Bae Systems Information and Electronic Systems Integration Inc.

Bae Systems, Inc.

Schorr, David

Cleveland, Kenneth

Butland, Adam

Pietrzak, Amy

Steenson, James, H.

Borysthen-tkacz, Joseph

James H Steenson, Jr

David J Schorr

Derek P Janiak

Jeremy B Gibson

Jason H Batchelder

Kenneth D Cleveland

Amy Pietrzak

Adam G Butland

Joseph D Vasile

Joseph Borysthen-Tkacz

David M Gillespie

Joseph P Cullen

Aaron B Johnson

Matthew F Damiano

Benjamin W Brown

Stephen W Bartlett

Matthew Damiano

David Schorr

Kenneth Cleveland

Techniques to dynamically adjust the corner frequency of a high-pass filter in response to a time-domain amplitude value of an output signal, thereby preserving accuracy while promptly recovering the signal's baseline value. A system can be configured to filter frequency-domain values of an input signal based on a filtering characteristic. The filtering characteristic can be set dynamically in response to a time-domain value of an amplitude of an output signal. The filtering characteristic can comprise a corner frequency, and the system can include a high-pass filter configured to filter out frequency components at frequencies lower than the corner frequency. The system is configured to dynamically change the corner frequency from a first value to a second value, in response to the time-domain value of the amplitude crossing a threshold value. The system may dynamically change the corner frequency within a time interval after the crossing.

Method for rapid baseline recovery for irregular frequency content large dynamic range unipolar data signals

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.

Guided munition systems for detecting off-axis targets

[A system and method for dynamic autopilot control comprising providing input to a guidance and control autopilot comprising Mach and dynamic pressure; tailoring parameters of the autopilot, the parameters comprising: roll gain; a pitch/yaw gain; a pitch/yaw loop compensator frequency; a guidance filter bandwidth; a guidance filter lead compensator frequency; and a navigation gain.

Dynamic autopilot

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.

Determination of guided-munition roll orientation

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.

Laser designation verification tool

A device, system, and method for shaping the trajectory of a projectile employing a Gravity bias, Gbias. The system includes a seeker, a guidance filter, a pitch rate filter, an actuator, pitch/yaw/roll coupled aerodynamics, and lateral rate sensors. It receives roll orientation input to a guidance and control autopilot; it applies Additional Gbias to that produced by the null rate command to the lateral control loops of the guidance and control autopilot device. The lateral rate command is equal to the desired Additional Gbias divided by an estimate of the projectile velocity. The Additional Gbias is translated to a rate command and incorporated into guidance loop commands to boost an Inherent Gbias to shape the trajectory of the projectile to the target.

Gbias for rate based autopilot

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.

Automated determination of rocket configuration

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.

System and method for stores communications

An apparatus for deploying stowed control surfaces of a projectile is disclosed. The apparatus for deploying stowed control surfaces of a projectile includes a first and second hot gas generators, a first and second gas chambers, a piston wedge, a piston and a barrel. Initially, the first hot gas generator discharges a surge of hot gas into the first gas chamber. In response to the surge of hot gas being discharged into the first gas generator, the piston wedge displaces at least one of the control surfaces to break an environmental seal covering the projectile. After a predetermined amount of time has lapsed, the second hot gas generator discharges a surge of hot gas into the second gas chamber. The surge of hot gas displaces the piston and barrel for deploying the control surfaces completely.

Apparatus for deploying stowed control surfaces of a projectile

A plurality of optical transmission sources provide data communication from a transmitting module to a common detector cooperative with a receiving module, the modules being subject to relative rotation about a shared axis. The detector can be located on the shared axis, each of the sources directing a beam onto the detector regardless of relative module orientation, and/or the light can be diffused, so that it is detected regardless of source and detector placement and relative module orientations. Transmissions can be distinguished according to synchronized timing, differing optical frequencies, differing baud rates, and/or differing circular polarizations. The detector can split the light into a plurality of beams which pass through different optical filters and are thereby distinguished. Cut-off circuits can prevent failed sources from transmitting. A diffused second light source and a second plurality of detectors can provide reverse communication from the receiving module to the transmitting module.

Wireless data interface with multiple, independent transmission sources

A method for controlling autopilot roll capture of a rocket comprising adapting the start time and the rate of roll capture such that regardless of the initial rocket spin rate, the roll capture process is completed at a predetermined time.

Predictive roll capture

An accurate and rapid method for characterizing the performance of an APD and setting its operating voltage Vop to an optimal value uses an on-board LED or other pulsed light source to measure APD responses at different operating voltages Vop. An estimated breakdown voltage Vb is determined by comparing the measured responses, and the Vop is adjusted to a new value at a fixed offset from the estimated Vb. The fixed offset is selected according to ambient light conditions, including the presence or absence of light background noise, and whether the sun is partially or fully in the field of view. The method is iterated until convergence, or until a maximum number of iterations is reached. In embodiments, a plurality of APD's having a common Vop can be adjusted, and the Vop is never set below a minimum value VopBW necessary to meet timing requirements for a missile guidance system.

Avalanche photodiode operating voltage selection algorithm

An apparatus and method improves the fault tolerance of a rocket or missile guidance system which includes a resonant sensor. When improper initialization is detected, the resonant sensor is reinitialized, repeatedly if necessary, until normal operation is achieved. Improper initialization is detected by comparing data from the guidance system with pre-specified physical limits to roll, pitch, yaw, and/or other features of the flight scenario. Embodiments can also detect a fault condition due to an error signal from a 'Built-in-Test' (BIT) module. The initialization sequence initiated by the invention can be identical to the power-on sequence, or it can be a separate, reinitiating sequence. Subsequent resets are initiated as needed, for example until the burn of the rocket fuel and the associated vibrations have ceased and the resonant sensor has been successfully initialized.

Automatic re-initialization of resonant sensors in rocket and missile guidance systems

A power supply includes a power source having first and second terminals. A circuit is coupled to the source and is operable to maintain a first quantity between the terminals within a predetermined range of values until a second quantity between the terminals has a predetermined value. Such a power supply provides the ability to delay activating a load until the current that the supply can provide is at a level acceptable for proper load function.

Growing community of inventors

New Boston, NH, United States of America

James H Steenson, Jr