Abstract: A system and method for controlling roll in a projectile. The novel system (56) includes first (52) and second (58) sections adapted to counter-rotate relative to each other and a mechanism (76) for inducing the counter-rotation to generate a roll torque on the projectile (50). In the preferred embodiment, the mechanism (76) is a motor comprised of a rotor (64) affixed to the first section (52), and the second section (58) which acts as a stator that rotates around the rotor (64) when a current is applied to the armature. In an alternative embodiment, the second section (58) is turned by a motor (80) attached to the first section (52) which drives a small gear engaging a full-diameter ring gear (82) on the second section (58). In the illustrative examples, the first (52) and second (58) sections are a missile forebody and a tail section of the projectile.

Abstract: The present invention relates to a long-range artillery shell (1) that is fin-stabilised in its trajectory and which is designed to be fired in a rifled gun barrel and thus has a slipping driving band (8) as main contact surface with the inside of the barrel, and has a so-called base-bleed unit (3) with a number of stabilization fins (9-14) that are deployable after the shell has left the barrel.

Abstract: An airplane 1 with a spiral inducing assembly 2 which is capable of inducing the airplane to travel in a continuous spiralling motion without the airplane rolling. Two fins 6 and 17 are attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The fins 6, 17 are able to rotate in a pivoting manner on the rotatable tube 3 with respect to the rotatable tube 3, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 3. Fin 6 is larger than fin 17. The difference in sizes between the fins makes the larger fin 6 exert a greater force on the rotatable tube 3 than the smaller fin 17 when the fins are pitched in unison. The aerodynamic imbalance between the fins thus causes the rotatable tube 3 to rotate. When pitched at an angle to the longitudinal axis in unison, both fins 6, 17 would exert a lateral force on the rotatable tube 3. Thus, as well as forcing the rotatable tube 3 to rotate, the fins 6, 17 would also push the rotatable tube sideways.

Abstract: A missile includes a missile body and a guide assembly mounted on the missile body. The guide assembly has a plurality of pivots and a plurality of vanes mounted on respective pivots for a swinging motion between a folded position of rest and a deployed flight position. The vanes are arranged for free pivotal motion during flight in response to forces acting thereon to determine the flight position. In the folded position of each vane, its center of gravity is situated at a greater distance from the longitudinal axis of the missile body than the pivotal axis of the respective vanes. Abutments limit the flight position of the vanes to a maximum angle between the length dimension of the vanes and the longitudinal axis of the missile body. The maximum angle is greater than 90°.

Abstract: An actuator system for controlling the external fins on a gun-launched projectile to control the flight path of the projectile. These actuator systems include an electric motor having a rotor and output shaft which is driven between travel limits that are less than 180 apart (less than 90 in either direction from a central rest position). Coupling from the motor shaft to the control shaft for the external fins is via a coupling between an eccentric ball on the motor shaft and an eccentric receptacle member on the fin shaft. As the angle of the motor shaft varies, the eccentric ball slides in a slot in the fin coupling member, causing the fin shaft angle to vary correspondingly. In another embodiment, the eccentric ball for controlling the fin shaft angle is mounted on a link arm that is coupled to the motor shaft, thereby permitting the motor to be mounted off the projectile axis and thus accommodating a shortened space in the projectile required for the actuator system and associated power supply.

Abstract: A tactical base for a guided projectile includes a base structure, and an adaptor structure for securing the base structure to a forward section of the projectile. The base further includes a plurality of fin slots. A plurality of deployable fins are pivotally mounted to the base structure and supported for movement between a stowed position and a deployed position.

Abstract: Method and arrangement for extending the range of fire of a fin-stabilized artillery missile. The fin-stabilized artillery missile (1), which is fired in a ballistic trajectory, has fins (3-6), which have been given a sawtooth-shaped leading wing edge (7) that has been found to give the missile (1) an extended range of fire and improved manoeuvrability.

Abstract: The invention is, in its various embodiments and implementations, a method and apparatus for planar actuation of a flared surface to control a vehicle. In one aspect, the invention comprises an apparatus for controlling a vehicle capable of moving through a fluid medium. The apparatus includes a flare; a planar yoke operably associated with the flare; a plurality of actuators capable of moving the planar yoke to manipulate the flare through the operable association between the planar yoke and the flare; and a load bearing structure through which the translating means imparts a moment from the flare to the vehicle. In a second aspect, the invention comprises a method for controlling the maneuvering of a vehicle capable of moving through a fluid medium. The method includes moving a planar yoke to deflect at least a portion of a flare.

Abstract: A penetrator includes a fore body having a center of aerodynamic pressure forward of a center of gravity and a stabilizing portion removably attached to the fore body such that, when attached to the fore body, a center of gravity for the penetrator is forward of a center of aerodynamic pressure for the penetrator. A method of using a penetrator includes propelling the penetrator toward a first target, penetrating the first target with a fore body of the penetrator, and detaching a stabilizing portion of the penetrator from the fore body. The method further includes impacting the second target with the fore body.

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: 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 one-piece wrap around fin for a projectile which includes a main portion, a first end and a second end. The main portion has at least one flap. The first end and the second end cooperate such that the fin is circumferentially mountable around the projectile.

Abstract: A retarding and locking mechanism for use between two mutually translatable bodies. A first body can be induced into motion and guided into a second body and, after a predetermined movement of the first body, the first body is subject to retardation and interlocked to the second body, such that the first and second bodies together form a unitary, integrated body. The first body has a radially outwardly directed shoulder and the second body has a radially inwardly directed shoulder corresponding to the radially outwardly directed shoulder of the first body. A compressible element is provided between the shoulders of the first and second bodies.

Abstract: A missile 1 with a missile attachment 2 according to this invention. The missile attachment 2 consists of a tube 3 with a protruding section 4. The protruding section 4 has a concave forward facing surface area 5. The concave curvature is such that it is noticeable when the protruding section 4 is at the highest position on the tube 3. The tube is in the form of a cylindrical tube and is fitted to the missile 1 so that it encircles part of the missile and such that it can rotate continuously relative to the missile 1 during flight of the missile.

Abstract: An apparatus for controlling a trajectory of a projectile includes a planetary drive train, a yaw drive assembly engaged with the planetary drive train, and a pitch drive assembly engaged with the planetary drive train. The apparatus further includes a plurality of fin assemblies linked with the planetary drive train such that, as the planetary drive train is actuated by at least one of the yaw drive assembly and the pitch drive assembly, corresponding displacements are produced in the plurality of fin assemblies.

Abstract: An apparatus for controlling a trajectory of a projectile includes a planetary drive train, a yaw drive assembly engaged with the planetary drive train, and a pitch drive assembly engaged with the planetary drive train. The apparatus further includes a plurality of fin assemblies linked with the planetary drive train such that, as the planetary drive train is actuated by at least one of the yaw drive assembly and the pitch drive assembly, corresponding displacements are produced in the plurality of fin assemblies.

Abstract: The present invention relates to a method and a device for correcting the trajectory (7, 8, 10, 11) of a spin-stabilised projectile (12) in azimuth by controlling its rate of spin by devices (18-21) deployable on the outside of the projectile (12) where they act on the airflow.

Abstract: Control group for directional fins on missiles and/or shells which have a containment body (15, 15′, 15″) that has on the outside of the containment body, two command surfaces in the form of half-fin surfaces (13, 14) which are hinged (at 24, 25), directable and motorized. The containment body (15, 15′, 15″) has two housings (16) each of which has an electric motor (17, 17′) which commands, through a reduction gear group (19, 29; 19′, 29′), the oscillation about the axis (Z) of a control group that is based on a pair of rings (21, 22), arranged in annular seats (31, 32) and in which end attachments (26) of the half-fins (13, 14) engage, the half-fins (13, 14) being hinged so that they are diametrically opposed in a further ring (20) arranged in an annular seat (23) of said containment body (15, 15′, 15″) where they are free to rotate about the (Z) axis.

Abstract: The apparatus of the invention allows flight vehicle and/or guided munition wings and control surfaces to be secured in a retracted and locked position prior to the launch by a control surface retainer. An electro-mechanical differential control system preferably releases the control surface retainer, extends the control surfaces, and servo controls the control surfaces subsequent to launch. The invention also provides a method for guiding a flight vehicle and/or guided munition by releasing the flight vehicle's and/or guided munition's control surface from a control surface retainer, extending the flight vehicle's and/or guided munition's wing/control surface assembly using a wing/control surface actuation system, and controlling the flight vehicle's and/or guided munition's control surfaces using a wing/control surface actuation system.

Abstract: Described is a rudder blade mounting arrangement (10) for a missile comprising a rudder blade (12) and a mounting element (16) for the rudder blade. The rudder blade (12) is displaceable about a rudder blade axis member (36) of the mounting element (16) between a retracted inactive position and a deployed active position. The rudder blade foot (14) of the rudder blade (12) is connected in positively locking relationship to the rudder blade axis member (36) in such a way that, in the deployed active position of the rudder blade (12), the rudder blade foot (14) is forced against a front face (62) of a side portion (24) of the mounting element (16).

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 submarine countermeasure vehicle includes an elongated body for supporting a countermeasure device, and a propulsion assembly mounted on an after end of the body. The propulsion assembly includes a rotatable propeller hub, propeller blades mounted on the hub and moveable between a first position wherein the blades extend substantially radially outwardly from the hub, and a second position wherein the blades extend generally axially of the hub. A spring is mounted on each of the blades and in the hub, the spring biasing the blades toward the first position, but of sufficient flexibility to permit the blades to move to the second position upon launch of the vehicle from an underwater launch tube.

Abstract: A fin disengagement device for limiting the range of a projectile uses an electronic safe and arm circuit to sense launch and spin levels. Once armed, the stored energy from the electronic safe and arm circuit is dumped into an initiator or directly to explosive bolts. The initiator ignites an energetic material to separate the fin from the projectile in-flight at a predetermined time. Alternatively, the explosive bolts separate the fin from the projectile in-flight at a predetermined time. In the embodiments using an initiator and energetic material, an opening or cavity in the rear portion of the projectile body or rod adapter acts as a pressure chamber. When enough pressure has built up from the burning of the energetic material, the front hub of the fin section expands enough to disengage the threads and separates the fin section from the projectile body.

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: 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 spin-stabilised artillery projectile (11) can be easily subsequently fitted with an axially symmetrical aerodynamic braking device for reducing the ballistic trajectory if the tip (14) which is equipped with the fuse (13) and which is easily removable from the projectile body (12) is equipped at approximately half its height with flap-shaped sectors (24) which are pivotably mounted in such a way that they can be pivotably extended and which in their launch position fit snugly into the conical peripheral surface of the tip (14) and in the operative position are pivotably extended to form a radial ring which is closed or which has gaps.

Abstract: A three axis control system employing four flaps is disclosed. The flaps are of uniform design, which decreases machining and manufacturing costs. The flaps are positioned on a vehicle orthogonally, but offset from a vehicle centerline. The system provides not only pitch and yaw control, but also bi-directional roll control with a minimum number of parts and minimal infringement of packaging envelope. The system provides quick response and increased capability for difficult maneuvers and is useable for hypersonic/supersonic applications.

Abstract: A tube launched projectile having a shaft member at the aft section is slidably mounted on a boom extending aft from the body of the projectile. The boom has a cavity in its aft end which receives some combustion gas from the projectile propellant burn and retains this gas at elevated pressure until the projectile exits the tube. Upon reaching atmospheric pressure, the stored cavity gas expands and drives the slidable shaft aft, elongating the projectile to its flight configuration.

Abstract: Accordingly, a shaft assembly for coupling a control fin to a missile includes outer and inner shaft portions which are detachably coupled together, allowing removal of one of the shaft portions while the other shaft portion remains in the missile. In an exemplary embodiment, the inner shaft portion, to which the control fin is coupled, is removable. The shaft assembly includes a pair of preload nuts to adjust the position of the control fin relative to the skin of the missile, the preload nuts being for example engaged on opposite threaded ends of the outer shaft portion.

Abstract: Accordingly, a shaft assembly for coupling a control fin to a missile includes outer and inner shaft portions which are detachably coupled together, allowing removal of one of the shaft portions while the other shaft portion remains in the missile. In an exemplary embodiment, the inner shaft portion, to which the control fin is coupled, is removable. The shaft assembly includes a pair of preload nuts to adjust the position of the control fin relative to the skin of the missile, the preload nuts being for example engaged on opposite threaded ends of the outer shaft portion.

Abstract: A projectile having a plurality of micro electromechanical (MEMS) devices disposed about the axis of flight for active control of the trajectory of the projectile. The MEMS devices each form an integral control surface/actuator. Control circuitry installed within the projectile housing includes both rotation and lateral acceleration sensors. Flap portions of the MEMS devices are extended into the air stream flowing over the projectile in response to the rate of rotation of the projectile, thereby forming a standing wave of flaps operable to impart a lateral force on the projectile. MEMS devices utilizing an electrostatically controllable rolling flap portion provide a large range of motion while consuming a small amount of power. The MEMS devices may be arranged in longitudinal strips along an ogive portion of the projectile. Packaging concepts for projectiles as small as a 30 caliber bullet are described.

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: Described is a rudder blade mounting arrangement (10) for a missile comprising a rudder blade (12) and a mounting element (16) for the rudder blade. The rudder blade (12) is displaceable about a rudder blade axis member (36) of the mounting element (16) between a retracted inactive position and a deployed active position. The rudder blade foot (14) of the rudder blade (12) is connected in positively locking relationship to the rudder blade axis member (36) in such a way that, in the deployed active position of the rudder blade (12), the rudder blade foot (14) is forced against a front face (62) of a side portion (24) of the mounting element (16).

Abstract: The invention relates to a missile for combating stationary and/or moving targets comprising a seeker head (100), an effective charge which is arranged behind said seeker head in the direction of flight, a thruster such as a solid fuel booster having lateral outlet nozzles which is arranged behind the effective charge in the direction of flight, and a guiding section (104) which is arranged behind the thruster in the direction of flight. The guiding section comprises controllable aerofoils (105a, 105b) such as lateral and/or tail fins, and a guiding device. The missile also comprises a cruise engine (107) which is arranged on the tail, whereby the cruise engine is detachably connected to the guiding section by means of a first quick-acting closure (109a, 109b) such as a manually operable bayonet closure or the like.

Abstract: A control group for directional fins on missiles and/or shells comprises a containment body (15, 15′, 15″) carrying on the outside two command surfaces in the form of fin or half-fin surfaces (13, 14) which are hinged (at 24, 25), directable and motorized, in which the containment body (15, 15′, 15″) foresees two housings (16) each of which receives an electric motor (17, 17″) which commands, through a gear-dowm group (19, 29; 19′, 29′), the oscillation about an axis (Z) of the control group of a pair of rings (21, 22), arranged in annular seats (31, 32) and in which end attachments (26) of the half-fins (13, 14) engage, the half-fins (13, 14) being hinged diametrally opposed in a further ring (20) arranged in an annular seat (23) of the containment body (15, 15′, 15″) free to rotate about the axis (Z).

Abstract: A fin-stabilized projectile includes a projectile body having a rear portion defining a rearwardly open cavity and a stabilizing assembly which has an axially slidable fin support in the cavity. The fin support has a retracted position in which the fin support is withdrawn into the cavity and an outwardly shifted position in which the fin support projects from the projectile body. A plurality of fins are pivotally held in the fin support. Each fin has a folded state in which it is withdrawn in the fin support when the latter is in the retracted position and a deployed state in which it is unfolded and extends substantially externally of the fin support when the latter is in its outwardly shifted position. When the projectile has left the weapon barrel, the fin support is axially shifted and the fins move into the deployed state.

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 fin lock device (12) for a missile. The device (12) provides a mechanism for locking a missile fin (14) by grasping an edge of the fin (14) and a mechanism (32, 42) for retracting the locking mechanism (18) to release the fin (14). The fin (14) is grasped by a notch (20) therein adapted to receive the edge of the fin (14). The piston (18) is retracted by burning a pyrotechnic powder in a cavity adjacent to the piston (18) to fill the cavity with gas and create a pressure differential to force the piston (18) away from the fin.

Abstract: A projectile includes an elongated forebody and an aft section secured to the forebody. The aft section includes a pair of fins affixed to an aerodynamic, cylindrical section. The lift generated by the low-drag pair of fins is sufficient to counteract most foreseeable angles of attack to be experienced by the projectile. The aft section further includes a bearing that couples the aft section to the forebody of the projectile and is capable of allowing the aft section to rotate freely about the longitudinal axis of the projectile and independently of the forebody. Thus, during flight the aft section rotates into the maximum lift plane and provides a restoring moment to the projectile, thus providing necessary stability to the projectile while imparting minimum drag.

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 missile 1 with a missile attachment 2 according to this invention. The missile attachment 2 consists of a tube 3 with a protruding section 4. The protruding section 4 has a concave forward facing surface area 5. The concave curvature is such that it is noticeable when the protruding section 4 is at the highest position on the tube 3. The tube is in the form of a cylindrical tube is fitted to the missile 1 so that it encircles part of the missile and such that it can rotate continuously relative to the missile 1 during flight of the misile.

Abstract: A smart bullet capable of in-flight maneuvers generated by the selective extension of a spoiler from a de-spun control section of the bullet into the stream of air passing the bullet. A micro gyro located in the control section provides a rotation signal used in the control of a motor rotatably attached between the control section and a spinning section of the bullet. A rearward facing lens and optical detector receive guidance information from a gun-mounted guidance system. The direction of extension of the spoiler is selectively controlled by controlling the operation of the motor in response to the guidance information. The detector and pre-amplifier circuit are bonded to the lens structure to minimize microphonic noise generation. An optical link is used to communicate information between the spinning and control sections of the bullet.

Abstract: An arrangement in a missile and a method for guiding the missile towards a moving target, for example, an aircraft, wherein the missile has information on its own position, velocity vector, and future velocity characteristic. The missile continuously receives information on the position and velocity vector of the target. The arrangement and method operate such that, a point of interception, at which the missile is expected to strike the target, is calculated from the information on the missile and the target, and a velocity vector of the missile is directed towards the predicted point of interception, which is continuously predicted on the basis of an assumption as to the future movement of the target, and a calculation of the time to impact.

Abstract: A fin disengagement device for limiting the range of a projectile uses an electronic safe and arm circuit to sense launch and spin levels. Once armed, the stored energy from the electronic safe and arm circuit is dumped into an initiator or directly to explosive bolts. The initiator ignites an energetic material to separate the fin from the projectile in-flight at a predetermined time. Alternatively, the explosive bolts separate the fin from the projectile in-flight at a predetermined time. In the embodiments using an initiator and energetic material, an opening or cavity in the rear portion of the projectile body or rod adapter acts as a pressure chamber. When enough pressure has built up from the burning of the energetic material, the front hub of the fin section expands enough to disengage the threads and separates the fin section from the projectile body.

Abstract: A guidance device for projectiles has stationary canards (40) and thrusters (50) positioned on the nose (20) of the projectile (10). The thrusters (50) are initiated from remote or local sensor to provide flight maneuverability to a target.

Abstract: A rudder of a missile, particularly an aircraft born ramjet missile, is attached to the missile by a plug and socket mounting. A bearing socket (B1) is attached to a base plate (B0) which is secured to the missile body (FK). The socket (B1) has a conical cavity (B3) tapering toward the base plate (B0). The plug (W1) is formed by a rudder shaft (W) also tapering toward the base plate and rotatably fitting into the conical cavity (B3). Bearings (L1, L2) in the cavity (B3) hold the plug end (W1) of the rudder shaft axially and permit rotation of the rudder shaft (W) relative to the bearing socket (B1). The socket thus holds the bearings and has an at least partly outer cylindrical contour with a diameter (B2) that fits into a standard 41 mm wide slot (S) in an aircraft that carries the missile, whereby the rudder (R) is recessed in the slot (S) when the missile is mounted to an aircraft.

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 self-orienting device comprises: a housing; a sensor mounted to the housing that is sensitive to a signal field and configured to produce a signal responsive to the signal field; a translation-inducing unit associated with the housing; rotation-inducing unit attached to the housing, wherein the translation-inducing unit and the rotation-inducing unit are configured such that the housing travels along a helical trajectory having an axis and is free to rotate about the axis; and a controller operably associated with the sensor for controlling the output of at least one of the translation-inducing unit and the rotation-inducing unit, wherein the controller is configured such that it receives the signal from the sensor and, responsive to the signal, controls the output of at least one of the translation-inducing unit and said rotation-inducing unit. A device so configured can automatically orient to a signal.

Abstract: Apparatuses and methods for controlling an object spinning at a first rate in a first direction. The apparatus includes a swash plate, a rotor, a spin actuator, a roll actuator, and a pitch actuator. The rotor is coupled to the swash plate. The spin actuator is coupled to the rotor and is configured to spin the rotor in a second direction opposite the first direction at a second rate. The roll actuator is coupled to the rotor and is configured to displace the swash plate along a longitudinal axis. The pitch actuator is coupled to the rotor and is configured to tilt the swash plate in a tilt direction about the longitudinal axis, the tilt direction being adjustable by adjusting the second rate relative to the first rate. The roll actuator may be coupled to the pitch actuator so that the pitch actuator keeps a substantially identical orientation with the swash plate as the swash plate is displaced along the longitudinal axis by the roll actuator.

Abstract: A locking and unlocking mechanism for moveable control fins extending from the surface of a missile. The locking mechanism includes a pin extending thru the outer surface of the missile into an opening provided in the movable fin. A link is pivotally connected between each of the pins and a slide member disposed internally of the missile and carried by a guide. The links are in a close to dead center position when the pins are extended into the openings in each of the fins. A striker assembly is disposed within the slide member and includes a rod carrying a hammer which is spring loaded spaced from the slide member when the pins are in their extend position.