Abstract: A method of maneuvering target tracing is disclosed. The present invention relates to the field of target tracking and more generally to a method of employing multiple model and variable sampling rate technique, which achieve good tracking performance for a high-g maneuvering target. The results show that the present invention can handle the missile sudden maneuver better and are accurate.

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 tactical surveillance sensor projectile system includes a propellant and primer chamber, a firing device, a sensor device, a signal processor, and a fiber optic cable; the firing device fires the primer and propellant to establish a powered phase of flight followed by a ballistic phase of flight to clear an obstacle; the sensor device generates surveillance signals representative of ambient characteristics beyond the obstacle at least during the ballistic phase of flight; the signal processor is responsive to the sensor device for converting the signals representative of ambient conditions to an optical data stream; and the fiber optic cable delivers the optical data stream to a ground station at least during the ballistic phase of flight.

Abstract: An device for correcting the in-flight trajectory of a munition consists of an impulse motor assembly body. The slug or multiple slugs and propellant(s) are located within the impulse motor assembly body. When a trajectory correction is desired and required, the individual impulse motor propellants are activated and fired, and the slug or multiple slugs are propelled out of the in-flight munition at a specific time and a specific angle on or near the gravimetric center of gravity of the in-flight munition. The reactive forces created by the explosion of the(se) heavy metal slugs does, by equal and opposite reaction, create a corrective vector and thereby does cause a correction in the trajectory of the in-flight munition.

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 method for providing a pilot with information associated with at least one region of a field of view visible to the pilot from within a cockpit without requiring a visual display. The method includes the steps of determining an eye gaze direction relative to a given frame of reference for at least one eye of the pilot, determining a reference direction relative to the given frame of reference, comparing the eye gaze direction with the reference direction, and if the eve gaze direction and the reference direction are equal to within a given degree of accuracy, generating audio output audible to the pilot and indicative of information associated with the reference direction.

Abstract: A method and apparatus for directing a pursuing vehicle, such as a torpedo, on an intercept trajectory from a launching vehicle to a target vehicle with evasion capabilities and the target vehicle is alerted to pursuing vehicle at the time that the pursuing vehicle enables its seeker. Models of the pursuing vehicle and evading target provide proposed trajectories based upon various environmental considerations. A guidance system uses estimates of initial operating parameter solutions for the pursuing vehicle, such as gyro angle, intercept time and run-to-enable time, to begin a convergent, iterative process that defines final operating parameter solutions from which the guidance parameters are determined and transferred to the pursuing vehicle at launch.

Abstract: An aircraft 1 in the form of an airplane with a spiral inducing assembly 2 which is capable of inducing the airplane to travel in a continuous spiralling motion without rolling. Two fins 3 and 4 are attached to a tube 5 that is able to rotate around the encircled part of the fuselage. The fins 3, 4 are able to rotate in a pivoting manner on the rotatable tube 5 with respect to the rotatable tube 5, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 5. Fin 3 is larger than fin 4. The diferene in sizes between the fins makes the larger fin 3 exert a greater force on the rotatable tube 4 than the smaller fin 4 when the fins are pitched in unison. The aerodynamic imbalance between the fins thus casues the rotatable tube 5 to rotate. When pitched at an angle to the longitudinal axis in unison, both fins 3, 4 would exert a lateral force on the rotatable tube 5. Thus, as well as forcing the rotatable tube 5 to rotate, the fins 3, 4 would also push the rotatable tube sideways.

Abstract: An active mirror guidance system for a vehicle is disclosed. The guidance system includes active mirrors to track a target. The mirrors are moved in response to disturbances detected by sensors or manually via remote control. The image provided from the mirrors is sent to a focus device for processing. A signature signal processing device and additional optics may also be used. A control system connects each of the components of the guidance system. The guidance system is also connected to the vehicle control equipment to steer the vehicle toward the target.

Abstract: A vehicle, such as a missile, with a pilot valve system controls the vehicle's thrust valves despite a hostile propellant gas environment. The pilot valve system can have one or more pilot valves. Using refractory elements, the pilot valve ball reciprocates between a supply seat and a vent seat which is subject to the filtered inflow of propellant thrust gases. When open, the pilot valve allows the stray thrust gas to communicate to a control chamber which closes a poppet against a valve seat in the nozzle. When an associated solenoid closes the pilot valve by pushing the pilot valve ball against the supply seat, the control chamber is vented to ambient. The poppet may then travel into the cylinder bore and the nozzle is opened to exhaust propellant gases and exert lateral thrust on the vehicle. Certain nozzle thrust geometries provide useful vehicle guidance.

Abstract: A system for controlling attitude about pitch, yaw, and roll axes and axial thrust of a body. The system comprises a main thrust generator located on an aft portion of the body and at least one reaction control system (RCS) located on a forward portion of the body. A thrust vector controller (TVC) is connectable to the main thrust generator and at least one RCS controller is connectable to the RCS. The RCS controller and the TVC are synchronized to adjust the direction of the principal line of thrust through the body center of gravity.

Abstract: A method of maneuvering target tracing is disclosed. The present invention relates to the field of target tracking and more generally to a method of employing multiple model and variable sampling rate technique, which achieve good tracking performance for a high-g maneuvering target. The results show that the present invention can handle the missile sudden maneuver better and are accurate.

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: The MLRS1 artillery rockets (11) which are stored in the depots of the consumer can enjoy in a technologically non-critical fashion an increase in performance in the sense of a substantially improved degree of delivery precision, insofar as the ogival head (13) is temporarily cut off so that it is possible to fit into same and thus into the foremost region of the original payload space (15), which is behind the fuse (12), in a position of surrounding the pyrotechnic delivery ejection system, an annular assembly frame (21) for a transverse thrust unit (23) with reaction elements (25), which blow out radially around the rocket, which, in dependence on position, can be individually triggered by a navigation satellite-supported course correction unit (20) which is also fitted there.

Abstract: A braking device for increasing the drag coefficient of an associated shell at a desired point while in flight is described. The device comprises: at least two braking vane means which, when released, extend substantially symmetrically into a surrounding airstream while said shell is in flight; retaining means for maintaining said at least two vane means in a retracted first position out of said airstream during an initial portion of said flight; releasing means to allow said at least two vanes to extend to a second position into said airstream at a desired point during said flight; said at least two vane means being extended by centrifugal force due to rotation of said associated shell about its axis; and, said at least two vane means further including co-operating means to ensure substantially symmetrical extension into said airstream.

Abstract: A system for operating and releasing a store of a first predetermined type includes an aircraft adapted to control the operation of stores of a second predetermined type and a bypass apparatus. The store is releasably secured to the aircraft, and the aircraft is capable of releasing the store. The aircraft is capable of being configured such that a store of the first predetermined type is capable of operating independent of operating instructions. The bypass apparatus is carried by the aircraft and adapted to facilitate operation of the store. The bypass apparatus can store operating instructions and thereafter transmit the operating instructions into the store. As such, after the aircraft releases the store the store is capable of operating according to the operating instructions. Also, the system can include an umbilical cable disposed between the aircraft and the store. The bypass apparatus can, therefore, be disposed within the umbilical cable.

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, in its various aspects and embodiments, includes a method for planning a mission profile in real time. The method comprises ascertaining a plurality of target information (including a target location, a target velocity, and a target location error) and autonomously determining a pattern from the ascertained target information.

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 device and a method of adjusting a trajectory of a projectile in flight includes increasing projectile drag to effect a downrange correction and altering the yaw of repose to effect a cross range correction. A method of a vernier correction to the trajectory is included.

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: The present invention, in its various aspects and embodiments, includes a method for planning a mission profile in real time. The method comprises ascertaining a plurality of target information (including a target location, a target velocity, and a target location error) and autonomously determining a pattern from the ascertained target information.

Abstract: The Rotational Canted-Joint Missile (RCJM) Control System utilizes a single or multiple body joints that rotate in planes that are not perpendicular to the missile body axis. The result is the deflection of a portion of the missile body for flight control purposes. The canted interface plane between any two adjacent movable sections of the missile body and a joint at the interface plane that allows one of the sections to be rotated by a pre-determined angle with respect to the other section comprise a rotational plane mechanism that offers an inclined bearing plane with a large mechanical advantage over typical “brute force” ball joint methods.

Abstract: An inertial reference system for a spacecraft includes an attitude control assembly and a plurality of force sensors. The attitude control assembly is coupled to a spacecraft body at a plurality of attachment points and at least one of the plurality of force sensors is integrated at each of the attachment points. In one embodiment, the force sensors are piezoelectric transducers. In another embodiment, the control assembly is coupled to the spacecraft body at four attachment points. In yet another embodiment, each of the force sensors is preloaded by a bolt that attaches the attitude control assembly to the spacecraft body.

Abstract: The present invention provides a robust means of adjusting the angular mounting of thrust producing devices such as airplane engines. The device provides independent adjustment of the thrust vector for each axis and offset adjustment to maintain the center line of the engine. A means of indicating the angle of adjustment is inherent in the design. The invention also provides for an opening along the centerline to accommodate power take-off shafts or to mount jet or ducted fan engines.

Abstract: A weapon system comprising a mobile platform (1) e.g. an aircraft incorporating a first three-axis attitude reference sub-system (13), and a guidable vehicle (3) launchable from the platform (1) and incorporating a guidance sub-system (15) incorporating gyros (17) wherein correction of gyro parameters, i.e. scale factor and zero offset, of the vehicle attitude reference sub-system (15) is effected prior to launch of the vehicle (3) on the basis of repetitive comparisons of attitude data as measured by the platform and vehicle sub-systems (13, 15). The vehicle (3) may comprise a dispenser of a number of munitions (5) each itself incorporating a guidance sub-system (25) incorporating gyros (27), in which case corrections of gyro parameters of the missile guidance sub-system (25) may be effected prior to missile launch on the basis of repetitive comparisons of attitude data as measured by the dispenser and munition sub-systems (15, 25).

Abstract: A precision-guided hypersonic projectile weapon system. The inventive system includes a first subsystem for determining a target location and providing data with respect thereto. A second subsystem calculates trajectory to the target based on the data. The projectile is then launched and guided in flight along the trajectory to the target. In the illustrative application, the projectile is a tungsten rod and the first subsystem includes a forward-looking infrared imaging system and a laser range finder. The second subsystem includes a fire control system. The fire control system includes an optional inertial measurement unit and predicts target location. The projectile is mounted in a missile launched from a platform such as a vehicle. After an initial burn, the missile launches the projectile while in flight to the target. The missile is implemented with a rocket with a guidance system and a propulsion system.

Abstract: The Rotational Canted-Joint Missile (RCJM) Control System utilizes a single or multiple body joints that rotate in planes that are not perpendicular to the missile body axis. The result is the deflection of a portion of the missile body for flight control purposes. The canted interface plane between any two adjacent movable sections of the missile body and a joint at the interface plane that allows one of the sections to be rotated by a pre-determined angle with respect to the other section comprise a rotational plane mechanism that offers an inclined bearing plane with a large mechanical advantage over typical “brute force” ball joint methods.

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: An unmanned airborne reconnaissance system, the unmanned airborne reconnaissance system including a lightweight, portable, powered aircraft and a foldable launch rail, the aircraft, in a broken down condition and the launch rail in a broken down condition fitable inside a box, the box capable of being carried by one man. The launch system includes an elongated launch rail with the carriage assembly, and a propulsion means for accelerating the carriage assembly from one end of the launch rail to the other. The carriage assembly releasably engages the aircraft so as to propel the aircraft from one end of the launch rail to the other. The propulsion may be by a cartridge that explodes and releases a gas through a cylinder, or by elastic cords. The aircraft is guided through the air either by a programmed onboard computer which controls the control surfaces of the aircraft and/or by remote control. The aircraft typically contains a camera for recording and transmitting images received from the ground below.

Abstract: Provided is a modified configuration that permits operation of instrumentation onboard platforms that may experience severe environmental conditions. The instrumentation permits autonomous acquisition of performance data. Acquired data may be recorded for later playback as well as provided to the platform's operator in real time in multiple formats, such as warning lights, digital displays, video, or audio. An application would be for sensor systems used on an automobile to record performance data, providing a warning when routine maintenance is due or a catastrophic failure is imminent. A specific application uses a flight-certified missile launcher pod on an F/A-18 aircraft, as incorporated in the aircraft's wingtip and modified to hold instrumentation conforming, at least in part, to the launcher pod's internal dimensions.

Abstract: An interference-aided navigation system for a rotating vehicle provides rotation angle estimates using interference or jamming signals. An antenna receives interference signals and desired navigation signals. A RF processing function connected to the antenna processes the received interference signals and the desired navigation signals into IF signals. An A/D converter connected to the RF processing function digitizes the interference signals and desired navigation signals and to provide a digitized IF signal. A tracking filter tracks amplitude variations of the interference signals and provides the rotation angle estimate signal of the rotating vehicle.

Abstract: Missile (10) includes one or more arrays of barrel assemblies (11) which are displaced from the centre of gravity of missile (10). Each barrel assembly (11) includes a plurality of projectiles axially disposed within a barrel, and each projectile is associated with a discrete propellant charge for propelling the projectile sequentially from the barrel. Each array of barrel assemblies (13, 14) is capable of selectively firing the projectiles from selected barrels (11a) whereby missile (10) is accelerated by the reactionary force generated by said firing of projectiles and the missile is deflected (A) onto a new course or trajectory. This enables missile (10) to be steered to intercept its target (20), even if the target is undertaking evasive manoeuvres. Each barrel assembly (11) can include up to twelve projectiles.

Abstract: An interference-aided signal acquisition and tracking system with temporal beam forming for a rotating vehicle enhances signal to noise ratio using interference or jamming signals. An antenna receives interference signals and desired navigation signals. A RF processing function connected to the antenna processes the received interference signals and the desired navigation signals into IF signals. An A/D converter connected to the RF processing function digitizes the interference signals and desired navigation signals and provides a digitized IF signal. A tracking filter tracks amplitude variations of the interference signals and provides a rotation angle estimate signal of the rotating vehicle. A signal modulation function connected to the tracking filter and the A/D converter varies gain of the IF signal to enhance the signal to noise ratio.

Abstract: In a method and apparatus for reducing pressure and temperature on the front of a missile at ultrasonic speed a spike with a spherical, ellipsoidal, or drop-shaped mounted is used on the front end. In contrast to conventional shapes, the sensitive nose of the missile is protected from damaging pressure and temperature, even at high angles of incidence.

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 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 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 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 magnetic roll rate sensor for measuring the roll rate or roll position of a missile. A pair of magnetic sensor elements mounted within the missile provide analog electrical signals representative of a change in the earth's magnetic field due to the presence of a ferromagnetic element within the field. The analog signals, representative of roll rate sensor data, are converted to a digital format, formatted into a PCM data stream and transmitted to a ground station. The ground station receives the PCM data stream, extracts the roll rate sensor data and processes the data using a personal computer to determine a roll rate for the missile.

Abstract: Provided is a modified configuration that permits operation of instrumentation onboard platforms that may experience severe environmental conditions. The instrumentation permits autonomous acquisition of performance data. Acquired data may be recorded for later playback as well as provided to the platform's operator in real time in multiple formats, such as warning lights, digital displays, video, or audio. An application would be for sensor systems used on an automobile to record performance data, providing a warning when routine maintenance is due or a catastrophic failure is imminent. A specific application uses a flight-certified missile launcher pod on an F/A-18 aircraft, as incorporated in the aircraft's wingtip and modified to hold instrumentation conforming, at least in part, to the launcher pod's internal dimensions. This arrangement enables autonomous onboard display and recording of data from the captive carry testing of an AIM-9X missile and follow-on designs that may be based on the AIM-9X.

Abstract: A dissolvable jet vane (22/30) is a composite structure, having a support frame (38), a plug leading edge (40) connected to the forward edge (42) of the frame (38), and an insulation layer (44) on the side walls of the support frame (38). The dissolvable jet vane materials withstand the pressure and thermal loads associated with missile steering during the first few seconds of rocket boost until the missile attains sufficient speed to use conventional external aerodynamic control fins for steering control. Once control passes to the external fins, the jet vanes rapidly and uniformly dissolve in the exhaust stream. The dissolvable jet vane provides a lightweight, reliable means of removing steering jet vanes from the exhaust stream of a solid rocket motor nozzle.

Abstract: A method for deflagrating/detonating anti-tank and anti-vehicle land mines, beach zone mines, and surf zone mines located in mine belts or individually using delayed active ignition high temperature incendiary flechettes or darts.

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 method for establishing a path from a launch point to a destination point that can include multiple way points while avoiding landmass areas. Launch points and destination points can lie outside or inside the particular landmass areas. The method includes steps for defining tangents path areas to be avoided, extending those tangents to define way points and testing the individual way points to assure conformance to various conditions and constraints. A subset of paths are optimized. The shortest of the optimized paths becomes a final path.

Abstract: Attitude of a spinning vehicle is determined by observing at least one of the apparent amplitude modulation and the apparent phase modulation of a navigation signal received from a navigation source. Vectors describing the direction from the vehicle to the navigation source are computed and used to determine attitude relative to the navigation source. Inertial sensors are demodulated to remove rotation artifacts and used to anticipate rapid maneuvers.

Abstract: A device and a method of adjusting a trajectory of a projectile in flight includes increasing projectile drag to effect a downrange correction and altering the yaw of repose to effect a cross range correction. A method of a vernier correction to the trajectory is included.

Abstract: A device for measuring a velocity and/or position of a body includes a magnetometer and a measurement unit. The magnetometer is configured to sense a magnetic flux to which the body is exposed. The measurement unit includes a sensor sensing one of an acceleration and a velocity of the body. The measurement unit also includes a processor coupled to the magnetometer and to the measurement unit and configured to determine one on a velocity value and a position value for the body based on the sensed magnetic flux and based or one of the sensed acceleration and the sensed velocity of the body.

Abstract: The invention relates to a target-detection and target-alignment device for a missile system whose field of view is expanded by a wide-angle lens system, which does not contain any optical components which must be additionally moved, and which is equipped with an integrated system for correction of homogeneity of the ambient conditions. Two radiometers or photometers are connected to two emission surfaces positioned on opposite sides of the image of the field of view to adjust the angle of the target detector to compensate for mismatch of the output signals of the emission surfaces.

Abstract: A training projectile that utilizes flutes or flats to augment roll damping characteristics and thereby cause the projectile to crossover into a gyroscopically unstable trajectory pattern at a predetermined time. Prior to the crossover, the training projectile maintains a gyroscopically stable trajectory, which enables extrapolation to ascertain the trajectory of a non-training projectile that does not have an augmented roll damping section. The unstable trajectory pattern substantially reduces the distance the training projectile can traverse, thereby reducing the amount of area required for a training range.