Method for detecting errors of an unmanned missile that is coupled in the carrier flight mode to a carrier aircraft, - wherein the missile comprises a central on-board computer on which it is possible to run control software that is stored in a memory device for the operation of the missile, and said on-board computer also comprises a volatile random access memory device and a non-volatile, reprogrammable data storage device, - wherein the missile comprises a first energy supply for electrical energy that is supplied by the carrier aircraft, - wherein the missile comprises a second, autonomous energy supply for electrical energy that can be supplied with electrical energy from an energy storage device that is provided in the missile, and - wherein the energy storage device in the missile supplies the missile by way of the second energy supply with electrical energy if the missile receives a corresponding activating signal from a weapon control computer in the carrier aircraft, wherein the method comprises the following steps: - performing a triggered and periodic system monitoring procedure of the missile in the carrier flight mode while the missile is supplied with energy from the carrier aircraft by way of the first energy supply, - ascertaining error data that occurs in the missile during this system monitoring procedure and storing said error data in the volatile random access memory device, - transmitting the error data that is stored in the random access memory device into at least one free storage segment of the non-volatile data storage device, by way of example a flash memory storage device, as soon as a fatal error that leads to a mission abort is detected and has been stored in the random access memory, - generating a mission abort signal and transmitting this signal to the weapon control computer of the carrier aircraft and - disconnecting the first energy supply. - wherein the missile comprises a central on-board computer on which it is possible to run control software that is stored in a memory device for the operation of the missile, and said on-board computer also comprises a volatile random access memory device and a non-volatile, reprogrammable data storage device, - wherein the missile comprises a first energy supply for electrical energy that is supplied by the carrier aircraft, - wherein the missile comprises a second, autonomous energy supply for electrical energy that can be supplied with electrical energy from an energy storage device that is provided in the missile, and - wherein the energy storage device in the missile supplies the missile by way of the second energy supply with electrical energy if the missile receives a corresponding activating signal from a weapon control computer in the carrier aircraft, - performing a triggered and periodic system monitoring procedure of the missile in the carrier flight mode while the missile is supplied with energy from the carrier aircraft by way of the first energy supply, - ascertaining error data that occurs in the missile during this system monitoring procedure and storing said error data in the volatile random access memory device, - transmitting the error data that is stored in the random access memory device into at least one free storage segment of the non-volatile data storage device, by way of example a flash memory storage device, as soon as a fatal error that leads to a mission abort is detected and has been stored in the random access memory, - generating a mission abort signal and transmitting this signal to the weapon control computer of the carrier aircraft and - disconnecting the first energy supply.