Abstract: A cooling system is provided for enclosed volumes having payloads of electronic or other equipment that are susceptible to failures when overheated. One particularly useful application of the present invention is in a cooling system for a turreted gimbaled system (i.e. a gimbal) that includes electronic and optical equipment typically used for surveillance, but many other applications will become apparent to those skilled in the art after being taught by the present disclosure. According to one aspect of the invention, a cooling system includes a pair of reciprocal openings between a gimbal sphere and yoke allowing for passage of air therethrough and a pair of fans for circulating the air between the sphere and yoke, thereby expanding the surface area available for heated air from the interior to conduct into the exterior air. In another example, a heat exchanger is provided in the yoke to allow further cooling of the circulated air.

Abstract: The present invention relates to an apparatus that controllably allows the relative rotation between structures, such as a gimbal and a structure to which it is mounted. According to one aspect, the apparatus includes a twist capsule assembly with internal stop mechanisms that controllably prevents the amount of clockwise and counterclockwise rotation with respect to a rotation axis. According to another aspect of the invention, by limiting the amount of relative rotation, other means of communicating power and signals between the structures can be used, thus avoiding or reducing the limitations imposed by conventional slip ring assemblies. According to yet another aspect, the invention includes techniques and structures for allowing conventionally shielded cables and wires to be used in place of slip rings, while allowing for rotation between structures, thus even further improving the communication of power and signals between structures.

Abstract: An apparatus for enhanced viewing of objects in two separate simultaneous frequency bands of light that is constructed in accordance with the principles of the present invention includes a primary mirror and a moveable secondary mirror that is disposed above the primary mirror to provide a long focal length. A beam splitter splits the optical path into two paths, one for infrared and another path for visible. Various optical elements and devices are described along each path. The secondary mirror is displaced away from its concentric position over the primary mirror to provide shorter focal lengths in IR and visible. Focal Plane Arrays (FPA's) are disposed where desired along both optical paths for real-time viewing and data acquisition. The preferred FPA in visible is a CCD. The preferred FPA in IR is disposed in a Dewar.

Abstract: An apparatus for the focusing of incident light includes a base assembly that is adapted to support a primary mirror. The primary mirror includes an outside circumference and an inside aperture. An upright member is attached to the base assembly at a first end thereof at a first location that is disposed inside the aperture and at a second location that is disposed outside the primary mirror. The upright member includes a second end that is distally disposed with respect to the first end. The second end is adapted to receive a turret that includes a secondary mirror and is adapted to pivot between two positions. An IMU is attached to the base assembly proximate the primary mirror.

Abstract: An apparatus for enhanced viewing of objects in two separate simultaneous frequency bands of light that is constructed in accordance with the principles of the present invention includes a primary mirror and a moveable secondary mirror that is disposed above the primary mirror to provide a long focal length. A beam splitter splits the optical path into two paths, one for infrared and another path for visible. Various optical elements and devices are described along each path. The secondary mirror is displaced away from its concentric position over the primary mirror to provide shorter focal lengths in IR and visible. Focal Plane Arrays (FPA's) are disposed where desired along both optical paths for real-time viewing and data acquisition. The preferred FPA in visible is a CCD. The preferred FPA in IR is disposed in a Dewar.

Abstract: A novel design concept for a torquer motor is useful for stabilizing apparatuses in a vibrating structure. According to one aspect, a novel design for a coil pair is provided. A first coil in the pair is box shaped with a hollow interior portion and windings provided on a surface opposite the hollow interior. A second coil in the coil pair is flat and torus shaped with windings provided on the surface. According to one example, the second coil is bent so as to conform to the shape of the first coil, and disposed over the first coil so that the respective windings are oriented orthogonally to each other in a common plane direction so as to define an active area. The active area may be further disposed in the magnetic field of a magnet pair in a torquer motor application. The design provides advantages such as inherent rigidity and more efficient heat transfer, while providing high torque or a desired range of movement.

Abstract: An apparatus for the control and alignment of a sensor on a moving vehicle is provided that includes a gimbal ball supported by an outer axis structure and adapted to pivot about an outer elevation axis and about an outer azimuth axis. The outer axis structure is mounted to a vehicle. An inner axis structure includes a cardan shaft that is provided in the ball and is used to support a payload. An inner elevation axis passes through the cardan shaft. The payload is moved about inner pitch inner roll and inner yaw axes over a limited range of motion by the use of a plurality of permanent magnet wide-gap motors that are disposed on the plane of the cardan shaft and maximally away from the yaw axis in the ball. The motors are adapted to each urge the payload to move in two perpendicular axes, depending upon the current that is applied through conductors which pass through a flux field. Control circuitry is used to energize the motors in any desired combination to produce motion in roll, pitch, or yaw.

Abstract: A fin cover release and deployment system designed for high G forces of gun-launched missiles. In one embodiment, a pyrotechnic actuator drives actuator arms to first release and eject the fin slot covers, followed by deployment of the fins radially outward to the steering position. Following complete ejection of the covers, the fins are driven outwardly by cam surfaces along the latch arms, followed by a spring and wedge mechanism installed interiorly of the fin steering shaft to lock the fins in the fully deployed state. In another embodiment, a motor and rotating threaded shaft replace the pyrotechnic actuator.

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: Pyrotechnic actuator cover/fin release system designed for high G forces of gun-launched-systems. As safety feature, system allows the pyrotechnic actuator to be installed as one of the last steps of the final testing sequence and removed safely on disassembly. A first cam action develops initial ejection. Subsequently firing the pyrotechnic pushes both the fins and the covers outward via a second cam surface. The release system both holds covers securely latched until commanded to release and then unlatches covers prior to pushing them open. The cover eject sequence results in the flight forward edge of cover being kicked into air stream. Thereafter the cover is lifted and rotates about its aft release hinge until, at about 30 degrees of rotation, the hinge disengages. The fins then are driven into the fully deployed state by a spring and piston/wedge mechanism on the actuator shaft.

Abstract: An integrated system for missile steering, which uses both jet reaction control (JRC) and aerofin control systems, is provided with a variable coupling mechanism for adjusting the relative responsiveness of the two systems in accordance with the pressurization state of the JRC system pressure chamber. In one embodiment, the pivoting action of a joystick which actuates the gas flow control pintles of the JRC system is permitted only under sufficient pressurization of the pressure chamber. In a second embodiment, the extent to which the pintles protrude from their controllable housings is adjusted according to the pressure in the pressure chamber. In this manner, when JRC is undesirable or is unavailable, the missile aerofins are permitted their full range of motion without being constrained by the pintles.

Abstract: A rosette or co-rotating vector scanning seeker detector array providing improved data rate and scanned field coverage. Several discrete detector elements are formed in an array on the detector surface in a coplanar arrangement, each of the detector elements providing target information when the scan sweeps across it. The array may be in the form of circular spots arranged around a central circular detector element. In an alternative embodiment, the central detector element is omitted and the peripheral detector elements are arranged sufficiently close together to preclude the likelihood of a target path passing between adjacent detector elements without being detected. Detector elements in a single array may be of different sizes and shapes.

Abstract: Pairs of aerofins used for stabilization and control of missile flight are deployed through shared longitudinal slots provided in the missile body. Before launch, the pairs of aerofins, each pair comprised of a canard and a deflector, are retained in a folded position by a releasable latch mechanism within the missile body. The deflectors are mounted in a laterally displaced position from the longitudinal slots and are constrained from sliding into alignment with the slots by the presence of the folded canards. When the canards are released by the latch mechanism and permitted to extend outward to their deployed positions, the deflectors are able to laterally shift, effectively displacing the canards in the alignment position and subsequently deploying. The latch mechanism is designed to simultaneously release all the canards following missile launch, with biasing torsional springs operating to urge the canards outward through the associated slots to the extended position upon release.

Abstract: A mechanism for locking the fins of a missile in place when the missile is not in use utilizes tabs inserted in slots of the output shafts of the fins to immobilize the output shafts and the fins. In one embodiment, the tabs are cantilevered on a locking plate from which they extend radially toward the output shafts. A cam plate slidably engages the tabs on the locking plate and simultaneously lifts all the tabs out of the slots when it is rotated. for disengagement of the locking mechanism. Operation of the locking mechanism can be effected either manually, using a specialized tool, or remotely, using for example a pyrotechnic actuation device.

Abstract: An optical system is provided with a plurality of field of view optical groups for insertion into the optical path. The field of view optical groups each subtend a prescribed field of view angle and are rotatably mounted on a rotary assembly for insertion into an operational position in the optical path. The rotary assembly is provided with hard stop contacts which rotate along a path and interact with stationary stops to locate the optical groups in the operational position. Additionally, movable stops are reciprocated into the rotation path of the hard stop contacts to provide additional modes, including a calibration mode. The system is also provided with extender optical groups which can be inserted in the optical path to provide intermediate fields of view between those of the field of view optical groups, thereby doubling the total number of fields of view available.

Abstract: In a missile thrust vector control (TVC) system, two yoke plates are used which surround a pair of pivotably-mounted rocket nozzles. The rocket nozzles pass through corresponding elongated slots disposed on each yoke plate, the elongate slots engaging said rocket nozzles and operating to actuate the movement of the rocket nozzles in accordance with command signals issued by the missile autopilot. The actuator yoke plates are mounted for movement in orthogonal directions, and for rotation in unison. The orthogonal movement of the yoke plates effects corresponding movement of the rocket nozzles in the yaw and pitch directions. Simultaneous rotation of the yoke plates produces a relative twisting of the pivotably-mounted rocket nozzles causing thrust angles to deviate from the missile central axis in opposite directions but equal degree, thereby imparting a roll moment to the missile. In this fashion, any combination of movements of the missile during flight is made possible.

Abstract: An actuation system for controlling the steerable nozzle of a missile or like vehicle is combined with an aerofin control system, both of which are driven in unison by associated drive motors and gear assemblies, one set for each aerofin. The nozzle steering system comprises two essentially identical yoke plates mounted along a plane generally transverse to the missile axis and oriented orthogonally relative to each other about the missile axis for pivoting the nozzle through mutually orthogonal axes, thereby achieving omni-directional steering. The yoke plates are coupled at opposite ends to pinion gears which are driven by the same gear assemblies which drive the associated aerofins. The arrangement permits common directional control of the steerable nozzle and the aerofins while maintaining the nozzle in a neutral direction when the aerofins are rotated to a missile roll control mode.

Abstract: A gimbal control system including a hand controller having a trackball and a mode select switch for determining the mode of gimbal control. The mode control switch is capable of selecting between four different control modes. The trackball is enabled to control movement of the gimbal in different control relationships depending on the control mode which is selected. The hand controller includes a plurality of other switches for enabling the trackball to provide additional system control capabilities. The hand controller is ergonomically designed to minimize operator stress and fatigue during extended missions. It has a particular shape and the various control elements are strategically positioned to provide ready access to an operator's manual digits when the controller is held in the right hand with both hands and arms in a naturally relaxed attitude oriented at approximately a right angle.

Abstract: An actuation system for controlling the steerable nozzle of a missile or like vehicle is combined with an aerofin control system, both of which are driven in unison by associated drive motors and gear assemblies, one set for each aerofin. The nozzle steering system comprises two essentially identical yoke plates mounted along a plane generally transverse to the missile axis and oriented orthogonally relative to each other about the missile axis for pivoting the nozzle through mutually orthogonal axes, thereby achieving omni-directional steering. The yoke plates are coupled at opposite ends to pinion gears which are driven by the same gear assemblies which drive the associated aerofins. The arrangement permits common directional control of the steerable nozzle and the aerofins while maintaining the nozzle in a neutral direction when the aerofins are rotated to a missile roll control mode.

Abstract: An actively damped steering rate sensing device for an autopilot control system capable of producing angular rotation in a control plane of an intentionally continuously axially rolling airframe such as a homing missile in response to a rotation related guidance command signal. The device includes an elongated armature member mounted to the airframe for pivotal movement about an axis extending through the member intermediate its length. The pivot axis is oriented with respect to the rotational axis of the airframe so that the armature member will pivot by gyroscopic precession in response to rotation in the control plane of the rolling airframe. Sensing and damping coils are mounted on opposite ends of the armature member. Magnets and flux path return elements are fixedly mounted adjacent each of the coils.