielding distribution.
5. If the spacecraft surface includes honeycomb panels, for worst case calculations, either:
(a) Incorporate in the radiation model only the face-panels of the honeycomb, or
(b) Agree with the customer the model to use to include the actual geometry and materials.
1. Specify the environment at (sub)system level in a way that the analysis of the (sub)system shielding and radiation effects can be made.
2. If the (sub)system has a box shape, either:
(a) Provide the dose or fluxes to each surface, or
(b) Mesh the surfaces and provide the values for each mesh element.
NOTE While useful for engineering purposes, it is important to recognise the uncertainties in this method. It can happen that the propagation directions of the radiation and possibly the type and energy of the radiation are not retained. Nevertheless, this is generally a conservative approach.
b. In any case other than requirement 6.3.2.4a, the actual internal arrangements of (sub)systems shall be provided by the customer and used by the supplier.
NOTE The satellite geometry and subsystem geometry can be exchanged between contractors and customers using available geometry exchange formats or tools.