Bae Systems Information and Electronic Systems Integration Inc.

Tracor, Inc.

Tracor Aerospace, Inc.

Other

Bae Systems Information and Electronics Systems Integration Inc.

David J Schorr

James H Steenson, Jr

Les H Richards

Jason H Batchelder

Kenneth D Cleveland

Jeremy B Gibson

Will R Grigsby

Amy Pietrzak

Somit S Mathur

Adam G Butland

Joseph Borysthen-Tkacz

J Ken Vinson

Joseph D Vasile

William C Alexander

Robert D Frey, Jr

Bradley T Sallee

Derek P Janiak

Eric M Louchard

James K Vinson

Mark J Kelley

Richie Spitsberg

Aaron B Johnson

Philip L McDuffie

Joseph McGaughey

Bill Alexander

Stephen W Bartlett

Matthew F Damiano

Edward R Coleman

Mitchell J Nord

Lex N Allen

Matthew Damiano

Aaron Johnson

Jr James H Steenson

James H Steenson Jr

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

An ordnance includes a nose cone configured to be attached to a fuze or a warhead. The nose cone, when attached or coupled to the fuze or warhead, covers the fuze and at least a portion of the warhead to provide the ordnance with an aerodynamic profile. The nose cone has a shape that improves the aerodynamic profile of the ordnance as compared to ordnance that does not include a cover over the fuze. The improved aerodynamic profile enables the ordnance to achieve a greater range (approximately 20% or more) than ordnance that does not have a separate nose cone covering the fuze.

Ordnance nose cone

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

Techniques are provided for detection, classification and tracking of surface contacts based on multispectral image data from sensors on maritime assets. An example system may include an anomaly detection circuit configured to detect an object based on anomalies in the variance of pixels of water surface image data. The system may also include an object motion tracking circuit configured to analyze motion of the object relative to water surface waves. The analysis may compensate for motion of the asset and sensors. The system may further include an object classification circuit configured to classify the object as an object of interest, based on the analyzed motion of the object, and as a threat, further based on size estimation, edge detection, surface texture analysis, and volume analysis. The range from the asset to the object may be estimated based on the relation of the object to a detected or estimated horizon line.

Detection, classification, and tracking of surface contacts for maritime assets

Techniques are provided for estimating the direction of a laser source under non-uniform illumination conditions such as laser speckle. An example system may include a detector array comprising sensors configured to detect the amplitude of the received laser signal. The sensors are disposed on the array at unique orientation angles relative to each other. The sensor size is selected based on the speckle pattern of the laser signal such that the sensors are small enough to be uniformly illuminated by the laser signal in the presence of speckle. The system also includes an amplitude ratio calculation circuit configured to calculate ratios of the amplitudes between each of two sensors of one or more pairs of sensors. The system further includes an angle of arrival calculation circuit configured to estimate the direction of the source of the laser signal based on the calculated ratios and the orientation angles of the sensors.

Laser source direction finding under non-uniform illumination conditions

A system for calculating airspeed and dynamic pressure comprises a system body, an internal accelerometer, located within the system body, an internal pressure sensor, located in the system body, the internal pressure sensor being not hermetically sealed within the system body and capable of measuring the static pressure of the ambient atmosphere, and a processor in reception of the internal accelerometer, and the internal pressure sensor, capable of calculating Mach number via an axial acceleration, and capable of calculating a dynamic pressure and a true airspeed via the Mach number.

Method and system of measurement of mach and dynamic pressure using internal sensors

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 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

The invention provides a method and apparatus for correcting for gain changes in detectors in a guided vehicle. In one version of the invention, an on board light source is used to generate a reference set of detector gains, which are stored in computer memory. The on board light source is then pulsed at subsequent times and the signals generated by the detectors are compared to the reference set of detector gains to determine whether any gains have changed.

Growing community of inventors

Austin, TX, United States of America

David J Schorr