Systemic design of the very-high-resolution imaging payload of an optical remote sensing satellite for launch into the VLEO using an small launch vehicle.

The very low Earth orbit (VLEO), which includes orbits with altitudes of 100-450 km, has distinct advantages for remote-sensing spacecraft. Lower altitudes allow payloads with smaller dimensions, weight, and power to achieve performances similar to or better than larger payloads in higher orbits in remote sensing and Earth observation missions. The most important advantage of low orbits for optical imaging systems is the higher resolution these payloads can attain. The present paper systemically designs the very high-resolution imaging payload of an optical remote sensing satellite for operations in the VLEO. The aim of this design is to achieve a high spatial resolution of the optical imaging platform and reach a 1-m ground sampling distance (GSD) as reported. Therefore, considering an orbital altitude of 300 km and system calculations, the implementation of this method is described. The results obtained show that the proposed platform (VHR4) has better diffraction-limited ground resolution compared to several examples of operational satellite platforms under approximately equal orbital conditions. Also, by calculating and estimating the weight, power, and dimensions of the proposed imaging platform (VHR4), it is shown that the platform meets the requirements of a small satellite launcher in terms of weight, dimensions, and power.