Abstract: A guided projectile includes a body and a deployable wing in which the deployable wing is coupled to and enclosed by the body. A linear distance from the leading edge to the trailing edge of the wing defines a chord line that, in the stowed position, forms an angle with a plane containing the chord line and extending parallel to a longitudinal dimension of the wing in a deployed position.

Abstract: A guided projectile includes a body and a deployable wing in which the deployable wing is coupled to and enclosed by the body. A linear distance from the leading edge to the trailing edge of the wing defines a chord line that, in the stowed position, forms an angle with a plane containing the chord line and extending parallel to a longitudinal dimension of the wing in a deployed position.

Abstract: A projectile includes a housing and a slot formed in the housing. A deployable flight surface is inside the housing. A cover is attached to the housing and covers the slot. A cutter is adjacent the cover and moves in the slot and slices the cover to open the slot and allow deployment of the flight surface through the slot.

Abstract: A lock block for use in a flight vehicle to deploy and lock wings in a deployed position with the lock block having a forward end and an aft end and including a support member, a resilient member adjacent the aft end of the lock block, a first deploy pin extending from the resilient member, a second deploy pin extending from the resilient member, and a wedge located on a bottom side of the resilient member. The first deploy pin and the second deploy pin are each configured to engage a groove in a wing of the flight vehicle to push each wing into a deployed position.

Abstract: A projectile includes a housing and a slot formed in the housing. A deployable flight surface is inside the housing. A cover is attached to the housing and covers the slot. A cutter is adjacent the cover and moves in the slot and slices the cover to open the slot and allow deployment of the flight surface through the slot.

Abstract: A flex gear includes a hub with an axis, a rim, and an interface feature, a tooth ring with gear teeth, and flex elements between the rim and the tooth ring.

Abstract: A control system for a flight vehicle includes first and second pivot pins each having a hollow cylindrical shape with an opening therein, first and second deployable wings configured to pivot about the first and second pivot pins between a stowed position and a deployed position with the first and second deployable wings each having first and second wing tip shafts extending between the first and second pivot pins and first and second ailerons at a tip of the deployable wings, first and second lever pins within the opening in the pivot pins with the first and second lever pins each having a first end that extends out from a top of the pivot pin and a second end connected to the wing tip shaft and with the first and second lever pins configured to rotate the wing tip shafts to control the ailerons.

Abstract: A wire release mechanism includes two components with adjacent longitudinal fingers and a wire that is wound about the fingers. The wire restrains one of the components in one position and includes a higher resistance fuse that causes the wire to be loosened about the fingers to allow that component to move to another position due to the flow of electrical current through the fuse.

Abstract: A wire release mechanism includes two components with adjacent longitudinal fingers and a wire that is wound about the fingers. The wire restrains one of the components in one position and includes a higher resistance fuse that causes the wire to be loosened about the fingers to allow that component to move to another position due to the flow of electrical current through the fuse.

Abstract: A flex gear includes a hub with an axis, a rim, and an interface feature, a tooth ring with gear teeth, and flex elements between the rim and the tooth ring.

Abstract: A lock block for use in a flight vehicle to deploy and lock wings in a deployed position with the lock block having a forward end and an aft end and including a support member, a resilient member adjacent the aft end of the lock block, a first deploy pin extending from the resilient member, a second deploy pin extending from the resilient member, and a wedge located on a bottom side of the resilient member. The first deploy pin and the second deploy pin are each configured to engage a groove in a wing of the flight vehicle to push each wing into a deployed position.

Abstract: A control system for a flight vehicle includes first and second pivot pins each having a hollow cylindrical shape with an opening therein, first and second deployable wings configured to pivot about the first and second pivot pins between a stowed position and a deployed position with the first and second deployable wings each having first and second wing tip shafts extending between the first and second pivot pins and first and second ailerons at a tip of the deployable wings, first and second lever pins within the opening in the pivot pins with the first and second lever pins each having a first end that extends out from a top of the pivot pin and a second end connected to the wing tip shaft and with the first and second lever pins configured to rotate the wing tip shafts to control the ailerons.

Abstract: A bearing assembly is described that includes a shaft and an inner race affixed to the shaft. An outer race is disposed radially around the inner race defining a bearing run space with rolling elements between the inner and outer races. An axial bore in the support or the rotor has a radial gap between the bore wall and the outer race, and the assembly is configured to provide a radial displacement between a portion of the outer race and the axial bore wall in response to a radial overload force applied to the rotor.

Abstract: A bearing assembly is described that includes a shaft and an inner race affixed to the shaft. An outer race is disposed radially around the inner race defining a bearing run space with rolling elements between the inner and outer races. An axial bore in the support or the rotor has a radial gap between the bore wall and the outer race, and the assembly is configured to provide a radial displacement between a portion of the outer race and the axial bore wall in response to a radial overload force applied to the rotor.

Abstract: A bearing system for a spin-stabilized projectile including bearing configurations that permit selective relative rotation between a spindle and a body portion and which facilitate automatic centering of the spindle. Each bearing configuration includes a conical bearing surface rotatable with respect to a corresponding conical body surface. One bearing configuration is in a forward portion of the body portion and selectively engages a first body surface upon the projectile experiencing set-back forces to direct forces away from bearing elements, and another bearing configuration is in a rearward portion of the body portion and engages a second body surface upon the projectile experiencing set-forward forces to direct forces away from the bearing elements.

Abstract: A bearing system for a spin-stabilized projectile including bearing configurations that permit selective relative rotation between a spindle and a body portion and which facilitate automatic centering of the spindle. Each bearing configuration includes a conical bearing surface rotatable with respect to a corresponding conical body surface. One bearing configuration is in a forward portion of the body portion and selectively engages a first body surface upon the projectile experiencing set-back forces to direct forces away from bearing elements, and another bearing configuration is in a rearward portion of the body portion and engages a second body surface upon the projectile experiencing set-forward forces to direct forces away from the bearing elements.

Abstract: In one aspect, column load cells are described herein. In some embodiments, a column load cell comprises a load bearing column, a plurality of first strain gauges coupled to surfaces of the load bearing column for determining axial strain and a load receiving surface comprising a plurality of load guides, the load guides substantially aligned with the first strain gauges.

Abstract: A recoil system for field-type guns automatically adjusts the recoil distance of the barrel according to the angle of elevation of the gun barrel relative to the ground. The system includes a recoil cylinder in fixed relationship to the gun barrel and a piston rod operably connected to a two-art piston valve within the cylinder. The rotational position of one of the valve parts is controlled by the angular position of the piston rod about its axis and the rotation position of the second valve part is controlled by its axial piston within the recoil cylinder bore. Fluid flow orifi are defined between the first and second valve part, the area of the orifi being determined by the rotational positions of the two valve parts relative to each other. As barrel elevation is increased, the piston rod is rotated via a camming device which is itself moved by a tooth riding in a non-axial and non-linear slot in the camming device.