Abstract: A winglet 3 has an inner end 5 and an outer 7. The winglet 3 has a varying radius of curvature (R) which:(i) decreases along the winglet over a first distanced1; (ii) remains constant over a second distanced2; and (iii) increases along the winglet 3 over a third distance d3. The sum of the first and third distances (d1+d3) is greater than the second distance (d2). The radius of curvature may vary according to the equation R=k1/dn. The parameter n may be equal to 1, such that the curvature follows an Euler spiral.

Abstract: The invention relates to a method for deflecting space debris comprising steps of: launching (E2) a thruster (2) by means of a sounding rocket (1) at a target altitude close to that of the one or more debris to be deflected. generating (E3) by the thruster a gas cloud (G) above the sounding rocket.

Abstract: The present invention provides a multi-rotor flying object including: a body; a plurality of rotor units each including a propeller and a power unit for driving the propeller; and a steering unit including a connection member connecting the plurality of rotor units to each other and an actuator installed on the body and activating the connection member to allow the plurality of rotor units to be simultaneously inclined at the same angle with respect to the body.

Abstract: Fluid systems are described herein. An example embodiment of a fluid system has a lengthwise axis, a chord length, a first body portion, a second body portion, a spacer, and a fluid pressurizer. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. The first body portion defines a cavity that is sized and configured to filter debris that enters the channel during use and provide a mechanism for removing the debris from the system.

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: Provided are animal containment systems and components, including single-use animal containment cages and modular rack units. Also provided are methods for assembling and using components of the animal containment systems.

Abstract: In an illustrative embodiment, electromechanical actuation systems and methods for use in an aircraft passenger suite include aircraft suite actuators for allowing passenger-initiated adjustment of a passenger seat and other suite components, a LRU coupled to each of actuators including control circuitry for controlling actuation of a given actuator in response to a passenger-initiated adjustment request, and wireless communication circuitry configured to: initiate communication links with LRUs creating a communication network, establish master/slave relationships with LRUs, and communicate actuation commands via the communication network.

Abstract: The present invention is directed to a solar-powered aircraft comprising a fixed wing panel, a motor driven propeller, a plurality of secondary wing panels, and a tail assembly having a first tail panel and a second tail panel. Each secondary wing panel being configured to rotate about a first longitudinal pivot axis extending from a distal end of the fixed wing panel through a central transverse portion of the secondary wing panel. The secondary wing panels may comprise an array of solar panels on its surface. The first tail panel comprises a second array of solar panels located on a surface of the first tail panel, the first tail panel being configured to rotate about a second longitudinal pivot axis through a central transverse portion of the first tail panel.

Abstract: A passenger lavatory unit has an enclosing structure enclosing a lavatory space, and a toilet assembly inside the lavatory space. The toilet assembly has a toilet bowl and a shroud to support the user during use. The toilet assembly serves as a hybrid toilet to be used as a sitting toilet or as a squatting toilet. The shroud includes an upper edge surrounding an upper opening of the toilet bowl. To accommodate a user sitting position, the upper edge is provided as a toilet seat, and a feet-placing area is provided on a floor segment in front of the toilet assembly. The shroud has two lateral tread portions, one on either side of the toilet bowl. To accommodate a user squatting position, the tread portions are provided as elevated rest-platforms arranged on an intermediate level provided above a floor level and below a toilet seat level.

Abstract: An aircraft fuel system includes one or more fuel cells adapted to contain fuel, a fuel cell receiving assembly having an inner surface adapted to receive the one or more fuel cells and a fuel cell cushion disposed between the inner surface of the fuel cell receiving assembly and the one or more fuel cells. The fuel cell cushion is machined from a foam substrate to form a shaped foam substrate that is substantially covered with a cushion coating. The cushion coating is sprayable onto the shaped foam substrate such that the fuel cell cushion is substantially nonabsorbent of fuel. The fuel cell cushion is interposable between the inner surface of the fuel cell receiving assembly and the one or more fuel cells to cushion the one or more fuel cells from damage.

Abstract: Described are commercial aircraft cabin arrangement comprising a plurality of seat units (14), each seat unit including a primary seat (16) and a secondary seat (18) arranged facing one another. The primary seat (16) and the secondary seat (18) are configured to combine into a single bed position for the seat unit. The plurality of seat units (14) are arranged in two columns separated by a wide central aisle (72).

Abstract: A cockpit control system and method for efficiently controlling ground travel in an aircraft equipped with an engine-free electric taxi system are provided. The cockpit control system is configured with a display that provides a maximum amount of information during aircraft ground movement with a minimal amount of input from and distraction to pilots or cockpit crew to facilitate essentially hands free operation and control of aircraft ground travel. System test and drive procedures ensure safe aircraft ground travel with the engine-free electric taxi system. Constant pilot hand or other input is not required to achieve safe and maximally efficient aircraft ground travel powered by the aircraft's engine-free electric taxi system or, under selected defined conditions, by the aircraft's engines to achieve this maximum efficiency. The system may further be designed to be uninterruptible by unauthorized persons.

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.

Abstract: A window assembly for an aircraft is provided that includes a windshield, a side window, a post, and an airflow surface. The windshield is oriented toward a front of the aircraft. The side window is oriented toward a side of the aircraft. The post is interposed between the windshield and the side window. The airflow surface is disposed on the post and on an exterior of the aircraft. The airflow surface extends along a length from a leading edge proximate the windshield to a trailing edge proximate the side window, and extends along a height between a top and a bottom. The airflow surface has a first radius of curvature proximate the leading edge and a second radius of curvature proximate the trailing edge, wherein the first radius of curvature is less than the second radius of curvature.

Abstract: An aircraft is disclosed, the aircraft having a fuselage having a centerline, and a wing extending from the fuselage and having a leading edge and a trailing edge. Additionally, the aircraft includes an engine mounted to the wing and having a rotating output shaft, and a propeller operably coupled to the output shaft and generating a rotating flow field to define a propeller wake when the propeller is rotated by the rotating output shaft. The propeller is located forward of the leading edge of the wing, so the propeller wake flows over the wing forming localized areas of effectively increased angle of attack generating a corresponding increased wing loading, with the wing having corresponding localized areas of reduced chord length to neutralize the otherwise increased wing loading. A method of countering the aerodynamic effects of propeller wake acting on a wing is also disclosed.

Abstract: An airflow modification patch 14 for reducing aeroacoustic noise generated by an aircraft assembly. The patch has a substrate 14a and a plurality of airflow disruption elements 14b.

Abstract: An exemplary rotational assembly includes a base having a circular collar and first and second arms that rotate about the circular collar in opposite angular directions. In a stored state the arms have substantially the same angle relative to the circular collar; in a deployed state the arms have rotated into opposing positions. Each end of a Nitinol wire is coupled to the first and second arms and contracts when heated by the flow of electrical current. This contraction causes the simultaneously application of a rotational force to the first and second arms causing the first and second arms to rotate about the circular collar in opposite angular directions. The simultaneous counter rotating angular forces during rotation of the arms causes no substantial change in angular inertia at the base.

Abstract: A helicopter with a fuselage and a composite tail boom. The composite tail boom has at least a tubular tail boom cone and a composite attachment ring segment that defines a mating face which is connected to the fuselage at an associated connection interface by means of a plurality of tension members that are oriented longitudinally with respect to a longitudinal extension direction of the composite tail boom. The plurality of tension members are distributed over a perimeter of the composite attachment ring segment 7. The composite attachment ring segment has a clamp ring section with a plurality of tension member accommodations. The clamp ring section defines the mating face of the composite attachment ring segment 7. The plurality of tension members is at least partly accommodated in the plurality of tension member accommodations.

Abstract: Sliding fastener systems can include a fastener configured to fixedly attach to a first component having a first thermal expansion coefficient, a tray configured to fixedly attach to a second component having a second thermal expansion coefficient different from the first thermal expansion coefficient, the tray defining a sliding surface, and at least a portion of a locking element configured to engage with the fastener, the locking element having a base with a contact surface that movably contacts the sliding surface of the tray when the tray, the fastener, and the locking element fasten the first component and the second component together. The fastener and the locking element are configured to move with the first component and the tray is configured to move relative to the fastener and the locking element with the second component when there is a differential thermal expansion between the first and second components.

Abstract: A miniature satellite that uses a modified structural frame in order to store and disperse propulsion fuel efficiently. The modified structural frame includes a plurality of structural members. Each of the plurality of structural members includes a tubular body, a first endcap, a second endcap, an outlet port, and an inlet port. The first endcap and the second endcap are oppositely positioned within the tubular body. The first endcap and the second endcap are each perimetrically connected to the tubular body in order to delineate a fuel storage volume. The inlet port is positioned in between the first endcap and the second endcap and is mechanically integrated into the tubular body. The outlet port disperses propulsion fuel and is also mechanically integrated into the tubular body. The inlet port is in fluid communication with the outlet port through the tubular body. Additionally, the structural members are mounted amongst each other.