Raytheon Company

Jaime Robledo

Andrew Gamalski

Richard E Jones

Sergey Kokoulin

Joel Reyes

Karla J Zamora

Daniel B Carman

Devin Raymond

Ashik Arefin

Brendon R Holt

Jason A Dahar

Dry ice cooling systems and methods of making dry ice cooling systems are disclosed. According to embodiments, dry ice cooling systems include a compression container including compressed liquid carbon dioxide. The dry ice cooling systems include a dry ice container coupled to the compression container to receive the liquid carbon dioxide and house dry ice as it forms. The dry ice container includes a liquid coolant. Further, the dry ice cooling system includes a heat exchanger to couple a heat-generating source to the dry ice container.

Consumable dry ice cooling

Apparatus and associated methods relate to using a plurality of antennas radially distributed about a rotatable turret to sequentially scan a field of view. Each of the plurality of antennas directs an electromagnetic beam and senses its reflection along a principal direction defined by a roll position of the rotatable turret and an azimuthal beam angle. The principal directions of the antennas have a unique azimuthal beam angle relative to a boresight (i.e., axis of rotation). As the turret rotates, each of these antennas is sequentially turned on at a first roll position and off at a second roll position. This enables electromagnetic beams generated by the antennas to pan a scene both in azimuth and roll. An image processor then determines, based on the reflected signals received by the plurality of antennas, directions to and/or velocities of objects within the scanned field of view.

Rotating multi-beam antenna

A simulated payload apparatus (SPA) for testing in a flight motion system (FMS), which has a body for mounting in the FMS, and which simulates an actual payload during the FMS test. The SPA may include a plurality of adjustable weights that are mountable on and/or removable from the body to vary the mass and/or center of gravity of the SPA. The SPA may include an adjustable bracket for interfacing with a motion drive of the FMS, in which the bracket is positionable along the body to vary the moment of inertia of the SPA. The SPA may include an onboard electronic measurement device that is configured to measure a motion characteristic of the SPA and/or communicate information about the measured motion characteristic in real-time during the FMS test. The SPA may include a laser alignment for aligning the SPA relative to test equipment of the FMS.

Simulated payload apparatus for flight motion system testing

In accordance with one embodiment of the present disclosure, a method may include installing a first seal around a motor shaft. The method may also include installing a second seal around the motor shaft, wherein the second seal and the first seal may form a hydrodynamic seal when the motor shaft rotates. The method may further include installing a spacer in-between the second seal and the first seal.

System and method for re-building a pump

A system and method for extracting seized components is disclosed. The method further grasping a seized component with a gripping mechanism and securing the gripping mechanism to the seized component by turning a camlock mechanism. A force is applied to a power transfer mechanism that moves a threaded axis that is threaded through the power transfer mechanism. The method additionally includes attaching the threaded axis to the gripping mechanism, which extracts the seized component. To facilitate extraction, the method also includes generating vibrations by a vibration mechanism, which may include a vibration mechanism rotating a rotary plate about a shaft. The method may also include generating vibrations by a cam attached to the rotary plate contacting one or more spring-loaded hammers. The spring-loaded hammers may be capable of impacting a strike plate, generating vibrations.

Rotary mechanical vibration mechanism

An apparatus may comprise a lever operable to rotate a crank arm. The apparatus may further comprise a slotted member affixed to an end of the lever. The slotted member may be operable to clip around a first handle of the crank arm. The apparatus may further comprise an alignment member affixed to the lever. The alignment member may comprise a hole that receives a second handle of the crank arm. The apparatus may further comprise a third handle affixed to the lever such that a force applied to the third handle causes the lever to rotate. The rotation of the lever may cause the crank arm to rotate in a particular plane. The third handle may be offset from the particular plane.

Leverage tool for a crank assembly of a radar system

A tool for installing a threaded object includes a bit or inner implement that has a tip for engaging a head of the threaded object, and a sleeve surrounding the inner implement for securing the threaded object to the tool during the installation process. The sleeve includes plural arms at least some of which have inner lips that engage the head of the threaded object to hold the head against the tip. The inner lips are chamfered to facilitate engagement and disengagement between the sleeve and the head of the threaded object. The sleeve is able to translate to a limited extent relative to the inner implement, in order to pull back and disengage from the threaded object head as the threaded object is received into a threaded opening.

Growing community of inventors

Sahuarita, AZ, United States of America

Jaime Robledo