Abstract: A system for monitoring the state of an unmanned aircraft includes a first communication unit, a second communication unit that can be integrated within the aircraft, a state transmission unit that can be integrated within the aircraft for transferring state data of the aircraft, a receiving unit integrated within the aircraft for receiving control commands, a computing unit assigned to the aircraft for validating the state of the aircraft, and an external control and monitoring unit connected to the computing unit. The computing unit executes a simulation model of the aircraft, which is based on numerical integration of a system of equations with a simulation state vector. The computing unit sends a warning signal to the control and monitoring unit on the occurrence of one or repeated instances of a model error correction term exceeding specified interval limits.

Abstract: A system for monitoring the state of an unmanned aircraft includes a first communication unit, a second communication unit that can be integrated within the aircraft, a state transmission unit that can be integrated within the aircraft for transferring state data of the aircraft, a receiving unit integrated within the aircraft for receiving control commands, a computing unit assigned to the aircraft for validating the state of the aircraft, and an external control and monitoring unit connected to the computing unit. The computing unit executes a simulation model of the aircraft, which is based on numerical integration of a system of equations with a simulation state vector. The computing unit sends a warning signal to the control and monitoring unit on the occurrence of one or repeated instances of a model error correction term exceeding specified interval limits.

Abstract: A drive system for an aircraft has a first energy store for supplying electrical energy, a second energy store for supplying electrical energy, and an electric drive for supplying drive power for the aircraft. An energy distribution unit of the drive system is designed to transmit the supplied electrical energy of the first energy store and the supplied electrical energy of the second energy store to the electric drive. The energy distribution unit is also designed to charge the second energy store using a first portion of the energy supplied by the first energy store and at the same time to transmit a second portion of the energy supplied by the first energy store to the electric drive, in order to supply the drive power for the aircraft. An aircraft having a drive system and a method for supplying drive power for an aircraft are disclosed.