Abstract: A low dielectric, low loss radome comprising microspheres integrated into a matrix. The microspheres reduce overall dielectric constant, whereby the radome has a dielectric constant less than 2.5 through a thickness of the radome.

Abstract: A low dielectric, low loss radome comprising microspheres integrated into a matrix. The microspheres reduce overall dielectric constant, whereby the radome has a dielectric constant less than 2.5 through a thickness of the radome.

Abstract: A low dielectric, low loss radome comprising microspheres integrated into a matrix. The microspheres reduce overall dielectric constant, whereby the radome has a dielectric constant less than 2.5 through a thickness of the radome.

Abstract: A kinetic energy system which transfers the kinetic landing into recoverable electric energy for an aircraft. The system incorporates at least one wheel supporting the aircraft for landing and takeoff coupled with a dynamic functioning motor/generator mounted to and operated by rotation of the wheel to create electrical energy from kinetic energy. An induction shoe structurally connected to the aircraft and electrically connected to the motor/generator, which shoe draws the converted energy from the generator which supplies the load created by the inductively coupled induction shoe to the an ancillary load provided by the resistive heat sink on by the capacitor storage bank. This provides the generator circuit for conversion of the rotational energy of the wheel to electrical energy and creates braking drag. In exemplary embodiments, the system employs an energy storage system acting as the load to store electrical potential energy created by the generator.

Abstract: A servicing bridge (14) for an airport (13) includes multiple servicing levels (82, 102). A bridge (81) includes one or more of the servicing levels (82, 102) and extends from a terminal of the airport (13). A ground support service sub-system is coupled to the servicing levels (82, 102) and is configured to mate with a service opening (26) of the aircraft (12). The ground support service sub-system provides services to the aircraft (12) through the service opening (26) and on the servicing levels (82, 102).

Abstract: A terminal (14) for an airport (13) includes multiple servicing levels (82, 102). A ground support service sub-system is coupled to the servicing levels (82, 102) and is configured to mate with a service opening (26) of the aircraft (12). The ground support service sub-system provides services to the aircraft (12) through the service opening (26) and on the servicing levels (82, 102).

Abstract: A mobile ground servicing unit (470) includes a stand-alone support structure (471). Wheels (473) are coupled to the support structure (471). The support structure (471) has one or more servicing levels (472, 474) that are associated with services. A ground support service sub-system is coupled to the servicing levels and is configured to mate with a service opening (26?) of an aircraft (12??). The ground support service sub-system provides the services to the aircraft (12??) through the service opening (26?) and on the servicing levels (472, 474).

Abstract: An aircraft (12) includes a servicing opening (26) and multiple service levels (82, 102). The service levels (82, 102) include a noncargo-based service level (82). The service levels (82, 102) are accessible through the service opening (26). An aircraft onboard primary servicing system (66) includes a primary service sub-system (151). An aircraft primary service coupler (154) is configured to attach to a corresponding terminal primary service coupler (152). The aircraft primary service coupler (154) and the terminal primary service coupler (152) providing at least one primary service therethrough.

Abstract: An aircraft (1000) includes multiple servicing levels (1014, 1016) and a flight deck level (1040) that is isolated from the servicing levels (1014, 1016). An aircraft security system (1001) includes a passive system (1030) and an active system (1032) that is in operation with said passive system (1030). The passive system (1030) includes a service opening (1050) for both passengers and cargo and the flight deck (1040) that is isolated from the service opening (1050).

Abstract: A powered nose aircraft wheel system (130) for an aircraft (12) includes landing gear (104) that extends from the aircraft (12). A wheel axel (136) is coupled to the landing gear (104). A wheel (134) is coupled to the wheel axel (136). A wheel motor (106) is coupled to the wheel axel (136) and the wheel (134). A controller (120) is coupled to the wheel motor (106) and rotates the wheel (134). A method of taxiing an aircraft (12) includes permitting the wheel (134) of the aircraft (12) to freely spin during the landing of the aircraft (12). Power is transferred from an auxiliary power unit (73) of the aircraft (12) to the wheel motor (106). The wheel (134) is rotated via the wheel motor (106). The aircraft (12) is steered and the speed of the wheel (134) is controlled via one or more controllers selected from an onboard controller (18, 118, 120) and an offboard controller (45, 58, 59).

Abstract: A kinetic energy system which transfers the kinetic landing into recoverable electric energy for an aircraft. The system incorporates at least one wheel supporting the aircraft for landing and takeoff coupled with a dynamic functioning motor/generator mounted to and operated by rotation of the wheel to create electrical energy from kinetic energy. An induction shoe structurally connected to the aircraft and electrically connected to the motor/generator, which shoe draws the converted energy from the generator which supplies the load created by the inductively coupled induction shoe to the an ancillary load provided by the resistive heat sink on by the capacitor storage bank. This provides the generator circuit for conversion of the rotational energy of the wheel to electrical energy and creates braking drag. In exemplary embodiments, the system employs an energy storage system acting as the load to store electrical potential energy created by the generator.

Abstract: An integrated operational ground mobility and support system (10) that includes an aircraft (12) having one or more service openings on a side of the aircraft (12). The integrated support system (10) may have an airport interface terminal docking port (14) that has a ground support service sub-system. The docking port (14) mates with the aircraft (12) at the service openings and has multiple service levels. The ground support service sub-system provides services to the aircraft (12) through the service openings and on the service levels. The integrated support system (10) may have in addition to or in replacement of the interface terminal docking port an aircraft loader/unloader. The loader/unloader has ground support service sub-systems and mates with the aircraft (12) at one or more of the service openings. The service sub-systems of the loader/unloader include a passenger ingress/egress system (62) and provide services to the aircraft (12).

Abstract: A dual drive system for a hydraulic pump and an air boost compressor is provided. Reversible power is transmitted to a shaft connected to clockwise and counterclockwise over-running clutches connected to different vehicle or equipment subsystems. Reversing the drive allows power to be alternately transmitted to one or the other of the subsystems. The invention includes utilizing the dual drive for hydraulic and air conditioning systems for an aircraft, with the provision of an additional drive motor providing constant power to one or more of the subsystems.

Abstract: A method and apparatus for controlling aircraft airflow. An apparatus in accordance with an embodiment of the invention can include an air scoop having an inlet and an outlet and configured to mount to the aircraft and be movable relative to at least a portion of the aircraft between a first position and a second position. The air scoop can be oriented to capture air when in the second position. The outlet can be configured to be coupled in fluid communication with a pressurized portion of the aircraft when the air scoop is in the second position to convey air from the inlet to the pressurized portion. The air scoop can be configured to significantly increase the drag of the aircraft from a first value when the air scoop is in the first position to a second value when the air scoop is in the second position.

Abstract: A dual drive system for a hydraulic pump and an air boost compressor is provided. Reversible power is transmitted to a shaft connected to clockwise and counterclockwise over-running clutches connected to different vehicle or equipment subsystems. Reversing the drive allows power to be alternately transmitted to one or the other of the subsystems. The invention includes utilizing the dual drive for hydraulic and air conditioning systems for an aircraft, with the provision of an additional drive motor providing constant power to one or more of the subsystems.

Abstract: A method and apparatus for controlling aircraft airflow. An apparatus in accordance with an embodiment of the invention can include an air scoop having an inlet and an outlet and configured to mount to the aircraft and be movable relative to at least a portion of the aircraft between a first position and a second position. The air scoop can be oriented to capture air when in the second position. The outlet can be configured to be coupled in fluid communication with a pressurized portion of the aircraft when the air scoop is in the second position to convey air from the inlet to the pressurized portion. The air scoop can be configured to significantly increase the drag of the aircraft from a first value when the air scoop is in the first position to a second value when the air scoop is in the second position.

Abstract: An improved chaff in which a plurality of metallic or metallic coated elets are joined as chain links that, when deployed, produce microarcs when the link elements make and break contact with each other in an electromagnet field such as that created by a high power radar transmitter. These microarcs will then in turn create current spikes that will reflect a radar signal that has a wider bandwidth than conventional chaff, so as to make it more difficult to distinguish the chain link chaff from a fast moving target such as an aircraft.

Abstract: An improved power wheelchair is provided that provides exceptional maneuverability, stability and directional tracking characteristics. The wheelchair includes a torsional frame and a rigid stability frame. Two main wheels and a pivoting drive wheel are coupled to the torsional frame. At least two freely rotating casters are coupled to the stability frame. The torsional frame and stability frame interact to provide automatic compensation for directional tracking errors caused by shifts in the mass center of an occupant. The wheelchair can be equipped with either manual or power steering. A unique three-point battery mounting assembly also permits easy replacement of batteries.

Abstract: A method and apparatus for converting thermal energy into mechanical energy by parametric pumping of rotary inertia. In a preferred embodiment, a modified Tesla turbine rotor is positioned within a rotary boiler along its axis of rotation. An external heat source, such as solar radiation, is directed onto the outer casing of the boiler to convert the liquid to steam. As the steam spirals inwardly toward the discs of the rotor, the moment of inertia of the mass of steam is reduced to thereby substantially increase its kinetic energy. The laminar flow of steam between the discs of the rotor transfers the increased kinetic energy to the rotor which can be coupled out through an output shaft to perform mechanical work. A portion of the mechanical output can be fed back to maintain rotation of the boiler.

Abstract: A method and apparatus for forming a set of simultaneous multiple antenna beams. The digital technique utilizes a Fermat Number Transform (FNT) processor which takes the transform of number sequences consisting of the output signals from the elements of a preferably circular, equiangularly spaced antenna array, then forms the complex linear vector product of the transformed signals and a stored beam-forming function, and finally processes the complex linear vector product through an inverse FNT network to generate a set of simultaneous multiple antenna beams. The advantages of utilizing the FNT include reduced hardware requirements, greater processing speed due to a reduction in multiplications required to be performed, and sharper output beams due to the absence in the FNT of round-off errors.