Abstract: A system for and method of indicating an angle of attack of an aircraft is provided. The system utilizes measurements from existing aircraft sensors so that a dedicated angle of attack sensor is not required. The system enables and benefits from a unique method that includes performing standard flight operations during a calibration flight. The system does not need any aerodynamic model of the aircraft because it utilizes information from the calibration flight to develop an estimated aerodynamic model of the specific airplane. The system utilizes the aerodynamic model and other information to estimate an angle of attack of the aircraft during flight. Finally, the system utilizes additional information to indicate the estimated angle of attack of the aircraft relative to an optimum angle of attack for the aircraft and/or a critical angle of attack of the aircraft. The system further enables recalibration, so as to accommodate aircraft aerodynamic modifications.

Abstract: A system for and method of indicating an angle of attack of an aircraft is provided. The system utilizes measurements from existing aircraft sensors so that a dedicated angle of attack sensor is not required. The system enables and benefits from a unique method that includes performing standard flight operations during a calibration flight. The system does not need any aerodynamic model of the aircraft because it utilizes information from the calibration flight to develop an estimated aerodynamic model of the specific airplane. The system utilizes the aerodynamic model and other information to estimate an angle of attack of the aircraft during flight. Finally, the system utilizes additional information to indicate the estimated angle of attack of the aircraft relative to an optimum angle of attack for the aircraft and/or a critical angle of attack of the aircraft. The system further enables recalibration, so as to accommodate aircraft aerodynamic modifications.

Abstract: A system for and method of indicating an angle of attack of an aircraft is provided. The system utilizes measurements from existing aircraft sensors so that a dedicated angle of attack sensor is not required. The system enables and benefits from a unique method that includes performing standard flight operations during a calibration flight. The system does not need any aerodynamic model of the aircraft because it utilizes information from the calibration flight to develop an estimated aerodynamic model of the specific airplane. The system utilizes the aerodynamic model and other information to estimate an angle of attack of the aircraft during flight. Finally, the system utilizes additional information to indicate the estimated angle of attack of the aircraft relative to an optimum angle of attack for the aircraft and/or a critical angle of attack of the aircraft. The system further enables recalibration, so as to accommodate aircraft aerodynamic modifications.

Abstract: A system for and method of indicating an angle of attack of an aircraft is provided. The system utilizes measurements from existing aircraft sensors so that a dedicated angle of attack sensor is not required. The system enables and benefits from a unique method that includes performing standard flight operations during a calibration flight. The system does not need any aerodynamic model of the aircraft because it utilizes information from the calibration flight to develop an estimated aerodynamic model of the specific airplane. The system utilizes the aerodynamic model and other information to estimate an angle of attack of the aircraft during flight. Finally, the system utilizes additional information to indicate the estimated angle of attack of the aircraft relative to an optimum angle of attack for the aircraft and/or a critical angle of attack of the aircraft. The system further enables recalibration, so as to accommodate aircraft aerodynamic modifications.

Abstract: A system for and method of indicating an angle of attack of an aircraft is provided. The system utilizes measurements from existing aircraft sensors so that a dedicated angle of attack sensor is not required. The system enables and benefits from a unique method that includes performing standard flight operations during a calibration flight. The system does not need any aerodynamic model of the aircraft because it utilizes information from the calibration flight to develop an estimated aerodynamic model of the specific airplane. The system utilizes the aerodynamic model and other information to estimate an angle of attack of the aircraft during flight. Finally, the system utilizes additional information to indicate the estimated angle of attack of the aircraft relative to an optimum angle of attack for the aircraft and/or a critical angle of attack of the aircraft. The system further enables recalibration, so as to accommodate aircraft aerodynamic modifications.

Abstract: A system for and method of indicating an angle of attack of an aircraft is provided. The system utilizes measurements from existing aircraft sensors so that a dedicated angle of attack sensor is not required. The system enables and benefits from a unique method that includes performing standard flight operations during a calibration flight. The system does not need any aerodynamic model of the aircraft because it utilizes information from the calibration flight to develop an estimated aerodynamic model of the specific airplane. The system utilizes the aerodynamic model and other information to estimate an angle of attack of the aircraft during flight. Finally, the system utilizes additional information to indicate the estimated angle of attack of the aircraft relative to an optimum angle of attack for the aircraft and/or a critical angle of attack of the aircraft. The system further enables recalibration, so as to accommodate aircraft aerodynamic modifications.

Abstract: A system for supporting a frame including a frame, a support, a mechanism rigidly connected to the frame, and movably connected to the support, and a linkage system comprising a first linkage member connected to the frame, a second linkage member pivotally connected to a structure and pivotally connected to the first linkage member.

Abstract: An enterprise software gateway, or interface, operable to remotely facilitate, by transparently performing protocol conversion and managing communication, access to a host system (22), such as a mainframe legacy system, by a client application or device (24), including software applications and input/output (I/O) devices. A viewer (28) is provided to allow for remote monitoring of interactions, including communication, between the host (22) and client (24), and to allow for remote configuration and control of the software gateway, thereby facilitating problem diagnosis and solution.

Abstract: A liquid-cooled welding torch assembly for use in robotic welding that includes a body tube with a set of male connectors, the body tube guiding an electrode, and a flow of coolant to a welding tip. A supply cable adapter including a set of female connectors corresponding to the set of male connectors. At least one of the male connectors includes a rigid tube with a plurality of axially compressible and radially expandable sealing members coaxially and slidably disposed about the rigid tube, whereby the plurality of axially compressible and radially expandable sealing members expand to create a seal between the at least one of the male connectors and a corresponding one of the set of female connectors.

Abstract: An improved robotic welding torch includes a conductive inner body tube with first and second receiving areas for receiving a rear housing retaining device and a robotic mount retaining device. A removable robotic mount is slidably positioned over the conductive inner body tube and is preferably held in a fixed axial position by the robotic mount retaining device on one end and a rear housing on the other end. The robotic mount may be replaced with another robotic mount of a desired diameter without dismantling the entire robotic torch assembly. The robotic welding torch may be assembled with an integrated robotic mounting arm in place of the robotic mount so that the torch assembly may be attached directly to a collision sensor on a welding robot.

Abstract: An improved automatic MIG welding torch assembly for use in automated welding environments includes a locking feature to provide an anti-rotational fit between a power adapter and a conductive inner body tube of a welding torch. The conductive inner body tube has a hollow body and a hexagonal shaped external circumference extending along at least a portion of the body tube. An outer tube for use in an automatic MIG welding assembly has a hollow body with at least one end having a polygonal cross-section. A pitch rack is detachably connected to the outer tube with at least two non-threaded fasteners. The outer body tube may also include a smoke exhaust integrally connected to the tube. Improved methods for assembling an automatic MIG welding torch and manufacturing the integral smoke exhaust are also provided.

Abstract: An apparatus for welding a workpiece comprises a body tube having a tapered portion defining a first angle, and an end fitting releasably connectable with the body tube and having a tapered portion defining a second angle. The tapered portion of the body tube is releasably connectable with the tapered portion of the end fitting. The first angle differs from the second angle by a distance sufficient for facilitating manual separation of the tapered portion of the body tube from the tapered portion of the end fitting. A liner has a first portion disposed within the end fitting and a second portion disposed within the body tube. A connection member operatively releasably connects the first portion of the liner with the second portion of the liner. A member is disposed on the body tube or the end fitting for releasably connecting the body tube to the end fitting. A positive stop member is formed the body tube or the end fitting for positively retaining the member on the body tube or the end fitting.