Abstract: A voltage tracking system for an ion thruster includes a discharge chamber, a screen grid, an accelerator grid, and an accelerator grid voltage controller. The discharge chamber contains plasma at a given potential. The screen grid is adjacent to the discharge chamber and is voltage biased relative to the plasma to form a plasma sheath that repels electrons and attracts ions from the discharge chamber plasma. The accelerator grid is adjacent to the screen grid and has a voltage for accelerating the ions to create thrust and prevent any electrons from backstreaming into the ion thruster from the beam plasma. The accelerator grid voltage controller supplies voltage to the accelerator grid. The accelerator grid voltage controller adjusts the magnitude of the accelerator grid voltage to minimize the amount of voltage required to prevent electron backstreaming into the ion thruster.

Abstract: A slot antenna for the fuse of artillery ammunition, is provided through a sandwich structure in which an axially divided resonator ring chamber axially enclosed between upper and lower metallic cover discs profiled to be stable in respect of shape, is provided with a dielectric ring disc which extends with a peripherally extending color radially opposite a central cylindrical reflector wall through an axial slot between the two hollow-cylindrical outside walls of the ring chamber to the outer surface of the fuse casing which is also peripherally slit.

Abstract: A reflected energy detecting device includes a transmitter for transmitting an electromagnetic signal and a receiver for receiving a reflected electromagnetic signal. An antenna may be operatively connected with the transmitter and the receiver for radiating the electromagnetic signal and capturing the reflected electromagnetic signal and the antenna may be movable. A main controller may be provided for controlling operation of the transmitter and the receiver and the movement of the antenna and the reflected energy detecting device may further include at least one platform. The at least one platform may support a remote reflector that is dimensioned and configured to redirect the transmitted electromagnetic signal in a desired direction and a platform controller that is configured to communicate with the main controller and to maintain alignment between the remote reflector and the antenna.

Abstract: A vehicle guidance system. The system includes a first mechanism for tracking a vehicle based on time-of-arrival information associated with energy emanating from the vehicle and providing vehicle position information in response thereto. A second mechanism steers the vehicle based on the vehicle position information. In a specific embodiment, the system of further includes a third mechanism for locating the target based on time-of-arrival information associated with energy radiating from the target and providing target location information in response thereto. The second the second mechanism steers the vehicle based on the target location information and the vehicle position information.

Abstract: A system and method that guides a device to an object using periodically adaptive guidance. The guidance and control system creates a reconstructed line-of-sight (LOS) vector to avoid system destabilization associated with small angle approximation during high bore sight engagements. The guidance system adaptively estimates the periodic maneuver of evasive objects with a set of harmonically balance Kalman filter banks. The Harmonically Balanced Kalman filter banks generate a set of probabilities that weight the effect of each individual Kalman filters on a resultant guidance command signal. The guidance command signal generated by the system acts perpendicular to the object LOS. The guidance and control system uses vectored proportional navigation guidance laws, optimal proportion navigation laws and periodically adaptive augmented guidance laws to generate a guidance command signal to supply to an autopilot.

Abstract: A method and apparatus for conducting proximity operations is disclosed. The method called inverser proximity operations includes maneuvering an active vehicle into general proximity to a target vehicle, transmitting from the target vehicle to the active vehicle data representing relative position and velocity between the target vehicle and the active vehicle, and maneuvering the active vehicle in accordance with the data to effect a desired proximity operation. Another method called distributed proximity operations includes maneuvering a carrier vehicle into general proximity to a target vehicle, releasing one or more active vehicles from the carrier vehicle, transmitting from the carrier vehicle to the active vehicle(s) data representing relative position and velocity between the target vehicle and the active vehicle, and maneuvering the active vehicle(s) in accordance with the data to effect a desired proximity operation.

Abstract: A target designation system for indicating a target to be destroyed by remotely guided ordnance comprising a receiver arranged to produce a receiver output signal in response to an incident electromagnetic signal from an attack aircraft. An auto-switch is connected to the receiver and arranged to produce a power signal in response to the receiver output signal. A transmitter is connected to the auto-switch to be activated by the power signal. When activated, the transmitter transmits a homing signal that indicates its location or the location of the target.

Abstract: A multi-staged missile includes a booster and a submunition delivery vehicle that has one or more submunitions. The booster rapidly accelerates the submunition vehicle, and then separates from the submunition vehicle. The submunition delivery vehicle is then maneuvered to approach a target. Individual submunitions finally separate, and are individually guided to the target. By providing multiple, independently-targeted submunitions, the missile greatly increases the chances of hitting the target.

Abstract: A guidance method for guidance systems is disclosed. The method includes forming a target track point with a target tracker. The method corrects the track point with a manual correction signal. A speed of rotation of the line of sight is determined with the target tracker. A track control system dynamic model is provided for forming an estimated value for the rotation speed of the line of sight. The estimated value for the rotation speed of the line of sight is formed from the determined speed of rotation of a line of sight corrected with a correction value generated with the dynamic model of the track control circuit based on the manual correction signal. The estimated value of the speed of rotation of the line of sight is then used for guidance.

Abstract: The present invention relates to a towed/surrogate decoy transmitter connectable via the tow cable to a platform or host aircraft using a wireless communicator link, the link providing useful performance and status information of the decoy transmitter to the host aircraft and providing the decoy with control and optimization information from the platform. The tow cable provides a mechanical connection to the host aircraft as well as a prime power connection and in some cases, a fiber optic (FO) interface. In order to optimize the protection provided by the towed/surrogate decoy transmitter, the host aircraft will use the wireless communication link to transmit operational status and control adjustment data back to the towed/surrogate decoy transmitter. The towed/surrogate decoy transmitter utilizes a wireless communicator link that can transmit data to any cooperative host aircraft and any other cooperative towed/surrogate decoy transmitters.

Abstract: A process to determine the impact location of a transmitter-bearing object which is released for tracking purposes or to hit a target within a geographical area, wherein data obtained from the impact location can be used to determine the relation of the impact location and the target.

Abstract: A target designation system for indicating a target to be destroyed by remotely guided ordnance comprising a receiver arranged to produce a receiver output signal in response to an incident electromagnetic signal from an attack aircraft. An auto-switch is connected to the receiver and arranged to produce a power signal in response to the receiver output signal. A transmitter is connected to the auto-switch to be activated by the power signal. When activated, the transmitter transmits a homing signal that indicates its location or the location of the target.

Abstract: An airborne missile launch system. The system includes a Harpoon aircraft command-launch control set (HACLCS) system, one or more Harpoon Block II missiles, and an interface controller coupled to the HACLCS system and the one or more Harpoon Block II missiles. The controller allows a user to create a missile profile mission. The controller combines the created missile profile mission with received positioning information. The missile(s) loads the combination into a navigation system of one of the Harpoon Block II missiles. The controller receives a mission-loaded signal upon completion of mission loading into one of the Harpoon Block II missiles, and converts the mission-loaded signal for interpretation by the HACLCS system.

Abstract: A target designation system for indicating a target to be destroyed by remotely guided ordnance comprising a receiver arranged to produce a receiver output signal in response to an incident electromagnetic signal from an attack aircraft. An auto-switch is connected to the receiver and arranged to produce a power signal in response to the receiver output signal. A transmitter is connected to the auto-switch to be activated by the power signal. When activated, the transmitter transmits a homing signal that indicates its location or the location of the target.

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 system, a missile tracking system, and a ship based 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: An autonomous onboard absolute position and orientation referencing system provides a means of efficaciously and economically embedding guidance and control components into the fins of supersonic, highly maneuverable small, medium-caliber and long range munitions. Embedded resonant cavities form an integral part of the referencing system. The magnitude and phase information received by the integral antennas is used to determine the munition orientation. Embedded sensors provide continuous, onboard information about the angular orientation of the munition, such as its pitch, yaw, and roll angles, as well as its absolute position relative to a ground station.

Abstract: A technique is provided that uses a dual mode seeker (IR and LADAR) for precise target dynamics measurement, which extends stripping to a much higher altitude than ground based radar. Initial results show that this approach works to altitudes in excess of 100 km. Stripping becomes a reliable way to discriminate lighter weight decoys from reentry vehicles at altitudes and ranges consistent with planned divert capabilities for terminal phase missile defense. It is a finding of this invention that the LADAR will improve the spatial resolution by a factor of five over typical missile defense IR seekers using a common aperture. The LADAR provides a 3D angle, angle, range (AAR) image for each laser pulse which is used to extract the precise target state vectors.

Abstract: The present invention relates to a method and an arrangement for guiding a missile. In accordance with the prior art, the angle position of a target (9) when the missile (3) is expected to reach the target is predicted on the basis of the angular velocity determined in a preceding time period. In order to improve the strike accuracy, the operator, in a second subsequent time period, tracks the actual position of the missile in relation to the predicted angle position of the target. If a deviation is observed, a correction command is transmitted to the missile in order to correct the missile trajectory. For this purpose, a communications link is provided to transmit the correction command given by the operator.

Abstract: A missile defense system includes a tracking station for monitoring the course and/or trajectory of an incoming missile. The incoming missile course and/or trajectory information is communicated to an intercept missile, whose course and/or trajectory are calculated based on the information of the incoming missile received from the tracking system and the intercept missile location received from, for example, a GPS system. The tracking system monitors the flight of the incoming missile to determine any changes to its course and/or trajectory, and communicates these changes to the intercept missile. The intercept missile adjusts its course and/or trajectory based on the updated information received from the tracking station to provide accurate and reliable intercept of the incoming missile.

Abstract: A target designation system for indicating a target to be destroyed by remotely guided ordnance comprises a receiver arranged to produce a receiver output signal in response to an incident electromagnetic signal from an attack aircraft. A switch is connected to the receiver and arranged to produce a power ON/OFF signal in response to the receiver output signal. A transmitter is connected to the auto-switch to be selectively activated and deactivated by the power ON/OFF signal. When activated, the transmitter transmits a homing signal that indicates its location or the location of the target being illuminated by the transmitter signal.

Abstract: A system and method (32) for measuring line-of-sight angular rates for all-weather precision guidance of distributed projectiles (16) and a guidance system (10) based thereon. In accordance with the novel method (32) for measuring line-of-sight angular rates, first the range rates of the target (14) relative to at least two projectiles (16) is determined, as well as the position and velocity of each projectile (16). Then, the line-of-sight angular rate of the target (14) relative to at least one projectile (16) is computed from the range rates, positions, and velocities. In the illustrative embodiment, the range rate of the target (14) relative to a projectile (16) is determined based on a monostatic target Doppler measurement, a monostatic projectile Doppler measurement, a bistatic Doppler measurement of the target (14) by the projectile (16), and the carrier frequency of a data link (26) between the projectile and the shipboard system.

Abstract: A munition article is to be provided with an antenna which, by virtue of a characteristic which is uniform all around, permits interference-free reception of items of satellite navigation information, even if in the manner of an artillery projectile it is fired with spin along an elongate ballistic trajectory, so that a tail antenna with a spherical characteristic does not allow the expectation of good reception factors in relation to navigation satellites which are as high as possible above the horizon. Therefore the tip (10) of the fuse tip (11) of the projectile is equipped with a dipole satellite antenna which faces in the direction of flight. Connected to the dipole (13) which is arranged concentrically with respect to the longitudinal axis (14) of the projectile are symmetrically disposed conductor portions (15) which rest with a close fit in recesses (19) in the ballistic cap (12).

Abstract: The present invention provides a ship self-defense missile (SSDM) weapon system for launching a plurality of light weight missiles from an existing vertical tube launch infrastructure. The system for vertically launching missiles from a ship comprises a plurality of tiers having a top tier and a bottom tier in which tier supports a plurality of missiles. The tiers are set into a launch canister having an interior wall to form a vertical stack in the launch canister. A launch means is used for selectively launching at least one of the plurality of missiles from the top tier. A means for ejecting ejects the top tier is depleted of missiles. A vertical movement means raises and lowers the tiers within the launch tube and the vertical movement means raises next tier in the vertical stack into a position to launch.

Abstract: A process for determining roll angle of a body launchable from a launcher. At least one inducing field is induced in the launchable body. A polarized carrier wave is transmitted from the launcher to the launchable body. The transmitted polarized carrier wave is detected in the launchable body with respect to rotation of the launchable body. The detected transmitted polarized carrier wave and the inducing field are analyzed to establish the roll angle as the launchable body leaves the launcher.

Abstract: A combined defense and navigational system on a naval Vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile.

Abstract: A process and a device for electromagnetic guidance of a craft, applied in particular to the tracking of targets. Guidance is carried out with respect to the axis of the beam of a monopulse antenna, by coding in space of the beam. The coding is carried out by appropriate modulation of the signals radiated by a sum pattern and difference pattern. A receiver is disposed in the craft to make it possible to determine the position of the craft with respect to the antenna radiation patterns, and hence its position with respect to the axis of the antenna, the determination of this position being performed by demodulating the signals captured by the receiver. The process and device may be applied in particular in respect of the guidance of any number of missiles or intelligent munitions, for example in the tracking of targets.

Abstract: Processing GPS signals received at moving targets and at a fixed location near instrumentation associated with timing and recording an event allows the determination of instantaneous target position to be made without a requirement for additional active tracking. An example is the recording and display of a test event involving a missile intercepting a target. The missile, target, and an instrumentation site all receive GPS signals. The signals are time tagged and the data contained thereon verified by a source and forwarded from each platform to a ground station. The data is correlated with other test data to provide a real time record and display of the missile intercepting the target. Both Time Space Position Information (TSPI) and Miss Distance Indication (MDI) are derived to a very high degree of accuracy using double difference error correction techniques. Both absolute and relative position information can be derived.

Abstract: The present invention is directed towards a mobile ballistic missile detection and defense system. The system of the present invention comprises a ship based antiballistic missile (“ABM”), a missile launch detection system, a missile tracking system, and a ship based signal processing system capable of receiving said tracking signal, calculating an intercept trajectory for an antiballistic missile to intercept a missile, and further capable of outputting an intercept trajectory program to an antiballistic missile. The ABM system of the present invention is capable of deployment in the vicinity of rogue nations which may pose a ballistic missile threat to the United States.

Abstract: The present invention is directed towards a mobile ballistic missile detection and defense system. The system of the present invention comprises a ship based antiballistic missile (“ABM”), a missile launch detection system, a missile tracking system, and a ship based signal processing system capable of receiving said tracking signal, calculating an intercept trajectory for an antiballistic missile to intercept a missile, and further capable of outputting an intercept trajectory program to an antiballistic missile. The ABM system of the present invention is capable of deployment in the vicinity of rogue nations which may pose a ballistic missile threat to the United States.

Abstract: A missile system and method for performing automatic fire control in which a reconnaissance vehicle is used to gather video reference information of a target and this information is then communicated to a launching vehicle from which missiles are caused to be trained on the selected target by utilizing an automatic target handoff correlator that identifies the selected target, causes an autotracker to be locked on and finally a computer is signaled by the automatic target handoff correlator to cause a missile to be fired.

Abstract: The invention relates to a missile guidance method, more particularly for anti-armor projectiles fired directly at a target. In order to avoid missing a target by a narrow margin, the invention provides that the distance to the target (3) be measured with a range finder (8) before the projectile is fired. The flying time previously calculated on the basis of target distance is inputted to the projectile (1). The projectile (1) has one or several sensors which are activated after a predetermined flying time, said sensor or sensors determining whether the projectile (1) will fly over the target at a minimum distance. Optionally, the projectile (1) conducts a single trajectory adjustment with a fixed value.

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: 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 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: An impulse radar guidance system and method for use with a spinning projectile. The system and method tracks the flight of the spinning projectile using an all-weather radar or tracker. A linearly polarized asymmetric waveform is transmitted at the projectile that comprises a series of repeating pulses having a relatively strong, short, positive electric field pulse followed by a relatively weak, long, negative electric-field baseline. The projectile contains a dipole antenna having a switching diode disposed between respective halves thereof.

Abstract: A method and system for increasing the availability of a satellite communications system is provided. A spare satellite is brought online by loading updated software in the satellite while the satellite is moving toward a new orbital position. The time required to bring the spare satellite into operation, and therefore restore service in the communication system, is thereby reduced.

Abstract: An interface between an aircraft and a precision-guided missile having automatic target recognition capability receives target image data and target location data from the aircraft, translates the data into formats usable by the missile, and downloads the target data to the missile at any time prior to launch of the missile. The interface includes a mission-planning unit and a terrain and elevation data storage unit enabling the air crew to call up terrain and elevation data on a visual display for planning a missile mission, and to transmit mission parameters to the missile during aircraft flight.

Abstract: A winged bomb is launched from a launch aircraft and glides to a target. During the glide the winged bomb follows a calculated guide path stored in a on board computer, with correction generated by the computer using data from an altimeter and global positioning receiver. Near the termination of the glide a television camera is activated and transmits signals to a remote location from which final correction are manually generated and transmitted by radio to the bomb. The bomb is designed with low radar cross section.

Abstract: A system and method for guiding an artillery shell in flight which includes a multi-element antenna having a large central access hole therein for receiving an airfoil actuator pin, the antenna array being switched during flight, as a function of the rotation of the shell, so that the upwardly directed portion of the radiation pattern predominates over a terrestrially directed segment of the radiation pattern.

Abstract: A detector assembly which includes an electrically conductive, two-piece, molded plastic housing including a relatively rigid bulkhead portion having a groove and a second dome portion having a sidewall extending over an adjacent bulkhead portion. The dome portion has a plurality of relatively flexible tabs, a part of each tab extending into the groove and making mechanical contact with the bulkhead portion via the groove to provide a press fit therebetween. An electrically conductive barrel is disposed within the housing and is electrically connected via an electrically conductive o-ring to the bulkhead to form an electrically shielded chamber within the housing in conjunction with the bulkhead and the dome portions. Equipment to be shielded is disposed within the chamber and is secured to the barrel.

Abstract: An air to air homing missile guidance algorithm based on a state-dependent Riccati equation solution of a spherical-based nonlinear intercept representation of the intercept kinematics problem. The achieved algorithm also provides characteristics asymptotically stabilizing the intercept kinematics achieved with the classic proportional navigation or PRONAV intercept algorithm but provides reduced hunting instability and other fuel-consuming and time consuming missile maneuvers. The disclosed algorithm is in the form of four state equations, two equations for an angular acceleration embodiment and two for a linear acceleration embodiment. Each such embodiment includes seven state variables each having a gain coefficient of complex fraction form; each embodiment is additionally refined for differing cross-channel couplings.

Abstract: A tail fin assembly for a munition having a housing configured for attachment to the munition, at least one flight control surface, an actuator for effecting movement of the flight control surface(s), so as to facilitate guiding of the munition, and a guidance system for controlling the actuator mechanism. The guidance system has a global positioning system (GPS) receiver for effecting control of the actuator mechanism.

Abstract: In an aiming or sighting device and an aiming method for determining the impact point of a ballistic flying body such as a rocket or a tube weapon projectile, specific characteristic values of the ballistic flying body are stored in a memory and an evaluating stage produces control signals in response to the specific characteristic values and in response to actual supplied system parameters. The control signals are transmitted to a display and to an adjustment drive. A model of the trajectory of the ballistic flying body is produced on the basis of all respective possible actual system parameters in an evaluating stage, whereby the trajectory is subdivided into at least two phases, each with a respective submodel. The submodel of the first phase is thereby a model with three or six degrees of freedom and the submodel of the second phase is a model with three degrees of freedom. An input unit permits adjusting the mode of operation and the correction of the impact location.

Abstract: A mobile space lift range system using a ground control station and an unmanned airborne vehicle that relayed data to and from a space lift vehicle to control it. The unmanned airborne vehicle may selectively include one or more sensor systems, a radar system, a command and telemetry system, and a user test system. The unmanned airborne vehicle is a high attitude, long endurance vehicle that provides a flexible, mobile range to support launch-anywhere space lift scenarios.