Abstract: A method for the at least partially automated diagnosis of aircraft gas turbine engines includes the steps of: 1) detecting actual parameter values of an aircraft gas turbine engine for several operational segments 2) determining deviations, of these actual parameter values from theoretical parameter values; and 3) determining damage pattern probabilities based on a similarity of at least one determined deviation, particularly based on a change between determined deviations, to deviation patterns of different known damage patterns.

Abstract: A method for determining the curing behavior of an adhesive- or sealant bead, the adhesive- or sealant bead being applied to a workpiece, places multiple test bodies on the adhesive- or sealant bead at different, pre-defined placement times, and deformations of the adhesive- or sealant bead, caused by the test bodies, are measured at a pre-defined end time.

Abstract: A non-conductive wire splice apparatus having a connector configured to be coupled between a first wire and a second wire. The connector having a non-conductor coupled between a first sleeve and a second sleeve. The first sleeve being attachable to the first wire. The second sleeve being attachable to the second wire opposite the first sleeve. The non-conductor being configured to electrically insulate the first wire from the second wire. An electrical current in the first wire is insulated from being conducted to the second wire.

Abstract: The present invention relates to a method for the at least partially automated diagnosis of aircraft gas turbine engines having the steps of: 1) detecting (S10) actual parameter values (NH, EGT) of an aircraft gas turbine engine for several operational segments (z1, z2, . . . ); 2) determining (S20) deviations (?NH, ?EGT), of these actual parameter values from theoretical parameter values; and 3) determining (S40) damage pattern probabilities (P(HPC), P(LPC)) based on a similarity of at least one determined deviation, particularly based on a change (?) between determined deviations (?), to deviation patterns (?NH, ?EGT) of different known damage patterns.

Abstract: A non-conductive wire splice apparatus having a connector configured to be coupled between a first wire and a second wire. The connector having a non-conductor coupled between a first sleeve and a second sleeve. The first sleeve being attachable to the first wire. The second sleeve being attachable to the second wire opposite the first sleeve. The non-conductor being configured to electrically insulate the first wire from the second wire. An electrical current in the first wire is insulated from being conducted to the second wire.

Abstract: Methods and computer program products are provided for controlling a plurality of control effectors of an aerodynamic vehicle based upon the mode shape direction of one or more structural modes excited by actuation of the control effectors. For example, control of the actuation of the control effectors may be provided to emphasize actuation of those control effectors that affect a structural mode having a mode shape direction that is substantially orthogonal to the mode shape of the structural mode. By affecting a structural mode in such a manner that the mode shape direction is substantially orthogonal to the mode shape of the structural mode, control structure interaction (CSI) is avoided without having to design a stiffer aerodynamic vehicle and without having to filter the sensor input and/or the actuator commands, unless it is otherwise desirable to do so.

Abstract: An air vehicle assembly and a corresponding method for launching an air vehicle assembly are provided, along with corresponding control systems and methods. The air vehicle assembly may include a plurality of air vehicles releasably joined to one another during a portion of the flight, such as during take-off and landing. By being releasably joined to one another, such as during take-off and landing, the air vehicles can rely upon and assist one another during the vertical take-off and landing while being designed to have a greater range and higher endurance following the transition to forward flight, either while remaining coupled to or following separation from the other air vehicles. By taking into account the states of the other air vehicles, the control system and method also permit the air vehicles of an air vehicle assembly to collaborate.

Abstract: A flightpath guidance system and method is disclosed for using moving waypoints for a curved route plan such as a Bezier curve. The actual location of a vehicle and a leading target point along the path are used to provide commanded guidance of the vehicle along the path and to correct for disturbances from the intended route. Waypoints along the path may be moving with respect to the reference frame in which the vehicle is measured. Curved flightpath guidance using moving waypoints may be used for aerial rendezvous and refueling, multiple vehicle applications such as formation flying and battlefield formation grouping, and carrier landing. Further application includes air traffic control and commercial flight guidance systems.

Abstract: Vehicle control systems and methods for sizing such systems are disclosed. In one embodiment of the invention, an actuator mechanism capability is selected, at least one operating requirement is selected, and the required number, size, and locations of a plurality of control surfaces needed to satisfy the at least one operating requirement are determined. In another embodiment, a set of control laws is selected, at least one operating requirement is selected, and the number size, and location of a plurality of control surfaces needed to satisfy the at least one operating requirement are determined.

Abstract: An air fitting with an integral check valve includes a housing having an inlet and at least one outlet, a passage extending between the inlet and the at least one outlet with a valve seat being formed in the passage adjacent the at least one outlet with a portion between the outlet and the valve having a plurality of channels separated by lands which form a guide surface for the valve as it is being forced onto the valve seat by a spring. The channels allow passage of air around the valve member with less restriction when the valve member is lifted off the valve seat.

Abstract: Apparatus and method for determining transient temperature and stress distributions in turbomachines and system components as a function of operating conditions where direct measurements on the rotating components are prevented. The apparatus includes a microprocessor which computes temperature and stress distributions in real time for components of complex shapes. The apparatus employs a memory containing a set of standard temperature distributions under particular operating conditions and the temperature stresses in the component are estimated on the basis of the closest temperature distributions in the set. The apparatus can be embodied as an on-board in-flight LCF monitor of aircraft engine rotors or as an LCF monitor of a turbomachine for power generation such as a stationary turbine generating unit.