A closed, self-contained ballistic apogee detection module for use in a projectile, such as a rocket, mortar round, or artillery round, fuses data from multiple built-in sensors, such as an accelerometer, a magnetometer, and a gyroscope, and processes the data using a microprocessor through a custom quaternion extended Kalman filter to provide accurate state and orientation information about the projectile so as to accurately predict apogee. The module outputs a signal indicating apogee detection or prediction which they projectile uses to initiate fuze arming, targeting control, airbody transformation, maneuvering, flow effector deployment or activation, payload exposure or deployment, and/or other mission activity. Because the system and method of the invention does not rely on external environmental data to detect apogee, it need not use a pressure sensor and can be completely sealed in and closed without requiring access to air from outside the projectile for barometric readings.

A mounting system is provided for mounting a forward package on the front of a munition. The front of the munition has a plate joined thereto with a beveled aft peripheral surface. The forward package includes a housing that has an aft portion defined by side walls that provides an opening at the rear of the housing. The aft portion of the housing is configured to fit around the periphery of the plate. Fasteners are provided that are engageable with the beveled surface, and are configured to temporarily hold the housing adjacent the forward surface of the plate while permitting rotational adjustment of the housing relative to the plate.

In one possible embodiment, a system capable of a self-propagating data link includes an unmanned vehicle having a data link transceiver and at least one deployable data link transceiver. The unmanned vehicle having a deployment means for deploying the at least one deployable data link transceiver.

A receiver determines a roll rate of a spinning projectile that receives a signal from a satellite or terrestrial transmitter at a directional antenna fixed to the projectile. The receiver tracks a code phase and a rate of change thereof of the received signal relative to a local model signal corresponding to the transmitter. A roll correlator of the receiver correlates the received signal with the model signal based on (i) the tracked code phase and rate, and (ii) a roll-correlator integration time assumed to produce a predetermined number N of correlation samples per revolution of the antenna, to produce sequential correlation samples for each of successive revolutions of the antenna. The receiver determines a time difference between successive periods of observed signal reception based on the correlation samples, and determines a roll rate based on the time difference.

A method for displaying successive image frames on a display. The method including: processing image data containing the successive image frames to identify features in an image frame and to display the image frame to a user with two or more of the identified features highlighted; manually selecting one of the identified features by a user; determining a portion of a subsequent image frame in which the selected feature is likely to be present; and if the selected feature is found in the portion of the subsequent image frame, displaying the subsequent image frame to change the position of the selected feature.

A method is presented by which a missile body roll angle relative to earth coordinates can be deciphered onboard the missile from ground-data relayed to the missile during flight The present method comprises of a horizontal pair and a vertical pair of antennas on the ground and an up-down pair and a right-left pair of antennas onboard the missile. The ground to pairs signals are sinusoidally amplitude modulated in 90 phase difference between the two pairs, causing the transmitted wave polarity to rotate in the modulation frequency. A reference pulse is transmitted from the ground whenever the wave polarity vector crosses a prescribed ground antenna direction, thereby enabling the missile to measure its body up, down, right and left directions relative to earth up, down, right and left directions and to further respectively align them together.

A closed, self-contained ballistic apogee detection module for use in a projectile, such as a rocket, mortar round, or artillery round, fuses data from multiple built-in sensors, such as an accelerometer, a magnetometer, and a gyroscope, and processes the data using a microprocessor through a custom quaternion extended Kalman filter to provide accurate state and orientation information about the projectile so as to accurately predict apogee. The module outputs a signal indicating apogee detection or prediction which they projectile uses to initiate fuze arming, targeting control, airbody transformation, maneuvering, flow effector deployment or activation, payload exposure or deployment, and/or other mission activity. Because the system and method of the invention does not rely on external environmental data to detect apogee, it need not use a pressure sensor and can be completely sealed in and closed without requiring access to air from outside the projectile for barometric readings.

A method of executing a mission for at least one mobile munition assembly in a mission environment is provided, the at least one mobile munition assembly having a container that encloses one or more launchers configured to receive and launch a munition. One or more electronic devices in communicatively coupling with one another in the mission environment form a secure network. A status of a situational awareness (SA) corresponding to each of the one or more electronic devices in the mission environment is transmitted. An input of parameters of the mission for the at least one mobile munition assembly is enabled, the parameters having one or more predefined rules associated therewith and configured to be applied to the parameters based on at least the status of the situational awareness (SA). An authorization or a denial of the mission for the at least one mobile munition assembly is requested.

A method for controlling at least one guided missile to be launched by an aircraft during flight, a guided missile and an aircraft, wherein at least one mission command is transmitted by light signal from the aircraft to the guided missile. The light signal may be transmitted to a transceiver temporarily connected to or integrated into the guided missile.