A system and method to aid in guidance, navigation and control of a guided projectile including a precision guidance munition assembly is provided. The system and method obtain raw position data during flight of the guided projectile, the raw position data including a plurality of position data points from the guiding sensor for determining positions of the guided projectile, establish a window including a portion of the plurality of position data points, smooth the portion of the plurality of position data points in the window, and determine a reduced noise position estimate of the guided projectile, based, at least in part, on the smoothed portion of the plurality of position data points in the window. The system and method may determine a velocity estimate of the guided projectile and predict an impact point of the guided projectile relative to a target.

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 AC 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.

Apparatus and methods for reducing device testing times, such as missile testing times, are disclosed. The apparatus and methods may execute tests or portions of tests in a parallel manner. The apparatus and methods ensure that tests or portions of tests executing in parallel do not interfere with one another. The apparatus and methods may assess the current state of the test environment to confirm whether it is acceptable to advance one or more tests. If the testing environment is not acceptable for a test to continue executing, the apparatus and methods do not allow the test to advance. The testing environment may be monitored by measuring one or more vital signs, where the vital signs may indicate whether it is safe for a particular test to advance. As such, the apparatus and methods provide an efficient way to test devices such as missiles.

A motion analysis system includes an acceleration measuring device, an acceleration processor, a velocity processor, a distance processor, a peak velocity processor, a profile correlation processor, and a vehicle action processor. The system determines a time for an initiation of an action for a vehicle by determining that a distance traveled by the vehicle is greater than a safe separation distance and that a peak velocity is greater than a minimum velocity. The system initiates the action for the vehicle based on the verified position of the vehicle and the confirmed profile data as determined by the profile correlation processor, and based on the determination that the distance traveled by the vehicle is greater than the safe separation distance and that the peak velocity is greater than the minimum velocity as determined by the vehicle action processor.

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.

A moving object command link system includes a transmitter which outputs a EM beam and a steering mechanism which directs the beam toward one or more objects, at least one of which is moving. The system may include a variable attenuator which modulates the average output power of the beam, and/or a divergence controller to maintain a desired beam size. The beam may be polarized, and the system may include a polarization modulator which changes the beam's polarization in accordance with a predetermined sequence and schedule. The system may include a 1×2 switch to selectively provide the beam to one of first and second outputs. A tiltable dichroic beam splitter may be used to couple beams received from first and second objects to track cameras having respective boresights that are offset with respect to each other.

A tracking system for a target flight vehicle includes at least two sensor nodes that are positioned at geographically diverse locations relative to a launch site from which the target flight vehicle is launched. The sensor nodes have a lens and a visible camera that captures images of an anticipated launch trajectory for the target flight vehicle. The sensor nodes determine position data for the target flight vehicle including timing, azimuth, and elevation based on the captured images. A fusion processing engine is communicatively coupled to the at least two sensor nodes for receiving and integrating the position data. The data is integrated to determine real-time state vectors including a velocity and a three-dimensional position for the target flight vehicle. The state vectors are sent to a range network that is configured to implement a flight termination system for the target flight vehicle based on the state vectors.

The invention relates to a method for determining characteristic-curve correction factors a matrix detector that images in the infrared spectral range. A good image correction can be obtained by virtue of an area of homogeneous temperature being recorded at two different temperatures by the matrix detector, there being two images with different integration times for each temperature. A signal gradient over the integration time is established for each of the pixels from the four pixel values at the two temperatures in each case and the gain being established from the difference of the signal gradients and characteristic-curve correction factors for the gain being stored.

A fragmentation warhead is provided, capable of being mounted in a carrier vehicle, the warhead having a longitudinal axis. In at least one example the warhead includes a shell that extends along the longitudinal axis. The shell includes a fixed shell portion and a fragmentation portion, and defines therebetween a cavity for accommodating therein an explosive charge. The fragmentation portion includes at least one set of serially adjacent fragments in correspondingly serially contiguous relationship in the fragmentation portion and in generally helical relationship with respect to the longitudinal axis. A corresponding carrier vehicle and a corresponding missile are also provided.

The presently disclosed subject matter includes a computerized method and system for determining miss-distance between platforms. The proposed method and system make use of an electro optic sensor (e.g. camera) mounted on one of the platforms for obtaining additional data which is used for improving the accuracy of positioning data obtained from conventional positioning devices. A navigation error is calculated where the relative position of the two platforms is converted to the camera reference frame. Once the navigation error is available, it can be used to correct a measured miss-distance.