Methodological principles of space vehicle design for the maximum energy supply of the payload

The design of a spacecraft at the initial stages is carried out in the presence of uncertainties in terms of parameters and conditions. Determination of design parameters is carried out step by step: determination of nominal values of design parameters, normalization of resource reserves (mass, volume, energy consumption) according to design parameters to parry uncertainties, designing a spacecraft for marginal resources. The operation of a spacecraft with an electrical load switched on includes several stages: launching into the target orbit, putting into regular operation, regular operation for the intended purpose, decommissioning from the intended use in case of emergencies. The power supply system is designed to provide uninterrupted autonomous power supply to the onboard equipment in all modes and at all stages during the period of active existence of the spacecraft, taking into account the presence of shadow sections of the orbit from the Earth and the Moon. In this article, methodological principles for designing a spacecraft for the maximum power supply of the payload in the presence of uncertainties in parameters and conditions are developed. Mathematical models for calculating the parameters of the energy balance of the spacecraft have been developed for various options for realizing the power of the session load, depending on the level of illumination of the orbit and the period of operation of the spacecraft. The effectiveness of using the methodological principles of designing a spacecraft for the maximum power supply of the payload, depending on the level of illumination of the orbit and the period of operation of the spacecraft, has been evaluated. A technique has been developed for rationing reserves by spacecraft energy resources to parry uncertainties in terms of parameters and conditions, as well as the principles of its application when designing a spacecraft for maximum payload power supply.