Abstract: A method to determine roll angle, pitch angle, and heading angle of a spinning projectile during a flight of the spinning projectile is provided. The method includes providing a magnetic unit vector in an inertial frame of the projectile at a projectile launch location prior to launch of the projectile; determining a magnetic unit vector in a body frame and in an inertial frame of the spinning projectile during the flight of the spinning projectile; determining a velocity unit vector in the body frame and in the inertial frame of the spinning projectile during the flight of the spinning projectile; and calculating the roll angle, the pitch angle, and the heading angle of the spinning projectile during the flight of the spinning projectile, regardless of the spin rate of the projectile. The roll angle and the pitch angle of the spinning projectile form an attitude of the spinning projectile.

Abstract: A system is provided for the remote control of a spinning projectile, the system comprising: a polarized radiation source emitting polarized radiation wherein commands are encoded; a projectile round; a polarized radiation receiver disposed on the projectile round and configured to receive the polarized radiation; and a projectile steering mechanism, the mechanism directing movement of the projectile according to the commands communicated by means of rotation of polarization of the polarized radiation source.

Abstract: A semi-active laser (SAL) sensing system is provided that uses a lightpipe to pass received reflected laser light from an aperture to a detector. The lightpipe facilitates further miniaturization of the SAL sensing system by taking the place of a larger lens system that would otherwise be required. For example, the use of the lightpipe in a missile or guided projectile can facilitate the placement of the SAL sensing system with other sensors in the limited available space at the front of the missile. In one embodiment, the lightpipe is formed from cladded optical fibers that are bundled together, shaped, and fused together. The core material from the optical fibers are then dissolved away, leaving the outer cladding. This remaining outer cladding remains fused together, and maintains its shape, thus forming a lightpipe that can be used in a SAL sensing system.

Abstract: A spin-stabilized projectile has its course controlled by counter rotation of an internal mass about a longitudinal axis of the projectile. The internal mass may be a boom within a cavity of an external body of the projectile. The internal mass may be tiltable relative to the hull, and may be configured to counter rotate relative to the hull about the axis of the hull. The counter-rotation may keep the boom in a substantially same orientation relative to the (non-spinning) environment outside of the projectile. The positioning of the boom or other weight within the projectile thus may be used to steer the projectile, by providing an angle of attack to the projectile hull. A magnetic system may be used to counter rotate the boom or other weight. The projectile may have a laser guidance system to aid in steering the projectile toward a desired aim point.

Abstract: A GNC device for use with a projectile, includes a rotating GNC portion and a non-rotating GNC portion, the rotating GNC portion being fixedly coupled to a projectile body, at least one bearing being interposed between the rotating GNC portion and a non-rotating GNC portion, the at least one bearing permitting the rotating GNC portion to rotate with respect to the non-rotating GNC portion. In a GNC device for use with a projectile, a method is further included.

Abstract: A countermeasure device for directing a mobile tracking device away from an asset is provided. The countermeasure device includes a continuous wave laser source whose output is directed at a seeker head of the mobile tracking device. The countermeasure device causes the generation of localized sources within the mobile tracking device and confuses the mobile tracking device as to the true location of the asset.

Abstract: A method for engaging a target missile includes sensing the position of the target and of an interceptor missile, and determining time-to-go to intercept and direction of thrust of the interceptor. A one-step intercept solution is determined based on position estimates of the target and the interceptor and is used to iteratively estimate at least two components of a three-dimensional unit thrust vector, and apply updated guidance commands to the interceptor. A system for thrust vector control of an interceptor against a target missile includes a processor for receiving sensed target signals, determining a one-step initial solution to produce time-to-go and current direction of thrust of the interceptor, iteratively estimating at least two components of a three-dimensional unit thrust vector, and producing a guidance vector for application to the interceptor.

Abstract: Embodiments of a multiplatform system and method for ranging correction use spread-spectrum ranging waveforms over a netted data link. Each node may have a trajectory toward a target and may have a navigational error with respect to the trajectory. The nodes may transmit coded waveforms at one or more scheduled times for receipt by one or more of the other nodes during unused time slots on the netted data link. The nodes may correlate coded waveforms received from the other nodes to estimate a range to at least some of the other nodes. Each node may reset its navigational error and revise its trajectory based on the range estimates to the other nodes to avoid a possible collision with one or more of the other nodes.

Abstract: A method for correcting a trajectory of terminally guided ammunition is provided. In order to achieve a high probability of hits, in particular when firing in bursts (continuous fire, rapid single shot fire), it is provided that every individual ammunition is addressed separately. The “imprinting” is performed based on the beam rider guidance principle of terminally guided ammunition. Every individual ammunition reads only the guidance beam identified for this ammunition and can, using additional information, determine its absolute roll attitude in space in order to achieve the proper triggering of the correcting propulsion unit.

Abstract: A method for commanding an attitude change of a boosting missile to tend to maintain good communication link quality includes the step of precalculating attenuation of a link between the boosting missile and a ground station in the presence and absence of multiple missile plumes. If the actual link attenuation is less than the precalculated attenuation in the absence of multiple missile plumes, no attitude change is commanded. If the actual link attenuation exceeds the precalculated value, the actual link attenuation is compared with the calculated attenuation in the presence of multiple missile plumes. If the calculated multiple plume RF attenuation is less than the actual link attenuation, the attenuation is deemed to be caused by some factor other than multiple plume attenuation, and produces a flag for commanding a change in attitude.

Abstract: A kit for upgrading a non-guided shell to an airborne guided shell includes a device to couple the kit to the body of the non-guided shell. A fastener provides for fastening the resulting airborne shell to an aircraft and for detaching it there from. The kit also provides for causing the trajectory of the shell to change once detached from the aircraft according to instructions received in the kit; for determining the position of the shell; and for transferring data from the carrying platform to the guidance kit.

Abstract: The present invention is directed to missile training systems, especially to those relating to the provision of a mechanism that allows missiles and similar devices to be fired at a target in a realistic, but safe, manner. The use of live fire exercises, in which army or other armed forces personnel use fully functioning weapons systems is well established. Live fire exercises can be used to provide realistic training scenarios, but also present obvious dangers. The present invention provides a module for attachment to an object (such as a missile), the object being adapted to be directed towards a target (such as a ship), the module comprising a control system providing an output signal indicative of whether or not said object is to be destroyed.

Abstract: A mobile terrestrial vertical missile launch system is provided for relocatable ballistic missile deployment. The system is connectable to a transport truck and includes a trailer, a pivotable canister, a plurality of stabilizing legs, and an equipment module. The trailer has a hitch for connecting to the truck, a base for supporting wheels for road travel, and a flatbed platform having a transverse hinge. The canister contains launcher for at least one missile and is configurable by rotation at the hinge for disposal in either a longitudinal position for stowage or an erected position for deployment. The stabilizing legs are disposed along a periphery of the trailer. The legs can be disposed in one of an elevated position for stowage and a retarded position for ground engagement. The equipment container supplies electrical power, environmental conditioning, tracking, communication and control for the missile.

Abstract: A surveillance vehicle (10) comprising a vessel (11) and a parasail (12). The vehicle (10) is loaded, in a pre-launch condition, into a mortar tube for projection therefrom towards an area of interest. In this pre-launch condition, the vessel (11) resembles a conventional mortar round and the parasail (12) is stowed within the vessel (11). Upon arrival at the area of interest, the parasail (12) is deployed from the vessel (11) and instrumentation collects survey data.

Abstract: In an IR jamming system for defense against missiles with IR-sensitive homing heads, one or more jamming beams are generated, whose diameter is less than that of the optical aperture of the IR-sensitive homing head of the missile. The optical aperture of the IR-sensitive homing head of the missile is at least partially illuminated by the jamming beam or beams.

Abstract: A method for onboard determination of a roll angle of a projectile.

Abstract: A spin rate tracking system comprising a guidance system suitable for adjusting a flight path of a vehicle based on a spin rate of the vehicle, a signal reception system configured for receiving signal information from a global navigation system wherein a spin rate of the vehicle is derived from a substantially harmonic pattern produced amongst a global navigation signal.

Abstract: A projectile is provided with a projectile tip having enhanced aerodynamic properties to improve accuracy of the projectile. The tip has a body having a base or lower end, an upper end and a curved, side wall between its upper and lower ends that defines an ogive tip length. The tip is received with a projectile jacket and also can have a series of aerodynamic features formed in its body to modify air flow about the body of the projectile in flight.

Abstract: A GNC device for use with a projectile, includes a rotating GNC portion and a non-rotating GNC portion, the rotating GNC portion being fixedly coupled to a projectile body, at least one bearing being interposed between the rotating GNC portion and a non-rotating GNC portion, the at least one bearing permitting the rotating GNC portion to rotate with respect to the non-rotating GNC portion. In a GNC device for use with a projectile, a method is further included.

Abstract: A network-centric targeting system includes a prepare module to plan for targeting engagements and to identify a target; a sense module to locate targets of opportunity and targets generated by the prepare module to form targeting information; a refine module to enhance the targeting information from the sense module; a track module to maintain a location of a target, a state of the target and target activity, the track module being coupled to the refine module; a target module to select effects and to coordinate delivery of selected effects to the target, the target module being coupled to the track module, the refine module and the sense module; a deliver module to deliver effects to the target, the deliver module being coupled to the track module, the refine module, the target module and the sense module; and an assess module to assess effectiveness of the delivered effects on the target.

Abstract: A control system includes a rate-damping loop that uses a motion parameter error (heading pitch, heading yaw, attitude pitch, attitude yaw, and attitude roll) to non-linearly scale a rate-feedback signal so that at lower motion parameter error values, an acceleration feedback term plays a greater role in pitch compensation, while at greater motion parameter error values, a rate-feedback term plays a greater role in the pitch compensation. In some embodiments, a control system and method of controlling a motion parameter of a moving body are provided. A signal representing a motion parameter error is non-linearly combined with a signal representing a rate-of-change of a motion parameter (or body angle) to generate a non-linear rate-damping signal. The non-linear rate-damping signal is subtracted from the signal representing the motion parameter error to generate a signal to control one or more elements of the moving body.

Abstract: There is disclosed a vehicle and methods for maneuvering the vehicle. The vehicle may include a plurality of multiple-impulse rocket motors, each of which comprises a plurality of independently ignitable solid fuel propellant charges, and a processor that generates at least one command to ignite at least one solid fuel propellant charge of at least one of the plurality of multiple-impulse rocket motors.

Abstract: A missile has a pair of systems to provide acceleration information during flight. The primary system is a microelectromechanical systems (MEMS) inertial measurement unit (IMU) that provides accurate rate sensor output, such as providing pitch and yaw rates, at low cost, over a wide range of conditions. However MEMS IMUs are susceptible to temporary incorrect responses when subjected to shocks, such as acoustic-range shocks, for instance in the range of 10-20 kHz. The missile includes a secondary system to temporarily provide acceleration data during the periods following shocks, when the MEMS IMU does not provide valid (reliable or usable) rate sensor output, for use in estimating pseudo pitch and yaw rates. The secondary system may be an accelerometer that does not provide navigation-quality acceleration data, but does provide a sufficiently accurate response in order to maintain stable flight during the post-shock period.

Abstract: A laser lead designator for guiding a laser guided weapon (LGW) to strike a moving target includes a laser source for providing a laser beam and a controller coupled to receive a position and a velocity of the moving target. The controller provides a control signal for pointing the laser beam a specified lead distance ahead of the position of the moving target to position a laser spot on a ground location ahead of the moving target. The lead distance compensates for an impact shortfall value that is a function of at least one shortfall parameter including a speed of the moving target so that the LGW shortfalls the laser spot on the moving target. The laser designator is separate from the LGW.

Abstract: A modular artillery projectile and method of engaging a target. A modular artillery projectile may include a payload module, a guidance module coupled to the payload module and a rear module coupled to the guidance module. The payload module may be selected from a plurality of interchangeable payload modules containing different payloads. The guidance module may include a transverse propulsion system to propel the modular artillery projectile transversely to a longitudinal axis of the modular artillery projectile, a global positioning system receiver, and a control system to control the transverse propulsion system responsive to the global positioning system receiver to guide the modular artillery projectile to a predetermined target position.

Abstract: An actuation assembly is provided. The actuation assembly includes a casing, a plurality of linear actuators coupled to the casing, each of the linear actuators having first and second components and being configured to move the second component thereof relative to the first component thereof along a respective first axis, and a plurality of translational member sets, each being coupled to the second component of a respective one of the linear actuators and the casing and being configured such that when the second component of the respective linear actuator moves along the respective first axis, a selected portion of the translational member set moves substantially along a respective second axis.

Abstract: A guidance and control unit assembly for use with a munitions projectile includes a guidance and control unit being roll isolated with respect to the munitions projectile such that roll of the munitions projectile about a projectile longitudinal axis, such roll being imparted to the munitions projectile during the act of launching the munitions projectile, may not be imparted to the guidance and control unit as desired. A munitions projectile is further included.

Abstract: A process of using finite element analysis for determining the behavior of a system, submitted to predetermined load and displacement boundary conditions with a degree of freedom relative to a local coordinate system released at one system node. For a geometrically non-linear solution scheme, a plurality of incremental steps are carried, for which computing for a finite element of the system a displacement vector at the nodes of the finite element is performed by minimizing the energy of the system. For a geometrically linear solution scheme, a single solving step is carried. The step of minimizing is carried out, for a node having a released degree of freedom, in a local frame of reference, and the released degree of freedom at the node is expressed along one axis of such frame. Hybrid reference frames allow expressing and considering in the formulation the constraints of the non-released degrees of freedom simply.

Abstract: An exemplary navigation system uses a master navigation component at a first location in a vehicle and a slave navigation component at a second location that is a variable displacement to the first location due to physical deformation of the vehicle. Static and dynamic location components provide static and dynamic information of the displacement between the first and second locations. An error estimator estimates errors in the navigational measurement data generated by the slave navigation component based on the navigational measurement data generated by the master navigation component and the displacement information provided by the static and dynamic location components. The master navigation component corrects the navigation measurement data of the slave navigation component based on the determined error and translates the corrected navigation measurement data of the slave navigation component into navigational measurement data in its coordinate system.

Abstract: A vehicle for launching from a gas gun having a housing; preferably incorporating a precessional attitude control system; and utilizing a flared base, fins, or active use of the attitude control system during passage through the atmosphere. Subtly canting the fins can produce desired spinning of the vehicle. The propulsion system can employ liquid, hybrid, or solid fuel. A removable aero-shell assists atmospheric flight with thermal protection being provided by anticipated ablation, an ablative aero-spike, or transpirational cooling. And a releasable sabot enhances the effectiveness of the launch.

Abstract: A countermeasure method for directing a mobile tracking device away from an asset is provided. The countermeasure method includes directing the output of a continuous wave laser source at a seeker head of the mobile tracking device. The countermeasure method causes the generation of localized sources within the mobile tracking device and confuses the mobile tracking device as to the true location of the asset.

Abstract: A guided projectile may include a projectile body. An inertial measurement unit may be disposed within the projectile body, the inertial measurement unit including sensors to measure motion parameters relative to first, second, and third mutually orthogonal axes. Each of the first, second, and third mutually orthogonal axes may form an oblique angle with a longitudinal axis of the projectile body. A controller may be configured to control a trajectory of the guided projectile in response, at least in part, to measurement data received from the inertial measurement unit.

Abstract: A guidance system may include an optical system to focus incident radiation onto a detector configured to generate at least one guidance signal in response to the focused incident radiation. The optical system may include a first lens having a first side and a second side, the first side consisting of a Fresnel lens formed on a generally convex surface and the second side being generally planar.

Abstract: An apparatus and method improves the fault tolerance of a rocket or missile guidance system which includes a resonant sensor. When improper initialization is detected, the resonant sensor is reinitialized, repeatedly if necessary, until normal operation is achieved. Improper initialization is detected by comparing data from the guidance system with pre-specified physical limits to roll, pitch, yaw, and/or other features of the flight scenario. Embodiments can also detect a fault condition due to an error signal from a “Built-in-Test” (BIT) module. The initialization sequence initiated by the invention can be identical to the power-on sequence, or it can be a separate, reinitiating sequence. Subsequent resets are initiated as needed, for example until the burn of the rocket fuel and the associated vibrations have ceased and the resonant sensor has been successfully initialized.

Abstract: A fuze guidance system is configurable by an end user, allowing the end user to select between different configurations of canards of the system. The different configurations of canards may include canards with different surface areas, optimized for providing appropriate control with different sizes of munitions. The different configurations may be accomplished by having canards with separable portions which may be broken off or otherwise removed by the end user, to reduce canard surface area and/or span. Alternatively the fuze guidance system may come in a kit with multiple sets of canards having different sizes or otherwise having different configurations for providing different aerodynamic characteristics. The end user may select a canard set based on the munition size or type that the fuze guidance system is to be used with.

Abstract: A projectile has a pair of different parts with respective orientation sensors for detecting orientation, such as the roll position of the parts. The orientation sensors may be any of a variety of sensors, such as magnetometers, light sensors, infrared (IR) sensors, or ultraviolet (UV) sensors. Orientation events of the orientation sensors, such as maxima or minima of sensor output, are determined. The orientation events of the two sensors are compared to produce an alignment correction factor for correcting for misalignment of the parts relative to one another, that is to correct for differences in alignment between the sensors of the two parts. This allows (for example) instructions produced at one of the parts to be usable at the other of the parts.

Abstract: The method for generating an integrated guidance law for aerodynamic missiles uses a strength Pareto evolutionary algorithm (SPEA)-based approach for generating an integrated fuzzy guidance law, which includes three separate fuzzy controllers. Each of these fuzzy controllers is activated in a unique region of missile interception. The distribution of membership functions and the associated rules are obtained by solving a nonlinear constrained multi-objective optimization problem in which final time, energy consumption, and miss distance are treated as competing objectives. A Tabu search is utilized to build a library of initial feasible solutions for the multi-objective optimization algorithm. Additionally, a hierarchical clustering technique is utilized to provide the decision maker with a representative and manageable Pareto-optimal set without destroying the characteristics of the trade-off front. A fuzzy-based system is employed to extract the best compromise solution over the trade-off curve.

Abstract: A compact SAL seeker for a projectile guidance system comprises an optical sub-assembly to focus incident electro-magnetic radiation (EMR) such that target bearing in object space is mapped to a spatial irradiance in image space and a detector sub-assembly to generate at least one guidance signal in response to the position of the centroid of the focused EMR. The optical sub-assembly includes an integrated filter stack of a primary optical element, a spreader, a filter and secondary optical element in which at least one and typically both of the spreader and filter are immersed within the optical media of the stack. The detector sub-assembly may include a field lens in which the detector is immersed. Immersion reduces the number of “air-to-glass” interfaces, hence improves optical throughput. The detector sub-assembly may be integrally formed with a mounting bracket adapted to mate with mounting features on the optical sub-assembly to provide a self-aligned seeker.

Abstract: The present invention provides apparatus and methods for accurate guidance of small munitions to a target. The guidance for the small munition is mainly provided by a device external to the small munition, such as an unmanned aerial vehicle (UAV). The UAV may provide external guidance commands by use of a command transmitter to the small munition. The small munition is equipped to receive the guidance commands and consequently use a maneuvering mechanism to react to the guidance commands. The UAV may determine a successful release point of the small munition and track a flight path from a release point toward the target of the small munition using a passive sensor mounted in a gimbaled mount, which is controlled by use of a closed-loop control system. The UAV may be controlled by a ground control device, such as an operator control unit (OCU), to release small munitions.

Abstract: A method of defeating an incoming missile, such as a rocket propelled grenade, includes soft launching an interceptor missile, and then using pitch over motors of the interceptor missile to alter course of the missile to a desired interception direction. By launching at a relatively slow speed, such as a speed less than or equal to 40 m/sec (130 ft/sec), the interceptor missile may reach the desired interception direction within 250 milliseconds of launch. The interceptor missile may be able to cover substantially all interception directions over a hemisphere or greater extent around a launch location. For example, the interceptor missile may be launched vertically from a ground vehicle, and be capable of altering course to any above-ground trajectory within 250 milliseconds.

Abstract: There is disclosed an apparatus and a method for guidance of a projectile. The method for guidance of a projectile, includes emission from the launching position of the projectile of beams pointing to the vertexes of a regular polygon, emission from the launching position of a beam encompassing the preceding beams, determination of position of the projectile relative to the beams, the determined position enabling to correct the projectile trajectory to maintain the projectile the closer to the center of the polygon formed by the beams.

Abstract: A process to preserve the kinematic state of a target includes determining an initial kinematic state estimate of the target using an observer with an active sensor. The initial kinematic state estimate includes a range from the observer to the target, a velocity of the target, and an acceleration of the target. The process further includes constructing an Extended Kalman Filter using the initial kinematic state estimate. The Extended Kalman filter is constructed by updating the initial kinematic state estimate as a function of time, receiving an angles-only measurement into the observer, calculating a new kinematic state as a function of the angles-only measurement, comparing the initial kinematic state estimate with the new kinematic state, constraining a rate of the target, and correcting the initial kinematic state estimate as a function of the comparison of the initial kinematic state estimate with the new kinematic state. The target is permitted to maneuver, and the observer is not required to maneuver.

Abstract: A system for launching, controlling and delivering in a preselected target pattern a plurality of low-cost, guided fire-retardant-containing vehicles, i.e., “smart water bombs” equipped with control surfaces sufficient to provide limited lift and maneuverability to respond to guidance command to place it at a selected GPS coordinate within a large footprint in time and space and to discharge its payload of fire retardant at a preselectable altitude in a very precise manner and dispersion pattern. A controller determines bombing patterns and timing for all bombs and trajectories for each guided bomb. Dynamic differential equations are used to determine location and time of release of the guided bombs to achieve the target while avoiding collisions among guided bombs and aircraft.

Abstract: In a co-boresighted SAL/IR seeker, the optical system and particularly the secondary lens and position of the SAL detector are configured to produce a well-corrected spot of laser energy at the SAL detector. A spreader is positioned between the secondary mirror/lens and the SAL detector, possibly on the secondary mirror, away from the aperture stop and not in the optical path to the IR detector. The spreader is configured to spatially homogenize the laser energy to increase the size of the spot of focused laser energy at the SAL detector to set the system transfer function to meet slope requirements. Spatial homogenization serves to reduce both boresight shift and slope non-linearities. This approach greatly simplifies the time and labor intensive calibration of the SAL detector's system transfer function.

Abstract: A system for protection of a vehicle against a possible threat approaching the vehicle. A sensor is configured to detect the possible threat and to transmit raw data and to continue the detection as long as there is a possible or confirmed threat. A control unit is configured to receive the raw data transmitted from the sensor and to evaluate the possible threat in view of the raw data to produce and transmit processed information. A counter-measure apparatus is configured to receive the processed information of the threat from the control unit if the evaluation by the control unit confirms that there is a threat. A launcher is configured to receive preliminary processed information of the direction of the threat from the control unit and to receive a launching signal from the control unit for launching the counter-measure apparatus towards the threat when the threat is confirmed.

Abstract: A tornado disarming network includes a command center, tornado detection systems, and tornado busting missile launch sites in communications with the command center. Tornado busting missiles are at the tornado busting missile launch sites. Each tornado busting missile includes a radar, a guidance system and a solid rocket motor for propelling the missile toward the tornado. A thruster control system causes the tornado busting missile to travel upward within the tornado upon reaching the tornado. An explosive discharge system explodes within the tornado to generate heat for causing the air within the tornado to expand, thereby weakening the tornado.

Abstract: A system senses the presence of a boosting missile or target and processes the information by comparison of the data with a plurality of predetermined templates of nominal missile characteristics, in order to determine the state of the missile. The processing includes estimation of burnout time and of early thrust termination. Both are determined by generating current stage state estimates including position, velocity, time index error into the thrust template, and motor scale factor error. The change in motor scale factor is compared with a threshold to determine if early thrust termination has occurred. The estimated burnout time of the current stage is calculated from the burnout times of the current and the previous stage processed with the estimated motor scale factor and with state estimates from a filter.

Abstract: Systems and methods for launching munitions are provided. In some embodiments, a launcher configured to retain a munition during transport by a vehicle may comprise a first housing, circuitry, and a second housing. The first housing may define a tube configured to hold a munition for transportation. The circuitry may provide electrical communication with a munition present within the tube. The second housing may define a tube corresponding to the tube defined by the first housing. The second housing may be configured to mount to the first housing so that the tubes defined by the first housing and the second housing combine to house and launch a munition.

Abstract: A method and a system for sensing a boosting target missile, estimate position and velocity and boost acceleration parameters of the target missile, and control an interceptor missile to the target missile. A boost-phase missile target state estimator estimates at least acceleration, velocity, and position using an acceleration template for the target vehicle. The nominal template is incorporated into an extended Kalman filter which corrects the nominal template acceleration with the filter states to predict future thrust acceleration, velocity and position. The correction can compensate for motor burn variations and missile energy management (lofted/depressed trajectory).

Abstract: A system and method for guiding a projectile is presented. A nozzle system includes a boom assembly body that can be attached to a rear end of a projectile. A gas tank in the boom assembly contains pressurized gas. Fins are attached to the boom assembly body to guide the projectile. A valve lets a pulse of gas out of the gas tank. A nozzle expels the pulse of gas to control an angle of attack and lift of the projectile to guide the projectile to a target.