Abstract: Technology for facilitating position determination is disclosed. A satellite with a known location can activate a light source on the satellite operable to emit light. The satellite can emit the light for a defined period of time to enable a receiver to detect the light and determine a geographical location using the light emitted from the satellite.

Abstract: Technology for facilitating position determination is disclosed. A satellite with a known location can activate a light source on the satellite operable to emit light. The satellite can emit the light for a defined period of time to enable a receiver to detect the light and determine a geographical location using the light emitted from the satellite.

Abstract: Passively measured NEO bearings are used to augment an existing navigation system on-board the platform to correct the position estimate generated by the navigation system. The technology provides only a position correction based on passive NEO sightings but is applicable to a wide variety of platforms with different maneuvering profiles and update requirements. The technology directly calculates a position error based on the current position estimate and the passively measured and estimated bearings to three or more NEOs and provides the position error to the navigation system as a correction to the position estimate. The estimated bearings are computed from the current position estimate and the known orbits of the NEOs. The position error may be calculated from a single observation of multiple NEOs, allowing for frequent updates as needed and placing no restriction on platform maneuverability.

Abstract: Passively measured NEO bearings are used to augment an existing navigation system on-board the platform to correct the position estimate generated by the navigation system. The technology provides only a position correction based on passive NEO sightings but is applicable to a wide variety of platforms with different maneuvering profiles and update requirements. The technology directly calculates a position error based on the current position estimate and the passively measured and estimated bearings to three or more NEOs and provides the position error to the navigation system as a correction to the position estimate. The estimated bearings are computed from the current position estimate and the known orbits of the NEOs. The position error may be calculated from a single observation of multiple NEOs, allowing for frequent updates as needed and placing no restriction on platform maneuverability.

Abstract: A sabot is used for enclosing a payload, such as a missile or projectile, during launch. The sabot includes a series of panels that are held together prior to launch by engagement with a cap having protrusions or delay pins that maintain the panels in a closed condition. When the launch is initiated, the cap begins to slide out of engagement with the panels. The cap is configured such that the disengagement does not occur immediately upon movement of the cap; instead the protrusions are sized to delay opening of the panels until the sabot and missile have cleared the launcher. Then the panels rotate outward and drop away from a base the sabot, for example using self-releasing hinges. The base of the sabot may be configured to disengage from the payload by introduction of pressurized gases into a space between the base and an aft end of the missile.

Abstract: A sabot is used for enclosing a payload, such as a missile or projectile, during launch. The sabot includes a series of panels that are held together prior to launch by engagement with a cap having protrusions or delay pins that maintain the panels in a closed condition. When the launch is initiated, the cap begins to slide out of engagement with the panels. The cap is configured such that the disengagement does not occur immediately upon movement of the cap; instead the protrusions are sized to delay opening of the panels until the sabot and missile have cleared the launcher. Then the panels rotate outward and drop away from a base the sabot, for example using self-releasing hinges. The base of the sabot may be configured to disengage from the payload by introduction of pressurized gases into a space between the base and an aft end of the missile.

Abstract: A spinning, rolling, or roll-stabilized vehicle, such as a projectile, includes a fuselage that rotates about its longitudinal axis (spins) during flight. A collar is positionable relative to the fuselage to steer the projectile, with the collar having ailerons to provide a roll force to position the collar. The collar also has elevators to provide lateral force to steer the projectile. The positioning of the collar may be accomplished by moderating the roll force of the ailerons to hold the position of the collar substantially constant with regard to a longitudinal axis of the projectile. The ailerons passively change angle of attack with changes in the dynamic pressure of the projectile. At low speeds the ailerons have a relatively large angle of attack, and at high speeds, the ailerons resiliently reduce their angles of attack, avoiding large rolling forces on the collar.

Abstract: An electronics module is provided for utilization onboard an airborne object. In one embodiment, the electronics module includes a housing having a cavity therein, a first printed circuit board (PCB) disposed in the cavity, a second PCB disposed in the cavity above the first PCB, and a supportive interconnect structure. The supportive interconnect structure includes a substantially annular insulative body and a plurality of vias. The substantially annular insulative body extends around an inner circumferential portion of the housing between the first PCB and the second PCB to support the second PCB and to axially space the second PCB from the first PCB. The plurality of vias is formed through the substantially annular insulative body and electrically couples the first PCB to the second PCB.

Abstract: An obturator can be secured to a projectile to be launched from within a launch tube. The obturator cooperates with the projectile to seal a pressurized gas within the launch tube during launch. The obturator has a plurality of segments that combine to form a ring. Each segment has connecting features that cooperate with corresponding connecting features of an adjacent segment to hold the segments together by restricting relative circumferential movement, without restricting radially outward movement of individual segments. Preferably, each segment is identical, making it easier to repair and assemble the obturator. Upon launch, the obturator segments can move radially outwardly to separate into relatively small, uniformly-sized pieces.

Abstract: A spinning, rolling, or roll-stabilized vehicle, such as a projectile, includes a fuselage that rotates about its longitudinal axis (spins) during flight. A collar is positionable relative to the fuselage to steer the projectile, with the collar having ailerons to provide a roll force to position the collar. The collar also has elevators to provide lateral force to steer the projectile. The positioning of the collar may be accomplished by moderating the roll force of the ailerons to hold the position of the collar substantially constant with regard to a longitudinal axis of the projectile. The ailerons passively change angle of attack with changes in the dynamic pressure of the projectile. At low speeds the ailerons have a relatively large angle of attack, and at high speeds, the ailerons resiliently reduce their angles of attack, avoiding large rolling forces on the collar.

Abstract: An air vehicle that is launched from inside a launcher, includes a release mechanism for releasing fins of the vehicle from a stowed condition to a deployed condition. The release mechanism includes a pin that is located within a cavity in the fuselage of the air vehicle. Pressurized gasses initially fill the cavity in the fuselage. The launcher includes a reduced-pressure portion such as from a muzzle brake. When the air vehicle passes into the reduced-pressure portion of the launcher, the gas pressure behind the air vehicle is reduced. This causes the pressurized gas within the cavity to drive the release mechanism backwards out of the cavity. The length of the pin may be used to control the timing of the fin deployment, the delay between the initial movement of the release mechanism out of the cavity, and when the fins are released.

Abstract: A dipole based decoy system provides an inexpensive alternative to chaff. A non-conductive filament patterned with lengths of conductive material that form dipole antennas at one or more radar frequencies is stored on the air vehicle and attached to a projectile. In response to a RWR warning, a programmed time or location or a time-to-target, a mechanism releases the projectile(s) to deploy the filament with its dipole antennas at a speed greater than or equal to the speed of the air vehicle to present an extended target or a separate false target to enemy radar. The projectile is either towed behind the air vehicle or launched away from the air vehicle. Either approach is effective to overcome Doppler and moving range gating by presenting coherent signal returns and ranges and velocities consistent with the air vehicle during a threat interval posed by the radar defense systems.

Abstract: A method of modifying a projectile includes removing material from an aft end of the projectile, and coupling a device to the aft end. The method may be used to convert a spin-stabilized projectile into a fin stabilized projectile, by modifying the aft end of a spin-stabilized projectile to accept a fin kit. The modifying may involve removing material with lathe, and may include forming external threads on the aft end that may engage corresponding internal threads on the device, to effect the coupling of the device to the aft end. The modification method allows versatility in employing projectiles, including existing stocks of projectiles. In particular the method allows spin-stabilized projectiles to be converted to more accurate fin-stabilized projectiles.

Abstract: A dipole based decoy system provides an inexpensive alternative to chaff. A non-conductive filament patterned with lengths of conductive material that form dipole antennas at one or more radar frequencies is stored on the air vehicle and attached to a projectile. In response to a RWR warning, a programmed time or location or a time-to-target, a mechanism releases the projectile(s) to deploy the filament with its dipole antennas at a speed greater than or equal to the speed of the air vehicle to present an extended target or a separate false target to enemy radar. The projectile is either towed behind the air vehicle or launched away from the air vehicle. Either approach is effective to overcome Doppler and moving range gating by presenting coherent signal returns and ranges and velocities consistent with the air vehicle during a threat interval posed by the radar defense systems.

Abstract: A guided projectile may include a projectile body, an inertial measurement unit disposed within the projectile body, one or more control surfaces extendable from the projectile body, and a controller which controls the one or more control surfaces in response, at least in part, to measurement data received from the inertial measurement unit. The inertial measurement unit may include sensors to measure motion parameters relative to first, second, and third mutually orthogonal axes, wherein each of the first, second and third mutually orthogonal axes is oblique to a longitudinal axis of the projectile body.

Abstract: A projectile has a fuze kit that includes deployable canards. The canards are ends of a strip of material. The strip of material is initially in an angled recess of a collar of the fuze kit, with the angled recess angled relative to a longitudinal axis of the projectile, defining a plane that is not perpendicular to the longitudinal axis. At some point in flight of the projectile, for example during mid-course of the projectile flight after a ballistic phase of the projectile flight, the canards are deployed by releasing the ends of the strip. This causes the ends of the strip to pull away from the longitudinal axis of the projectile, out of the recess, into the airstream around the projectile. Resilient forces in the strip may cause the ends to be moved out of the recess when the ends are released.

Abstract: A projectile, such as a missile, rolls during at least a portion of its flight, while retaining its roll reference to enable navigation during the rolling period of flight. The roll reference may be retained by using a sensor, such as magnetometer, to periodically check and correct the roll reference. Alternatively or in addition the missile may alternate roll directions, for example varying roll rate in a substantially sinusoidal function. By rolling the missile inaccuracies in an inertial measurement unit (IMU) of the missile may be ameliorated by being to a large extent canceled out by the changes in orientation of the missile as the missile rolls. This enables use of IMUs with lower accuracy than would otherwise be required to obtain accurate flight. Thus accurate flight may be accomplished with less costly IMUs, without sacrificing the ability to navigate.

Abstract: A multi-caliber fuze kit includes a fuze housing configured for coupling with multiple projectiles. One or more canards are moveably coupled with the fuze housing. The one or more canards are adjustable between two or more canard configurations. In a first canard configuration, the one or more canards are at a first canard angle relative to a bore sight of the fuze housing, and the first canard angle is configured for use with a first projectile. In a second canard configuration, the one or more canards are at a second canard angle relative to the bore sight of the fuze housing, and the second canard angle is configured for use with a second projectile. The first and second canard angles are different. In another example, in the first canard configuration the one or more canards include a first canard shape configured to provide a first specified trajectory with the first projectile.

Abstract: A gun fired projectile includes a rocket motor housing including a pressure chamber and an exhaust nozzle. A plurality of propellant cells are positioned within the pressure chamber. The rocket motor propellant is mechanically supported during the severe gun fire event. This support may take several forms, each of which is discussed herein. The projectile further includes a support structure including one or more supports: wherein each of the one or more supports is engaged with the rocket motor housing. Each of the one or more supports is engaged with one propellant cell of the plurality of propellant cells, and each of the one or more supports suspends an individual propellant cell from the remainder of the plurality of propellant cells. All of these approaches provide the opportunity to tailor the performance of the rocket motor by combining a combination of propellant formulations and geometries to optimize the projectile performance.

Abstract: A projectile, air vehicle or submersible craft with a spinning or rolling fuselage, rotating on its axis, has a collar which can be positioned relative to a longitudinal axis of the projectile using aerodynamic forces. Aerodynamic surfaces, such as lift-producing surfaces, for example tails or canards, are coupled to the collar, and rotate with the collar. An actuator system or mechanism controls orienting of the lift-producing surfaces, such as tilting of the lift producing surfaces, to direct the collar into a desired position relative to a longitudinal axis of the projectile, and to maintain the collar in that position. With such a control the projectile is able to be steered using bank-to-turn maneuvering. The actuator system may use any of a variety of mechanisms to move the lift-producing surfaces, thereby positioning the collar.