Abstract: A system is provided for monitoring at least one data bus of an aircraft. The system includes an aircraft adapted to control the operation of stores of a second predetermined type (e.g., Harpoon Block I missiles). However, the aircraft is also capable of carrying a store of a first predetermined type (e.g., Harpoon Block II missiles), and capable of communicating with the store across a communication bus (e.g., MK-82 Digital Data Bus). The system also includes a bus monitor assembly capable of capturing data communications transferred across the communication bus between the aircraft and the store, the data communications being captured from the communication bus. The bus monitor assembly is also capable of preparing the data communications, and monitoring the communication bus across which the data communications are transferred, the communication bus being monitored based upon the prepared data communications.

Abstract: A system for increasing a warhead's chance of hitting a target comprises a system for causing the warhead to deviate from its projected trajectory so that it will have an increased chance of avoiding intercepting force such as a kill vehicle a missile, an airplane, an explosive gun, a laser gun, an electron gun, radiation gun, a particles gun, a fire gun, a jet air gun, and/or a remote control guided explosive. The warhead has one or more thrusters, which cause it to deviate from its projected trajectory. An on-board computer controls the thrusters' ignition and burning time in a closed loop with an on-board Global Positioning System (GPS) unit. The GPS data is used for predicting the warhead's trajectory and to assure that the thrusters provide motion displacements of the warhead. In the event the GPS unit fails, the warhead computer and controller can be overridden by an off-board remote control.

Abstract: The present invention is directed towards a ballistic missile detection and defense system. The system of the present invention comprises a ship based interceptor or antiballistic missile, a missile launch detection and tracking system, and a signal processing system capable of receiving said tracking signal calculating an intercept trajectory for an antiballistic missile to intercept a ballistic missile, and further capable of outputting an intercept trajectory program to an antiballistic missile.

Abstract: Embodiments of the invention, therefore, provide improved systems and methods for tracking targets in a simulation environment. Merely by way of example, an exemplary embodiment provides a reflected laser target tracking system that tracks a target with a video camera and associated computational logic. In certain embodiments, a closed loop algorithm may be used to predict future positions of targets based on formulas derived from prior tracking points. Hence, the target's next position may be predicted. In some cases, targets may be filtered and/or sorted based on predicted positions. In certain embodiments, equations (including without limitation, first order equations and second order equations) may be derived from one or more video frames. Such equations may also be applied to one or more successive frames of video received and/or produced by the system.

Abstract: Trajectory is controlled by a control system having fins that de-spin a section of the control system relative to a projectile or missile. The control system also includes aero-surfaces that produce a lift when brought to rotation speed of about 0 Hz relative to a reference fame and a brake that couples the guidance package to the rotational inertia of the projectile or missile. In one example, no electric motor is used in the trajectory control system, saving weight and increasing reliability.

Abstract: A system and method for performing attitude determination for projectiles comprises a projectile; a plurality of magnetometers arranged orthogonally to one another in the projectile, wherein the plurality of magnetometers are adapted to take first flight vector measurements of the projectile; a plurality of angular rate sensors in the projectile and proximate to the plurality of magnetometers, wherein the plurality of angular rate sensors are adapted to take second flight vector measurements of the projectile; a digital signal processor adapted to combine the first and second flight vector measurements to estimate Euler angles associated with a position of the projectile; and a calculator adapted to determine an attitude of the projectile based on the estimated Euler angles. Preferably, the plurality of magnetometers comprises three magnetometers aligned within the projectile, and wherein a first one of the magnetometers is aligned with a spin axis of the projectile.

Abstract: Disclosed are antenna embodiments and air vehicles so equipped that include a first antenna component, and a second antenna component, separated by a free space gap, where the antenna embodiments are adapted to capacitively couple the first antenna component and the second antenna component across one or more portions of the free space gap and where the first antenna component member has a degree or axis of rotation, relative to the second antenna component.

Abstract: The invention described herein provides an apparatus and a method to cooperatively track and intercept a plurality of highly maneuvering asymmetric threats using networks of small, low-cost, lightweight, airborne vehicles that dynamically self-organize into an ad hoc network topology. This is accomplished using distributed information sharing to maintain cohesion and avoid vehicle collisions, while cooperatively pursuing multiple targets. An oracle vehicle relays network information to a control base.

Abstract: The present invention relates to process for producing a transparent missile dome having a spanning angle larger than 180°, comprising the step of: (a) growing from single crystals of a ceramic material a first dome portion, said first dome portion being a portion of a sphere (b) growing from single crystals of a ceramic material a second dome portion, said second dome portion being a complementary sphere-portion for said first dome portion (c) attaching said complementary dome portion to said first dome portion and to the body of the missile, thereby forming a missile with a front dome having a spanning angle larger than 180°.

Abstract: A rocket tube for housing a reloadable rocket motor is connected to a spacer element and a wire-rider element. A sensor target for reflecting radar signals is screwably attached to the rocket tube. The sensor target is provided with a plug for effectively sealing one end of the rocket tube with the other end of the rocket tube being utilized to reload a rocket motor upon completion of a test firing. A guide wire is threaded through the wire-rider element with the guide wire serving as a travel path. The rocket tube, spacer element, and wire-rider element are connected in an easily assembled, aerodynamic manner that allows for multiple radar tests using the same components within a brief time period.

Abstract: There is provided a guidance system for allowing an air vehicle to guide a moving object, comprising a Synthetic Aperture Radar located on the air vehicle, and a means of communication for allowing the air vehicle to communicate with the moving object, wherein the Synthetic Aperture Radar is capable of determining the position and orientation of the air vehicle relative to a desired location, and information provided by the Synthetic Aperture Radar is used, via the means of communication, to guide the moving object towards the desired location. A guidance system wherein a seeker is utilised on the moving object is also provided.

Abstract: A trajectory control system includes a first control mechanism having a pair of outputs operably associated with a first pair of control surfaces, the first control mechanism operable to articulate the first pair of control surfaces in unison and a second control mechanism having a pair of outputs operably associated with a second pair of control surfaces, the second control mechanism operable to articulate the second pair of control surfaces in unison. The second control mechanism is nested in the first control mechanism such that the pair of outputs of the first control mechanism is substantially coplanar with the pair of outputs of the second control mechanism.

Abstract: The present invention includes, in its various aspects and embodiments, a method and apparatus for determining whether a moving target is maneuvering. The method comprises determining an expected motion for the target assuming the target is not maneuvering; determining an upper bound and a lower bound for the expected motion; and determining whether the actual motion exceeds at least one of the upper and lower bounds of the expected motion. In one aspect, the apparatus is a program storage medium encoded with instructions that, when executed by a computing apparatus, perform such a method. In another aspect, the apparatus is a computing apparatus programmed to perform such a method.

Abstract: An optical matrix switch station (1) is shown mounting a plurality of optical switch units (15, 17), each of which includes a mirror (29), moveable in two axes, for purpose of switching light beams from one optical fiber to another. A mirror assembly (41) is formed from a single body of silicon and comprises a frame portion (43), gimbals (45), mirror portion (47), and related hinges (55). Magnets (53, 54) and air coils (89) are utilized to position the central mirror surface (29) to a selected orientation. The moveable mirror and associated magnets along with control LED's (71) are hermetically packaged in a header (81) and mounted with the air coils on mounting bracket (85) to form a micromirror assembly package (99) mounted in each optical switch unit.

Abstract: The centroid of the discrete components forming the overall radar return from a target onto which a homing weapon is being guided may not coincide with a desired aimpoint on the target. Herein proposed is the discrimination and comparison of returns from different portions of the weapon sensor's field-of-view, i.e. different portions of the target and guidance of the weapon in dependence upon the relative values of the differences between those returns. As a result, the weapon can hit say the center of a tank turret roof rather than the probably heavily armored area forward of the turret roof.

Abstract: A method and apparatus for guiding a vehicle to intercept a target is described. The method iteratively estimates a time-to-go until target intercept and modifies an acceleration command based upon the revised time-to-go estimate. The time-to-go estimate depends upon the position, the velocity, and the actual or real time acceleration of both the vehicle and the target. By more accurately estimating the time-to-go, the method is especially useful for applications employing a warhead designed to detonate in close proximity to the target. The method may also be used in vehicle accident avoidance and vehicle guidance applications.

Abstract: System for launching a missile from a launch region within the atmosphere of a planet, the missile being located within a flying vehicle before launching the missile, the system including a missile support coupled with the missile, and a foldable control-surface mechanism coupled with the missile support, the foldable control-surface mechanism being in a folded position before ejecting the missile support and the missile from the flying vehicle, the foldable control-surface mechanism moving from a folded position to an operational position after ejecting the missile support and the missile from the flying vehicle, wherein the foldable control-surface mechanism maneuvers the missile and the missile support to a predetermined orientation suitable for launching the missile, wherein the missile support is decoupled from the missile when the missile and the missile support are at the predetermined orientation, and wherein the missile is launched after reaching the predetermined orientation.

Abstract: Disclosed are a system, method, and program storage device implementing the method, of data fusion, wherein the method comprises determining pre-launch data affecting a flight of a self-sensing air-bursting ballistic projectile, the projectile comprising a plurality of independent data sensors; predicting a trajectory path of the projectile based on a target location of the projectile; calculating trajectory path errors based on the predicted trajectory path; generating in-flight data from each of the data sensors; combining the in-flight data into a single time-series output using a fusion filter; tracking a trajectory position of the projectile based on the single time-series output, pre-launch data, and the trajectory path errors; comparing the tracked trajectory path with the predicted trajectory path; analyzing the in-flight data to gauge successful navigation of the projectile to the target location; and self-guiding the projectile to the target location based on the trajectory position.

Abstract: Measurement of a spatial velocity vector in order to make determination of a geographical position possible. A spatial velocity meter includes an inertial measurement unit, a direction-sensing module and a velocity processor. The inertial measurement unit registers acceleration parameters and angular velocity parameters in three dimensions. The direction-sensing module registers a natural reference signal. The velocity processor receives the acceleration parameters, the angular velocity parameters and the natural reference signal, and based thereon, generates the spatial velocity vector.

Abstract: The present invention relates to planning of a trajectory for minimum threat exposure in a given geographical region. A trajectory is planned from a start node to a final node in a digital representation of the geographical region. The threat exposure for a vehicle moving along the trajectory is determined. Navigation performance of the vehicle along the trajectory is evaluated. A rate of survival based on threat exposure and navigation performance along the trajectory is estimated. A new trajectory is planned from the start node to the final node until a best rate of survival is established for the planned trajectory.

Abstract: A target identification and tracking system includes a carrier vehicle and one or more tracking vehicles. The carrier vehicle may determine an aimpoint of a target from a high resolution image of the target and may generate an offset from a tracking point to the aimpoint. The offset may be conveyed to an assigned tracking vehicle for tracking the tracking point of the target while navigating toward the aimpoint of the target. The tracking point may be the target's centroid. The carrier vehicle may employ a high-resolution LIDAR imaging system to identify the aimpoint from a target's features; while the tracking vehicle may employ a lower resolution optical imaging system for tracking the target's tracking point. The carrier vehicle may correct the offset for parallax and the offset may be revised as the tracking vehicle approaches the target.

Abstract: A fast acting active protection system for military vehicles defeats RPG (rocket propelled grenade) threats fired from close ranges. The system minimizes the hazard to troops and civilians nearby. The system uses a plurality of passive sensors to locate the threat and initialize the system. A low cost radar or laser tracker is used as the means to determine range, velocity, and (if required) angular position of the threat. The countermunition used may be one of several choices, with the requisites being that the countermunition provides fast response with low inertia, and is able to damage or destroy the detected threat. A multi-barrel recoilless gun is the weapon of choice. A launching device is used to deploy and aim the countermunition and the tracking means. On board software and electronics are used to control the system.

Abstract: A system for measuring a position and orientation of an object in flight relative to a reference coordinate system is provided.

Abstract: A method for intercepting and a defeating rocket propelled grenade (RPG) which includes the steps of detecting a thermal signature from a launch of the RPG; and cueing a narrow beam radar which locates the RPG and develops a ballistic solution and target intercept point for intercepting the PPG with an intercept vehicle.

Abstract: A wide field-of-view optical system that may be used in determining a direction to a source of light, or for determine steering corrections to direct a vehicle toward a target, is disclosed. The optical system, which may be used as a seeker in a missile or other weapon, comprises a spherical ball lens truncated to provide one or more facets on which detectors may be mounted to measure relative intensities as a blur spot image of a source of light, which may be a reflection from a laser designated target, moves across the detectors, which may be individual elements in a quadrant detector. Narrow band filters may be used to suppress undesired wavelengths and enhance performance. The innovative design enables implementation of a wide field-of-view seeker with no moving parts. The spherical ball lens may be used directly as an aerodynamic surface without a need for a separate optical dome.

Abstract: A dual-mode target seeking apparatus having a seeker dome defining an aperture and transmissive to microwave frequency energy of a first frequency and to light wave energy at a second frequency and at a third frequency. An optics system within the seeker dome is transmissive to the microwave frequency energy reflective to the light wave energy received via the aperture. A first detector receives the microwave frequency energy via the aperture, and a second detector images a target by the light wave energy of the second and third frequencies via the optics system.

Abstract: A deployment and orientation device for projectile control surfaces, the deployment being carried out by means of springs between a loading position in which the control surfaces are folded inside the projectile and held against the action of the spring means using blocking means, and a deployed position in which the control surfaces may be oriented with respect to the projectile, device wherein it incorporates motors ensuring firstly the deployment of the control surfaces and secondly their orientation, the blocking means for the control surfaces being single means ensuring the immobilization of all the control surface and enabling them to be released simultaneously, the blocking means being immobilized by first locking means released by the pivoting of the bodies of the motors.

Abstract: A covert tracer round has an infrared emitter of radiation mounted to its front, side or back. The radiation (which may be coherent or incoherent) is detected by a sensor that displays an image of the target and the beam. The sensor receives the beam directly if the emitter is on the back of the round and by reflection off the target or nearby objects if the emitter faces forward. The round may include a fixed or moveable collimating lens. The emitter may radiate radially from the round to signal troops or devices located along its path. The round may include sensors that gather significant information about chemicals or biological agents, about magnetic or gravitational anomalies or any other remotely detectable property and transmit that information to the sensor by modulating the emitted radiation.

Abstract: A guidance system for a missile with a laser beam source located at a distance from the missile generating a modulated laser beam that is directed towards the missile. A group of backward looking sensors on the body of the missile detect any radiation scattered from the laser beam along with a group of forward looking sensors located on the missile. Both groups look at an angle to the missile's longitudinal axis. Signals from the sensors are applied to processing electronics in the missile that determine the phase shift in signals derived from when a backward looking sensor detects scattered radiation from a laser beam and a forward looking sensor detects scattered radiation from that beam. The processing electronics can then accurately determine the distance between the missile and the beam from the phase shift and correct the missile's trajectory to maintain its position with respect to the beam.

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiralling motion without the aircraft rolling. Two fins 6 and 17 are attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The fins 6, 17 are able to rotate in a pivoting manner on the rotatable tube 3 with respect to the rotatable tube 3, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 3. Fin 6 is larger than fin 17. The difference in sizes between the fins makes the larger fin 6 exert a greater force on the rotatable tube 3 than the smaller fin 17 when the fins are pitched in unison. The aerodynamic imbalance between the fins thus causes the rotatable tube 3 to rotate. When pitched at an angle to the longitudinal axis in unison, both fins 6, 17 would exert a lateral force on the rotatable tube 3. Thus, as well as forcing the rotatable tube 3 to rotate, the fins 6, 17 would also push the rotatable tube sideways.

Abstract: A 2-D correction system uses intermittent deployment of aerodynamic surfaces to control a spin or fin stabilized projectile in flight; correcting both crossrange and downrange impact errors. Intermittent surface deployment develops rotational moments, which create body lift that nudge the projectile in two-dimensions to correct the projectile in its ballistic trajectory. In low spin rate projectiles (“fin stabilized”), the rotational moment directly produces the body lift that moves the projectile. In high spin rate projectiles (“spin stabilized”), the rotational moment creates a much larger orthogonal precession that in turn produces the body lift that moves the projectile. The aerodynamic surfaces are suitably deployed over multiple partial roll cycles at precise on (deployed) and off (stowed) positions in the cycle to nudge the projectile up or down range or left or right cross range until the desired ballistic trajectory is restored.

Abstract: A heat seeking missile decoy device mounted on a military vehicle to change the infrared signature of the military vehicle. The device is at ambient temperature when stored on the military vehicle. When a heat seeking missile is fired at the military vehicle, the decoy device deploys and increases in temperature, changing the infrared signature of the vehicle and causing a hot spot away from vulnerable components of the vehicle. The hot spot radiates in the infrared in an area that is away from vulnerable parts of a military vehicle, drawing the heat seeking missile toward it. The termination trajectory of the heat seeking missile is at the end of the decoy device and not the vulnerable parts of the military vehicle. The energy required to heat the device is passive waste energy from the vehicle engine exhaust.

Abstract: In some pseudo-orthogonal waveform embodiments, a radar system transmits pseudo-orthogonal waveforms and performs multiple correlations on a combined single receiver channel signal. In some quadratic polyphase waveform embodiments, a radar system may simultaneously transmit frequency separated versions of a single quadratic polyphase waveform on a plurality of transmit antennas, combine the return signal from each antenna into a combined time-domain signal, and perform a Fourier transformation on the combined time-domain signal to locate a target. The radar system may identify a target, such as sniper's bullet, incoming projectile, rocket-propelled grenade (RPG) or a mortar shell. In some embodiments, the system may estimate the target's trajectory to intercept the target. In some embodiments, the system may estimate the target's trajectory and may further extrapolate the target's trajectory to locate the target's source, such as the sniper.

Abstract: A guidance system for a missile utilitizes a laser beam source at a missile launch pad to generate a laser beam that is directed towards a target. A sensor on the body of a spinning missile detects radiation scattered from the laser beam, the sensor looking sideways and backward at an angle to the missile's longitudinal axis. Signals generated by that sensor are applied to a missile's guidance system's processing electronics that then determines the distance from the missile to the beam from the width of the signal generated by the sensor due to detecting scattered radiation from that laser beam. Once the distance between the missile and the beam is determined, the missile's guidance system corrects the missile's trajectory to maintain its position at a predetermined distance from the beam.

Abstract: A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.

Abstract: A method for ballistic target defense including identifying a launched ballistic target having a target launch point, a target launch direction, a target speed, and a target trajectory; launching a target interceptor in a launch direction that is generally the same as the target launch direction and with a speed that is less than the target speed; providing the interceptor with an approximate target intercept trajectory; and accelerating the interceptor at an approximate point of intercept to substantially match the target trajectory. During a relatively long target engagement time, the interceptor has approximately a zero net relative velocity with respect to the target.

Abstract: A system and method for interconnecting analog legacy stores to both legacy and modern aircraft. One aspect of the invention provides for a dual mode launcher having a first interface for interfacing with a modern aircraft and a second interface for interfacing with a legacy aircraft. Either the first or the second interface is connected to the aircraft depending on the hardware platform supported by the aircraft. Signals received from either interface are converted to digital and placed on a digital input/output bus and converted to analog for use by the store. Likewise, signals transmitted by the store to the aircraft are converted to digital and placed on the digital input/output bus for transmission to the aircraft. The signals are further acted upon depending upon which interface is connected to the dual mode launcher assembly. The dual mode launcher provides seamless operation of the store interface regardless of which type of aircraft is equipped to carry the analog store.

Abstract: A method for attitude alignment of a slave inertial measurement system connected to a rotationally mobile platform supported by a vehicle that is stationary relative to a reference navigation frame comprises the steps of mounting a master reference inertial measurement system on the rotationally mobile platform and determining a master reference system attitude using measurements of acceleration and angular rates of the master reference inertial measurement system relative to the reference navigation frame. A slave system attitude is determined using measurements of acceleration and angular rates of the slave inertial measurement system relative to a slave system navigation reference frame and comparing the slave system attitude to the master reference system attitude to determine an attitude difference. The attitude difference is processed to obtain a correction to the slave system attitude.

Abstract: A guidance system for guiding each of several projectiles toward a moving target has a platform having a radar system for illuminating the target with a radar signal. Each projectile has a receiver for receiving the radar signal reflected from the target, a transponder for replying to Global Positioning System (GPS) like timing signals from several timing signal sources, and a data link transceiver for establishing a bidirectional data link to the platform. The data link carries the measured frequency shift of the radar signal reflected from the target as measured by the projectile. A computer on the platform computes a relative position of each projectile with respect to the target from tracking the moving target using the radar system and the reply signal from the transponder on each projectile. The data link sends guidance commands from the platform to each projectile to guide the projectile to the target.

Abstract: A missile includes a tail section having a multi-nozzle grid with both fixed nozzlettes, and movable, thrust vector nozzlettes. The movable nozzlettes may be configured in a number of discrete array bars, each containing multiple of the movable nozzlettes. Movement of one or more array bars may be used to vector the thrust of the missile, providing roll, yaw, or spinning of the missile, for example.

Abstract: A process to control the trajectory of a spinning projectile. The projectile's accelerations are measured by means of an inertial unit in three axes within a reference linked to the projectile so as to prepare the piloting commands for the projectile's trajectory. The velocity vector V components (VX, VY, VZ) of the projectile are measured using a global positioning system (GPS) along three axes and within a land reference (GX, GY, GZ). Based on these measurements, the components (?X,?Y,?Z) of the acceleration vector ? are evaluated in the same land reference (GX, GY, GZ). At each of these measurements and periodical evaluations by the GPS, the Euler angles of the projectile are recalculated by combining the resultants of the velocity (V) and acceleration (?) measurements given by the GPS and those of the acceleration given by the inertial unit.

Abstract: An interceptor device for protecting a platform against an incoming threat is provided. The interceptor device comprises a housing and a countermeasure device. At least one detonating charge is capable of deploying the countermeasure device. A controller device housed by the housing is capable of directing the detonating charge(s) to deploy the countermeasure device at least partially radially outward of the housing, corresponding to the threat trajectory. A sensor device is in communication with the controller device, and comprises a range-finding apparatus including one of a LADAR, a RADAR, and a LIDAR device, capable of sensing the threat and/or a range thereof, at least partially radially outward of the housing, and notifying the controller device if the threat is sensed, to cause the controller device to direct the detonating charge(s) to deploy the countermeasure device to impact the threat in the intercept zone. Associated systems, and methods are also provided.

Abstract: A three-axis attitude control propulsion device and a flying object like a rocket including the device are provided in which combustion gas for attitude control can be efficiently used. A three-axis attitude control propulsion device 4, having six nozzles has a motor case 6 and three-way discharge changeover valves 10, 10? of a valve plug rotation type enabling a changeover of a flow passage by rotation of the valve plug. Combustion gas 18 is generated by combustion of propellant 8 in the motor case 6. The three-axis attitude control propulsion device is operated so that one or two of the nozzles are opened to thereby discharge the combustion gas 18 and the remaining five or four nozzles are fully closed. Thereby, a three-axis attitude control of pitch control, roll control and yaw control, and control of a neutral state, can be selected.

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiralling motion without the aircraft rolling. Two fins 6 and 17 are attached to a tube 3a that is able to rotate around the encircled part of the fuselage. The fins 6, 17 are able to rotate in a pivoting manner on the rotatable tube 3a with respect to the rotatable tube 3a, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 3a. Rotation of the rotatable tube is achieved by using an electric motor 3b turning a wheel 3c. The wheel 3c makes contact with the rotatable tube. When pitched at an angle to the longitudinal axis in unison, both fins 6, 17 would exert a lateral force on the rotatable tube 3a. But as the rotatable tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiralling motion of the aircraft when in flight. The rotation of one fin causes the rotation of another fin.

Abstract: A guided missile having a longitudinally extending airframe with a tip, a seeker head arranged in the tip and a window located in front of the seeker head for closing the airframe at the tip so as to protect the seeker head. A jettisonable protective cap consisting of at least two separable parts is attached to the airframe in front of the window for protection of the window.

Abstract: A method and structure for a full-bore artillery projectile fin deployment device comprising a projectile stabilization fin comprising an aperture and a movable pawl; a rod comprising a head portion and a shaft portion terminating with a beveled tip configured for engaging the pawl; a tailboom configured for housing the fin, wherein the tailboom comprises a hollow bore configured for receiving the rod; a pin slotted through the aperture and attached to the tailboom; and a bias member adjacent to the head portion of the rod. The rod is slotted to simultaneously engage a plurality of fins. The tailboom comprises a forward end and a rearward end and a slot configured for permitting the fin to articulate out of the tailboom, and wherein the tailboom connects to a projectile. Additionally, the power source for the device is the naturally occurring launch accelerations.

Abstract: A weapons system is disclosed that provides hot-start navigational information to the Global-Positioning-System receivers on missiles prior to flight. The system comprises a Global-Positioning-System receiver that uses a classified red cryptographic key to decode the P(Y) signal from one or more of the Global-Positioning-System constellation of satellites. Once the P(Y) signal is decoded, one or more characteristics of the P(Y) signal is derived. These characteristics of the signal—and some other information including a black cryptographic key that comprises the red cryptographic key—are then provided to the Global-Positioning-System receivers on missiles prior to flight. By giving the missiles this information, the missiles are able to acquire the P(Y) signals, which enables them to determine their position more quickly than they otherwise could.

Abstract: Disclosed is an autonomous radar guidance of an otherwise radar-directed projectile (RDP). The preferred embodiment uses an inexpensive radar receiver with an inexpensive slow wave antenna, placed internally in a gun projectile, and on the surface of the projectile, respectively. The receiver detects the angle and range of the target relative to the body coordinates of the projectile. The radar receiver operates as a bistatic radar apparatus with the primary illumination emanating from the fire control radar directing the fire of the gun. When integrated with an on-board trajectory correcting system, such as divert thrusters of miniature proportions, the projectile autonomously refines its otherwise ballistic trajectory to the target. The trajectory refinements produce improved kills per round, with the potential for reducing the ammunition expended and time-loading on the fire control system and its guns.

Abstract: An interceptor device adapted to protect a platform associated therewith against an incoming threat having a trajectory by intercepting the threat in an intercept zone is provided. Such an interceptor device comprises a housing defining an axis and a countermeasure device operably engaged with the housing. At least one detonating charge is housed by the housing and is operably engaged with the countermeasure device. A controller device is in communication with the at least one detonating charge, wherein the controller device is housed by the housing and is configured to direct the at least one detonating charge to deploy the countermeasure device at least partially radially outward with respect to the axis of the housing and in correspondence with the trajectory of the threat to thereby cause the countermeasure to impact the threat in the intercept zone. Associated apparatuses, systems, and methods are also provided.

Abstract: A system for determining the distance between a target (4) and a laser guided weapon traveling towards the target (4). The system (1) comprises a laser designator (5) on a remote platform (2) for radiating a first train of pulses (l1) on a set wavelength in the direction of the target (4). In the weapon (3) a receiver (6) is arranged to receive and detect pulses on the set wavelength reflected from the target (4). There is also a direction sensing means in the weapon (3) for determining the direction of the target (4). A transmitter (7) is arranged in the weapon (3) to periodically transmit a second train of pulses (l2) on the set wavelength in the direction of the target (4). There are means in the receiver (6) to extract a reflection from the target (4) of the second train of pulses (l2). There are further timing means to determine the period of time from transmitting the second train of pulses (l2) to receiving the reflection from the target (4) of the second train of pulses (l2).