Elliptical orbiting satellites passing through the inner radiation belt are exposed to high-energy and high-flux protons and electrons. Therefore, electronic devices of satellites need to resist ultra-high cumulative radiation doses.

This study aims to propose a composite material structure for shielding space protons and electrons, instead of the traditional aluminum structure.

The interaction of elliptical orbital protons and electrons with four shielding materials (polyethylene/polypropylene, tantalum and aluminum) was simulated by the MULASSIS (Multi-Layered Shielding Simulation Software). The radiation particle energy spectrum calculated by SPENVIS software was used as the input of MULASSIS particle energy spectrum. The changes of total dose and displacement dose after shielding with areal density of the four shielding materials were compared and analyzed. Finally, the most suitable composite shielding structure was selected by considering the proton and electron shielding effects and mechanical properties of the four materials.

The results show that under same areal density, the order of the shield effectiveness from large to small, of four different materials on orbital proton and electron is polypropylene, polyethylene, aluminum and tantalum, among which polypropylene and polyethylene have almost the same shielding effect. The polyethylene-aluminum composite shielding structure is selected for construction design. The shielding targets of total dose and displacement dose to ensure the reliable operation of elliptical satellites are 50 krad(Si) and 2×10¹⁰ p?cm^-2 (equivalent to 10 MeV protons) respectively.

Compared with the single aluminum shield, at least 27.8% shielding mass is saved by using the polyethylene-aluminum composite protective structure in the above ratio.