Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: An improved door assembly has a single movable door and may have a separate movable high platform threshold. The door assembly is formed of an upper door section and a lower door section which is fixed to the upper door section. A support member may be integral with or slidably engaged with the door assembly, disposed as an angle iron fixed to the door assembly, or disposed on the side of a stairwell of a rail passenger car.

Abstract: 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).

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A system, apparatus, and method for detonating a projectile which includes receiving data by a microprocessor located in the projectile from an external ballistic computer. Calibrating a low frequency oscillator located in the projectile using an internal precision reference oscillator also located in the projectile that can withstand launch accelerations of tens of thousands of g's. Powering off the reference oscillator when calibration is complete to save energy and transmitting a detonation signal from the microprocessor to a detonation circuit located in the projectile.

Abstract: 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.

Abstract: 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.

Abstract: 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).

Abstract: 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).

Abstract: 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).

Abstract: 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.

Abstract: An improved door assembly has a single movable door and may have a separate movable high platform threshold. The door assembly is formed of an upper door section and a lower door section which is fixed to the upper door section. A support member may be integral with or slidably engaged with the door assembly, disposed as an angle iron fixed to the door assembly, or disposed on the side of a stairwell of a rail passenger car.

Abstract: 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.

Abstract: 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.

Abstract: 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.