The system and method of improving the analysis of and implementation of a combat identification (CID) server system including providing correlation reports. There are at least two forms of correlation report, namely incident report and a summation report. The summation report has two types of totals, a summary total of all interrogations, and a breakdown of totals based on the Source JU. In one example, a correlated incident would be the combination of a Lock On or Mark Point with a Weapon Release, Disengage, or Attack.

Infrared vision systems, headpieces, and methods include an eyepiece and a body module. The eyepiece is configured to be worn over a user's eyes. The eyepiece includes an infrared sensor, configured to detect external infrared information. For example, the infrared sensor may include a plurality of short-wave infrared (SWIR) sensors. The eyepiece includes a display, configured to visually provide external infrared information to the user. For example, the display may include a see-through color display. The body module is in wired or wireless communication with the eyepiece. The eyepiece may include an adjustable strap, coupled to the eyepiece. The adjustable strap is configured to wrap around the user's head.

A data processing method and apparatus, the method comprising: storing, at a first memory location in a memory, a first copy of a set of data; storing, at a second memory location in a memory, a second copy of a set of data; comparing the first copy to the second copy so as to identify, within the first copy, a pointer, the pointer being located at a first data element of the first copy, the pointer specifying a second data element of the first copy; determining an offset for the identified pointer, the offset specifying a number of data elements between the first data element and the second data element; and modifying the first copy such that the pointer within the first copy specifies the second data element using only the first data element and the offset.

A network of scopes, including one or more lead scopes and one or more follower scopes, is provided to allow scope operators of the respective scopes to track the same presumed target. A lead scope locates a target and communicates target position data of the presumed target to the follower scope. The follower scope uses the target position data and its own position data to electronically generate indicators for use to prompt the operator of the follower scope to make position movements so as to re-position the follower scope from its current target position to move towards the target position defined by the target position data received from the lead scope.

A network of scopes, including one or more lead scopes and one or more follower scopes, is provided to allow scope operators of the respective scopes to track the same presumed target. A lead scope locates a target and communicates target position data of the presumed target to the follower scope. The follower scope uses the target position data and its own position data to electronically generate indicators for use to prompt the operator of the follower scope to make position movements so as to re-position the follower scope from its current target position to move towards the target position defined by the target position data received from the lead scope.

Techniques are provided for determination of a guided-munition orientation during flight based on lateral acceleration, velocity, and turn rate of the guided-munition. A methodology implementing the techniques, according to an embodiment, includes obtaining a lateral acceleration vector measurement and a velocity of the guided-munition, and calculating a ratio of the two, to generate an estimated lateral turn vector of the guided-munition. The method also includes integrating the estimated lateral turn vector, over a period of time associated with flight of the guided-munition, to generate a first type of predicted attitude change. The method further includes obtaining and integrating a lateral turn rate vector measurement of the guided-munition, over the period of time associated with flight of the guided-munition, to generate a second type of predicted attitude change. The method further includes calculating a gravity direction vector based on a difference between the first and second types of predicted attitude change.

Techniques are provided for determination of a guided-munition orientation during flight based on lateral acceleration, velocity, and turn rate of the guided-munition. A methodology implementing the techniques, according to an embodiment, includes obtaining a lateral acceleration vector measurement and a velocity of the guided-munition, and calculating a ratio of the two, to generate an estimated lateral turn vector of the guided-munition. The method also includes integrating the estimated lateral turn vector, over a period of time associated with flight of the guided-munition, to generate a first type of predicted attitude change. The method further includes obtaining and integrating a lateral turn rate vector measurement of the guided-munition, over the period of time associated with flight of the guided-munition, to generate a second type of predicted attitude change. The method further includes calculating a gravity direction vector based on a difference between the first and second types of predicted attitude change.

Systems are disclosed for navigating a missile to a target using a fixed sensor onboard the missile. In an embodiment, a system includes a launch platform traveling a pre-programmed route to deliver the missile within an area. The missile travels a first flight path through the area in effort to detect targets. If no targets are detected along the first flight path, the missile transitions to a second flight path, different from the first flight path, to locate targets off-axis relative to the first flight path. While the missile travels the second flight path, the sensor receives signal identifying a target located at a position off-axis relative to the first flight path. The missile then adjusts the second flight path to direct the missile to the target. In an example embodiment, the first flight path is straight or arced, while the second flight path is u-shaped, corkscrew-shaped, or spiral-shaped.

A method for authorizing a mission for at least one portable launch assembly in a defined hazard area is disclosed. One or more electronic devices may be communicatively coupled to one another. At least signals representative of a situational awareness (SA) corresponding to each of the one or more electronic devices, and parameters of the mission for the at least one portable launch assembly, may be received. One or more predefined rules may be selectively retrieved, and may be applied to the parameters of the mission based on at least the signals representative of a situational awareness (SA) corresponding to each of the one or more electronic devices. And, a request for an approval of the mission for the at least one portable launch assembly may be obtained, the request for the approval based on at least the one or more predefined rules related to the parameters of the mission.

A network of scopes, including one or more lead scopes and one or more follower scopes, is provided to allow scope operators of the respective scopes to track the same presumed target. A lead scope locates a target and communicates target position data of the presumed target to the follower scope. The follower scope uses the target position data and its own position data to electronically generate indicators for use to prompt the operator of the follower scope to make position movements so as to re-position the follower scope from its current target position to move towards the target position defined by the target position data received from the lead scope.