Abstract: An improved aircraft design to harness advantages of vertical or short-takeoff and landings (V/STOL) and efficient horizontal flight. Configuration improves aircraft flight stability and efficiency in flight profiles: (1.) vertical flight; (2.) transition to and from horizontal flight and; (3.) horizontal flight on wings. The aircraft is capable of stable flight at any airspeed from hover to its maximum designed speed. It has the possibility of a controlled emergency landing using autorotation or, wings or, a combination of the two. Aircraft design includes: multiple thrust sources and, wings free to rotate on a spanwise axis. Wing rotation is independent—not coupled—with either the fuselage or, the thrust sources. Wing configurations include single, tandem or, multiple sets. Wings are coupled each other such that rotation induced in one wing affects rotation in all wings. Thrust sources are directed vertically during hover and some degree forward of vertical for horizontal flight.

Abstract: A bluff body adaptive wake reduction system includes a series of fairings mounted to outer surfaces of the aft end of the road vehicle. The fairings are streamlined in geometry with an outer surface, a partially hollow core, and with a rear end surface curved such that left and right hand sides are convergent behind the vehicle. The fairings are coupled to at least one ram air inlet and also include at least one blown slot positioned on the rear end of the fairings enabling air flow to exit the fairings tangent to the rear end surface of the fairings. Air flow enters the system through the ram air inlets and exits through the blown slots. Air flow exiting the blown slots promotes flow traveling over the outer surface to remain attached to the outer surface and thus to the rear end surface. The rear end surface then deflects air flow to follow a convergent trajectory behind the vehicle in such a fashion as to reduce the size of the wake, and as a result reduce the aerodynamic drag.

Abstract: A system and method for achieving vertical navigation by using a satellite based navigation system exemplified by a GPS system and implementing the vertical navigation features in an autopilot unit interfaced to the satellite based navigation system. The autopilot reads waypoint information output from the satellite navigation system and receives VNAV altitudes and other commands from the pilot. The autopilot then performs VNAV calculations and guidance in accordance with the VNAV program. VNAV setup and progressive status are displayed on an economical small screen autopilot display. Modes are disclosed for exemplary GPS direct to waypoint VNAV, waypoint transition VNAV, multiple waypoint VNAV and other VNAV modes. Safety limits may be imposed on the VNAV program.

Abstract: An aircraft includes a housing and a powerplant coupled to the housing and configured to rotate a drive shaft around its longitudinal axis. The aircraft may include at least one lift fan assembly coupled to its housing and including a gearbox and at least one lift fan. The gearbox is coupled to the drive shaft and configured to transfer rotational energy from the drive shaft to the lift fan or fans. The lift fan assembly or assemblies may include at least two pivot assemblies, the first pivot assembly configured to pivot the lift fan assembly on a first axis and the second pivot assembly configured to pivot the lift fan assembly on a second axis that is substantially perpendicular to the first axis.

Abstract: A rotating launcher system includes a plurality of rocket or missile housing tubes arranged in a circular pattern within a carousel, a set of frames, a cylindrical protective skin, an aerodynamically optimized nose cone with a bore, and an optional door covering the bore, enabling rockets or missiles to exit the launcher. The rotating launcher system may also include an aerodynamically optimized tail cone with a bore, and an optional door covering the bore, enabling exhaust from the rockets or missiles to exit the launcher. The rotating launcher system also includes an integral controller for an indexing motor, and an indexing motor enabling the bores of the nose and tail cones to align with different rockets or missiles in the carousel by either rotating the nose and tail cones, or by rotating the carousel.

Abstract: A rotating launcher system includes a plurality of rocket or missile housing tubes arranged in a circular pattern within a carousel, a set of frames, a cylindrical protective skin, an aerodynamically optimized nose cone with a bore, and an optional door covering the bore, enabling rockets or missiles to exit the launcher. The rotating launcher system may also include an aerodynamically optimized tail cone with a bore, and an optional door covering the bore, enabling exhaust from the rockets or missiles to exit the launcher. The rotating launcher system also includes an integral controller for an indexing motor, and an indexing motor enabling the bores of the nose and tail cones to align with different rockets or missiles in the carousel by either rotating the nose and tail cones, or by rotating the carousel.

Abstract: A flight instrument and associated method where vertical speed information is combined with gyro information to produce gyro enhanced vertical speed information that is displayed to a pilot. The gyro information may include a pitch rate gyro and may include an azimuth rate gyro. The pitch rate gyro and azimuth rate gyro may be combined to yield a corrected pitch rate in turns. In one embodiment, the display is an airplane symbol that moves relative to a horizon line responsive to the gyro enhanced vertical speed information. The horizon line may also tilt in response to the azimuth rate gyro.

Abstract: A flight instrument displays azimuth information in combination with horizon information and other optional information such as altitude and/or airspeed. Azimuth information is displayed using an elliptical pattern placed below a horizon line displaying horizon information. The horizon information may be based on gyro enhanced vertical speed and/or vertical axis information. The elliptical pattern may be representative of a horizontal circular heading indicator viewed from above and behind the circular indicator. In one embodiment, the elliptical azimuth pattern moves in response to movement of the horizon line to maintain position below the horizon line. Airspeed and/or altitude information may be displayed at the sides of the screen area using a circular arc display pattern.

Abstract: A flight instrument displays azimuth information in combination with horizon information and other optional information such as altitude and/or airspeed. Azimuth information is displayed using an elliptical pattern placed below a horizon line displaying horizon information. The horizon information may be based on gyro enhanced vertical speed and/or vertical axis information. The elliptical pattern may be representative of a horizontal circular heading indicator viewed from above and behind the circular indicator. In one embodiment, the elliptical azimuth pattern moves in response to movement of the horizon line to maintain position below the horizon line.

Abstract: Autopilot control of an aircraft is accomplished using a servo wherein the input shaft and output shaft are collinear. In one embodiment, the output shaft is supported, in part, by the input shaft. In further embodiments an engage clutch mechanism is provided to allow decoupling of the motor from the output shaft, and a slip clutch mechanism is provided to limit the torque output of the servo to enhance the safety of operation. The collinear shaft arrangement enables the engage clutch mechanism and slip clutch mechanism to synergistically utilize components for multiple functions.

Abstract: A system for providing automatic trim control associated with a control surface in an aircraft that utilizes at least two sensors that must agree in direction before trim adjustment is made. Each sensor is provided with a separate an independent controller channel to further enhance fail-safe operation. A trim sensor is placed in the coupling link between a servo and aircraft primary control linkage leading to the associated control surface. A trim sensor is provided that utilizes a spring with a portion disposed laterally with respect to the direction of the force to be measured. An arm is attached to the lateral portion of the spring to effect motion that can be sensed by various sensors including optical, mechanical switch and magnetic sensors.

Abstract: The present invention is directed to novel primary flight displays, moving map displays and engine parameter displays for aircraft cockpits. These displays process data gathered from various aircraft sensors and, using an various electronic databases, generate intuitive symbols that aid the pilot. The present invention also uses various novel algorithms that use data gathered from inexpensive sensors to derive parameters normally requiring far more expensive sensors.

Abstract: A system and associated method where a vertical flight dynamic sensor is stabilized using pitch rate gyro information combined with azimuth rate gyro information corrected by scaling the azimuth rate gyro information in accordance with feedback derived from the difference between the vertical flight dynamic sensor signal and the corrected vertical flight dynamic output. In one embodiment, the vertical flighy dynamic sensor may be a vertical speed sensor. In another embodiment, the vertical flight dynamic sensor may be a pitch attitude sensor derived from the difference between an inertial based acceleration signal and a velocity based acceleration signal. The velocity based acceleration signal may be based on airspeed or GPS velocity.

Abstract: The present invention is directed to novel methods for depicting glide range on moving map displays and on perspective-view primary flight displays. These methods involve processing data gathered from various aircraft sensors and, using a variety of electronic databases, generating intuitive symbols that aid the pilot.

Abstract: A joint assembly is provide between a machine element gear and a shaft or between two shafts. The joint is brought about by forming a predetermined configured surface on the exterior of the machine element and forming a similar configuration of the same general dimensions on a raised surface on the shaft. The shaft is initially inserted into the machine element in a light force fit so that the similar predetermined configurations on the machine element and the raised surface of the shaft are in alignment. A metal cylindrical torque ring is positioned over and surrounding the two mating and abutting predetermined surfaces. By the process of magneforming, the cylindrical torque ring is deformed inwardly to be tightly pressed against the predetermined surfaces, thereby spanning the exterior of those surfaces and providing a tight joint between the machine element and the shaft.

Abstract: A spreading tool which includes a hollow tube, a first ram member, and a second ram member. The hollow tube has a tubular wall with an axial throughbore and at least one opening extending through the tubular wall. The ram members are slidingly disposed within the throughbore, and at least one ram member is capable of extending beyond the outer edge of the hollow tube. The tool can be adapted for use with a force multiplying device which transmits an output force through a relative displacement between at least two spreadable tips. The first and second ram members are capable of being spaced apart by the force multiplying device such that the tool is capable of extending the expandable distance of the jaws and increasing the distance over which the output force is transmitted.

Abstract: A jam-tolerant geared rotary actuator, capable of performing in a normal operating mode and a jam-tolerant operating mode, which includes: an output spline member for releasably connecting the movable ring gear to the output ring; a decoupling member which includes an input shaft disposed within a hollow timing shaft, and a shear member for sensing excessive torque and initiating the jam-tolerant mode; a sun gear spline member for connecting the sun gear to the hollow timing shaft; an axial displacement member for engaging the output spline member with the movable ring gear and the output ring; and an input engagement member for releasably connecting the axial displacement member to the input shaft. The axial displacement member includes a decoupling bushing and a double threaded decoupling nut. The nut is disposed between the timing shaft and the decoupling bushing.

Abstract: An apparatus and method for determining a current state of charge of a battery are disclosed. The apparatus includes a battery signal developer, a threshold developer, a comparator, and a bi-directional integrating device. The battery signal developer receives a battery voltage and develops a corresponding battery signal. The threshold developer receives an integration result signal based on an integration value representative of the current state of charge of the battery, and develops a threshold signal based on the integration value. The comparator provides first and second comparison signals, respectively, when the battery signal magnitude is greater than and less than the threshold signal magnitude. The integrating device accumulates the integration value and receives a comparison result signal based on the first and second comparison signals.

Abstract: A threaded joint assembly is provided comprising a first metallic workpiece having an internally threaded cylindrical opening, and a second metallic workpiece having an externally threaded cylindrical surface which is threadingly engaged with the internally threaded opening of the first workpiece. The interthreaded joint between the first and second workpieces are electromagnetically deformed into a permanent interference fit. In consequence of the magneforming process, individual threads at the joint are slightly flattened and squeezed together tip to root to provide a high axial and radial pre-load in the joint. Preferably at least the portions of the first and second workpieces defining the joint are hollow cylinders, and preferably the threads of the joint are tip relieved.

Abstract: A refueling system mounted to an aircraft fuselage for transferring fuel from a tanker aircraft to a receiver aircraft. The refueling system including a pylon extending from the fuselage at a position aft of the main wing and having a refueling pod mounted thereto at an outboard location. A refueling hose is disposed within and extendable from the refueling pod and functions to transfer fuel from the refueling pod to the receiver aircraft. A means for transferring fuel from a fuel source, located within the aircraft, to the refueling hose is also provided. The pylon and refueling pod are configured so as to channel the refueling hose in a preferred direction to maximize safety during refueling. The channeling of the refueling hose is accomplished by mounting the refueling pod at an angle to the pylon, mounting the refueling pod at an angle to a horizontal plane, mounting the pylon at angle to the fuselage, or a combination of these mounting arrangements.