Abstract: A method for launching a round from an airborne platform, receiving a plurality of RF signals at the round, determining an amount of time between a first and second received RF signal, where the second signal is a multi-path signal and the first signal is a direct path signal. An altitude of the round is determined based on the delay between the first and second received signal and aligning the round's flight path with an initial velocity vector of the aircraft platform to reduce dispersion. The round can include a plurality of sensors for detecting the RF signals. The second received RF signal may be a multi-path signal having been reflected off of the earth's surface or another object on the earth's surface. The altitude of the round can be determined using the known altitude of the airborne platform, the delay of time between the first and second received signals, and the speed of light.

Abstract: There is provided a user-vehicle interface, comprising a gesture control system that is arranged to: sense a direction of a gesture of a user of the vehicle; and process the sensed gesture to control a location of an indicator on a display in accordance with that sensed direction, such that a location of the indicator is arranged to move in accordance with changes in the sensed direction, the indicator being used to show a current position for user interaction with content on the display, and being in a plane in which that content resides.

Abstract: There is provided a user-vehicle interface, comprising: a gesture control system, arranged to sense a gesture of a user of the vehicle; the gesture control system being arranged to process the sensed gesture to control interaction with content on a display, in accordance with that sensed gesture; the vehicle comprising a physical actuator for controlling the vehicle, and the gesture control system is arranged to facilitate interaction with content on the display, when a body part of the user associated with a provision of the gesture is engaged with the actuator.

Abstract: This invention relates to a parachute sea anchor system deployable from a payload tube. There is provided a parachute sea anchor system suitable for launch from a vessel comprising at least one payload tube, said payload tube, comprising a payload canister, which comprises a parachute sea anchor, wherein said parachute sea anchor comprises a buoy tethered thereto, wherein said payload canister is attached to said vessel.

Abstract: An optical waveguide for a head up display is disclosed. The optical waveguide is configured to provide pupil expansion in two dimensions and having an input end and an output end and a first axis substantially parallel to the direction of propagation of light in the waveguide and substantially parallel with a direction from the input end to the output end. The optical waveguide comprising: an input region at the input end; a beam splitter configured to expand light received from the input region; a symmetrical diffraction grating comprising complementary first and second grating portions, wherein the second grating portion is substantially symmetrical to the first grating portion along a line of symmetry that is substantially parallel to the first axis. Light received at the symmetrical diffraction grating from the beam splitter is configured to be diffracted by the symmetrical diffraction grating towards the line of symmetry by the first grating portion or the second grating portion.

Abstract: There is disclosed a line apparatus for inhibiting an airborne target. The line apparatus comprises at least one line comprising: a flexible tubular member, having a wall and defining a bore; and a fluid adhesive housed within the flexible tubular member, wherein the flexible tubular member is configured to express the fluid adhesive through the wall.

Abstract: There is provided an arming apparatus for a store, the apparatus comprising: a first attachment system and a second attachment system; a linking connector coupled with the first attachment system and the second attachment system; and an arming connector coupled with the linking connector and a first fuze input of the store; wherein each of the first attachment system and the second attachment system comprises: an arming unit; a first frangible connector coupled with the arming unit and the linking connector; and a second frangible connector coupled with the linking connector and the store.

Abstract: A V-band clamp includes first and second clamp sections each having an arcuate shape with a first end, a second end, and inside surface defining a recessed channel. A hinge pivotably connects the second end of the first clamp section to the first end of the second clamp section. At least one fastener is configured to releasably connect the first end of the first clamp section to the second end of the second clamp section in a closed position. When the V-band clamp is in the closed position, each fastener extends through an opening in an end face on the first end of the first clamp section and into a bore in an end face on the second end of the second clamp section.

Abstract: There is disclosed an aircraft for intercepting an airborne target, the aircraft comprising: a frame; a plurality of lines of a first type, each attached to the frame at a first end, and free at the other end; and a plurality of lines of a second, different, type, each attached to the frame at a first end, and free at the other end.

Abstract: Apparatus for configuring a mission automation and decision support system for an unmanned aerial vehicle comprising a user interface and a computer-implemented module configured to: receive data representative of at least one task to be performed by the UAV, the task being defined by one or more decision points that correspond to system actions or responses that could result from respective specified mission information; for each decision point(s), request user inputs in response to questions, the questions being designed to determine an extent to which each system action or response can be automated and a respective level of mandated operator approval therefor; and allocate to each decision point a set of one or more corresponding automation levels, each automation level comprising data representative of a measure of automation to be applied at a respective decision point.

Abstract: There is provided an integrity monitor configured to monitor the integrity of a component protection device. The component protection device comprises a protective medium to protect at least one electronic component, and having associated therewith a magnetic element and a Hall Effect sensor. The at least one of the magnetic element and the Hall Effect sensor is embedded within the protective medium and the Hall Effect sensor is located, when in use, to sense a magnetic field generated by the magnetic element. The integrity monitor has an input for receiving an output of the Hall Effect sensor indicative of the sensed magnetic field and the integrity monitor is configured to identify from the received output any change to the sensed magnetic field and determine, based on the change to the sensed magnetic field, an integrity of the component protection device.

Abstract: A ground imaging system for use on a guided aerobody includes one or more lenses designed to receive EM radiation from a ground level, a filter substrate having a plurality of filters, a sensor array designed to receive the EM radiation from the filter substrate, and a processing device coupled to the sensor array. The filter substrate is located at a focal plane of the one or more lenses such that the filter substrate receives the EM radiation from the one or more lenses. The plurality of filters includes at least polarization filters and multispectral filters. The processing device is designed to analyze multispectral and polarization signatures of the electromagnetic radiation from identified objects at the ground level and determine that one or more of the objects is not a desired target based at least on the hyperspectral and polarization signatures of the one or more objects.

Abstract: An antenna positioner provided on a deployable vehicle. The antenna positioner includes a base and a frame having a plurality of plates oriented at an angle relative to one another. Each plate may include a low band antenna and a high band antenna. The base is located inside a chamber of the deployable vehicle. The frame is movable relative to the base between a collapsed position, where the entire frame is positioned within the chamber, and an extended position wherein at least a portion of the frame extends outwardly through an opening in the deployable vehicle's exterior wall. The frame is pivotally engaged with the base and a gearing mechanism pivots the frame between the collapsed position and the extended position to arrange the antennas at a desired orientation relative to the deployable vehicle's exterior wall so as to maximize the antenna's near-vertical Field of View (FoV).

Abstract: The system and method for cooling a laser using a split liquid cooled heat exchanger. The temperature of coolant entering the system is applied to a portion of the system most in need of lower temperatures and a second heat exchanger uses the outflow from the first heat exchanger to cool a remaining portion of the system that has a tolerance for higher temperatures. The laser cooling system is compact, e.g., less than 45 cubic inches and can handle thermal loads of about 800 W.

Abstract: A control system (400) for an active inceptor (103) for a fly by wire aircraft permits a zero force null point to settle to a non-zero displacement trim position. An internal position state of a second order mass spring damper model is moved in conjunction with force-displacement characteristic coordinates. This results in no second order dynamics being superimposed on the feel of the inceptor (103) when dynamically adjusting the trim position, thereby eliminating the possibility of any unpleasant buzzing been felt by the operator of the inceptor during a trimming operation.

Abstract: A radiation backscatter detector assembly comprising: a source array comprising source components for irradiating a shared sample location, at least two source components of the array generating radiation in different respective source energy bands; a detector array comprising detector elements for detecting backscattered radiation detection events from different respective spatial portions of the shared sample location, the detector elements each generating a pulse output in response to each radiation detection event it detects; and an energy meter for measuring the energies of the pulse outputs by different respective detector elements.

Abstract: The invention relates to the field of Free Space Optics (FSO), more specifically it is directed to: a method of obtaining a connection between at least two optical signal nodes, of a FSO, communication system each node comprising a transmitting device and receiving device; and transmitting via the transmitting device of a first node, a first diverged optical signal into an optical medium; receiving at the receiving device of the second node the first diverged optical signal and transmitting via the transmitting device of the second node a second diverged signal to the receiving device of the first node to establish a location of said first node establishing a connection, after which; the first node switches from the diverged optical signal to a narrower optical signal for the transmission of data via the connection.

Abstract: A modular electronic warfare (EW) framework that is implemented into a first preexisting EW system with associated hardware and firmware to leverage the capabilities of the first preexisting EW system into a second, different preexisting EW system with associated hardware and firmware. The modular EW framework includes a tracking framework and a logic framework. The tracking framework is configured to receive a first set of objects from a preexisting EW system and augments the first set of objects with at least one parameter and outputs the second set of objects. The logic framework is configured to receive the set of second objects from the tracking framework and implements at least one process onto the second set of objects and outputs a third set of objects. A multi-core processor is used to operate the modular EW framework.

Abstract: The present invention relates generally to a method and system (10) for classifying vehicle behaviour, particularly abnormal behaviour of civil aircraft (12). The method may comprise receiving aircraft data from an aircraft (12) which is to be classified; and determining whether the received aircraft data comprises identification information for the aircraft (12). In response to a determination that the received aircraft data comprises identification information, the method may comprise using said identification information to classify the behaviour of the aircraft (12). In response to a determination that the received aircraft data does not comprises identification information, the method may comprise obtaining the position of the aircraft and comparing the obtained position to an expected route for the aircraft to classify the behaviour of the aircraft (12).

Abstract: The present invention relates to an arrangement (A) for balancing a gun barrel (20) of a vehicle mounted weapon system (C). The weapon system comprises the gun barrel (20) mounted to a turret (10) via a weapon cradle (30). The weapon cradle (30) is arranged to allow elevation movement of the gun barrel (20) about an elevation axis (Z1). Said arrangement (A) comprises a suspension system (S) configured to provide a torque opposing imbalance of the gun barrel (20). The arrangement further comprises an adjustment device (50; 150) for automatically adjusting the torque provided by the suspension system (S) based on imbalance of the gun barrel (20) so as to dynamically counteract imbalance of the gun barrel (20). The invention also relates to a vehicle with an arrangement according to the present invention.