A fuzzy logic controller for controlling towed objects includes comprises a winch controller to control extension or retraction of a tow cable based on a control signal. A fuzzy logic controller controls a speed at which the tow cable is extended or retracted. The fuzzy logic controller includes an altitude controller storing a membership function defining ranges for a delta altitude variable and determines an altitude control signal based on the range for the measured delta altitude variable. A gain controller stores respective membership functions defining ranges for speed, heading rate, and cable length variables and determines a gain control signal based on the ranges for the determined speed, heading rate, and cable length variables. A command controller determines the control signal based on the gain control signal and the altitude control signal.
G05B 15/02 - Systems controlled by a computer electric
G05B 13/02 - Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric
2.
Graphical conversion between test program languages
A parser may be graphically modified without needing to directly alter the parser software and may be graphically modified to adjust for extensibility of the source test program language. The parser may be graphically modify to adjust for extensibility of the destination test program language and to translate a new text based test program language not inherently built into the parser.
A system, method and computer program product provides for estimating the range of a target. An acquisition window of an imaging device is adjusted to fit a target at an unknown range in response to a user input. An angle subtended by the largest dimension of the target viewed from the acquisition window is determined. The range of the target is estimated from a largest dimension of the target and the angle subtended by the largest dimension of the target. The device may be a man-portable aircraft survivability equipment (ASE) system trainer (MAST), or any simulator simulating a man-portable air defense system (MANPADS).
G01C 3/22 - Measuring distances in line of sight; Optical rangefinders using a parallactic triangle with variable angles and a base of fixed length at, near, or formed by, the object
4.
Ballistic sealing, component retention, and projectile launch control for an ammunition cartridge assembly
A telescoped ammunition cartridge assembly including a case having a front end and a base end positioned along a longitudinal axis. A projectile is positioned along the longitudinal axis towards the front end of the case. An endcap is coupled to the front end of the case and is adapted to retain the projectile entirely within the case. A primer is positioned along the longitudinal axis towards the base end of the case. A primer support is coupled to the base end of the case and is adapted to support the primer within the case. The cartridge assembly includes at least one obturating lip seal to seal at least one of the endcap or the primer support to the case.
A high fidelity simulation of Doppler that may exactly replicate the phenomenology of the physical world. Compute the linear (Line of sight) kinematics (Slant Range, Radial Velocity, and Radial Acceleration) for each of a multiplicity of emitter-receiver pairs in accordance with exact 3D vector mathematics. Smoothly interpolate the linear kinematic parameters to produce accurate instantaneous values of these parameters at sample rates sufficient to produce negligible error effects in the presence of realistic aircraft maneuvers. Calculate the Doppler frequency, in accordance with well known physics, from the emitter carrier wavelength and a high sample rate. Calculate the Doppler effect as a differential phase (Doppler frequency×sample time) and apply the effect as incremental phase shifts to the carrier signal.
A system and method for correlating first pulsed signals with second pulsed signals includes a first receiving unit, a second receiving unit and a correlation device. The first receiving unit is disposed to receive from a first device one or more first pulsed signals. The first device may include a plurality of pulsed radio frequency source under test signal sources. The second receiving unit is disposed to receive from a second device one or more second pulsed signals. The second device may include a local oscillator pulsed signal source. The correlation device can correlate the first pulsed signals with the second pulsed signals to align a timing characteristic of the first pulsed signals to the equivalent timing characteristic of the second pulsed signals.
An apparatus for the recovery of an aircraft includes a capture device and first and second pole pairs. The first pole pair includes first top and bottom poles respectively placed near first top and bottom portions of the capture device. The first pole pair is configured to move from a first position, in which the pole pair holds the capture device in an open position to capture the aircraft, to a second position, in which the pole pair holds the capture device in a closed position to contain the captured aircraft after impact of the aircraft on the capture device. The second pole pair includes second top and bottom poles respectively placed near second top and bottom portions of the capture device. The second pole pair is also configured to move from the first position to the second position. Further, energy elements are coupled on one end to a respective top or bottom portion of the capture device and on another end to a respective top or bottom pole. The energy elements are disposed to absorb the force of the impact of the aircraft.
A method for using a “B” channel of a dual channel measurement receiver as a transfer standard for power measurement, which may include, in an exemplary embodiment, correlating a measurement made with an “A” channel of the dual channel measurement receiver to a measurement made with an RF Power Meter on one RF signal source, so that readings from the “A” channel are aligned to the RF Power Meter; aligning the “B” Channel to the “A” Channel, once the “A” channel has been aligned to read the same as the RF Power Meter; and using the “B” Channel as a transfer standard to measure all remaining RF signal sources in the system.
An apparatus for registering time and location of a weapon firing of a weapon. The apparatus includes a microcontroller, a pressure sensor located in proximately is provided to the weapon and adapted to determine pressure data based on air pressure in proximity to the weapon and provide the pressure data to a microcontroller, an accelerometer located in proximity to the weapon and adapted to determine acceleration data based on movement of the weapon and provide the acceleration data to the microcontroller; a time device adapted to keep time and provide the time to the microcontroller; a location sensor located in proximity to the weapon and adapted to determine a location of the weapon and provide the location of the weapon to the microcontroller; and a memory coupled to the microcontroller.
An exemplary embodiment, the present invention sets forth a method for correlating at least one weapon firing event to at least one scoring event. The method comprising: receiving information relating to a first scoring event; receiving information relating to a first weapon firing event; calculating an angle between a reference line, extending from location of the first weapon event to the location of the first scoring event, and the reference direction at the first computing device; comparing the time of the first scoring event to the time of the weapon firing event at the first computing device; comparing the angle of incidence for the projectile to the calculated angle at the first computing device; and identifying whether the weapon firing event and the scoring event are an unambiguous, one-to-one pairings at the first computing device.
An exemplary embodiment of the present invention sets forth an apparatus for registering a scoring event. The apparatus includes a target having a surface; a sensor, positioned in proximity to the target, adapted to detect the occurrence of a scoring event caused by the presence of a projectile in the scoring area and to determine a trajectory of the projectile; a time tracking device adapted to keep track of time of the scoring event; a location sensing device adapted to identify a location of the apparatus; a true north detection device adapted to detect the direction of true north with respect to the surface of the target; and a controller, coupled to the sensor and the true north detection device.
G01B 17/00 - Measuring arrangements characterised by the use of infrasonic, sonic, or ultrasonic vibrations
G01H 17/00 - Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves, not provided for in the other groups of this subclass
G01P 13/00 - Indicating or recording presence or absence of movement; Indicating or recording of direction of movement
G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H)
A method, and corresponding system, apparatus, and computer program product for automated collection and correlation for tactical information includes identifying an entity in imagery based on a field of view of the imagery using a processor, creating a relationship between the imagery and the entity, and storing the relationship in a database.
A system and device that provides for the retention of a sensor shield for a sensor such as a microphone, hydrometer, chemical sensor, or other detector. This invention provides for the quick attachment and release of a reduced visibility and reduced bulk shield retention assembly. In a battlefield environment, a smaller profile sensor shield presents less visibility as a prospective target of interest to enemy forces. Also, the sensor shield may be readily replaced without the use of any tools. The snap-lock feature provides a positive means for holding, for example, a windscreen in its respective position, requiring reasonable, but yet not objectionable force to install and remove the windscreen from the sensor's mounting shaft. Furthermore, the snap-lock feature, when engaged, may provide positive location of the sensor shield's sweet spot by maintaining a slight air space between the sensor shield and the sensor, and thereby precluding direct physical contact.
A method for characterizing the effect of each step attenuator state, on phase and amplitude, which may include in an exemplary embodiment: activating each step attenuator state as the sole contributor to attenuation, and measuring at least one of a step attenuator amplitude contribution (SAAC) and/or a step attenuator phase contribution (SAPC).
Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto; and a netting disposed within the fuel bladder and disposed to prevent collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV).
Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto; and a spiral tubing disposed within the fuel bladder and disposed to prevent collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV).
A method for using a “B” channel of a dual channel measurement receiver as a transfer standard for power measurement, which may include in an exemplary embodiment: correlating measurements made with an “A” channel to measurements made with an RF Power Meter on one RF signal source, so that readings from the “A” channel are aligned to the RF Power Meter; aligning the “B” Channel to the “A” Channel (Transfer alignment of Channel B to the RF Power Meter), once the “A” channel has been aligned to read the same as the RF Power Meter; and using the “B” Channel as a transfer standard to measure all remaining RF signal sources in the system, on a time-line much faster than may be accomplished using a power meter.
Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto. The fuel bladder may include an embossed pattern disposed to prevent a vacuum being formed by the collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV).
An aircraft launcher includes a base frame, a first sliding frame that slides with respect to the base frame, a second sliding frame that slides with respect to the first sliding frame, an aircraft support located on the second sliding frame, and a drive apparatus adapted to slide at least one of the first sliding frame and the second sliding frame with respect to the base frame.
A shock tube apparatus may include a plenum to hold a volume of gas. The plenum may include a hollow chamber having a first end and a second end located opposite one another along a longitudinal axis, the first end of the chamber defining a shock egress opening. A valve assembly may be positioned at the first end of the chamber to seal the shock egress opening. A piston may be positioned within a recess located at the second end of the chamber. The piston may separate a first volume located between the piston and the first end of the chamber from a smaller second volume located between the piston and the second end of the chamber. A tension supporting rod may connect the valve assembly to the piston. A release valve may be in fluid connection with the second volume and a switch may be operable to open the release valve to release gas from the second volume and trigger opening of the valve assembly to generate a shock wave through the shock egress opening.
A method of providing an integrated approach to automated system alignment is set forth, which may include in an exemplary embodiment: providing amplifier compression alignment, (which may include characterizing and/or compensating for a parasitic effect); providing continuous internal alignment of phase and amplitude of a synthetic stimulus instrument (SSI) output signal; providing external measurement port alignment; and providing transfer alignment of internal measurement paths. According to another exemplary embodiment, a receiver apparatus may include: a dual-channel coherent measurement receiver which may include at least one internal channel operative to measure time-division-multiplexed (TDM) feedback signals from each signal source of a synthetic stimulus instrument (SSI); and at least one external channel operative to make direct measurement at an external alignment port output.
A fuel pickup includes a fuel pickup tube having a plurality of holes for receiving fuel from inside a fuel container; and a wicking material enveloping at least one of the plurality of holes. Aircraft fuel systems including a fuel pickup comprising a wicking material are also disclosed.
A vent-on-demand fuel sump and vehicle fuel system having such a fuel sump are provided. The fuel sump may include a pressurized vessel and at least two sensors configured to detect a level of fuel within the vessel. A valve coupled to the vessel may be configured to release air and/or fuel vapor to the atmosphere. The fuel sump may also include a programmable electronic controller configured to modulate the valve between a closed position and an open position based on signals received from the sensors corresponding to the fuel level. The valve may be configured to remain in the closed position until the fuel level drops below a predetermined level and the controller sends a signal to open the valve to release air and/or fuel vapor from the vessel into the atmosphere. The vehicle fuel system having such a fuel sump may include a fuel container and an engine having an intake. The pressurized vessel of the fuel sump may include a fuel inlet coupled to the fuel container and a fuel outlet coupled to the engine intake.
F02M 37/20 - Apparatus or systems for feeding liquid fuel from storage containers to carburettors or fuel-injection apparatus; Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines characterised by means for preventing vapour lock
A portable unmanned air vehicle and launcher system that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.
A method for generating a synthesized waveform from a desired arbitrary waveform via a convolution processor includes: providing a data stream input signal to the convolution processor including an extended duration impulse signal; computing one or more filter coefficients of the convolution processor; and generating the synthesized waveform substantially similar to the desired arbitrary waveform using the filter coefficients. The convolution processor may be a finite impulse response (FIR) filter. The convolution processor may perform a convolution upon the extended duration impulse signal, where: the extended duration impulse signal is successively delayed via one or more taps and the output of each tap is multiplied by a filter coefficient corresponding to a delay; and the summation of the products of tap outputs and filter coefficients is the desired arbitrary waveform.
G01S 7/02 - RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES - Details of systems according to groups , , of systems according to group
H03B 21/02 - Generation of oscillations by combining unmodulated signals of different frequencies by beating unmodulated signals of different frequencies by plural beating, i.e. for frequency synthesis
A switch mechanism is provided that has a tubular enclosure; a contact pin electrically insulated from the tubular enclosure; a g-weight positioned inside the tubular enclosure and movable from an open position to a closed position; and a transparent closure that encloses one end of the tubular enclosure. The g-weight is in electrical contact with the contact pin and the tubular enclosure when the g-weight is in the closed position, such that a continuous electrical path exists from the contact pin to the tubular enclosure. The g-weight is for moving from the open position to the closed position when the switch mechanism is subjected to an acceleration greater than a threshold acceleration. The g-weight is visible through the transparent closure such that the position of the g-weight can be determined without removing the transparent closure from the tubular enclosure.
F42C 15/24 - Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by inertia means
27.
Method and system for eliminating VSWR errors in phase and amplitude measurements
A method and system for canceling VSWR effects is provided. The exemplary method includes taking multiple measurements of parameters of a signal with a phase of the microwave signal shifted for each measurement; and processing the measured parameters to eliminate VSWR effects and determine the true magnitude and phase of the signal.
H04B 15/00 - Suppression or limitation of noise or interference
G01R 29/26 - Measuring noise figure; Measuring signal-to-noise ratio
G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H)
28.
Angular encapsulation of tandem stacked printed circuit boards
A method is provided for making an encapsulated stack of circuit boards. The method includes assembling the stack of circuit boards from a plurality of circuit boards, the circuit boards being spaced apart from each other; inserting the stack into an internal volume of a shell, the shell having a first end and a second end opposite the first end, an input orifice adjacent the first end, and an output orifice adjacent the second end and on a side opposite the input orifice; positioning the shell such that the input orifice is at a lowest point of any part of the internal volume of the shell, and such that the output orifice is at a highest point of any part of the internal volume of the shell; angling the shell relative to horizontal; and injecting an encapsulating compound into the input orifice to fill the internal volume of the shell with the encapsulating compound.
H01R 43/00 - Apparatus or processes specially adapted for manufacturing, assembling, maintaining, or repairing of line connectors or current collectors or for joining electric conductors
H05K 13/00 - Apparatus or processes specially adapted for manufacturing or adjusting assemblages of electric components
H05K 3/36 - Assembling printed circuits with other printed circuits
H05K 3/30 - Assembling printed circuits with electric components, e.g. with resistor
B28B 1/00 - Producing shaped articles from the material
B32B 15/00 - Layered products essentially comprising metal
29.
System and method for controlling and communicating with a vehicle
Embodiments of the present invention provide a software core controller for facilitating communication between a UAV control system, a UAV, and other peripheral devices used to control or to determine the status of the UAV. Different UAVs, control systems, and peripheral devices may require that data be transmitted and received according to their own particular specifications, such as a particular data rate and a particular format. The software core controller may be configurable to interface with these devices using the devices' interfaces. The interfaces may be specified by the devices' interface control documents (ICDs). The ICDs may be used to configure the software core controller upon initialization. The software core controller may asynchronously receive and provide data at the data rate specified in the various ICDs. The software core controller may support a plurality of different physical interfaces in order to communicate with different control systems, UAVs, and peripheral devices.
A system and method to generate a trigger signal based on a real-time adaptive threshold. The system may include a microphone to receive an audio signal, a device to generate a trigger signal based on a real-time adaptive threshold coupled to the microphone to form an adaptive threshold and generate a trigger signal if a magnitude of the audio signal is greater than a magnitude of the adaptive threshold. The system may also include a waveform capture module coupled to the microphone to receive the audio signal and convert the audio signal into a series of waveform packets and a waveform analysis processor to extract characteristics from the waveform packets.
A phase persistent agile signal source method, apparatus, and/or computer program product provides a direct digital synthesizer (DDS) clock rate, provides a frequency tuning word (FTW) for a desired output frequency, provides a DDS update for a desired DDS update rate, provides an equivalent frequency least significant bit (LSB) for the desired DDS update rate, provides a current phase of an LSB accumulator, and generates a coherent phase of the desired output frequency based on the DDS clock rate, FTW, DDS update rate to the DDS, equivalent LSB for the desired DDS update rate, and current phase of the LSB accumulator. The coherent phase can be the fraction portion of the result obtained from the multiplication of the FTW and the current phase of the LSB accumulator.
A launcher includes a plurality of launch tubes for stowing and launching a plurality of air vehicles. A central air manifold is operatively connected to an air storage tank; a first launch tube air manifold is operatively connected to a first group of the launch tubes and operatively connected to the central air manifold. The first launch tube air manifold has a separate port corresponding to each launch tube of the first group of launch tubes. A release valve mechanism is removably mounted in one of the ports of the first launch tube air manifold, the release valve mechanism controlling the passage of launch air between the first launch tube air manifold and the launch tube corresponding to the port in which the release valve mechanism is mounted. A plug is removably mounted in each of the ports not occupied by the release valve mechanism.
A portable unmanned air vehicle and launcher system including a foldable unmanned air vehicle with a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.
patents
