Abstract: An auxiliary device is provided for a high-altitude airplane. The auxiliary device includes a drive, which is independent of the airplane, for the ascent of the airplane into the stratosphere. The airplane is releasably coupled to the auxiliary device. The auxiliary drive is releasable from the airplane altitude on the latest on reaching a predetermined mission.

Abstract: A position indicating process includes the steps of receiving at least four radio signals emitted by different transmitter stations; determining a channel pulse response of the transmission channel for each of the received radio signals; estimating the direct signal path for each of the received radio signals based on the respectively determined channel pulse response; and determining the receiving position of the radio signals by evaluating the estimated direct signal paths of the received radio signals.

Abstract: A system for determining the position and orientation of a flying object such as a missile includes a ground segment having at least one pseudolite station located on the earth's surface which transmits into space a navigation signal that uniquely identifies the pseudolite station, and a user segment having at least one sensor which is situated in the missile and is designed to receive the navigation signal from the at least one pseudolite station and to determine its absolute position and orientation in space on the basis of the received navigation signal.

Abstract: A position indicating process includes the steps of receiving at least four radio signals emitted by different transmitter stations; determining a channel pulse response of the transmission channel for each of the received radio signals; estimating the direct signal path for each of the received radio signals based on the respectively determined channel pulse response; and determining the receiving position of the radio signals by evaluating the estimated direct signal paths of the received radio signals.

Abstract: A system for determining the position and orientation of a flying object such as a missile includes a ground segment having at least one pseudolite station located on the earth's surface which transmits into space a navigation signal that uniquely identifies the pseudolite station, and a user segment having at least one sensor which is situated in the missile and is designed to receive the navigation signal from the at least one pseudolite station and to determine its absolute position and orientation in space on the basis of the received navigation signal.