Abstract: A device for the unambiguous measurement of the angle of roll of a projectile, comprises at least a radar equipped with means of processing and sending a signal to the casing of the projectile in at least one direction of incident polarization; a set of parallel grooves made on the casing, the depth of which is modulated dissymmetrically with respect to the axis of symmetry of the projectile; the axis of symmetry of the projectile not passing through the point of the antenna of the radar where the antenna beam is generated, the processing means analyzing, in reception, a signal back-scattered by the casing of the projectile, the signal being modulated as a function of the angle of roll of the projectile, the modulation having two maximum local values corresponding to two angular roll positions of the projectile such that the polarization {overscore (E)} is parallel to the grooves, the processing means removing the 180° ambiguity by comparing the levels of the local maximum values.

Abstract: A submunition for delivery in a carrier, the submunition including a satellite aided global location system guidance system mounted on the submunition for guiding the submunition towards a pre-selected target after delivery to a target area by the carrier, and a method for guiding a submunition after delivery from a carrier, the method including mounting a satellite aided global location system guidance system on the submunition and utilizing the satellite aided global location guidance system to guide the submunition towards a pre-selected target.

Abstract: The Magnetostrictive Missile Guidance System pivots the missile nosecone about a multi-directional joint on the missile axis to produce aerodynamic control forces for missile flight path control. The nosecone is driven by magnetostrictive materials in conjunction with displacement amplification devices. The determination of the nosecone deflection angle necessary to achieve any change in the flight path is made by a sensing device that produces position signals and a guidance computer that produces the desired flight path command signals. The sensing device senses the current position of the nosecone and this position signal is compared with the command signal by the computer to yield an error signal, which is indicative of the difference between the two input signals. Then appropriate magnetic field is applied to the magnetostrictive materials to cause them to grow in length and deflect the nosecone until the error signal is eliminated and flight path is changed.

Abstract: In order to perceptibly reduce the inevitable trajectory scatter or spread of ballistically fired projectiles in the target area without the technological expenditure involved in automatic target-seeking control, and in order thereby substantially to improve the level of target hit accuracy, the minimum trajectory path is laid through the previously ascertained target position, having regard to the error budget of the weapon and the external influencing parameters to be expected so that all real trajectories up to the maximum trajectory of that overall error budget are behind the target position. The descent of the projectile into the target area is then shortened from the real trajectory to the minimum trajectory, that is to say towards the target position.

Abstract: The invention relates to a missile for combating stationary and/or moving targets comprising a seeker head (100), an effective charge which is arranged behind said seeker head in the direction of flight, a thruster such as a solid fuel booster having lateral outlet nozzles which is arranged behind the effective charge in the direction of flight, and a guiding section (104) which is arranged behind the thruster in the direction of flight. The guiding section comprises controllable aerofoils (105a, 105b) such as lateral and/or tail fins, and a guiding device. The missile also comprises a cruise engine (107) which is arranged on the tail, whereby the cruise engine is detachably connected to the guiding section by means of a first quick-acting closure (109a, 109b) such as a manually operable bayonet closure or the like.

Abstract: Given a trajectory and unit pointing vectors determined based on a planar or other approximation of a shock wave, a method and apparatus are provided to calculate times the sensors should have detected, based on a conical geometry of the shock wave. A difference between the calculated times and the actual times measured by the sensors may be minimized. The minimization may be performed by perturbing the unit vectors. When the perturbation of the unit vectors results in an acceptable difference between the calculated times and the measured times, an accurate trajectory of the projectile can be generated from the perturbed unit pointing vectors.

Abstract: A switch modulated low duty cycle low energy mass limited radio frequency beacon system for locating spent, un-exploded or experimental munitions projectiles in a large open-air test range or within a dirt backstop. The disclosed locator beacon is mounted on a rear portion of a projectile before launch and includes a protective (and antenna length-shortening) resin dielectric material housing in which locator beacon circuit components are contained and immunized against high G forces by a combination of component supporting, energy deflecting and energy absorbing protective arrangements.

Abstract: The invention relates to a method for combating near-surface and/or surface targets such as tanks or the like by using a missile comprising a seeker head, an effective charge and at least one thruster. According to the invention, the missile is redirected into an essentially horizontal cruising and seeking phase after completing an essentially vertical start phase. During said cruising and seeking phase, the missile scans the terrain ahead of it using the seeking head, whereupon an approaching phase which is directed in an essentially downward direction follows after the finally ensues head locks onto an identified target. An external reconnaissance system in an appropriate aircraft and/or spacecraft such as in a helicopter, a drone or in a satellite receives information for guiding the missile which is transmitted to the same.

Abstract: A satellite positioning-based guidance system and method that utilize a simulated inertial navigation system are disclosed. The trajectory of the body of a non-thrusted flight vehicle is used instead of a conventional inertial navigation system. The attitude of the flight vehicle is determined using a satellite receiver, and the Extended Kalman filter is used to implement the navigation function.

Abstract: A rocket spin control system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned erodible or retractable vanes inside of the nozzle. The vanes are removed from the rocket propelling thrust at rocket exit from the tube.

Abstract: A projectile includes an elongated forebody and an aft section secured to the forebody. The aft section includes a pair of fins affixed to an aerodynamic, cylindrical section. The lift generated by the low-drag pair of fins is sufficient to counteract most foreseeable angles of attack to be experienced by the projectile. The aft section further includes a bearing that couples the aft section to the forebody of the projectile and is capable of allowing the aft section to rotate freely about the longitudinal axis of the projectile and independently of the forebody. Thus, during flight the aft section rotates into the maximum lift plane and provides a restoring moment to the projectile, thus providing necessary stability to the projectile while imparting minimum drag.

Abstract: An arrangement in a missile and a method for guiding the missile towards a moving target, for example, an aircraft, wherein the missile has information on its own position, velocity vector, and future velocity characteristic. The missile continuously receives information on the position and velocity vector of the target. The arrangement and method operate such that, a point of interception, at which the missile is expected to strike the target, is calculated from the information on the missile and the target, and a velocity vector of the missile is directed towards the predicted point of interception, which is continuously predicted on the basis of an assumption as to the future movement of the target, and a calculation of the time to impact.

Abstract: A guidance device for projectiles has stationary canards (40) and thrusters (50) positioned on the nose (20) of the projectile (10). The thrusters (50) are initiated from remote or local sensor to provide flight maneuverability to a target.

Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state.

Abstract: A deployable nose is used on an underwater vehicle to provide a shorter length when in a retracted position and to provide a reduced drag when in the deployed position. The deployable nose includes a plurality of nose sections and a deployment mechanism that moves the plurality of nose sections from the retracted position to the deployed position. The nose sections include a base nose section attached at the end of the underwater vehicle, an outer nose section having a rounded contour, and one or more intermediate nose sections between the base nose section and outer nose section. In the retracted position, the outer nose section and one or more intermediate nose sections are retracted generally within the base nose section. In the deployed position, the outer nose section and intermediate nose sections extend outwardly from the base nose section and interlock proximate the edges of the nose sections to form the deployed nose.

Abstract: A self-orienting device comprises: a housing; a sensor mounted to the housing that is sensitive to a signal field and configured to produce a signal responsive to the signal field; a translation-inducing unit associated with the housing; rotation-inducing unit attached to the housing, wherein the translation-inducing unit and the rotation-inducing unit are configured such that the housing travels along a helical trajectory having an axis and is free to rotate about the axis; and a controller operably associated with the sensor for controlling the output of at least one of the translation-inducing unit and the rotation-inducing unit, wherein the controller is configured such that it receives the signal from the sensor and, responsive to the signal, controls the output of at least one of the translation-inducing unit and said rotation-inducing unit. A device so configured can automatically orient to a signal.

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 present invention uses aerodynamic heating caused by air-friction during flight of a training projectile. The training projectile includes a nose, a body and a tail section. The body has a forwardmost end secured to the nose, and a rearwardmost end secured to the tail. Air friction during flight causes deployment of “passive” shape memory alloy (SMA) aerodynamic members in an assembly to induce drag of the training projectile thereby limiting an effective range of the projectile.

Abstract: The Multispectral-Hyperspectral Sensing System (MHSS) comprises a control center, a surveillance platform and at least one weapon battery with known sensing and destroying capabilities. The control center has access to pre-existing information relating to the target scene and potential targets, although not necessarily current, as well as the capabilities and limitations of the available weapons. This pre-existing information is communicated to the surveillance platform to be used in collecting hyperspectral/multispectral image data of the target scenery and to derive from the collected image data the relevant current target data subset. The derived data subset is then down-linked to the control center, which performs further processing to make it useful to the selected weapon. The weapon receives the target signature update from the control center and, in response, performs a significantly more precise strike at the selected target than based just on the a priori knowledge base.

Abstract: An encapsulated insulation composite system for increasing the burn through resistance of an aircraft fuselage includes: an insulation layer of glass fiber or foam insulation and a coating or interleaf barrier layer of a high temperature resistant material and/or a coating or barrier layer of a high temperature resistant material on an outer major surface of the insulation layer of the composite and a film encapsulating the composite. Preferably, the barrier layer or layers include a reflective mineral, such as a reflective mineral containing coating carried on a sheet material. Preferably, the encapsulating film is a polymeric film such as a polyimide film.

Abstract: In a projectile launched by a gun, the projectile including a fuze with a longitudinal axis of symmetry and a braking device, an apparatus disposed in the fuze for determining a time of deployment of the braking device, the apparatus including a first accelerometer having a sense axis and mounted with its sense axis coincident with the longitudinal axis of symmetry of the fuze; a second accelerometer having a sense axis and mounted a known axial distance from the first accelerometer and with its sense axis coincident with the longitudinal axis of symmetry of the fuze; a magnetometer having a sense axis and mounted with its sense axis orthogonal to the longitudinal axis of symmetry of the fuze; a field-programmable memory unit loaded with aiming data of the gun, magnetic field direction at the gun, a nominal path length table, and a braking device maneuver authority table; and a microprocessor connected to the first and second accelerometers, the magnetometer, the field-programmable memory unit and the braking

Abstract: A sole means global navigation apparatus adapted for use on an aircraft includes a GPS receiver to provide GPS measurement data and an inertial sensor system adapted to provide inertial translational and rotational data which during time periods is independent of the GPS position data. A navigation system coupled to both of the GPS receiver(s) and the inertial sensor system determines a navigation solution as a function of both the condition of the GPS satellite data and the uncertainty in the Inertial data. An augmentation system coupled to the navigation solution determining system is used to increase the accuracy and/or integrity of the GPS/inertial sensor, thereby achieving style means navigation requirements.

Abstract: In a first aspect, the invention uses the thrust and axial aerodynamic forces of and on the missile system as the primary mechanism for altering the missile system's flight path as opposed to the missile system's aerodynamic normal force. In accordance with this first aspect, a first embodiment is a method for changing the direction of travel of a vehicle moving through a fluid medium to a desired direction of travel measured in the vehicle's inertial frame of reference, the vehicle comprising a body including a nose, a moment generating control device, and an axial propulsive device. The method comprises actuating the moment generating control device to align the nose substantially with the desired direction of travel, and applying the axial propulsive device as the primary mechanism to redirect the vehicle's velocity to the desired direction of travel. In a second aspect, the invention provides a missile control system implementing the first aspect of the invention.

Abstract: The subject of the invention is a translational braking device for a projectile during its trajectory comprising at least two airbrakes that are radially deployable so as to increase the projectile's aerodynamic drag. Each airbrake is a flap pivoting around a pivot integral with the projectile and parallel to its axis. The device incorporates at least one pyrotechnic piston locking at least one of the flaps in its folded position and at least two flaps are stacked one on top of the other when they are in their folded position, at least a first of the two flaps incorporates a mechanism to retain the second of the two flaps in its folded position.

Abstract: A rudder of a missile, particularly an aircraft born ramjet missile, is attached to the missile by a plug and socket mounting. A bearing socket (B1) is attached to a base plate (B0) which is secured to the missile body (FK). The socket (B1) has a conical cavity (B3) tapering toward the base plate (B0). The plug (W1) is formed by a rudder shaft (W) also tapering toward the base plate and rotatably fitting into the conical cavity (B3). Bearings (L1, L2) in the cavity (B3) hold the plug end (W1) of the rudder shaft axially and permit rotation of the rudder shaft (W) relative to the bearing socket (B1). The socket thus holds the bearings and has an at least partly outer cylindrical contour with a diameter (B2) that fits into a standard 41 mm wide slot (S) in an aircraft that carries the missile, whereby the rudder (R) is recessed in the slot (S) when the missile is mounted to an aircraft.

Abstract: A predictive guidance algorithm maneuvers a fly-by vehicle in a direction towards an object vehicle with a time varying line-of-sight rate. After initial predictive guidance, a modified proportional navigation maneuvering phase accelerates the fly-by vehicle towards an object vehicle on an intercept line-of-sight path. The proportion navigation maneuvering is terminated prior to interception so that the fly-by vehicle does not intercept the object vehicle, but rather flies by the object vehicle at a desired miss distance, well suited for fly-by monitoring and imaging missions of space vehicles and planetary objects.

Abstract: A submunition for delivery in a carrier, the submunition including a satellite aided global location system guidance system mounted on the submunition for guiding the submunition towards a pre-selected target after delivery to a target area by the carrier, and a method for guiding a submunition after delivery from a carrier, the method including mounting a satellite aided global location system guidance system on the submunition and utilizing the satellite aided global location guidance system to guide the submunition towards a pre-selected target.

Abstract: A device for reducing base drag on cylindrical rear truncated objects moving in a fluid, caused by the shedding of vortices at the base of the object. The device consists of ring shaped winglets attached to the rear of the object which may be sub-divided into a plurality of hinged partial winglets. The parameters of distance of winglet from cylinder shaped object, winglet circumference, angle, profile and chord length may be varied automatically for optimum drag-reducing capability.

Abstract: The adaptive body bending estimator comprises a band pass filter which receives an accelerometer signal from a missile's accelerometer. The band pass filter, which has a bandpass of 25-70 hertz, rejects frequencies which are not of interest. The band-passed signal is then supplied to a notch filter bank comprising six notch filters within a frequency range of between 42 hertz and 55 hertz. The six notch filters are centered at different frequencies, the frequencies being 42 Hz, 44.32 Hz, 46.78 Hz, 49.37 Hz, 52.11 Hz and 55.00 Hz. The notch filters reject signals at these frequencies. The signals from the filter bank are supplied to an absolute value generator which generates an absolute value for each signal. The absolute value of each signal is passed through a low pass filter bank. The low pass filter bank processes these absolute value signals providing a time weighted average for each signal. The low pass filter bank provides its output signals to a find frequency module.

Abstract: A control system for aerodynamic vehicles has a fuselage nose segment and at least one strake. The fuselage nose segment is rotationally adjustable with respect to the aircraft fuselage. The at least one strake is mounted on the fuselage nose segment so that the strake can swing out.

Abstract: In missile guidance systems, knowledge of the target's flight policy and doctrine, along with an analysis of local topographic features, are used in a minimum commitment guidance policy. By assuming certain objectives of the target, paths may be defined by evaluating the degree of detection avoidance provided by the terrain adjacent to the various paths. To maximize the probability of intercept, a missile may be guided in a direction covering the most likely of these paths for periods while the target is hidden. The paths are then reevaluated each time the target is detected. For highly maneuverable targets that are capable of executing violent changes in direction and speed, the topography-aided guidance system maximizes the probability that the target can escape the missile intercept envelope.

Abstract: There is provided a rocket trajectory estimating method comprising the steps of: measuring a GLOS angle of a flying rocket a tracking system; passing the GLOS angle data through a batch filter to reduce noises; estimating a rocket trajectory on the basis of the GLOS angle data, the noises of which have been reduced; passing the resulting rocket trajectory data through a Kalman filter to reduce biases; and estimating the rocket trajectory again on the basis of the corrected GLOS angle data and the positional information of the tracking system. Thus, there is provide a rocket trajectory estimating method capable of reducing observation errors (noises and biases) of a tracking system of a passive ranging system, which does not have need of any laser range finders, to enhance the accuracy of rocket trajectory estimation.

Abstract: A method for the automated generation of ballistic constants for use in a trajectory control system. The potential trajectory of a pursuing vehicle is divided into a plurality of multiple sequential phases wherein each phase is characterized by a plurality of ballistic parameters. Known simulated data from a number of runs concerning the pursuing vehicle is analyzed. Ballistic parameter values for each run are obtained and statistically analyzed to produce generic constants for a particular set of operating conditions. Resulting matrices are stored as part of a two-dimensional, kinematic vehicle model to facilitate the propagation of projected trajectories during firing control solutions.

Abstract: A system for intercepting targets having predictable flight trajectory, the system comprising a platform carrying an interceptor missile which includes a seeker unit, propulsion system steering system and destruction capability system, all communicating with a processor device. The processor device is further coupled to a data link for communicating with the platform.

Abstract: A self starting predictor corrector method of arbitrary order is disclosed that uses exact stability integration in network designs for application in systems optimizing control of aircraft through improved numerical techniques. Such method defines a self starting predictor corrector routine for a numerical solution of differential equations having a main process that computes derivatives of the states with a n-th order numerical solution for a n-th order differential equation. Moreover, such method configures an exact stability algorithm for generating a numerical integration of a high order of any type linear or nonlinear filter or network by constraining extraneous eigenvalues in the high order filter or network to be a definite value.

Abstract: The present invention relates to a method and a system for determining a weapon firing strategy for an evading target. The method of the present invention comprises the steps of sensing the motion of the target, analyzing the motion of the target, providing a weapon employment decision aid, determining the evasion region for the target using the weapon employment decision aid and the analyzed motion, visually displaying the evasion region, feeding operator knowledge about the evading target, and generating a representation of the probability of the location of the evading target. The weapon employment decision aid utilizes beta density functions to determine the evasion region. The weapon employment decision aid displays target course and speed in the form of bar graphs and allows the operator to input information about target evasion course and speed and uncertainty levels.

Abstract: A device is described which incorporates three components: a tracking error estimator, a detector, and a red light indicator to alert a pilot to the potential loss of tracking control. The tracking error estimator uses the difference between the target and the desired response of the tracking aircraft to estimate the divergence from a desired tracking path. This difference is acquired by such systems as, for example, the Global Positioning System (GPS) and radar. The tracking error and its derivatives are then converted into three different metrics. The metrics represent percentage points when the tracking error and its derivatives are in an unstable or stable portion of its phase plane. Depending upon whether these metrics and/or their combinations are above a particular threshold, the detector and indicator will alert the pilot or operator whether or not corrective action needs to be taken. The threshold is determined by a predetermined logic tree.

Abstract: Two new adaptive homing guidance laws are developed which are variants of Augmented Proportional Navigation (PRONAV). The first guidance law commands flight path angle rate and is referred to as adaptive matched augmented PRONAV (AMAAP). The second guidance law commands linear acceleration and is referred to as adaptive matched augmented linear PRONAV (AMALP). The major attributes of these guidance laws are (1) they are the solutions of a linear quadratic control problem, (2) they do not require an estimate of time-to-go (tgo), (3) they are matched to a nonlinear model of the target's motion, (4) they adapt in real time to provide optimal guidance over each small segment of the intercept trajectory, and (5) they optimally account for missile deceleration.