Abstract: An attitude control system includes one or more control moment gyro pairs, with gyros of individual of the pairs being counter-rotated to rotate the rotation axes of flywheels of the gyros of a gyro pair in opposite direction. The flywheels of a gyro pair may be in paddle configuration, with the rotation axes of the flywheels rotating in the counter-rotation through separate planes as the gyros are rotated. The rotation of the gyros of a gyro pair may be accomplished by coupling both of the gyros to a servo motor with suitable coupling gears, or by using independent servos for each gyro. The counter-rotation of gyros of an individual pair produces a resultant torque about a fixed global axis, such as the axis of a flight vehicle of which the attitude control system is a part. Further control may be accomplished for example by varying rotation speeds of the flywheels.

Abstract: An attitude control system includes one or more control moment gyro pairs, with gyros of individual of the pairs being counter-rotated to rotate the rotation axes of flywheels of the gyros of a gyro pair in opposite direction. The flywheels of a gyro pair may be in paddle configuration, with the rotation axes of the flywheels rotating in the counter-rotation through separate planes as the gyros are rotated. The rotation of the gyros of a gyro pair may be accomplished by coupling both of the gyros to a servo motor with suitable coupling gears, or by using independent servos for each gyro. The counter-rotation of gyros of an individual pair produces a resultant torque about a fixed global axis, such as the axis of a flight vehicle of which the attitude control system is a part. Further control may be accomplished for example by varying rotation speeds of the flywheels.

Abstract: The disclosed system, device and method for deploying a sub-module from a carrier vehicle generally includes: a sub-module projectile (100) housed within a carrier vehicle; a rolling diaphragm (115) sealed between a first pressure chamber volume (145) and a second sub-module containment volume (e.g., substantially formed on the opposing side of rolling diaphragm 115 relative to pressure chamber 145); and a release mechanism (500), wherein the sub-module projectile (100) is secured until releasable deployment from the carrier vehicle. Disclosed features and specifications may be variously controlled, adapted or otherwise optionally modified to improve ejection, deployment and/or dispersal of a variety of sub-modules from a variety of carrier modules. Exemplary embodiments of the present invention generally provide for the ejection and dispersal of kinetic energy rod warheads from a kill-vehicle.

Abstract: The disclosed system, device and method for deploying a sub-module from a carrier vehicle generally includes: a sub-module projectile (100) housed within a carrier vehicle; a rolling diaphragm (115) sealed between a first pressure chamber volume (145) and a second sub-module containment volume (e.g., substantially formed on the opposing side of rolling diaphragm 115 relative to pressure chamber 145); and a release mechanism (500), wherein the sub-module projectile (100) is secured until releasable deployment from the carrier vehicle. Disclosed features and specifications may be variously controlled, adapted or otherwise optionally modified to improve ejection, deployment and/or dispersal of a variety of sub-modules from a variety of carrier modules. Exemplary embodiments of the present invention generally provide for the ejection and dispersal of kinetic energy rod warheads from a kill-vehicle.

Abstract: A stator assembly is provided for a multi-phase motor. The stator assembly includes a stator with a plurality of teeth and a plurality of slots defined between the teeth. In addition, the stator assembly includes a plurality of windings representing respective phases of the multi-phase motor. The windings are wound within the slots and around the teeth to define respective magnetic poles. Further, each slot includes no more than a single turn or small number of turns of any given one of the plurality of windings.

Abstract: A dynamic load fixture (DLF) applies a torsion load to a unit under test (UUT) to achieve the demanding aerodynamic load exposures encountered by a control actuation system (CAS) in flight. Instead of fixing the end of the torsion bar, the DLF controls the application of torque to the torsion bar, hence the UUT via a DLF motor. The dynamic load can be independent of the angular rotation of the UUT, which allows the DLF to more effectively reproduce desired acceptance tests such as torque-at-rate and nonlinear loads. Furthermore, application of the loads through a torsion bar allows the system the compliance needed to generate precise loads while allowing for the flexibility of changing torsion bars to test a wide variety of UUT on one test platform. To achieve the demanding aerodynamic load exposures encountered by a CAS in flight, the controller must be able to respond both very fast and very precisely.

Abstract: A dynamic load fixture (DLF) for testing a unit under test (UUT) includes a lateral load system that applies a time-varying lateral load profile to the UUT drive shaft and an encoder that measures its angular rotation. An isolation stage suitably constrains the encoder from rotating about the axis while allowing it to move in other directions in which the application of the lateral force induces motion. The lateral load system includes a load bearing around the drive shaft, an actuator that applies a lateral force to the load bearing, a force sensor for measuring the applied lateral force, and a lateral controller for adjusting a command signal to the actuator to implement a lateral load profile. The DLF may also include a torsion load system that applies a time-varying torsion load profile to the drive shaft.

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: 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: 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: An in-line multi-plug self-aligning electrical connector assembly includes a receptacle, and a pair of connectors that matingly engage the receptacle. The receptacle has an alignment feature on a mating face of an end of the receptacle which mates with mates with the connectors. In an exemplary embodiment, the alignment feature is a wedge-shaped protrusion which corresponds in cross-sectional shape to one of the connectors. The receptacle may be cylindrical, and the connectors may be complimentary such that when engaging the receptacle they together form a cylindrical shape. The connectors may be coupled to different components. In an exemplary embodiment one of the connectors is electrically connected to a motor of a missile fin actuator and the other of the connectors is electrically connected to a potentiometer of the actuator.