21results about "Influencers by generating vortices" patented technology

A wing assembly for an aircraft including a fixed wing and a wing tip device rotatable about a joint assembly. The wing assembly is configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. The wing assembly includes joint-bordering structure located adjacent the joint assembly, the joint-bordering structure having a rib, an upper cover and a lower cover. The joint assembly includes a moveable panel. The panel includes a first hard stop element, and the joint-bordering structure includes a second hard stop element. The first hard stop element is integrally formed in the panel, and the second hard stop element is integrally formed in one of the rib, the upper cover or the lower cover of the joint-bordering structure. The hard stop elements may be configured to self-align.

A hinge arrangement for an aircraft wing is provided, for providing a folding wingtip. The hinge arrangement comprises a first mount for securing in a first wing section and a second mount for securing to a second relatively foldable wing section, each having a plurality of hinge elements arranged along a hinge axis. The arrangement comprises a latching arrangement for securing the mounts against folding movement, the latch arrangement having a latch axis being spaced from the hinge axis in a substantially spanwise direction for example so as to extend into the wing box. This can provide an efficient arrangement which may be contained within the outer mould line of the wing which can reduce the need for a fairing.

Vortex generators include a vane that rotates between a stowed position and a deployed position. In the deployed position, the vane is configured to reduce noise created by an airflow around or along the aerodynamic surface. A spring controls deployment of the vane and includes an elongate tube formed of a superelastic shape memory alloy. To deploy or stow the vane, the elongate tube is twisted due to a stress-induced response caused by airflow around or along the aerodynamic surface, thereby building up and storing torque in the elongate tube. A mounting base receives the vane when it is in the stowed position, and operatively couples the vortex generator to the aerodynamic surface. To create the torque in the elongate tube, a first end of the elongate tube is fixed with respect to the aerodynamic surface while a second end of the elongate tube is free to rotate.

An assembly (30) is provided for an aircraft propulsion system (20). This assembly (30) includes an open propulsor rotor (34) and an open guide vane structure (36). The open propulsor rotor (34) is configured to rotate about an axis (24). The open propulsor rotor (34) includes a plurality of open propulsor blades (42) arranged circumferentially about the axis (24) in a blade array. Each of the open propulsor blades (42) projects spanwise into an environment (22) external to the aircraft propulsion system (20) to a respective blade tip (46). The open propulsor blades (42) include a first span propulsor blade (42A) and a second span propulsor blade (42B). The first span propulsor blade (42A) has a first span length (48A). The second span propulsor blade (42B) has a second span length (48B) that is less than the first span length (48A). The open guide vane structure (36) is axially next to the open propulsor rotor (34).

This invention relates to the field of aerodynamic component technology, and in particular to a wing spoiler device for a ground effect vehicle (GEV). The wing spoiler device for a GEV includes: a base, a movable flap, the front end of which is hinged to the front of the base, and the rear end of which is fixed to the rear of the base via an adjusting fastener passing through a pre-set first adjusting and fixing hole. The spoiler device is mounted above the front wing of the GEV via the base, so that when the incoming airflow passes over the upper wing surface, it obstructs the downwash airflow converging at the trailing edge of the wing, generating vortices inside the spoiler device to reduce the lift of the upper wing surface and increase the ground effect ratio of the lower wing surface, thereby suppressing the aerodynamic center of gravity shift of the GEV. The advantages of this invention are its simple structure, low manufacturing cost, and the elimination of the need for active control components such as servos or other transmission electronic devices. It also features a robust structure, better adaptability to harsh water environments, reduced safety hazards, and extended service life of the aircraft.

A passenger vertical take-off and landing aircraft includes a flying wing comprising a passenger compartment, a first set of rotors positioned at least partially forward of a leading edge of the flying wing, and a second set of rotors positioned at least partially rearward of a trailing edge of the flying wing. The first set of rotors may include at least four rotors and the second set of rotors may comprise at least two rotors. The first set of rotors, the second set of rotors, both, or neither may be tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft.

There is provided a twin rudder arrangement (300) for a craft (250). The twin rudder arrangement (300) comprises a first rudder blade (310) and a second rudder blade (320), wherein the first rudder blade (310) and the second rudder blade (320) are configured to be provided at either side of a propeller (200) of the craft (250). At least part of the first rudder blade (310) or the second rudder blade (320) comprises a vortex generator arrangement (400), wherein the vortex generator arrangement (400) is arranged to induce vortices in fluid flow passing / interacting with the twin rudder arrangement (300). Also provided is an aircraft or watercraft comprising at least one twin rudder arrangement (300).

A wing hinge assembly (13) is disclosed. The wing hinge assembly (13) comprises a wing tip fitting (19) pivotally mounted to a fixed wing fitting (15). The wing tip fitting (19) is rotatable about a hinge axis (H) with respect to the fixed wing fitting (15). One of the wing tip fitting (19) and the fixed wing fitting (15) defines a locking channel (26). The other of the wing tip fitting (19) and the fixed wing fitting (15) comprises a locking member (34) which defines a locking member axis. The wing hinge assembly (13) is configurable to a locked configuration in which the locking member (34) is received in the locking channel (26) by moving the locking member (34) in a direction perpendicular to the locking member axis.

A flight vehicle includes: a rotor shaft projecting upward from a body; a rotor head connected to the rotor shaft at an upper side of the body; and a pair of plate structures located at the upper side of the body and extending in a front-rear direction at right and left sides of the rotor shaft. Each of the pair of plate structures includes a front end, a rear end, an inner surface facing inward in a left-right direction, and an outer surface facing outward in the left-right direction. The front ends of the pair of plate structures are located away from each other in the left-right direction. The rear ends of the pair of plate structures are located away from each other in the left-right direction. Each of the pair of plate structures has such a shape that during forward flight, pressure at a side where the outer surface is located becomes lower than pressure at a side where the inner surface is located.

The invention relates to a flow control device (60) located on a structural member such that strain in the structural member is at least partially transferred to the flow control device. The flow control device has at least two states or shapes separated by an elastic unstable region. The flow control device is arranged to rapidly transition or snap from a first state to a second state when strain in the structural member exceeds an activation threshold of the flow control device (60). In an example, a spoiler (12) on an airfoil has a rest position in which the spoiler is substantially flush with a low pressure surface and an activated position in which the spoiler protrudes from the low pressure surface and changes the airflow over the surface. The spoiler (12) flexes to move from the rest position to the activated position when strain in the airfoil exceeds a threshold. The deployed spoiler (12) reduces lift on the airfoil, thereby reducing strain in the airfoil to which the spoiler is attached due to lift.

A mould for moulding a sleeve of protective material 25 onto a wiring harness 15. The mould comprises: a mould body 33; an inlet 37; an outlet 39; and a channel 35 extending through the mould body 33 and connecting the inlet 37 to the outlet 39. The mould also comprises a plurality of centralising spacers 41, configured to hold the wiring harness 15 centrally within the channel 35 as the wiring harness 15 extends between the inlet and the outlet. The mould also comprises an injection port and an exit port arranged to convey fluid sleeve material into and out of the channel. The channel 35 follows a path along a helical curve as it extends between the inlet and the outlet of the mould.

The invention relates to a flow control device on a structural member such that strain in the structural member is at least partially transferred to the flow control device. The flow control device has at least two states or shapes separated by an elastic unstable region. The flow control device is arranged to rapidly transition or snap from a first state to a second state when strain in the structural member exceeds an activation threshold of the flow control device. In an example, a spoiler on an airfoil has a rest position in which the spoiler is substantially flush with a low pressure surface and an activated position in which the spoiler protrudes from the low pressure surface and changes the airflow over the surface. The spoiler flexes to move from the rest position to the activated position when strain in the airfoil exceeds a threshold. The deployed spoiler reduces lift on the airfoil, thereby reducing strain in the airfoil to which the spoiler is attached due to lift.

An aircraft wing is disclosed having a main fixed wing portion and a wing tip device at a tip thereof. The wing tip device is configurable between a flight configuration and a ground configuration, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced. A hinge arrangement connects the main fixed wing portion and the wing tip device and enables the wing tip device to rotate between the ground configuration and the flight configuration. The hinge arrangement protrudes beyond an outer surface of the main fixed wing portion and wing tip device. A fairing covers at least part of the hinge arrangement on at least a suction side of the wing.

A rotary actuator mounting system configured to attach a rotary actuator (10) to and between two relatively moveable parts (1, 2), the rotary actuator being attached to a first (1) of the two relatively moveable parts and to a second (2) of the relatively moveable parts such that operation of the actuator causes one of the first and second relatively movable parts to rotate relative to the other of the first and second relatively movable parts about an axis of the rotary actuator, the system further comprising a compliant attachment component (30) connecting the actuator to the first relatively moveable part, the compliant attachment component having a first end (301) attached to the first movable part (1) and a second end attached to the actuator (10), and wherein at least one of the first and the second end is in the form of a ball bearing arranged to be received in a complementary socket on the actuator and / or the first movable part.

An aircraft wing is disclosed having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing, such that the wing tip device is rotatable about the hinge, and an actuation system for rotating the wing tip device about the hinge. The actuation system includes a motor, at least one geared rotary actuator, a reduction gearbox, a clutch for selectively decoupling rotation of the motor from rotation of the geared rotary actuator, the geared rotary actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion and is arranged to rotate the wing tip device relative to the tip of the fixed wing. The reduction gearbox is positioned between the clutch and the geared rotary actuator along a drive train between the motor and the geared rotary actuator.

An aircraft wing comprising: a wing structure supporting a wing cover, the wing cover having an outer aerodynamic surface, which forms part of an aerofoil profile of the wing, and a recess stepped back from the wing aerofoil profile; and a spoiler device comprising a spoiler coupled to the wing structure by a spoiler actuation mechanism for moving the spoiler between a retracted position and a deployed position, the spoiler having a surface which follows a contour of the wing aerofoil profile and where the spoiler is housed entirely in the recess when the spoiler is in the retracted position, and wherein the spoiler surface is extended away from the wing cover when the spoiler is in the deployed position.