Abstract: The invention relates to a clamping ring for connecting cylindrical units of a missile, which have each a circumferential projection and a flat-conical engagement surface. The clamping ring comprises a circumferential portion bent to a arc of a circle and having two ends, which can be tightened together by means of a turnbuckle. The clamping ring has cheeks along its rims. The cheeks have flat-conical engagement surfaces corresponding to the flat-conical engagement surfaces of the circumferential projections of the cylindrical units to be connected. The clamping ring extends with the cheeks over the circumferential projections of the units. In order to increase the strength of the clamping ring by suitable shaping within a predetermined space, the inner surface of the clamping ring is free from edges and guided tightly about the outer contours of the circumferential projections.

Abstract: The invention relates to a clamping ring for connecting cylindrical units of a missile, which have each a circumferential projection and a flat-conical engagement surface. The clamping ring comprises a circumferential portion bent to a arc of a circle and having two ends, which can be tightened together by means of a turnbuckle. The clamping ring has cheeks along its rims. The cheeks have flat-conical engagement surfaces corresponding to the flat-conical engagement surfaces of the circumferential projections of the cylindrical units to be connected. The clamping ring extends with the cheeks over the circumferential projections of the units. In order to increase the strength of the clamping ring by suitable shaping within a predetermined space, the inner surface of the clamping ring is free from edges and guided tightly about the outer contours of the circumferential projections.

Abstract: The invention relates to a clamping ring for connecting cylindrical units of a missile, which have each a circumferential projection and a flat-conical engagement surface. The clamping ring comprises a circumferential portion bent to a arc of a circle and having two ends, which can be tightened together by means of a turnbuckle. The clamping ring has cheeks along its rims. The cheeks have flat-conical engagement surfaces corresponding to the flat-conical engagement surfaces of the circumferential projections of the cylindrical units to be connected. The clamping ring extends with the cheeks over the circumferential projections of the units. In order to increase the strength of the clamping ring by suitable shaping within a predetermined space, the inner surface of the clamping ring is free from edges and guided tightly about the outer contours of the circumferential projections.

Abstract: A locking assembly in a launcher for missiles comprises a pivotally mounted blocking latch which is provided with two blocking lugs for extending over a shoe provided on the missile. The blocking latch is biased by a spring toward a blocking position, in which the shoe of the missile is retained by the blocking lugs. A locking lug is provided on the blocking latch. In the blocking position the locking lug engages a safety lever having a contact surface, when inertial forces of the missile act on the blocking latch such that the blocking latch is retained in the blocking position, in which the blocking lugs extend over the shoe of the missile. The safety lever is pivotable about a pivot axis out of the pivotal path of the locking lug. The safety lever comprises means for reducing the distance between the contact surface and the pivot axis during the pivotal movement of the safety lever, such that the contact surface is removed from the locking lug during the pivotal movement.

Abstract: A locking unit for a missile launching device comprises a pivoting pawl. The pawl has two locking lugs to clamp a shoe on the missile. The pawl is preloaded by a spring towards a locking position in which the shoe of the missile is held by the lugs. A locking lug on the pawl co-operates with a safety pawl against which the locking lug bears in the locked position. The pawl is thus held in the locked position in which the shoe is gripped by the lugs. A safety pin can be fitted through a housing of the locking unit with the pawl in the locked position. This provides a check whether the system has been properly fitted and the pawl is in the correct position. To prevent errors during this check, there is a connecting link on the pawl projecting into the path of the safety pin if the pawl is not in its proper locking position.

Abstract: A gyro-stabilized seeker comprises a rotor which is mounted universally movably about a central point and arranged to be driven about a rotor-fixed axis of rotation passing through the central point, as well as an imaging optical system on the rotor which is arranged to image a field of view in a plane perpendicular to the axis of rotation of the rotor. Detector means (130) for generating target signals are located in this plane. The detector means are arranged at a structure-fixed heat-insulating cooler housing (120) and are cooled by a cooler. The axis of rotation is aligned to a target. A convexo-spherical bearing surface (124) is structure-fixedly attached to the cooler housing (120). The detector means (130) are located on a carrier (128) which is universally pivotably mounted on this convexo-spherical bearing surface (124) and are aligned by a rotor carrier (106) according to the axis of rotation of the rotor.

Abstract: An optical scanning device comprises a bearing portion (12), which is rotatably mounted in a base portion (10) about an axis of rotation (16). A holder (18) is rotatably mounted in the bearing portion (12) about an axis of rotation (22), which is eccentric with regard to the axis of rotation (16). A pair of lenses (26,38) is located eccentricly in the holder (18) and forms part of an imaging system, through which a field of view is imaged in the plane of a base portion-fixed detector. The bearing portion (12) and the holder (18) are driven in opposite directions.

Abstract: An air-to-air guided missile with solid propellant rocket motor is retained by a locking device having a blocking device during a predeterminable delay time after the rocket motor has been fired. Thereby, at high altitude or with a high speed, such a proportion of the propellant can be burnt off that the guided missile is not accelerated to an inadmissibly high speed.

Abstract: The invention relates to a device for righting and stabilizing a gyro vertical comprising: a disc arranged on the gyro housing and perpendicular to the gyro spin axis to be driven in the same sense as the gyro rotor, a cavity provided in the disc and a liquid drop movable in the cavity, the cavity being formed such that the liquid drop, with an inclination of the gyro spin axis with respect to the vertical, flows downhill into an edge portion of the cavity remote from the gyro spin axis, in which cavity it is taken along and lifted by the wall of the cavity in an angle range, thereby producing a righting torque.

Abstract: The invention relates to a device for erecting and stabilizing of a gyro vertical, comprising a disc arranged on the gyro housing and perpendicular to the gyro axis, said disc being driven in the same sense as the gyro rotor but at a reduced rate as compared thereto, and having at least one guideway, in which a mass is movably guided, the guideway being arranged such that the disc with the mass is balanced with respect to the gyro axis, when the mass abuts the rear end, with respect to the rotary movement, of the guideway, and that the movement of the mass in the guideway causes an erecting torque, when the gyro spin axis deviates from the vertical direction observed.