Abstract: This invention provides a shock mitigation means that attenuates the high frequency energy transmitted to the floating element of an inertial measurement unit (IMU) device in a cannon launched guided projectile or cannon launched munition improving the ability of the IMU to survive the extreme forces of such cannon launched environment. The invention utilizes a crushable foam mitigator located in the IMU device's housing to interfere and apply a compressive force to the floating element of the IMU device, plus a rubber pad attenuator element placed above the foam mitigator to further tailor the transmission of shock energy to the floating element in the IMU device.

Abstract: A hardened subminiature telemetry and sensor system for a ballistic projectile having a radome, antenna, steel insert, S-band transmitter circuit board, data recorder, sensor or measurement device and battery. The entire assembly is contained in such a way that the assembly can be threaded into the existing tracer well of a kinetic energy projectile.

Abstract: A system which is packaged within a projectile fuze body and obtains data relative to the projectile during a launch. Sensors are provided which obtain in-bore data as well as in-flight data. The in-bore data is recorded at a fast rate during in-bore travel of the projectile and is read out, continuously, at a slower rate during in-flight travel. Both in-bore data and in-flight data are encoded and transmitted to a ground station for analysis.

Abstract: A payload carrying device which is inserted into a remote area of interest by means of a projectile carrier to obtain data, or the like, from the remote area. The device has counter rotating main blades as well as tail blades carried on a tail rotor. The particular payload is carried in a canister which may also include a power source, a command and control unit and a motor, if hover or lateral flight is desired. The pitch of the tail blades is variable as well as their orientation around an axis, the combination of which generates a thrust vector in a particular direction for controlled lateral flight.

Abstract: An optical alignment device having a sensor housing with obstructing geomy which restricts the amount of sunlight that enters the sensor and impinges upon a photoelectric cell within the sensor body. The restriction of light properly maintains a constant area of illumination of the photoelectric cell over a wide range of incident angles about the insensitive axis. Variations in incident angle about the sensitive axis produces a significant change in illumination area for small changes in the incident angle. Thus, the device produces a significant change in output with respect to alignment with its sensitive axis and an invariant output with respect to alignment to its insensitive axis.

Abstract: A range correction module which is designed to fit onto a spin stabilized llistic projectile for correcting range error. The range correction module is a self-contained module within the fuze which screws into the forward portion of the projectile. The range correction module is designed such that changes are not required to the existing projectile. During the course correction phase, sixteen semi-circular plates will deploy from the module. The plates create a blunt cross-sectional area in front of the projectile, thus creating more drag and effectively slowing the projectile.

Abstract: A range correction module which is designed to fit onto a spin stabilized ballistic projectile for correcting range error. The range correction module is a self-contained module within the fuze which screws into the forward portion of the projectile. The range correction module is designed such that changes are not required to the existing projectile. During the course correction phase, semi-circular plates will deploy from the module. The plates create a blunt cross-sectional area in front of the projectile, thus creating more drag and effectively slowing the projectile.

Abstract: A trajectory (range) control device which is designed to fit behind the f of a fin stabilized ballistic projectile for correcting range error. The trajectory (range) control device is a self-contained, add-on module, which will screw into the forward portion of the projectile. The fuze will then screw into the trajectory (range) control module, which has a small through hole that will coincide with the center of the fuze and the center of the projectile. This through hole is intended to provide a channel in which the fuze can detonate the intended booster charge which will in turn ignite the high explosive payload or function the payload of the fin stabilized ballistic projectile. The trajectory control device will not make changes to the existing projectile or fuze. During the course correction phase, eight spring loaded flare tabs will deploy from the device. The flare tabs create a blunt cross-sectional area in front of the projectile, thus creating more drag and effectively slowing the projectile.

Abstract: A fin stabilized kinetic energy tank training device comprising a project having a nose and having nose and end sections, and constructed of a low density material such as aluminum, and having a hollowed-out section to further reduce weight thereof, so as to minimizing penetration of an armor system on impact thereon.