Methods and means of increasing the efficiency of the AIST-2 type spacecraft for the task of monitoring the territory of Myanmar

An analysis of the factors influencing the target characteristics and the required characteristic velocity during an orbital maneuver to improve the target characteristics of small spacecraft is presented. The analysis was performed for the AIST-2 type small spacecraft in orbits with an altitude in the range from 350 to 700 km, taking into account the angle of deviation of the optical axis of the spacecraft. To estimate the active life of the AIST-2D spacecraft, changes in air density caused by solar activity during the spacecraft’s orbiting are taken into account. In order to ensure the active life of the AIST-2 typesmall spacecraft for more than 10 years, and taking into account the fact that the target characteristics are the most stable as soon as the spacecraft descends to a certain height, the engines are started to maneuver the spacecraft to its initial height. The required characteristic speed is obtained from the height difference of the orbit that must be re-raised to solve the task of monitoring Myanmar’s territory, and based on this value, the required fuel mass, the mass of the propulsion system and the most suitable engine type are determined.