Abstract: An accommodation system for an accommodation space for storing rollable containers in a vehicle. After a front container, which is arranged at the insertion opening, has been removed in the conventional manner, it is possible, through the use of the accommodation system, to remove the rear container which is arranged considerably spaced apart from the insertion opening in the interior of the accommodation space. For this purpose, a rail system is provided in the floor region of the accommodation space. A transfer plate is movable on the rail system in the floor region of the accommodation space and can assume a storage position and a removal position for the rear container.

Abstract: An aircraft cabin door system has a cabin door having an outer side and an inner side, a drive device coupled to the cabin door for moving the cabin door into an open position, a first actuation device, a second actuation device, and an emergency chute unit coupled to the cabin door and having an emergency chute and an actuation mechanism. The emergency chute unit can be moved into an active state, in which opening the cabin door leads to activation of the emergency chute, and an inactive state, in which opening the cabin door does not lead to activation of the emergency chute. The emergency chute unit is in the inactive state when the cabin door is opened after actuation of the first actuation device. The emergency chute unit is in the active state when the cabin door is opened after actuation of the second actuation device.

Abstract: Provided is a vibration control system for a compound helicopter with a rotor and a fixed wing. The fixed wing includes a movable flap that is mounted on a rear edge of the fixed wing. The vibration control system periodically moves the movable flap so as to periodically change lift of the fixed wing such that vibration aerodynamically generated by the fixed wing is in anti-phase with vibration caused by rotation of the rotor.

Abstract: A ducted fan propulsion comprises a duct with a cutout and a movable duct section that is moved between a retracted position within the cutout and am extended position relative to the duct. An actuator is disposed within the duct wall and is connected to the movable duct section with actuating linkage. A control linkage connects the movable duct section to the cutout edges. The movable duct section is extended when the ducted fan propulsion transitions from vertical takeoff to a level flight or transitions from level flight to a vertical landing. The movable duct section is retracted into cutout an becomes integrated with the duct during level flight.

Abstract: An anti-torque rotor is described for a helicopter, comprising: a mast rotatable about a first axis; a plurality of blades hinged on the mast, extending along respective second axes transversal to said first axis and rotatable about respective said second axes to alter the respective angles of attack; a control element sliding and rotating with respect to the mast, and operatively connected to said blades to cause the rotation of said blades about respective second axes following a translation of said element along the first axis; a control rod sliding axially along first axis with respect to the mast and angularly fixed with respect to the first axis; and a bearing interposed between the control rod and the control element, sliding along the first axis with respect to the mast and integrally with the control rod; the anti-torque rotor further comprises an interface made of an antifriction material interposed between said control rod and said bearing.

Abstract: An inflation control system for an inflatable is disclosed. In various embodiments, the inflation control system includes a source of a pressurized gas; a valve module connected to the source of the pressurized gas and configured to control a flow of the pressurized gas to the inflatable; a stretch sensor configured for mounting to the inflatable and to provide a real-time stretch data of an elastic deformation of the inflatable; and a controller configured to receive the real-time stretch data and to transmit a control signal to the valve module to control the flow of the pressurized gas to the inflatable.

Abstract: An aerial vehicle has a passenger cabin for receiving at least one passenger, a load-bearing structure beneath the cabin, and a propulsion system including a number of propulsion units, which propel the aerial vehicle for powered flight and vertical take-off and landing (VTOL). The propulsion units are preferably carried by support arms attached to the load-bearing structure and extending upwards therefrom so as to support the propulsion units at a level above the cabin. The aerial vehicle is preferably reconfigurable to a compact configuration after landing, with at least some of the propulsion units overlapping the cabin and/or each other, while still allowing passenger transfer in and out of the vehicle, thereby facilitating efficient use of space for implementing a vertiport.

Abstract: A device for releasing a panel of an aircraft, the device being configured to be secured to a support, the support having an opening and the device being attached to cover a periphery of the opening, the device comprising a panel configured to be arranged at least opposite the opening. Such a device comprises: at least two ejector members, each of the at least two ejector members comprising at least one link; and at least one control member for applying a pulling force to the at least one link.

Abstract: A stowage and removal system is provided for a receiving space for container storage in a vehicle. It has a rail system in a bottom region of the receiving space, on which a transfer plate can be moved and which can assume a storage position and an entry and removal position for the container. The container storage position is provided with its rear wall in a region of the receiving space rear wall. The entry and removal position is provided in the region of a push-in opening, lying opposite the rear wall, for pushing in and removing a container into or from the receiving space.

Abstract: A magnetic spacer system for a spinner of a rotorcraft includes a first ring of a plurality of magnets secured to the spinner and having an inner surface facing radially inward, and a second ring of a plurality of magnets secured to a nacelle of the rotorcraft and having an outer surface facing radially outward. The first and second rings of multiple magnets are arranged concentrically, and a portion of the inner surface of the first ring of a plurality of magnets and a portion of the outer surface of the second ring of a plurality of magnets have the same polarity to repel one another. In other aspects, the magnetic spacer system may be replaced by a low-friction system.

Abstract: An aircraft includes fuselage, a seat, and battery compartment. Fuselage extends along a longitudinal axis. Seat is configured to support a passenger. The battery compartment that includes a battery configured to provide power to propel the aircraft. The battery compartment, including the battery, is located laterally adjacent to the seat along the longitudinal axis.

Abstract: A method is proposed for installing system components in a portion of an aircraft fuselage. The method provides at least one planar structural arrangement to be secured on or in the aircraft fuselage, secures system components on the structural arrangement, couples system lines to the system components and arranges the system lines on the structural arrangement. The method includes positioning of the structural arrangement with the system components and system lines arranged thereon at a designated installation location of the structural arrangement, and mechanical coupling of the structural arrangement to the aircraft fuselage.

Abstract: A stowage and removal system for an accommodation space for storing rollable containers in a vehicle is provided. It preferably has a rail system in the floor region of the accommodation space, on which rail system a transfer plate is movable, which transfer plate can assume a storage position and an insertion and removal position for the container. The storage position of the container is provided with its rear wall in the region of the rear wall of the accommodation space. The insertion and removal position is provided in the region of an insertion opening, arranged oppositely in relation to the rear wall, for the insertion and removal of a container into the accommodation space.

Abstract: An assembly for arming/disarming a slide of an airplane door according to the invention comprises a system with two releasable connection mechanisms (2) linked with the door (1) and a cabin floor of the airplane, each mechanism (2) comprising a releasable connector (21b) secured to the door (1), extending at right angles to the floor on each side of a door bottom, and an anchor fitting (22b) fixed to the cabin floor. Each connector (21b) is equipped with an elastic centering element (70) and a locking/unlocking grab (25b) on the corresponding anchor fitting (22b), the connectors (21b) being linked by a girt bar (5). Each grab (25b) being rotationally mobile, one of the grabs (25b) is driven by a single command (5; 25b) which drives the other grab in rotation via the girt bar (5).

Abstract: An arrowhead aircraft includes a pair of counter-rotating propellers, a jet engine module, and an exhausted module, wherein the counter-rotating propellers propel the aircraft but does not have angular momentum, and the exhausted module deployed around the exhausted end of the jet engine module, which reuses the waste heat from the exhausted end and reduces the noise. Wherein, the airflow system includes a shutter deployed at the bottom side of the body that controls the streamlines of airflow through the aircraft and a plurality of airfoils that will force the aircraft tilted to the desired direction. The present invention resolved the helicopter's vulnerabilities, such as its intricate mechanism, dragging response, dangers blades, hard to control angular momentum, high cost, and high training level.

Abstract: A Short Takeoff and Landing (STOL) aircraft has a fuselage with an axis and an engine providing thrust, a first aileron at an end of a first wing, a second aileron at an end of a second wing, a first slot having a length through the first wing proximate the first aileron, orthogonal to the axis; a second slot having a length through the second wing proximate the second aileron, orthogonal to the axis; a first electric motor in the first wing driving a first two-blade propeller in the first slot, a second electric motor in the second wing driving a second two-blade propeller in the second slot, and a control mechanism enabling a user to drive the first and second electric motors in a same rotary direction, to reverse the rotary direction, and to drive the first and second motors at a same rpm.

Abstract: There is provided a method of mounting equipment to an aircraft having an empennage. The method comprises mounting equipment to a mounting structure for mounting to the aircraft; removing an access panel from the outer skin of the empennage of the aircraft to reveal an access panel opening into the empennage; and attaching the mounting structure to or within the access panel opening such that at least a portion of the equipment extends beyond the outer skin of the empennage. The shape of the mounting structure at least partly conforms to the shape of the access panel opening. The method also comprises covering the mounting structure and the equipment mounted thereon with a cover, and attaching the cover to the mounting structure or the empennage. An assembly, structure, tailplane and aircraft are also provided.

Abstract: A system and a method for autonomous hydrogen refueling of vertical lift aircraft using a landing pad with sensors, a hydrogen storage tank, a refueling arm configured to couple the hydrogen storage tank to the aircraft and a controller configured to control a flow of fuel from the hydrogen storage tank to the aircraft.

Abstract: Structural composite airfoils include a front C-channel spar having an upper flange coupled to an upper skin panel, and a lower flange coupled to a lower skin panel. The lower skin panel includes a joggle adjacent a lower leading edge end, with the joggle being positioned forward of the front C-channel spar. An upper skin surface of the lower leading edge end faces an internal volume defined between the upper skin panel and the lower skin panel. A lower skin surface of the lower leading edge end faces an internal surface of the upper leading edge end of the upper skin panel, and the lower leading edge end of the lower skin panel is coupled to the upper leading edge end of the upper skin panel forward of the front C-channel spar. The leading edge has a bullnose shape defined by the upper skin panel.

Abstract: A method of protecting a margin for controlling the yaw attitude of a hybrid helicopter that includes a lift rotor as well as at least one first propeller and at least one second propeller. A thrust control is configured to generate at least a first order issued to increase a first pitch of first blades of the first propeller and a second pitch of second blades of the second propeller. After a first order has been issued, the method includes an inhibition step for having a control computer inhibit the first order when a yaw attitude control margin, with regard to an envelope delimiting a flight control domain, is and/or will be less than or equal to a threshold.