Abstract: Methods and systems for designing, testing, and validating genome designs are described herein. A computer-implemented method includes receiving data for a known genome and a list of alleles, identifying and removing occurrences of each allele in the known genome, determining a plurality of allele choices with which to replace occurrences in the known genome, generating a plurality of alternative gene sequences for a genome design based on the known genome, applying a plurality of rules or constraints or conditions or parameters or features to each alternative gene sequence by assigning a score for each rule or constraint or condition or parameter or feature in each alternative gene sequence, resulting in scores, scoring each alternative gene sequence based on a weighted combination of the scores, and selecting at least one alternative gene sequence as the genome design based on the scoring.

Abstract: A helicopter has a fuselage, a main rotor system connected to the fuselage and configured to rotate in a rotor direction, the main rotor system comprising a retreating rotor blade side and an opposing advancing rotor blade side, and a first wing extending from the fuselage on the retreating rotor blade side. The helicopter comprises no tail rotor system and comprises no counter-rotating rotor system coaxial with the main rotor system.

Abstract: Various aspects relate to using structured messages within systems that implement instant messaging function in a distributed computing environment. In particular, structured information may be encoded and embedded in unstructured instant messages and communicated among one or more computer systems, networks, applications or other entities. In one aspect, instant messaging may be leveraged as middleware for application integration. Other aspects relate to using structured message information to perform functions in a distributed instant messaging system. For example, structured message information may be used to control the display of instant message information to a user, or may be used to control how the instant message information is distributed, processed, or otherwise handled by a receiving system, application or process. Other aspects relate to an interface for displaying information relating to a number of instant messaging conversations to a user.

Abstract: Methods and systems for synchronizing a database schema (or data structure) of a source database to a target database are disclosed. A source data structure definition is generated, including definitions of each object in the source database structure. A target database structure is generated, including definitions of each object in the source database structure. Object definitions are compared between the source database structure and the target database structure. A data definition language change instruction sequence is generated that, when executed, will modify the target database structure to correspond to the data structure definition. The change instruction sequence is executed on the target database.

Abstract: An aircraft having a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes a fuselage and an X-tiltwing that is rotatable relative to the fuselage between a vertical lift orientation and a forward thrust orientation. The X-tiltwing has oppositely disposed V-wing members each having first and second wing sections. In the vertical lift orientation, the first and second wing sections of each V-wing member are generally in the same horizontal plane. In the forward thrust orientation, the first and second wing sections of each V-wing member are generally in the same vertical plane. A distributed propulsion system is attached to the X-tiltwing such that a plurality of propulsion assemblies is attached to each wing section. A flight control system is operably associated with the distributed propulsion system to independently control each of the propulsion assemblies.

Abstract: Database schema management systems and methods. An intake engine can receive a platform-specific schema definition language and an intake template for converting the input schema to a platform-neutral schema. The intake template can define one or more translation operations required to convert from the first platform-specific schema definition language to a platform-neutral schema definition language. In embodiments, the intake engine can validate the input schema based on one or more design criteria. A repository can store platform-neutral schemas and deployment information. An output template can define one or more translation operations to convert from the platform-neutral schema definition language to a platform-specific schema definition language. A deployment engine can deploy a selected schema to a target database upon request.

Abstract: An unmanned aircraft system has a vertical takeoff and landing flight mode and a forward flight mode. The unmanned aircraft system includes an airframe, a rotor assembly rotatably coupled to the airframe and a propeller rotatably coupled to the airframe. The rotor assembly including at least two rotor blades having tip jets that are operably associated with a compressed gas power system. The propeller is operably associated with an electric power system. In the vertical takeoff and landing flight mode, compressed gas from the compressed gas power system is discharged through the tip jets to rotate the rotor assembly and generate vertical lift. In the forward flight mode, the electric power system drives the propeller to generate forward thrust and autorotation of the rotor assembly generates vertical lift.

Abstract: This invention is directed toward a surfboard made from at least two different types of foam and laminating methods. The general invention has a central core, preferably of EPS foam, and two outside panels—located either on the sides, or rails, of the blank, or above and below the central core. In a preferred embodiment, the panels are made from PU foam, and the panels are attached to the central core through a laminating substrate, which can be another type of foam or copolymer, such as TPU, or a harder material such as plastic or wood. The invention produces a blank that can be shaped into a surfboard that is both strong and flexible.

Abstract: An apparatus for testing a die can comprise a first printed circuit board (PCB), a space transformer, and a plurality of probes. The first PCB can be configured to connect to a second PCB. The space transformer can be attached to the PCB. The space transformer can include a plurality of traces. Each of the plurality of probes can be connected to one of the plurality of traces.

Abstract: A tail sitter aircraft includes a fuselage having a forward portion and an aft portion. The forward portion of the fuselage includes first and second rotor stations. A first rotor assembly is positioned proximate the first rotor station. A second rotor assembly is positioned proximate the second rotor station. A tailboom assembly extends from the aft portion of the fuselage. The tailboom assembly includes a plurality of landing members. In a vertical takeoff and landing mode of the aircraft, the first and second rotor assemblies rotate about the fuselage to provide vertical thrust. In a forward flight mode of the aircraft, the first rotor assembly rotates about the fuselage to provide forward thrust and the second rotor assembly is non-rotatable about the fuselage forming wings to provide lift.

Abstract: A portable two-wheeled self-balancing personal transport vehicle comprises a single support platform having first and second foot placement sections, one or more inertial sensors operable to provide pitch data for the platform. The first foot placement section and the second foot placement section are associated with a first wheel and a second wheel respectively controlled by a first and a second drive motor. At least one load sensor provides first load data for the first foot placement section and at least one load sensor provides second load data for the second foot placement section. Control circuitry is connected to the first and second drive motors, and operable to transmit to the first and second drive motors balancing signals for self-balancing the support platform housing in response to the pitch data, as well as one or more steering torque signals in response to the first and second load data.

Abstract: A tail sitter aircraft includes a fuselage having a forward portion and an aft portion. The forward portion of the fuselage includes first and second rotor stations. A first rotor assembly is positioned proximate the first rotor station. A second rotor assembly is positioned proximate the second rotor station. A tailboom assembly extends from the aft portion of the fuselage and includes a plurality of landing members. A pusher propeller extends from the tailboom assembly. In a vertical takeoff and landing mode, the first and second rotor assemblies rotate about the fuselage to provide vertical thrust. In a forward flight mode, rotation of the pusher propeller provides forward thrust and the first and second rotor assemblies are non-rotatable about the fuselage forming a dual wing configuration to provide lift.

Abstract: A tiltrotor aircraft has a fuselage and a wing having upper and lower surfaces with a plurality of channels extending therebetween, each with a cycloidal rotor mounted therein. At least two pylon assemblies are rotatably coupled to the wing to selectively operate the tiltrotor aircraft between helicopter and airplane flight modes. Each pylon assembly includes a mast and a proprotor assembly operable to rotate with the mast to generate thrust. At least one engine provides torque and rotational energy to the proprotor assemblies and the propulsion assemblies. Each of the cycloidal rotors has a plurality of blades that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor is operable to generate a variable thrust and a variable thrust vector, thereby providing vertical lift augmentation, roll control, yaw control and/or pitch control in the helicopter flight mode.

Abstract: A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. At least two wings are supported by the forward portion of the fuselage. A distributed propulsion system includes at least one propulsion assembly operably associated with each fixed wing and is operable to provide forward thrust during forward flight and vertical thrust during vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage and includes a plurality of rotatably mounted tail arms having control surfaces and landing members. In a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces. In a landing configuration, the tail arms are radially extended relative to the fuselage axis to form a stable ground contact base with the landing members.

Abstract: A tri-wing aircraft includes a fuselage having a longitudinally extending fuselage axis. Three wings extend generally radially outwardly from the fuselage axis and are circumferentially distributed generally uniformly about the fuselage at approximately 120-degree intervals. The wings have airfoil cross-sections including first and second surfaces having chordwise channels therebetween. A distributed propulsion system includes a plurality of propulsion assemblies. Each propulsion assembly includes a variable thrust cross-flow fan disposed within one of the chordwise channels of one of the wings. At least two variable thrust cross-flow fans are disposed within the chordwise channels of each of the wings. A flight control system is operably associated with the distributed propulsion system such that the flight control system and the distributed propulsion system are operable to generate a triaxial dynamic thrust matrix.

Abstract: A stacked motor assembly for an aircraft includes a forward motor having an exhaust port and an aft motor disposed aft of the forward motor, the aft motor having an intake port. The stacked motor assembly includes an exhaust conduit originating from the exhaust port of the forward motor and disposed at least partially around the aft motor such that exhaust from the forward motor bypasses the aft motor. The stacked motor assembly also includes an intake conduit terminating at the intake port of the aft motor and disposed at least partially around the forward motor such that intake air for the aft motor bypasses the forward motor.

Abstract: A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. A main lifting surface is supported by the forward portion of the fuselage. A propulsion system is operably associated with the main lifting surface and operable to provide thrust during forward flight, vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage. The tailboom assembly includes a plurality of rotatably mounted tail arms having control surfaces and landing members wherein, in a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces and, wherein, in a landing configuration, the tail arms are radially extended relative to one another about the fuselage axis to form a stable ground contact base with the landing members.

Abstract: In some embodiments, a rotorcraft includes a fuselage, a tailboom, a drive system and a variable thrust cross-flow fan system. The cross-flow fan system includes a cross-flow fan assembly that is mechanically coupled to a drive shaft and operable to rotate with the drive shaft about a longitudinal axis. The cross-flow fan assembly includes first and second driver plates having a plurality of blades rotatably mounted therebetween. The blades are disposed radially outwardly from the longitudinal axis and have a generally circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis. The blades are moveable between a plurality of pitch angle configurations. A control assembly is coupled to the blades. The control assembly is operable to change the pitch angle configuration of the blades to generate variable thrust at a substantially constant rotational speed of the cross-flow fan assembly.

Abstract: A portable two-wheeled self-balancing personal transport vehicle comprises a single support platform having first and second foot placement sections, one or more inertial sensors operable to provide pitch data for the platform. The first foot placement section and the second foot placement section are associated with a first wheel and a second wheel respectively controlled by a first and a second drive motor. At least one load sensor provides first load data for the first foot placement section and at least one load sensor provides second load data for the second foot placement section. Control circuitry is connected to the first and second drive motors, and operable to transmit to the first and second drive motors balancing signals for self-balancing the support platform housing in response to the pitch data, as well as one or more steering torque signals in response to the first and second load data.

Abstract: A cargo transportation system includes a cargo platform having an upper surface and a perimeter. A propulsion system is disposed about the perimeter of the cargo platform. The propulsion system includes a plurality of propulsion assemblies, each including a propulsion unit disposed within a housing defining an airflow channel having an air inlet for incoming air and an air outlet for outgoing air such that the outgoing air is operable to generate at least vertical lift. A power system disposed within the cargo platform provides energy to drive the propulsion system. A flight control system operably associated with the propulsion system and the power system controls flight operations of the cargo transportation system.