Abstract: The Dual-Sliding Fin Lock Assembly provides a simple, cost-effective and secure locking mechanism that engages on the initial opening stroke of a fin of a flying object, using a minimal number of parts that are easy to manufacture. Two sliding locks, each having a protruding step, engage with two fin lugs each of which has a corresponding notch. When a step and a notch fit together, they form a contact plane which may be straight horizontal or inclined to ensure robust locking operation without the need for extremely tight tolerances on the individual parts or on the assembly. Since the sliding locks do not rotate around the pin that holds the fin lugs, they engage the fin lugs to arrest the rotation of the fin and retain it securely in the deployed position for the duration of the object's flight, guiding the object more accurately toward its destination.

Abstract: The Trajectory Correction Kit (TCK) is a completely self-contained retrofit kit that is externally and fixedly mounted as an add-on to the rear (aft of the tailfins) of an existing, unguided rocket. The TCK continuously measures the pitch and yaw of the rocket as it is released from the launch tube and during the initial seconds of the flight and calculates the trajectory correction that is necessary to eliminate the measured pitch and yaw. Then it activates selected thrusters among the thrusters that are positioned around the circumference of the rocket body so as to steer the rocket in a direction until the measured pitch and yaw are eliminated. This results in significant reductions in both the rocket flight path dispersion and collateral damage.

Abstract: The Variable-Force Payload Ejecting System, residing within an air vehicle, utilizes multiple pressure generators, one or more of which may be activated, to produce variable levels of force. A controlling computer within the air vehicle determines when and how much pressure needs to be generated to eject a given item, such as a submunition, from the vehicle. In its determination, the computer factors in the vehicle's forward velocity and height over the intended target at the time of ejection and the characteristics of the particular submunition to be ejected. An activating mechanism activates one or more pressure generators to produce the determined amount of pressure. The pressure thusly generated acts on an inflatable tube that inflates and expels the selected submunition. The result is a more precise delivery of the submunitions onto the intended targets.

Abstract: Stereolithography is used to fabricate directly a single-piece, missile-usable, accurate, flightweight igniter without the use of intermediate, non-operational molds or prototypes in the fabrication process. The same prototype-less, direct stereolithography can be used to produce other missile-usable parts by designing each such part to be of a single-piece configuration and by using material that is suitable for both stereolithography and functional missile application.

Abstract: Sliding-Action Magneto-Mechanical Injector Throttling Device (SLAMMIT) provides on-demand, yet accurate, throttling of the mass flow of the fuel and/or oxidizer into the combustion chamber of a vortex injector. At least two SLAMMIT sub-assemblies comprise the SLAMMIT Device and each sub-assembly is integrated into a manifold and is driven to slide in a given direction by a drive block that is internal to the sub-assembly. The drive block is, in turn, actuated by an electromagnet that is external to the SLAMMIT sub-assembly. As the SLAMMIT sub-assemblies slide, flappers inside the sub-assemblies achieve the effective opening size of the injection orifices anywhere between fully open and fully closed.

Abstract: A radial piezoelectric motor comprises a housing, a motor shaft rotatably mounted in the housing and a plurality of piezoelectric actuators inside the housing radially disposed about the axis of the motor shaft. The motor also includes circuitry for applying a voltage to the piezoelectric actuators to expand the actuators repeatedly and in succession and apparatus responsive to the repeated and successive expanding of the actuators for rotating the motor shaft.

Abstract: Parametric processing capability is added to a typical sensor so that a target object can be more clearly distinguished from the background clutter in a given scenery. A polarizer with several segments of different polarization orientations is used to improve the typical sensor. The segments are sequentially advanced to pass therethrough infrared radiation images of pre-selected polarization orientations which are then collected by respective polarized frame grabbers. Image processing circuit processes these images to yield the polarization difference between any given pair of orthogonal polarizations. In a surveillance network, the polarization differences are subsequently used in the control center, to which such sensors are connected, to enhance the distinction of the observed objects against the background clutter suspended in the propagation medium.

Abstract: Asymmetrical Control Surface System for Tube-Launched Air Vehicles places one control surface, such as a wing or a horizontal tail, above horizontal midplane axis of an air vehicle, such as a tube-launched missile, and the opposing control surface below the midplane axis. Such asymmetrical arrangement of the control surfaces increases the lift and maneuverability of the air vehicle during flight. For stowage inside the tube prior to launch, each control surface slides into its corresponding slot in the body of the vehicle, making the entire control system compact.

Abstract: The system and method for radar calibration using antenna leakage is a simplified means of calibrating the channels in amplitude and phase using natural signal leakage between antennas. It utilizes as calibration signal a wideband sinusoidal Frequency Modulated Continuous Wave (FMCW) waveform with a modulation index and modulation frequency chosen to generate spectral components (or discrete signal frequencies) that fall within the receiver Doppler passband of the radar. The calibration signal is radiated out of the transmitting antenna and enters the radar receiver front-end through the transmit-to-receive antenna leakage which occurs naturally. This technique provides a low-complexity (simpler hardware realization) means for achieving a wideband calibration rapidly and is a practical alternative to the conventional calibration approach that relies on generating offset Doppler signals that are coupled into the radar receiver front-end through the use of couplers and cabling within the radar.

Abstract: Applicant's Differential-Pressure Torque Measurement System generates the torque signal from a differential gas pressure measured across the power turbine. The gas pressure differential is measured by using two pressure taps, the first tap taking the pressure reading of the expanding gas as the gas travels from the gas-generating turbine to the power turbine of the engine and the second tap taking the pressure reading of the gas as it escapes the engine through the exhaust port. The differential between the two pressure readings is determined. The pressure differential is then input to a processor which processes it in a pre-determined fashion along with the rotational speed signal of the power turbine, initial pressure and the temperature measurements of the air as the air is initially inlet into the engine. The result of the processing are various engine parameter indications including the torque.

Abstract: Applicants' ATR system is weather-agile because it is comprised of a primary target sensing means that is capable of surveilling the target scene in foul or fair weather, and a secondary target sensing means that is also capable of sensing targets in various weather. The primary and secondary sensing means communicate through a control center so that ultimately, among several weapons available, the most strategically located and equipped weapon is activated for the destruction of a selected target, given the weather. The control center accomplishes the communication by receiving the sensed target signature from the primary sensing means, processing the signature using database already resident in the center and transmitting the processed target signature to the weapon possessing the greatest potential for successfully destroying the target.

Abstract: Applicants' Contention-Resolution System for a Command-Response Data Network uses a base unit (base) that detects the occurrence of collisions for the entire network and controls the maximum length of time allowed for the multiple remote units (remotes) in the network before re-trying to send responses to the base. The base either expands or contracts this maximum time delay as needed to accommodate the number of the possible network remotes, depending on the detected collision rate and the overall utilization of the network until the base determines that there are no remotes to be registered or all of the available network slots are filled, whichever occurs first.

Abstract: A Real-Time Optical Correlating System produces holograms that contain both amplitude and phase information and have none of the time constraints of the traditional holographic methods. It has been demonstrated to operate at television field rates (60 Hz) employing currently available devices of moderate resolution. Using the System, the holographic matched filter of an input scene is calculated optically as an analog sum, captured by a charge-coupled device (CCD) camera and transmitted directly or through a computer to and displayed on a commercially available liquid crystal display (LCD) device. The correlation plane may be viewed immediately on a suitable screen because there is no film to process or computer calculations to be performed. Concurrently with the creation of the holographic matched filter of the input scene, a Fourier transform of a test scene is produced and both are imaged on another charge-coupled device camera for any correlation between the input and test scenes.

Abstract: The Continuous Aimpoint Tracking System is comprised of a position detection device (PDD) and a laser pointing device (LPD) that projects an infrared crosshair onto the PDD. The PDD is coupled to a computer and comprises a multitude of photodiodes and associated circuits, the photodiodes being evenly spaced and arranged to form a frame that can be mounted on the computer so as to surround the computer video display. When a “shot” is fired from the LPD, the crosshair projection is interrupted briefly. The PDD determines the position of the four crosshair intersections and reports them to the computer which, in response, generates the video signals that form the resolved aimpoint on the screen, matching the LPD aimpoint to the video image. Further, the tracking system determines the rotation of the LPD over a range of at least 10 degrees clockwise or counter-clockwise.

Abstract: An improvement in a semi-active laser last pulse logic missile seeker is disclosed and claimed. In one embodiment, the improvement includes a first polarizer disposed in the detection field of view of the PIN photodiode detector and a second polarizer disposed in the detection field of view of the staring imaging infrared focal plane array. Each of the first and second polarizers has an identically configured plurality of segments. Each segment allows transmission of a different polarization than other segments and is sized to completely cover the fields of view of both the PIN photodiode detector and the staring imaging infrared focal plane array. First and second actuators are connected to the first and second polarizers, respectively, to synchronously and simultaneously step identical and corresponding segments in a plurality of discrete steps within the fields of view in response to incoming temporal and spatial laser returns.

Abstract: The locking and stabilizing device for grenades utilizes a solid nylon ring and multiple nylon ribbons that are attached to the ring at regular intervals around its circumference. During storage, the ring surrounds and locks the slider of the grenade in its storage position. But upon deployment, under aerodynamic forces the ring moves away from the slider, releasing the slider. When the slider is thusly released, it slides out and brings the detonator in place to be impacted upon by the pin when the grenade hits the target, thus detonating the grenade. The multiple ribbons extending from the ring unfurl due to the aerodynamic forces and provide stability to the grenade flight.

Abstract: The Dragless Flight Control System for Flying Objects utilizes paired fins that are mounted to rotate in opposite directions. When no lift is desired during the object's flight, the fins are completely retracted into their housings that are recessed into the body of the object. This minimizes the drag. The fins are set to a maximum no-stall angle relative to the body axis of the flying object. To provide lift and other flight controls, such as roll and yaw, the fins are selectively exposed outside the exterior skin of the flying object by being rotated on their axes, the two fins in a pair always being rotated in opposite directions. Varying the amount of exposed area of the counter-rotating fins can generate lift effect that is proportional to the exposed area and similar to that produced by the current, permanently-extended standard rotational fins.

Abstract: The Multiple-Antenna Jamming System (MAJS) is useful for missile-borne jamming of active protection system radars that operate in close proximity to the frequency band of the missile's radio frequency seeker. The MAJS utilizes multiple receiving and transmitting antennas to reduce shadowing effects due to the transmissive radome. It also channelizes the jamming signals into in-seeker-band and out-of-seeker band signals to synchronize the transmission of jamming signals with the emit-listen pattern of the missile seeker and to eliminate the problem of de-sensitizing the RF seeker from the jammer energy. The in-seeker-band jamming signals are transmitted only concurrently with the missile seeker emissions and any signals emanating from an enemy radar are received only during the listen mode of the missile seeker.

Abstract: The Dragless Flight Control System for Flying Objects utilizes paired fins that are mounted to rotate in opposite directions. When no lift is desired during the object's flight, the fins are completely retractable into their housings recessed into the body of the object. This minimizes the drag. The fins are set to a maximum no-stall angle relative to the body axis of the flying object. To provide lift and other flight controls, such as roll and yaw, the fins are selectively exposed outside the exterior skin of the flying object by being rotated on their axes, the two fins in a pair always being rotated in opposite directions. Varying the amount of exposed area of the counter-rotating fins can generate lift effect that is proportional to the exposed area and similar to that produced by current permanently extended standard rotational fins.

Abstract: On-Board Power Generation System for a Guided Projectile eliminates the need for batteries as a power source to power the guiding mechanism residing inside the projectile. Instead, an electrical generator and a wind-driven turbine to drive the generator are utilized to produce power. In this way, a small portion of the projectile's kinetic energy is converted into electrical energy. The power thusly produced is, then, coupled to the guiding means. The projectile is appropriately configured to accommodate therein the power generaion system and air inlets and exhaust ports that are necessary to enable the system to operate.