17 results about "High-lift device" patented technology

An aircraft wing assembly includes a wing box including an upper surface, a lower surface, and a leading edge structure connecting the upper surface to the lower surface and secured to the upper surface at a connection point. The aircraft wing assembly includes a drive mechanism secured to the wing box and a high lift device mounted to the drive mechanism. The drive mechanism is configured to move the high lift device between a retracted position and an extended position in use, and wherein the high lift device is configured to overlap the connection point when in the retracted position.

The invention discloses an aircraft high lift device two-dimensional to three-dimensional optimization method based on deep reinforcement learning, and belongs to the technical field of aircrafts. According to the method, in an environment based on two-dimensional computational fluid mechanics, an efficient and universal aircraft high lift device optimization strategy suitable for a target three-dimensional optimization problem is trained, the training cost of the three-dimensional optimization problem is remarkably reduced, and high calculation overhead of traditional three-dimensional flow field simulation is avoided; the flow field locality and strategy translation invariance are utilized to decompose a three-dimensional problem into a plurality of two-dimensional profiles for independent optimization, so that an intelligent agent only needs to process a low-dimensional action space, and the problem of curse of dimensionality caused by a high-dimensional action space is effectively solved; when the trained intelligent agent is used for solving the similar optimization problem, the optimization efficiency is high, the convergence speed is high, and the method has high universality for variable design working conditions and the appearance of the high lift device by means of the previous experience for solving the similar problem.

To provide a high-lift device capable of sufficiently bringing out a performance.SOLUTION: A high-lift device includes: a blade; a flap stored in a storage continuous to a front edge of the blade and expanding in front of the front edge; and a link mechanism for moving the flap between a standby position of being stored in the storage and a deployment position of expanding forward. The front edge of the blade includes an interference avoidance opening through which a link member constituting the link mechanism enters and exists when moving between the standby position and the deployment position.SELECTED DRAWING: Figure 1

A wing assembly is disclosed having a fixed wing portion, a high-lift device, and a connecting assembly movably connecting the high-lift device to the fixed wing portion, such that the high-lift device is movable between a retracted position and at least one extended position. The connecting assembly includes a first connecting element, which extends from a first end portion, at which the first connecting element is rotatably connected to the fixed wing portion, to a second end portion, and a second connecting element, which extends from a first end portion, at which the second connecting element is rotatably connected to the second end portion of the first connecting element, to a second end portion.

The invention discloses a compressible turbulence frictional resistance decomposition method and device, a medium and equipment. The method comprises the following steps: acquiring an instantaneous variable of a compressible turbulence flow field to be subjected to resistance decomposition; calculating an average value and a pulsation value of a plurality of single variables in the vorticity transport equation based on the instantaneous variables; respectively calculating the spatial derivative value of the average value, the spatial derivative value of the pulsation value and the spatial derivative value of the instantaneous variable of each single variable; according to the average value, the pulsation value and the spatial derivative value of each single variable, calculating the average value and the pulsation value of a plurality of combined variables; performing integral calculation on a plurality of parameters of the vorticity transport equation based on the average value and the pulsation value of the plurality of combined variables; and calculating the contribution value of each parameter to the compressible turbulence friction resistance according to the integral calculation result of each parameter. The device fills the blank of compressible fluid mechanics, can be applied to high lift devices such as vortex generators, and has the advantages of high comprehensiveness, diversity and universality.

A high-lift device is provided that can sufficiently exert performance. The high-lift device includes a wing, a flap configured to be retracted in a storage communicating with a leading edge of the wing and to be extended to a front side of the leading edge, and a link mechanism configured to move the flap between a standby position where the flap is retracted in the storage and a deployment position where the flap is extended to the front side. The wing's leading edge includes an interference-avoidance aperture through which a link member in the link mechanism moves in and out when the link member moves between the standby and deployment positions.

The present invention relates to a leading edge assembly (9) for a wing (3). The leading edge assembly includes a housing (11) and an actuating element (13). The housing is configured to be connectable to a fixed wing section (59) of the wing (3), and a first opening (19) is formed in the housing that connects the exterior (45) of the housing (11) to the interior (47) of the housing (11). The actuating element is movably connected to the housing (11) such that the actuating element (13) can move between a first position and at least one second position. The actuating element (13) extends through the first opening (19) and includes a first section (49) and a second section (51). The first section is disposed in the interior (47) of the housing (11), and the second section is disposed in the exterior (45) of the housing (11) and is configured to be connectable to a high-lift device.

The invention relates to the technical field of aerodynamic noise reduction of aviation aircrafts, and particularly discloses a noise reduction method for a slat sliding rail of a high lift device for blocking a main wing notch. According to the method, a main wing notch is dynamically sealed through an elastic plugging part, and airflow disturbance noise in a sliding rail cabin is restrained. When the front edge slat is opened, the blocking component seals the notch, and airflow is prevented from entering the sliding rail cabin. The shape of the plugging component is in smooth transition with the pneumatic shape of the main wing, the thickness is equivalent to that of the skin, the plugging component is made of a silicone rubber-carbon fiber reinforced composite material, the outer side of the plugging component is fixed through a high-strength aviation adhesive, the edge is coated with a polysulfide sealant layer, and the inner side and the sliding rail form a closed structure. Experiments prove that the broadband noise is reduced by about 3-5 dB, the sound pressure level at the center frequency of 6000 Hz is reduced by 10 dB, and the aerodynamic performance loss can be neglected.

A support arrangement for a leading-edge high lift device comprising a support arm for movably supporting the leading-edge high lift device on a wing structure. In order to accommodate the supply of the leading-edge high lift device with a fluid such as an anti-ice fluid, for example pressurized hot air, the support arm is configured as a fluid conduit for feeding fluid to and / or from the leading-edge high lift device. The leading-edge high lift device may be configured as a droop nose device.

A leading-edge high-lift device is deployable and retractable from / into a fixed leading edge of a main wing of an aircraft and includes a slat main body and a buffering portion. The slat main body includes a leading edge portion, a trailing edge portion, a cusp portion formed at a lower edge of the leading edge portion, a cove portion formed between the cusp portion and the trailing edge portion, and an inboard end surface that is formed between the leading edge portion and the cove portion and is positioned on a fuselage side of the aircraft. The buffering portion is provided at an inboard end portion of the slat main body including the inboard end surface and an inboard-side surface of the cove portion and reduces pressure fluctuations in airflow on the inboard end surface or the inboard-side surface of the cove portion.

The utility model provides an aviation turbofan engine outer duct airflow high lift device and a vector control device, and belongs to the technical field of aerospace. The outer duct airflow high lift device of the aviation turbofan engine comprises an outer mounting ring, an inner fixing ring and an airflow high lift assembly. And the two airflow lift augmentation assemblies comprise lift augmentation front edge plates, the two lift augmentation front edge plates are fixedly connected with the opposite faces, in the transverse direction, of the outer mounting ring and the inner fixing ring correspondingly, and one sides of the two lift augmentation front edge plates are rotationally connected with lift augmentation rear edge plates. According to the high-bypass-ratio turbofan engine, the lift augmentation assembly and the direction control surface are additionally arranged on the outer duct of the high-bypass-ratio turbofan engine, airflow distribution and the vector direction in the outer duct are accurately regulated and controlled, collaborative optimization of thrust and lift force of the engine is achieved, and therefore the overall efficiency and fuel economy of the engine are improved.

Systems and methods according to embodiments of the present technology vary engine throttle and flight control surfaces (such as high-lift devices, which can include flaps and / or slats) during takeoff, climb, approach, and / or landing of a supersonic aircraft to reduce noise. A representative computing device automatically controls thrust output of the propulsion system according to a schedule of thrust output, such that the thrust output remains below levels at which the jet exhaust becomes supersonic, and such that noise is reduced to comply with noise regulations or other limitations. The computing device also automatically controls the position and configuration of flight control surfaces to compensate for the reduced thrust and to maintain an appropriate climb and / or descent rate.

High lift systems for aircraft and associated methods are provided. A high lift system includes a movable high lift device, an inboard track for guiding an inboard portion of the high lift device, and an outboard track for guiding an outboard portion of the high lift device. An actuator drives the high lift device between a retracted position and a deployed position. The actuator is disposed inboard of the inboard track. An inboard bell crank connects the actuator to the inboard portion of the high lift device. An outboard bell crank connects the actuator to the outboard portion of the high lift device. A connecting link connects the inboard bell crank to the outboard bell crank such that the outboard bell crank driveably connects the actuator to the outboard portion of the high lift device via the connecting link and the inboard bell crank.

A method for determining morphological parameters of a high lift device and a computing device, a first sample set and a second sample set are obtained, the first sample set is composed of a plurality of first training samples including low-precision performance tags, and the second sample set is composed of a plurality of second training samples including high-precision performance tags; the number of the second training samples is smaller than that of the first training samples; training a performance prediction model by using the first sample set and the second sample set, and performing forward propagation by using a low-precision prediction branch and an output layer for the first sample set; forward propagation is carried out on the second sample set by using a high-precision prediction branch and an output layer; the performance prediction model is used for determining the recommended morphological parameters in the parameter space after being trained, and the recommended morphological parameters can be determined in the preset parameter space with low calculation cost and time cost.

An aircraft (10) comprising: a starboard swept wing (14A) and a port swept wing (14B), each swept wing having an inner wing section (32) comprising an integrated payload fuselage and an outer wing section (34) for extending the wingspan, in which each outer wing section (34) has a thickness less than a thickness of the corresponding inner wing section (32); a central region (12) where the starboard swept wing meets the port swept wing; a starboard transition region where the starboard inner wing section (32A) meets the starboard outer wing section (34A); a port transition region where the port inner wing section (32B) meets the port outer wing (34B) section; in which at least one high-lift device is disposed on or at a trailing edge of the inner wing section of each swept wing.

The invention relates to a high-lift device for an aircraft of a lifting surface, to a lifting surface and to an aircraft. In one aspect, a high-lift device for an aircraft of a lifting surface is described. The high-lift device comprises a skin comprising an upper skin, a lower skin and a nose, the high-lift device comprising: - a flexible skin implementing a deformed high-lift device, the flexible skin having a rear upper edge and a rear lower edge, at least the rear upper edge sliding along a chord direction between a retracted position and an extended position; - a linear actuator connected to the nose and connected in a pivotable manner to the lifting surface between a retracted position and an extended position, such that in the extended position, the nose is in a downward position relative to the position of the nose in the retracted position and at least the rear upper edge is in a forward position relative to the position of the rear upper edge in the retracted position.

An aircraft 10 comprising: a starboard swept wing 14A and a port swept wing 14B, each swept wing having an inner wing section 32 comprising an integrated payload (5, not shown) fuselage and an outer wing section 34 for extending the wingspan, in which each outer wing section 34 has a thickness less than a thickness of the corresponding inner wing section 32; a central region 12 where the starboard swept wing meets the port swept wing; a starboard transition region where the starboard inner wing section 32A meets the starboard outer wing section 34A; a port transition region where the port inner wing 10 section 32B meets the port outer wing 34B section; in which at least one high-lift device 26A, 26 B is disposed on or at a trailing edge of the inner wing section of each swept wing.