A narrow band antenna is configured to guide a munition toward a target location during a flight of the munition from a launch location toward the target location. The antenna has a first mode of operation operable during a first portion of the flight at a first bandwidth, and a second mode of operation operable during a second portion of the flight at a second bandwidth, the second bandwidth being a harmonic of the first bandwidth, and may be a third harmonic of the first bandwidth. The method includes transmitting a target location information to the munition in the first bandwidth during the first portion of the flight and then transmitting the target location information to the munition in the second bandwidth during the second portion of the flight. The first band may be X-band and the second band may be Ka-band.

A follow-on object for use in a salvo mission in which one or more lead objects (LO) and a follow-on object track a target. A track state of a tracked object within a sensor field-of-view (FOV) of the follow-on object is initialized. Target-state estimator (TSE) processing based on sensor measurements from the sensor FOV is performed to maintain the track state of the tracked object. Kinematic characteristics of the tracked object are evaluated based on the sensor measurements to compute a probability that the tracked object is an LO based on the evaluated kinematic characteristics. If the probability is not greater than a threshold, the tracked object is designated as the target and TSE processing is resumed. Otherwise, the tracked object is designated as an LO and the track state is re-initialized and the track of the LO is excluded from some intercept task considerations.

A radar antenna includes a plurality of horns in the annular space of a munition nose cone. The horns are disposed near the exterior surface of the nose cone. In a further aspect, the nose cone may be injection molded or additively manufactured so that the horns are embedded a known distance from the exterior surface. In a further aspect, the horns placed in either a transmit mode or a receive mode so as to maintain a minimum special separation between transmitting horns and receiving horns.

An electronically scanned array is comprised of a plurality of radiating horns embedded in a nose cone. The radiating horns are configured as an electronically scanned array. The nose cone comprises a dielectric material with a known thickness in front of the radiating horn opening. Each radiating horn is driven by a phase shifter. The phase shifters are configured to produce a radiation pattern with attenuated side lobes.

A missile, in particular a guided missile, has a missile body and a radar sensor unit for acquiring a target object. The radar sensor unit contains at least one radar antenna, strip-shaped in the longitudinal direction, that is mounted or integrated on a circumferential surface of the missile body such that the longitudinal direction of the at least one strip-shaped radar antenna is aligned in the direction of the missile longitudinal axis.

A method for controlling at least one missile radar sensor moving along a trajectory with a missile. The missile radar sensor is set up to recognize a target object. The operating parameters for modulation of the missile radar sensor are adaptively adjusted during the movement along the trajectory depending on target object data on the target object.

In a guiding device, a communication device receives a signal containing detection data of a target, and a processing unit. In the processing unit, a course setting section sets a flight course for a lofted flight based on the detection data, and a guiding section determines a progressing direction based on the flight course and outputs a guidance signal containing the progressing direction. The course setting section sets a first flight course when the flying object is launched. Also, the course setting section changes the first flight course to a second flight course based on the detection data after launching of the flying object.

A missile controller guides a missile along a flight path to a stationary or moving target object. The missile controller has at least one side-looking sensor, configured to record surroundings data and has a field of view aligned transverse to the longitudinal axis of the missile, and a control unit having a reception unit for receiving target object data regarding the target object. The target object data containing position data, orientation data and/or speed data of the target object. The control unit is configured to set the orientation of the missile during the guidance at least partly based on the received target object data such that the target object is located in the field of view of the side-looking sensor at least in sections of a final guidance phase.

A rescue system includes a wearable article, such as a wristband, which includes a radio frequency identification (RFID) tag, a radio frequency (RF) beacon, and a power supply. One or more RFID readers (collectively, an RF network) are located on a vessel, the RFID readers being configured to communicate with the RFID tag. Should the RF network detect a passenger overboard event, a modular rocket system is deployed. The modular rocket system comprises a guidance module, the guidance module including a guidance system for guiding the modular rocket system toward a target. A flight control module is removably attached to the guidance module, said flight control module including a plurality of airfoils. A flotation module is removably attached to the flight control module, said flotation module including a flotation device. A rocket motor module removably attached to the flotation module, said rocket motor module including a rocket motor configured to propel the modular rocket system.

A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a reoriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value.