A ground power unit for providing electrical energy for aircraft, the ground power unit comprising: - a base frame; - a cable system, which is formed in the base frame; - at least one rectifier module for converting an input alternating voltage applied to a rectifier module input side into an intermediate direct voltage output at a rectifier module output side, wherein the rectifier module output side is coupled to an intermediate circuit conductor; - at least one inverter module for converting the intermediate direct voltage applied to an inverter module input side into an output alternating current which is output at an inverter module output side, wherein the inverter module input side is coupled to an intermediate circuit conductor; characterized in that the rectifier module and the inverter module are each realized as units formed to be structurally independent, which can be replaced individually and independently of the base frame, and that at least two rectifier modules are formed, which are electrically connected in parallel with one another, and/or that at least two inverter modules are formed, which are electrically connected in parallel with one another, and that a load distribution system is formed, which is configured such that a load distribution between the rectifier modules and/or between the inverter modules can be carried out in an automated manner. - a base frame; - a cable system, which is formed in the base frame; - at least one rectifier module for converting an input alternating voltage applied to a rectifier module input side into an intermediate direct voltage output at a rectifier module output side, wherein the rectifier module output side is coupled to an intermediate circuit conductor; - at least one inverter module for converting the intermediate direct voltage applied to an inverter module input side into an output alternating current which is output at an inverter module output side, wherein the inverter module input side is coupled to an intermediate circuit conductor; characterized in that the rectifier module and the inverter module are each realized as units formed to be structurally independent, which can be replaced individually and independently of the base frame, and that at least two rectifier modules are formed, which are electrically connected in parallel with one another, and/or that at least two inverter modules are formed, which are electrically connected in parallel with one another, and that a load distribution system is formed, which is configured such that a load distribution between the rectifier modules and/or between the inverter modules can be carried out in an automated manner. characterized in that the rectifier module and the inverter module are each realized as units formed to be structurally independent, which can be replaced individually and independently of the base frame, and that at least two rectifier modules are formed, which are electrically connected in parallel with one another, and/or that at least two inverter modules are formed, which are electrically connected in parallel with one another, and that a load distribution system is formed, which is configured such that a load distribution between the rectifier modules and/or between the inverter modules can be carried out in an automated manner.