Abstract: An aircraft including a wing and an aeroengine having a longitudinal main axis and including a ducted nacelle with at least one fan is disclosed. The wing includes an acoustic treatment surface on a bottom portion of its outer shell on either side of the longitudinal main axis and over a width perpendicular to the longitudinal main axis that is not greater than three times the diameter of the fan. The acoustic treatment surface includes a layer of porous material for attenuating acoustic waves coming from the fan.

Abstract: A constellation of Earth-orbiting spacecraft includes a first spacecraft disposed in a first orbit and a second spacecraft disposed in a second orbit. Each of the first orbit and the second orbit is substantially circular with a radius of approximately 42,164 km. The first orbit and the second orbit have a respective inclination with respect to the equator within a range of 5° to 20°. The first orbit has a first right ascension of ascending node (RAAN1) and the second orbit has a second RAAN (RAAN2) of approximately RAAN1+90°.

Abstract: Embodiments are directed to systems and methods for a sliding door in a pressurized aircraft. In one embodiment, an aircraft comprises a fuselage having a door opening, and a door configured to slide into the door opening from within the fuselage, the door held in a closed position in the door opening by excess air pressure within the fuselage during operation of the aircraft.

Abstract: A distributed parachute system is disclosed. In various embodiments, a parachute is at least partially deployed along one or more dimensions. A deployment mechanism configured to deploy the parachute is provided. The distributed parachute system is configured to be deployed in an aircraft that comprises a channel oriented along the one or more dimensions.

Abstract: An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight.

Abstract: An aircraft that includes torque rotor and a lifting rotor, and generates torque from the torque rotor. The torque rotor may optimize drag production while the lifting rotor may optimize lift production limiting compromise between drag and lift production rotor.

Abstract: A deformable closure mechanism for an aperture that may include an aperture seal that has a seal seat between an internal support structure and an external support structure. A barrier structure may be configured to resealably close the aperture, and have a central membrane and a barrier sealed that is inflatable in order to engage the barrier structure with the aperture seal.

Abstract: A reinforcing arrangement for an opening in an aircraft fuselage structure has a fuselage skin having an inner side, an outer side and a first opening with a first opening contour, and a one-piece reinforcing structure having a thickening section and at least one projecting profile. The first opening contour is surrounded on the inner side of the fuselage skin by an opening edge surface having a thickness corresponding to a thickness of the fuselage skin surrounding the opening edge surface. The thickening section has a bearing surface matched to the opening edge surface and has a receiving section facing away from the bearing surface and surrounding a second opening. The bearing surface is in surface contact with the opening edge surface, and the reinforcing structure is connected to the fuselage skin, with the result that the first opening and the second opening lie one above the other.

Abstract: An inflatable pressure structure includes an airtight flexible membrane having collapsed and inflated configurations. The inflatable pressure structure includes an elongated pressure-assisted seal that is configured to selectively seal an opening in the airtight flexible membrane. The pressure-assisted seal includes first and second seal components that sealingly engage one another and prevent escape of gas from inside the airtight flexible membrane. The airtight flexible membrane, when inflated, generates a force transverse to the pressure-assisted seal tending to pull the first and second seal components apart. Pressurized gas inside the airtight flexible membrane causes the first and second seal components to more securely engage one another whereby a force transverse to the pressure-assisted seal does not disengage the first and second seal components.

Abstract: An electrical control mechanism having a support. A central body that is movable in rotation about a central axis of rotation (AXROTC) carries a button that is movable in rotation relative to the central body about an offset axis of rotation (AXROTD) parallel to the central axis of rotation (AXROTC). First return means are interposed between the central body and the button, with second return means being interposed between the central body and the support. Two primary electric switches are interposed between the button and the central body on either side of a plane containing the central axis of rotation (AXROTC) and the offset axis of rotation (AXROTD). Two secondary electric switches are interposed between the support and the central body on either side of the plane.

Abstract: A stacking device for a space vehicle comprises a plurality of hold down and release mechanisms and is configured to hold, temporarily, n space appendages, n being an integer strictly greater than 2, on one and the same support of a space vehicle using hold down and release mechanisms. The stacking device is arranged such that several space appendages are held by one and the same hold down and release mechanism. An associated space vehicle comprising at least one such stacking device is also provided.

Abstract: A release system for an evacuation slide assembly of an aircraft includes a fluid delivery manifold, a first actuator, and a second actuator. In various embodiments, a fluid is configured to flow into and pressurize the fluid delivery manifold from a fluid source in response to an evacuation event. In various embodiments, the first actuator is fluidly coupled to the fluid delivery manifold, wherein the first actuator is configured to release a blowout panel of the evacuation slide assembly in response to the fluid pressurizing the fluid delivery manifold. In various embodiments, the second actuator is fluidly coupled to the fluid delivery manifold, wherein the second actuator is configured to release a soft cover of the evacuation slide assembly in response to the fluid pressurizing the fluid delivery manifold.

Abstract: Described herein is a thrust system for a vehicle that includes at least three electrical power controllers, at least four electrical switches each configured to receive electrical power from at least one of the at least three electrical power controllers, and at least three thrusters each configured to receive electrical power from at least one of the at least three electrical switches. The at least four electrical switches are operable to switch a supply of electrical power from any of the at least three electrical power controllers to any one of the at least three thrusters.

Abstract: Methods and systems for vertically landing space vehicles are described herein. In one embodiment, a reusable space vehicle lands in a vertical, nose-up orientation by engaging a system of cables suspended from an elevated framework during a controlled descent.

Abstract: A manifold attached to the UAV and a cartridge removably and replaceably attached to the manifold. Inside the cartridge is a removable insert for drawing contents out of the cartridge with a suction tube selectively positioned in fluid communication with a pump for removing chemicals from the cartridge for application by the UAV. The suction tube comprises a plurality of baffles around its circumference for dampening movement of the chemicals in the cartridge while the UAV is in motion.

Abstract: In one embodiment, an apparatus is attached to a feature to be deployed on a satellite. The apparatus includes a first material having an impedance, a second material coupled to the first material configured to provide a current or voltage to the first material causing the first material to generate heat based on the impedance after a launch process of a launch vehicle carrying the satellite has completed, and a third material configured to change state at a transition temperature. A release mechanism is coupled to the third material and holds the feature in an undeployed position on the satellite. The heat generated by the second material causes the third material to change state when the transition temperature range is reached and the release mechanism is released from the third material when the third material is in the second state to deploy the feature.

Abstract: An air launched rocket for placing payloads in earth orbit comprising a lifting body having a cross sectional shape of an airfoil extending in a spanwise direction between a first and a second wing tip. The lifting body further comprises at least one rocket engine positioned at the first wing tip oriented for propelling the lifting body in the spanwise direction. The air launched rocket is combined with a carrier aircraft which is removably attached to a suction surface of the airfoil.

Abstract: A passenger seat system for a transport means has a carrier structure which can be attached, fixedly with respect to a structure, and a seat having a seat frame displaceable and arrestable on the carrier structure, a bottom side lying on the carrier structure, and a top side holding a seat surface. The seat frame has an arresting device and has an operating unit, coupled to the arresting device. The operating unit is movable into an arresting position and an unlocking position, is coupled to a traction mechanism. The arresting device has an arresting body, coupled to the traction mechanism, is forced by action of a pressure spring into an engagement position, and can be moved by the traction mechanism into a release position and has a locking unit, coupled to the traction mechanism, locking the arresting body in the engagement position and releasing the locking by the traction mechanism.

Abstract: In an example, an overhead payload module is described. The overhead payload module comprises a ceiling assembly, an aisle floor assembly, a first payload assembly attached to the ceiling assembly and the aisle floor assembly to form a first side of the overhead payload module, and a second payload assembly attached to the ceiling assembly and the aisle floor assembly to form a second side of the overhead payload module. The first payload assembly comprises a first payload module and a first overhead stowbin module structurally integrated with the first payload module and having a first stowage area configured to receive stowbins. The second payload assembly is positioned opposite the first payload assembly to form an aisle therebetween and comprises a second payload module and a second overhead stowbin module structurally integrated with the second payload module and having a second stowage area configured to receive stowbins.

Abstract: An apparatus for use as part of, or attached to, an unmanned aerial vehicle (UAV) to intercept and entangle a threat unmanned aerial vehicle, includes a flight and payload control system for controlling power to the UAV and for controlling maneuvering of the UAV. A host-side mount may be coupled to the UAV and is in communication with the flight and payload control system. A payload-side mount is removably attached to the host-side mount and includes a power interface and a control interface between the payload-side mount and the host-side mount. A counter-UAV system is coupled to the payload-side mount and includes a deployable chute net having a cross-sectional area sized for intercepting and entangling the threat unmanned aerial vehicle; and a deployment mechanism for mounting to the unmanned aerial vehicle.