Raytheon Company

Hughes Aircraft Company

Hughes Electronics Corporation

Michael L Wells

Richard J Sand

John A Tyson

Thomas E Jenkins

Eric B Sutton

John D Isker

Daniel P Brown

Hongthu K Nguyen

George L Gaskell

Richrad J Sand

Jane L Pauwels

Glenn S Higa

Carl P Chaplin

Melvin A Olson

An accelerometer module for measuring acceleration in a stabilized platform system includes a power supply configured to accept an input AC reference signal and to generate a regulated DC signal and a reference signal in phase with the input AC reference signal; an accelerometer configured to receive the regulated DC signal from said power supply and to generate an output signal in response to an external force acting on the accelerometer module and an analog multiplier unit configured to receive the output signal from the accelerometer and the reference signal from the power supply, and to modulate the reference signal with the output signal so as to output a modulated accelerometer signal. A method for servicing a stabilized platform system comprising is also provided.

Carrier modulating accelerometer

A method of mapping a first array to a second array is useful where (1) each of the arrays has pixels in sequential columns and rows and the first array has sequential integers identifying each row of pixels, (2) sequential integers identify each column of pixels, and a numerical value is associated with each pixel, (3) the first and second arrays have (or can be made to have) a one to one pairing between columns of the first and second arrays, and (4) groups of four unique pixels in the same column of the first array are paired one to one with a pixel in the paired column of the second array. The method includes the steps of, for each column in the first array, selecting the values associated with the pixels in four sequential odd numbered rows to form an odd group of four unique pixels, combining the values associated with the pixels in the first three odd numbered rows of the odd group to form an odd combined value, and mapping the odd combined value to the pixel in the column and row of the second array with which the odd group is paired, and thereafter selecting the values associated with the pixels in four even numbered rows to form an even group of four unique pixels, combining the values associated with pixels in the last three rows of the even group to form an even combined value, and mapping the even combined value to the pixel in column and row of the second array with which the even group is paired.

Modern thermal sensor upgrade for existing missile system

The need in the art is addressed by the improved missile fire control system of the present invention. In the illustrative embodiment, the inventive system is adapted for use with TOW missile systems and includes a telescope cluster assembly () for generating target position signals (). A digital error detector (') receives and processes target position signals () from the telescope cluster assembly (). The processed signals () are then fed to a stabilization control amplifier (), where a microcontroller () steps through a set of instructions eliminate angular noise from the target position signals (). The stabilization control amplifier () subsequently provides feedback to the telescope cluster assembly () for adjusting the line-of-sight in the telescope cluster assembly (). Software instructions for the microcontroller () and constant reference data are stored in the microcontroller memory (not shown). An erasable programmable logic device () is used to output discreet signals for controlling mirror positioning. The inventive set of instructions includes sampling azimuth and elevation error signals (); calculating the average of said azimuth and elevation error signals (); performing a comparison of the average to a specified boresight limit (); performing calculations on the averages in response to information received from the output of the comparison for determining motor runtimes (); and repeating the above steps as necessary for obtaining azimuth and elevation signals within a specified limit.

Missile fire control system

An adjustable fixture for mounting any of a plurality of weapon sets to an aircraft includes a bracket and lugs that are adjustably mechanically coupled to the bracket. The fixture may be adjusted once, to achieve proper orientation relative to the aircraft for boresighting, and may thereafter allow switching of weapon sets, either of the same type or of different types, without a need for re-boresighting. Quick-release fasteners, such as quick-release pins, may be used to couple the weapon sets to the fixture, to allow for easy and rapid change of weapon stores. The fixture may include one or more adapters used to allow various kinds of weapon sets to be coupled to the bracket.

Fixture for mounting weapons, and method of using

A system ( ) for tracking a missile ( ) in flight, the missile ( ) having an optical beacon generator ( ) that outputs a modulated signal ( ) having a predetermined frequency, including an optical system ( ) for transmitting image data along an optical path ( ) onto an array of detectors ( ), such that each detector in the array ( ) receives substantially simultaneously the image data from the optical system ( ). The system ( ) further includes means for processing (46) the image data transmitted onto the array of detectors ( ) in order to locate the optical beacon ( ).

Solid state modulated beacon tracking system

A coordinate transformation apparatus (,) in an aircraft-based missile guidance and tracking system for adjusting aircraft and missile position signals for a roll angle about the line of sight in the guidance and tracking system sight unit (,) caused by roll of the aircraft subsequent to firing of the missile. The apparatus (,) incorporates analog to digital converter means (,), (,), (,), (,) and (,) to convert the analog aircraft and missile position signals to digital signals for input into a microprocessor (,). The microprocessor (,) computes the roll angle as well as a change in roll angle over time around the line of sight of the sight unit (,) and subsequently adjusts the digital signals to compensate for the computed roll angle and change in roll angle. Digital to analog converter means (,), (,) and (,) convert adjusted digital signals to analog signals and output the adjusted analog signals for computation of missile guidance signals by the system.

Coordinate transformation system

An error detector apparatus (42) producing a signal used in the computation of a missile guidance signal in an aircraft-based missile guidance and tracking system. The error detector apparatus (42) incorporates means (146), (148), (150), (152), and (154) for producing a first envelope signal from a tracking signal emitted by a missile. The envelope signal is then converted, along with a reference signal, to a digital signal by an analog to digital converter (158). A microcontroller (168) calculates an error correction signal from the digital signals. A digital to analog converter (160) converts the digital error correction signal to an analog error correction signal and outputs the analog error correction signal to the system for use in computing a missile guidance signal.

Error detector apparatus with digital coordinate transformation

A closed-loop missile tracking system (10) employs a missile (12) with a thermal beacon (22) and an optical beacon (24). A target designator (40) defines a boresight from a missile firing location, such as an aircraft, to a target. The closed-loop missile tracking system (10) employs a first tracker (48) and a second tracker (64) with a forward looking infrared (FLIR) sensor (52) to track the displacement of the optical beacon (22) and thermal beacon (24) from the boresight. The first tracker (48) generates a first set of azimuth and elevation error signals. The second tracker (64) further includes a video demultiplexing interface (70) which transforms serial multiplexed video signals, which are output by the FLIR sensor (52) and contain a field with M rows and L columns of pixels, into a demultiplexed parallel video signal. A video thermal tracker (VTT) (58) selects the N adjacent horizontal rows of pixels and generates a second set of azimuth and elevation error signals therefrom. The VTT (58) selects at least one of the first set of error signals, the second set or a combination thereof to guide the missile (12).

Missile tracking system with a thermal track link

A missile launch safety enhancement apparatus (135) for inhibiting the launch sequence of a missile launched from an aircraft-based or land vehicle-based missile launch system. The apparatus (135) incorporates means for producing a prefire signal (102a). The prefire signal produced is then compared to a reference signal level by comparing means (167). If the prefire signal is not below the reference signal level by a predetermined amount, interrupting means (216, 240) inhibits the firing sequence of the missile and thus prevents the missile from being launched. If the prefire signal is below the reference signal level by a predetermined amount indicating proper current drawn by the circuit, the firing sequence is not inhibited, and the missile is launched.

Missile launch safety enhancement apparatus

A drive system comprising an integrated gearhead motor system that produces relatively high torque output with minimal backlash. The present invention uses two axially mounted electric or air motors and gearhead assemblies integrated into a single unit. The two motor and gearhead assemblies are connected to concentric output drive shafts, and each output shaft mates to a respective gear of a split gear assembly. The split gear assembly is coupled to a drive shaft of a device that is to be driven by the system. A tachometer is coupled between the first motor and a position sensor is coupled to the drive shaft of the device that is to be driven. The tachometer and position sensor are coupled to a controller that is used to control the respective torques provided by the two motors in response to rate and position signals provided thereby. By controlling the relative amount of torque provided by the two motors, the split gear assembly removes the backlash from the gearheads and gear interfaces to the drive shaft of the device that is to be driven. The present invention incorporates the two motors and two gearhead assemblies into a single assembly, reducing weight and space requirements. The design of the present invention also permits retrofitting of the drive system into existing single motor drive systems.

Growing community of inventors

Hawthorne, CA, United States of America

Michael L Wells