In order to obtain the optimal aerodynamic shape of the return capsule under hypersonic conditions during the overall scheme design stage of the small cargo return capsule, an optimization platform is built based on Isight software, and an optimization model is established with the lift-drag ratio and drag coefficient as optimization objectives and the head stagnation point heat flux, cargo hold volume utilization rate and cargo hold volume as constraint conditions. The aerodynamic shape of small cargo reentry capsule is optimized. In order to improve the precision of single objective optimization, different combination optimization algorithms are proposed to give full play to the advantages of global optimization algorithm being insensitive to initial value, strong global convergence, fast convergence and high precision of numerical optimization algorithm. The optimization results show that the error of the aerodynamic parameters calculated by the model based on modified Newton theory is less than 5%, and the prediction accuracy is high. The lift to drag ratio is increased by 27.7% with the single objective optimization. It is found that in order to obtain the maximum volume, we should not only use the volume ratio as the constraint condition, but also add the volume as the constraint condition to carry out optimization. And the single objective optimal solution is only a particular solution of Pareto multi-objective optimal solution set. Therefore, the optimization platform can be applied in the design and selection of small cargo return capsule, providing good support for the shape optimization of return capsule.