Abstract: A shape-change material includes a shape memory material layer with an electrically conductive layer on a surface of the shape memory material layer. The conductive material may be used to heat the shape memory material by electrical resistance heating. The conductive material may be a primary heater, providing the heating to cause softening or shape change in the shape memory material, or may be a secondary heater in conjunction with a greater amount of heating from a primary heater, such as a conductive plate that provides electrical resistance heating to a surface of the shape memory material on an opposite side of the shape memory material from the conductive material. One use for the shape-change material is as the skin material for a shape changing material.

Abstract: The invention relates to a section of fuselage for an aircraft, including frames and bays for receiving cabin windows. According the disclosed embodiments, at least some of the frames include at least one frame segment that surrounds at least one bay, the frame segment having two branches that are disposed to the side of the bay. The ends of the branches are attached to each of the ends of the frame segment such as to form a Y.

Abstract: An active vortex control system (AVOCS) includes a set of primary injectors that inject gas into a cavity to generate a vortex in front of and possibly around components inside the cavity. The vortex interferes with an external flow field in an opening to the cavity to protect the components from the external environment. Sets of secondary injectors may inject gas at a reduced mass flow into the cavity to compensate for energy losses to maintain the coherence of the vortex. The AVOCS is well suited for use in windowless endo- and exo-atmospheric interceptors to protect the electro-optical imagers and optical components from Earth atmosphere.

Abstract: A modular artillery projectile and method of engaging a target. A modular artillery projectile may include a payload module, a guidance module coupled to the payload module and a rear module coupled to the guidance module. The payload module may be selected from a plurality of interchangeable payload modules containing different payloads. The guidance module may include a transverse propulsion system to propel the modular artillery projectile transversely to a longitudinal axis of the modular artillery projectile, a global positioning system receiver, and a control system to control the transverse propulsion system responsive to the global positioning system receiver to guide the modular artillery projectile to a predetermined target position.

Abstract: An automatic cloning apparatus is disclosed which comprises a housing having an interior divided into a plant compartment and a water compartment. The plant compartment has a plurality of porous net pockets adapted to allow plants to rest thereon and water to drain therethrough. Above the water compartment is a mixing area having a mist generator thereon. The mist generator is mounted to the housing and has a motor with a hollow tapered shaft extending downwardly therefrom into the water compartment. The shaft is tapered whereby when spinning rapidly, the combination of centripetal force on the water and the outwardly sloping inner surface of the tapered shaft forces water upwardly therein. A disk is mounted atop the open upper end of the tapered shaft and adapted to receive water therefrom. The disk throws the water off in a radial movement in small droplets in the mixing area and also forces air within the mixing area outwardly throughout the mixing area.

Abstract: Embodiments of separation apparatuses are generally described herein. Other embodiments may be described and claimed. In an embodiment, a separation apparatus is provided that is configured to be disposed between a first component and a second component associated with an aerospace vehicle. The separation apparatus comprises a sealed cavity filled with gas, and the separation apparatus is configured to expand based on a decrease in atmospheric pressure. This expansion is configured to separate the first component from the second component.

Abstract: An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

Abstract: A rotor system for a rotorcraft, the rotor system is a rotor hub having six rotor blades attached to a rotor mast via a rotor yoke assembly. Each rotor blade is angularly spaced in 30° and 90° alternating angular increment about a mast axis of rotation. Such rotor blades spacing reduces the vibration that is translated into the rotorcraft through the rotor mast.

Abstract: A high-lift device suppresses the occurrence of aerodynamic noise while minimizing an increase in airframe weight. The device includes a slat main body disposed to be able to extend from and retract into a main wing, and a concave part formed on the slat main body at a location facing the main wing and able to accommodate at least a part of a leading edge of the main wing. The device also includes an airflow control part disposed at an area in the concave part facing an upper surface of the main wing, that is accommodated between the main wing and the concave part when the slat main body is refracted into the main wing, and that suppresses turbulence colliding against the area in the concave part facing the upper surface of the main wing when the slat main body is extended from the main wing.

Abstract: Trailing edge (3) of an aircraft stabilizer surface (1), where this surface (1) is manufactured of a composite material and comprises an outer cladding (40) and an inner cladding (41) that are connected by a connecting clip type element (20) on this trailing edge (3), the connecting clip type element (20) comprising at its ends some recesses (23) used for coupling to the inner zone of the upper and lower claddings (40, 41) of the stabilizer surface (1), such that the connecting clip type element (20) is flexible enough to be pinched so that its ends will be housed, by means of these recesses (23), between the outer and inner claddings (40, 41) of the aircraft stabilizer surface (1), whereby the outer zone of the stabilizer surface (1), on its trailing edge (3), is formed by a continuous aerodynamic surface without changes of gradient.

Abstract: Apparatus for selectively applying a liquid plant chemical such as a herbicide to a plant includes a hollow tubular reservoir, an integrated funnel handle at the upper end of the reservoir, and an applicator tip at the lower end of the reservoir. The applicator tip includes a valve and a wick that allows the chemical to be dispensed in a controlled manner onto a specific plant, avoiding chemical drift. A protective cap fits over the applicator tip during storage, while retainer tabs keep the protective cap from squeezing the wick. The retainer tabs may be sharp enough to prick the plant to place the chemical internally.

Abstract: The present invention provides a fuselage structure for an aircraft or spacecraft with an outer skin. The fuselage structure comprises a rib element for stiffening the outer skin and ad cross member element. Here the rib element is bent in the shape of an arc to correspond to an inner contour of the outer skin. The cross member element connects two arc sections of the rib element transversely to each other. The cross member element has a higher strength than the rib element. From another point of view the invention provides an aircraft with such a fuselage structure.

Abstract: The combination of a container and a growing medium for a plant. The container is made to simulate the appearance of an egg shell bounding a receptacle. The growing medium is provided in the receptacle.

Abstract: The invention provides an aircraft with an auxiliary power unit isolated from the aircraft. An auxiliary power unit suspension system includes at least one suspension linkage. The suspension linkage terminates with a first low stiffness elastomeric rod end. The low stiffness elastomeric rod end has a low spring rate with the aircraft auxiliary power unit suspension system providing the aircraft auxiliary power unit with a suspended auxiliary power unit natural frequency, the suspended auxiliary power unit natural frequency below the aircraft auxiliary power unit operation frequency.

Abstract: A vibration suppressor system includes an annular electric motor system which independently controls rotation of at least two masses about the axis of rotation to reduce in-plane vibration of the rotating system. A method of reducing vibrations in a rotary-wing aircraft includes independently controlling a relative angular position of a multiple of independently rotatable masses to reduce vibrations of a main rotor system.

Abstract: A large-capacity airplane principally includes a fuselage which has no region of constant width between the front and the rear and a wing fixed to the fuselage. As a preference, the engines are fixed at the rear under a horizontal tail held above the fuselage by vertical stabilizers and maintenance wells are formed in the fuselage in vertical alignment with each engine to allow the engines to be fitted and removed. The width of the fuselage is determined, on the one hand, so that the airplane landing gear is fixed to the fuselage and in the up position is included within the interior volume of the fuselage and, on the other hand, so that the rear engines are above the fuselage in order to make use of the beneficial effects of this position.

Abstract: Upgrading existing aircraft braking systems to accommodate replacement of existing brake units employing sintered friction materials with brake units employing carbon-carbon composite friction materials is often desirable. However, when upgrading the braking systems it is necessary to ensure that the integrity of the existing airframe is not compromised by the use of the new brake assemblies employing the carbon-carbon composite friction materials. Consequently, the present invention replaces existing pressure control valves of existing braking systems with an electronic control unit (126) coupled to a pressure control servovalve (128), thereby ensuring proper application of hydraulic pressure to brake assemblies (122). An advantage of this invention is that the pressure profile of the hydraulic fluid is controllable and hence the integrity of the airframe is maintained.

Abstract: A roller assembly comprises a first race and a second race. The second race is coaxial with the first race and is axially movable relative to the first race. The first and second races are movable between a static axial position and a dynamic axial position relative to one another. The roller assembly includes at least one biasing member that is operative to bias the first and second races from the dynamic axial position toward the static axial position.

Abstract: A system is disclosed for controlling an aircraft when the hydraulic system of the aircraft has been compromised. The system includes a digital fly-by-wire control system configured to rescale at least one gain vector. The gain(s) may then used by a digital control to modulate engine thrust. In this manner, engine thrust modulation may be used for stabilization and control of control-configured aircraft without requiring a substantial change in piloting technique.

Abstract: A device for launching unmanned missiles from an aircraft with a pallet, on which at least one container is provided to receive a missile. The container has an upper container section that has a pylon for the suspended, detachable support of the missile. The container has a lower container section that is embodied as a support area for the missile.