Abstract: An interferometric position sensor for sensing the position of an object is disclosed. The position sensor comprises a light source arranged to emit light, a beam splitter, and a detector array. The beam splitter is arranged to split the light between first and second optical paths, which are configured such that the split light is recombined so as to form an optical interference pattern dependent on the difference between the optical path lengths of the first and second optical paths. The detector array is arranged to measure the intensity of at least a part of the optical interference pattern. At least one of the first and second optical path lengths is arranged to be dependent on the position of the object, such that changes in the optical interference pattern can be related to changes in the position of the object.

Abstract: A circuit assembly (200) is disclosed comprising a substrate (210) and conducting layers (250) on opposing sides of the substrate (210), there being at least one via (220) through the substrate (210), which via (220) forms a conductive path between the conducting layers, wherein the substrate (210) is a foam substrate, and wherein the via (220) is provided with a solid dielectric lining (270) plated with a conducting material (250).

Abstract: The present invention provides a thrust flow powered vehicle comprising a first thrust flow expeller for expelling a first thrust flow in a first direction, a second thrust flow expeller for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, a thrust flow deflector surface at an angle to the plane of the first and second directions, and an outlet portion for providing an output thrust flow, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow such that the output thrust flow has a component in the plane of the first and second directions, and a component out of that plane.

Abstract: A method of targeting a missile. A plurality of images of a target, taken from a plurality of viewpoints, are received. Features in the images characteristic of the target are identified. Data representing the characteristic features are provided to the missile to enable the missile to identify, using the characteristic features, the target in images of the environment of the missile obtained from an imager included in the missile.

Abstract: A mission planning method for use with a weapon is disclosed. The method comprises: obtaining a first training data set describing the performance of the weapon; using the first training data set and a Gaussian Process (GP) or Neural Network to obtain a first surrogate model giving a functional approximation of the performance of the weapon; and providing the first surrogate model to a weapons system for use in calculating a performance characteristic of the weapon during combat operations.

Abstract: A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a closure for closing the inlet so as to prevent ingress of debris; and a fastening attachable to an aircraft-mounted launcher and configured such that the cover remains attached to the aircraft on launch of the missile.

Abstract: An inductive power transfer system (1) for coupling a power source to a load across an air gap (11) is disclosed. The system (1) comprises a primary unit (3) associated with a host platform and a secondary unit (5) arranged to receive power transmitted inductively from the primary unit (3). The primary unit (3) includes a phase detection circuit (21) configured to detect phase changes in a signal in the primary unit (3) indicative of changes in an operating condition within the secondary unit (5), and a drive circuit (17). The drive circuit (17) is configured to adjust the power level transmitted to the secondary unit (5) depending on the detected phase.

Abstract: A composite reactive material for use in a munition is disclosed. The composite reactive material comprises a metal lattice structure having interstitial spaces and a powder in the interstitial spaces. The powder comprises at least one metal powder and/or at least one halogen-containing polymer powder.

Abstract: A method of manufacturing ceramic matrix composite objects is disclosed. The method comprises the steps of providing first and second substantially two dimensional arrangements of one or more fiber plies, and machining the first and second arrangements to predetermined configurations to form first and second preforms. The second preform is made to conform to a surface of the first preform such that at least some of the fibers of the second preform are orientated at least partially in a plane outside that defined by the fibers of the first preform, and fixed to the first preform to form a combined first and second preform. The combined first and second preform is rigidized. Ceramic matrix composite objects manufactured by this method are also disclosed.

Abstract: A target designator for a guided weapon is disclosed. The designator has a sight arranged to display, in operation, a reticule superimposed upon a field of view. The reticule is moveable within the field of view. The designator further comprises an eye tracker operable to track the gaze of the operator whilst the operator uses the sight. The eye tracker communicates with the sight such that the reticule moves so as to be aligned with the direction of the gaze of the operator.

Abstract: In a method of carrying a munition on a munition launcher platform, the munition launcher platform is provided with a data tag activator and a data tag reader. A munition is attached to the munition launcher platform, the munition being provided with a data tag. An activation signal is transmitted from the data tag activator to the data tag. As a result of receiving the activation signal, the data tag returns a data response to the data tag reader. The receiving of the data response provides the munition launcher platform with an indication that the munition is still attached to the munition launcher platform.

Abstract: A morphing skin for an air vehicle structure, the skin being formed by a composite material which includes: a multiplicity of fibers, a matrix incorporating the fibers, and a thermo-sensitive material, such as a thermo-plastic. The thermo-sensitive material can be reversibly transitionable in response to a change in temperature, between (i) an ambient temperature mode in which the thermo-sensitive material is capable of transferring loads in the composite material, and (ii) a heated mode in which the ability of the thermo-sensitive material to transfer the loads is reduced. This can allow the stiffness of the skin to be temporarily reduced to enable the skin to be morphed into a different shape.

Abstract: An aircraft comprises a weapons bay, the weapons bay comprising a cavity having an opening through which stores may be deployed, and a door assembly for exposing/closing the opening of the cavity. A first store is held in the cavity via a launcher and a first structure is disposed inside the cavity, for controlling the aero-acoustic environment. The first structure for controlling the aero-acoustic environment is removeably mounted in the weapons bay, such that if the first store is exchanged for a second, different, store, the structure for controlling the aero-acoustic environment may be unmounted from the weapons bay and removed, to be exchanged for a second, different, structure for controlling the aero-acoustic environment.

Abstract: An interferometric position sensor for sensing the position of an object is disclosed. The position sensor comprises a light source arranged to emit light, a beam splitter, and a detector array. The beam splitter is arranged to split the light between first and second optical paths, which are configured such that the split light is recombined so as to form an optical interference pattern dependent on the difference between the optical path lengths of the first and second optical paths. The detector array is arranged to measure the intensity of at least a part of the optical interference pattern. At least one of the first and second optical path lengths is arranged to be dependent on the position of the object, such that changes in the optical interference pattern can be related to changes in the position of the object.

Abstract: A ground-based source of a jamming signal capable of disrupting a GNSS satellite-based navigation system, for example a GPS jammer, is located with a detector carried by a suitable platform, for example an airborne UAV or missile. The detector, when the platform is at a first location, measures a characteristic of the jamming signal. The platform and its detector are then moved to a chosen second location, from which a further measurement of the jamming signal is made. The measurements made by the detector are then used to determine the location of the source of the jamming signal.

Abstract: A target designator for a guided weapon is disclosed. The designator has a sight arranged to display, in operation, a reticule superimposed upon a field of view. The reticule is moveable within the field of view. The designator further comprises an eye tracker operable to track the gaze of the operator whilst the operator uses the sight. The eye tracker communicates with the sight such that the reticule moves so as to be aligned with the direction of the gaze of the operator.

Abstract: In a method of tracking an object, a plurality of images of a target object is obtained. A super-resolved image of the target object is calculated from the plurality of images. A further image of the target object is obtained. The further image is correlated with the super-resolved image, in order to identify the location of the target object in the further image.

Abstract: A method of targeting a missile. A plurality of images of a target, taken from a plurality of viewpoints, are received. Features in the images characteristic of the target are identified. Data representing the characteristic features are provided to the missile to enable the missile to identify, using the characteristic features, the target in images of the environment of the missile obtained from an imager included in the missile.

Abstract: A method of conducting a strike against a target using a designator and a missile. The following steps are conducted: (i) the designator designates the target using a first signal, such as a laser; (ii) the missile detects the laser reflected off the target; (iii) after detecting the reflected laser, the missile emits a second signal, such as a LADAR signal, to designate the target; (iv) the missile tracks the so-designated target; (v) the designator detects the LADAR signal reflected off the target; and (vi) in response to detecting the reflected LADAR signal, the designator stops the designation of the target. This may enable the designator to perform other tasks, while the missile tracks and engages the target.

Abstract: In a method of guiding a missile in flight to a target (FIG. 1), the location of the missile and the range to the target are measured at a plurality of moments during the flight of the missile (step 10). The location of the target is calculated from the measured ranges and the measured missile locations (step 20). A required velocity vector angle is calculated from the calculated location of the target and a guidance law (step 30). A lateral acceleration required to provide the missile with a velocity oriented to the target at the required velocity vector angle is calculated for the missile (step 40). The missile is caused to accelerate with the calculated lateral acceleration, so that the missile to follows a trajectory according to the guidance law (step 50).