A method and apparatus for generating, in an aircraft in flight, a feasibility display indicative of the feasibility of a weapon, the method comprising: providing a performance envelope for the weapon; determining, using the performance envelope, configuration data for configuring a generic algorithm; uploading the configuration data to the aircraft; generating feasibility data N indicative of the feasibility of a weapon carried on the aircraft successfully engaging a target and/or the feasibility of a weapon carried on the target successfully engaging the aircraft; determining, on board the aircraft, using the same generic algorithm and the uploaded configuration data, one or more test criteria; performing, on board the aircraft, an assessment process including determining whether or not the feasibility data satisfies the one or more test criteria; and, based the assessment, using the feasibility data, generating the feasibility display.

A launch control system relates to a method and apparatus for launch control packet processing that is provided in the launch control system and configured to allow interworking between a plurality of firing control systems and the launch control system. The launch control system comprises a plurality of operation equipments, a system control device, and control the plurality of operation equipments, a launch control packet processing unit, a control signal distribution device, and a status display device.

Techniques are provided for a laser designation verification device and a method of laser designation verification using the device. The laser designation verification device includes: a lens to sense a first reflection, the first reflection coming from an encoded first laser beam reflecting off a first target; an electronic processing element to decode the sensed first reflection into a first code; and a portable electronic annunciator to provide identification of the first target to an operator of the device based on the decoded first reflection. The method includes: sensing a first reflection using the lens, the first reflection coming from an encoded first laser beam reflecting off a first target; decoding the sensed first reflection into a first code using the processing element; and providing, by the annunciator to an operator of the device, identification of the first target based on the decoded first reflection.

Systems and methods for testing an Arm and Fire Device (AFD). The system includes an AFD arm controller and a first power supply coupled to the AFD controller to provide arming power to the AFD controller. The system further includes a monitoring module coupled to the AFD controller through a plurality of means of isolation and communication. The monitoring module may include one or more monitor circuits for the AFD to test at least one circuit in the AFD, at least one circuit external to the AFD, or combination. The system further includes at least one output for the AFD to provide data from the monitoring module. The system may further include a first switch to control the monitoring module is powered and a second switch to control power to the AFD arm module. The system can include an input for applying data to the AFD.

Test systems coupled to a device under test (DUT) with different segments or stages and related methods are provided. Exemplary test systems include logic that executes concurrent determinations or tests for multiple DUT segments or stages. Exemplary test systems can include logic that concurrently executes various tests associated with different DUT segments including determinations or testing for a specified DUT test environment, determinations or tests of when data will be made available to various DUT segments, and various determinations or tests that may be completed before data is made available to specified DUT segments. At least one embodiment of a first stage concurrent determination test system determines first stage tests do not require a specified target and high pressure gas conditions for DUT testing and at least one embodiment of a second stage concurrent test system does require a specified target and high pressure gas conditions for DUT testing.

Methods, systems, and devices solving Euler's rotational rigid body equation of motion, formed within two non-inertial frames of reference, that determine the vector inconstant variables of angular acceleration, velocity, and trajectory using a single piezoresistive accelerometer sensor, an ?C coupling algorithm and 1.sup.st and 2.sup.nd running integrals to in-flight acquire rotational inconstants in high-density Terramedia Terraflight and determine a Penetrator's loading profiles and method to parse vector Terraflight for rotational Pitch and Yaw enabling precision trajectory tracking utilizing three axial facing piezoresistive accelerometers, a differencing algorithm and 1.sup.st and 2.sup.nd running integrals enabling Penetrator flight control and precision guidance.

A system for transferring power and/or data between a host and a store over a single-wire umbilical cable is herein described. The system comprises a host-store interface configured to allow the transfer of both power and data between the host and a store in operative communication therewith. The store comprises a microcontroller and memory operatively coupled thereto, allowing the microcontroller to be powered on and to receive and store data sent by the host in its memory through a single-wire without requiring additional electronic systems that the store may comprise to also be powered on. This data may later be incorporated into pre-programmed systems onboard the store at full power-on, thereby enabling the reprogramming of the store without powering it on prior to launch.

A time domain detection system to measure and report on hypervelocity impacts HVI between an interceptor vehicle and a target vehicle. Wherein, said time domain detection system comprises a target vehicle components installed on said target vehicle, a one or more panels arranged on a portion of said target vehicle at a potential HVI locations, and a hit detection system wired into said one or more panels. Said target vehicle components comprise at least said hit detection system, and a lines. Said one or more panels are wired into said hit detection system with said lines. Said hit detection system is configured to communicate with said one or more panels over said lines. Said one or more panels can each comprise a one or more detector panel layers, and a two or more insulator layers.

A system for transferring power and/or data between a host and a store over a single-wire umbilical cable is herein described. The system comprises a host-store interface configured to allow the transfer of both power and data between the host and a store in operative communication therewith. The store comprises a microcontroller and memory operatively coupled thereto, allowing the microcontroller to be powered on and to receive and store data sent by the host in its memory through a single-wire without requiring additional electronic systems that the store may comprise to also be powered on. This data may later be incorporated into pre-programmed systems onboard the store at full power-on, thereby enabling the reprogramming of the store without powering it on prior to launch.

Techniques are provided for automated determination of a rocket configuration based on acceleration during rocket motor burn-out and temperature. The rocket configuration is associated with a class of warhead affixed to the rocket. A methodology implementing the techniques according to an embodiment includes measuring the acceleration of the rocket over a period of time associated with the flight of the rocket. The method also includes calculating an acceleration difference between the measured acceleration associated with the start of rocket motor burn-out and the measured acceleration associated with the end of rocket motor burn-out. The method further includes measuring an internal temperature of the rocket and selecting a delta acceleration threshold based on the measured temperature. The method further includes comparing the calculated acceleration difference to the selected delta acceleration threshold, to estimate the rocket configuration. The estimated rocket configuration is used by guidance and control circuitry to select autopilot parameters.