Abstract: A coil support and a winding arranged thereon, especially one including a fiber-optic waveguide, whose turns are mutually fixed by a binding agent. The binding agent drys while a volatile solvent diffuses off. The coil support is permeable to solvent and is designed such that it has essentially the same coefficient of thermal expansion as the winding. This achieves the uniform, thorough drying of the binding agent over the entire winding and reduces the risk of damage to the fiber-optic waveguide during the transportation and the unwinding of the winding in a coil form.

Abstract: The invention provides an apparatus for the remote control of missiles or torpedoes launched from a launching container, by means of a cable of which a portion is wound onto a supply reel connected with the launching and of which the other portion is wound onto a supply reel in the missile or the torpedo. The supply reel in the launching container is arranged on the forward end of the container, and the supply reel in the missile or torpedo is arranged on the rearward end of the missile or torpedo. The cable section between the two supply reels, before the launching of the missile or torpedo, is fastened along the major portion of its length on the interior wall of the launching container, by means of a gluing arrangement which consists of a material whose combustion temperature is at least by 800.degree. C. lower than the melting temperature of the optical waveguide, or by means of a flexible clamping arrangement whose holding force can be adjusted.

Abstract: A missile optical waveguide for the transmission of signals is wound as a package body, can be withdrawn from the package body during missile flight, and is provided with an outer coating having a rectangular outer contour and a wall thickness which is cross-sectionally non-uniform and is thickest in the corner areas of the outer coating. The coating can be provided with embedded fiber reinforcements, whereby the light-signal-transmitting glass fiber of the optical waveguide is effectively protected from unacceptably high tensile and pressure loads which interfere with the quality of the transmission. The winding volume is thereby reduced and problem-free axial withdrawal of the optical waveguide from the package body is ensured.

Abstract: A device is provided for the real-time picture transmission in the case of a guided missile which is connected with a ground guiding station by way of a beam waveguide. The picture transmission takes place using a camera arranged on a platform which has objective lenses of different focal lengths. The camera is constructed as a double focal length camera with a single lens system member having a short focal length section integrated in the center of the surrounding lens section for the long focal length. A common support is provided for the picture raise of both focal lengths. The single electronic camera system is provided for both picture arrays and includes an electronic change over system for the respective required focal length of arrays to be viewed.

Abstract: The invention relates to a picture transmission system of a guided missile which is connected with a ground facility by way of an optical wave guide. This system is arranged that, without any increase of the transmission band width of the optical wave guide, two TV pictures are transmitted to the ground guiding facility, in which case, in addition to the moving picture for the navigation of the guided missile, enlarged stationary pictures for a target identification may also be retrieved, without interfering with the picture-supported navigation. An embodiment is disclosed which includes a camera with a single fixed lens body containing a centrally disposed wide angle lens for sensing navigation aiding images and a surrounding longer focal distance lens for sensing target identification aiding images.

Abstract: The present positional gyroscope is used for stabilizing and steering a fng body, especially a secondary flying body ejected from a primary or carrier flying body which is rotating or rolling about its longitudinal or roll axis. Such gyroscopes are supposed to sense and take over the rolling position information from the gyroscope of the carrier flying body. For this purpose it is necessary that the gyroscope of the secondary flying body avoids course deviations. Hence, the gyroscope is supported in a first locked frame (3, 8) which in turn is suspended in an auxiliary rolling frame (4). A drive mechanism or motor (2) is connected to the rolling frame (4). The driving motor (2) may be switched on for rotating the auxiliary rolling frame (4) prior to activating or ejecting the secondary flying body.