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244 - Aeronautics and astronautics

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Class / Patent application numberDescriptionNumber of patent applications / Date published
244300150 Automatic guidance 115
244300240 Externally mounted stabilizing appendage (e.g., fin) 49
244300110 Remote control 32
244300230 Stabilized by rotation 4
20090277990Aircraft spiraling mechanism with jet assistance - f - An aircraft in the form of multi-stage missile 11-12-2009
20100213307Hybrid spin/fin stabilized projectile - A hybrid spin/fin stabilized projectile. The novel projectile includes a body, a first mechanism for spin stabilizing the body during a first mode, and a second mechanism for fin stabilizing the body during a second mode. In an illustrative embodiment, the projectile includes a rifling band adapted to engage with rifling in a gun during gun launch to impart a spin rate compatible with spin stabilization to the projectile, and a plurality of folding fins attached to an aft end of the body. A fin locking mechanism locks the fins in an undeployed position during the first mode and unlocks to deploy the fins at a predetermined time to switch the projectile to fin stabilization during the second mode. The projectile also includes a mechanism for reducing the spin of the projectile to a rate compatible with guided flight during the second mode.08-26-2010
20080315032Techniques for providing surface control to a guidable projectile - A guidable projectile has a central shaft, a projectile body, and a surface control assembly. The projectile body is arranged to rotate around at least a portion of the central shaft during flight of the guidable projectile to provide stabilization. The surface control assembly is supported by the central shaft. The surface control assembly includes a movable member arranged to control a trajectory of the guidable projectile during flight of the guidable projectile, and an electromagnetic actuator interconnected between the central shaft and the movable member. The electromagnetic actuator is arranged to control movement of the movable member relative to the central shaft.12-25-2008
20120248239STEERABLE SPIN-STABILIZED PROJECTILE - A spin-stabilized projectile has a collar around the middle of its spun fuselage, longitudinally spanning a center of mass of the projectile. The collar includes lift-producing aerodynamic surfaces. Positioning the collar relative to the spinning fuselage produces a direct lift force on the projectile that may be used to steer the projectile. Since the projectile is constantly spinning, the positioning may be accomplished by a brake, such as a magnetic brake or a fiction brake, that allows the collar to be positioned substantially fixed relative to inertial space, with the collar not rotating with the fuselage about a longitudinal axis of the projectile. Since the lift force is applied close to the center of mass of the projectile, the steering occurs with no substantial change in the angle of attack of the projectile.10-04-2012
20090194632METHODS AND APPARATUS FOR TRANSFERRING A FLUID - Methods and apparatus for a missile having an external system operate in conjunction with an airframe and a fluid transfer system. The airframe includes an interior surface defining a substantially enclosed internal chamber. The fluid transfer system selectively connects the internal chamber to the external system, for example to provide pressurant or coolant to the external system.08-06-2009
20130037651NUTATING SPLIT PETAL FLARE FOR PROJECTILE FLUID DYNAMIC CONTROL - A system and methods for fluid dynamically controlling a projectile are disclosed. At least one actuator coupled to at least one common actuation structure is actuated to provide an actuation force via the common actuation structure. The actuation force is transferred through at least one linkage structure to at least one fluid dynamic control surface coupled thereto.02-14-2013
20120181372ACTUATION ASSEMBLY - 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.07-19-2012
20120217338ROLL ISOLATION BEARING - 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.08-30-2012
20080308671Techniques for articulating a nose member of a guidable projectile - A guidable projectile has a nose member, a projectile body, and a nose member articulation assembly which couples the nose member to the projectile body. The nose member articulation assembly includes a stator attached to the nose member, a rotor attached to the projectile body, and rotational support hardware interconnecting the stator to the rotor. The stator defines a central axis. The rotational support hardware is constructed and arranged to guide rotation of the rotor around the central axis defined by the stator. Such a guidable projectile enables circuitry such as the driver of the stator and the power source to reside at fixed locations relative to the stator thus alleviating the need for slip rings which would otherwise present potential points of failure.12-18-2008
20080308670SYSTEMS AND METHODS FOR OPTIMIZING THE AIMPOINT FOR A MISSILE - Methods and systems are disclosed that automatically display an optimized aimpoint on a target image received seeker data. In one embodiment, a method receives missile seeker target data. Then, seeker mode data is extracted from the received missile seeker target data. The location of an optimized aimpoint is identified based on a comparison of target library data with seeker image data. A marker is generated at the location of the optimized aimpoint; and output to a display.12-18-2008
20090272839SYSTEM AND METHOD FOR CONTROLLING HIGH SPIN RATE PROJECTILES - A method is disclosed for controlling a flight trajectory of a spinning projectile. In one aspect the method may involve supporting a nose of the projectile in a manner permitting the nose to be wobbled. At least one electrically responsive component may be coupled at a first end to the nose and at a second end to a base portion of the projectile. An angular position of the nose of the projectile may be sensed as the projectile flies through an atmosphere after being fired from a weapon. An electrical signal is controllably applied to the electrically responsive component, in relation to the sensed angular position of the nose, to control an attitude of the nose during flight of the projectile.11-05-2009
20090294574METHODS AND SYSTEMS FOR WAVE GUIDES - Methods and systems for a wave guide according to various aspects of the present invention may be implemented in conjunction with a radiation collection device comprising a light pipe, a first plate and a second plate. The first plate and the second plate may be inserted into the interior of the light pipe to divide the light pipe into sections. In one embodiment, a first section plate and at least a second section plate are inserted into a light pipe. The inserted first section plate and the at least second section plate may be secured to the light pipe.12-03-2009
20110204177PROJECTILE DIVERTER RELEASE AND METHOD OF DIVERTING A PROJECTILE - A diverter for changing the trajectory of a projectile includes a release mechanism that extends along a longitudinal axis between first and second ends. A mass is coupled to the first end, and the second end is coupled to the projectile. The release mechanism includes a groove and an explosive charge. The groove is disposed between the first and second ends and cinctures the longitudinal axis. The explosive charge is disposed along the longitudinal axis between the groove and the second end.08-25-2011
20100224719METHOD OF VARYING FIRING RANGE AND EFFECT IN TARGET FOR SHELL AND SHELL CONFIGURED FOR THIS PURPOSE - The present invention relates to a method and a shell (09-09-2010
20090114760SYSTEMS AND METHODS FOR BORESIGHT ADAPTERS - Boresighting systems and methods are disclosed. In one embodiment, an assembly adapted for boresighting a launch system includes first and second elongated members adapted to be coupled to the launch system. First and second alignment members are coupled to and extend between the first and second elongated members and are adapted to position the elongated members in a substantially aligned, spaced-apart relationship. A mirror assembly is coupled to each elongated member, the mirror assemblies being adapted to provide an average angular position resulting in a single corrector value for the launch system. In a particular embodiment, each of the first and second elongated members is sized to simulate a Stinger missile.05-07-2009
20090114761RAM neutralization system and method - An article for neutralizing an enemy weapon comprising an interceptor and a deployable net attached to the interceptor, said deployable net remaining attached to the interceptor upon deployment is disclosed. A method of neutralizing an airborne enemy weapon comprising launching an interceptor, with a capture sock, towards the enemy weapon and deploying the capture sock just prior to the interceptor encountering the enemy weapon is also disclosed. The capture sock remains attached to the interceptor upon deployment.05-07-2009
20080230649Aircraft spiraling mechanism with jet assistance - D - An aircraft 09-25-2008
20080203216Multi-Environment Engine - The inventive multi-environment engine (08-28-2008
20100282892CONTROL SYSTEM FOR AN EXOATMOSPHERIC KILL VEHICLE - A control system for a maneuverable kill vehicle is provided. The control system includes a pressurized fluid source configured to provide a pressurized fluid, a valve in fluid communication with the pressurized fluid source, and a voice coil actuator comprising a magnet and a conductive coil oriented relative to the magnet such that when current flows through the coil, the coil moves relative to the magnet. The voice coil actuator is coupled to the valve such that the relative movement of the coil causes an adjustment in a flow rate of the pressurized fluid through the valve.11-11-2010
20080217465Piezoelectric fiber, active damped, composite electronic housings - A vibration controlled housing. The novel housing includes a housing structure and a mechanism for receiving a control signal and in accordance therewith electronically tuning a structural response of the structure. In an illustrative embodiment, the housing structure includes a composite material containing a plurality of piezoelectric fibers adapted to generate an electrical signal in response to a deformation in the structure and to deform the structure in response to an electrical signal applied thereto. A control circuit receives the sensed signal from the fibers and generates an excitation signal that is applied to the fibers to increase the stiffness or compliance of the fibers at predetermined frequencies. In an illustrative embodiment, the control signal is adapted to provide low frequency stiffness and strength performance while attenuating high frequency vibrations to protect electronics housed within the structure.09-11-2008
20090308970POD launched unmanned air vehicle - A method for attacking dispersed targets from a single aircraft standing off at a significant distance from the target area, wherein pods of individually targeted UAVs are carried in lieu of a bomb on a conventional bomb rack.12-17-2009
20120153070AUTOMATIC RE-INITIALIZATION OF RESONANT SENSORS IN ROCKET AND MISSILE GUIDANCE SYSTEMS - 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.06-21-2012
20100270418MISSILE TRAINING SYSTEM - 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. Live fire exercises present opportunities for checking that weapons systems function correctly and allow users, such as soldiers, to practice using real weapons in situations that are more realistic than firing ranges. It is known to use live missiles and torpedoes in naval training exercises and trials. For example, missiles can be fired at a ship to check the effectiveness of mechanisms for tracking and destroying such missiles. Clearly, there are substantial safety and costs issues to address before such a live firing regime is likely to be approved. A first approach for firing live missiles at a ship involves the use of a dummy ship, but crucially requires no personnel to be on board, thereby eliminating the risk to human life. This approach has clear disadvantages. A second approach involves firing a missile or other projectile at a target, such as a ship, so that the missile or projectile passes over the ship and lands on the other side. This approach enables personnel to be on board the ship and enables the on-board systems to be used in a realistic manner to attempt to destroy the incoming missile. However, there is a lack of realism. A third approach is to direct a missile towards a ship but to program its route so that it moves away from the ship immediately prior to any impact. This system also lacks realism. Other approaches exist. 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.10-28-2010
20120091252SYSTEM, APPARATUS AND METHOD FOR PROTECTION OF A VEHICLE AGAINST A POSSIBLE THREAT - 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. The counter-measure apparatus includes a guiding unit configured to guide the counter-measure apparatus towards the threat based on the processed information of the threat that is continuously received via the control unit, during acceleration of the counter-measure apparatus. The counter-measure apparatus further includes a counter-measure element that is launched in a direction against the threat by a releasing and activating module configured to release and activate the counter-measure element when the counter-measure apparatus has reached within the vicinity of the threat, such that the counter-measure element can defeat the threat.04-19-2012
20130015288SPRING CLIP RETENTION SYSTEMS SUITABLE FOR USAGE WITHIN VEHICLES AND GUIDED MUNITIONSAANM Hernandez; Christopher L.AACI VailAAST AZAACO USAAGP Hernandez; Christopher L. Vail AZ USAANM Egbert; Ryan A.AACI TucsonAAST AZAACO USAAGP Egbert; Ryan A. Tucson AZ US - Embodiments of a spring clip retention system are provided for securing a generally cylindrical component, as are embodiments of a guided munition including a spring clip retention system. In one embodiment, the spring clip retention system includes a captive feature and a spring clip. The captive feature includes opposing ledges and a channel formed beneath and partially enclosed by the opposing ledges. The spring clip includes opposing retainer arms and a base portion, which extends between the opposing retainer arms and which is received within the channel. The spring clip deflects outward when the component is inserted between the opposing retainer arms. The base portion abuts the undersides of the opposing ledges when the spring clip is deflected outward by insertion of the component to prevent disengagement of the base portion from the captive feature in a direction substantially normal to the longitudinal axis of the channel.01-17-2013
20080237391GUIDED PROJECTILE WITH POWER AND CONTROL MECHANISM - A projectile has the ability to generate and provide power to components located in two sections of the projectile which have relative rotation to each other. The projectile has a pair of generators allowing the powering of components in two sections. The projectile has a force-producing device for altering the direction of the projectile as the projectile moves along the longitudinal axis of the projectile and the relative rotational position of the force-producing device on the projectile is controlled by a generator.10-02-2008
20100314487PREDICTING AND CORRECTING TRAJECTORIES - Technology for predicting and correcting a trajectory is described. The technology can create a model to predict a position of the reusable launch vehicle at a time in the future; observe a wind condition during ascent of the reusable launch vehicle; store the observed wind condition in a wind map; predict during ascent a position and a terminal lateral velocity of the reusable launch vehicle at a terminal altitude; and correct a flight trajectory of the reusable launch vehicle based on the wind map.12-16-2010
20110272518Stackable, Easily Packaged and Aerodynamically Stable Flechette - A flechette has a forward section or body (11-10-2011


Patent applications in all subclasses MISSILE STABILIZATION OR TRAJECTORY CONTROL