25 results about "Variable geometry" patented technology

The invention discloses a morphing wing device integrating variable sweepback and variable dihedral angle functions. The morphing wing device comprises two actuating mechanisms, the actuating mechanism comprises a metamorphic mechanism and a wing connecting assembly; the metamorphic mechanism comprises an input semi-ring and an output semi-ring, and each of the input semi-ring and the output semi-ring comprises a first short rod, a second short rod and a long rod; one joint in the input half ring is a coupling joint, the corresponding joint in the output half ring is a coupling joint, and the other four joints are revolute pairs; in the input semi-ring, the first short rod and the long rod are driven by a driving device to open and close; the wing connecting assembly comprises four hooke joints and two guide rods, the two hooke joints are arranged at joints between the first short rod and the second short rod respectively, and the other two hooke joints are arranged on the two long rods respectively; the guide rod is parallel to the longitudinal axis of the wing; fixed connecting blocks, sliding connecting blocks and sliding connecting grooves are fixedly arranged on the lower surfaces of the wings; the front guide rod penetrates through the fixed connecting block and the sliding connecting block; the sliding connection groove is located between the two hooke joints on the rear guide rod.

The application discloses a shaft-symmetrical rocket-based combined engine with a variable geometry throat, which comprises a combustion chamber and a square flow channel section in communication in an axial direction from front to back; the shell of the combustion chamber is surrounded by a bottom support bottom plate and a top plate, the bottom support bottom plate is horizontal, and the top plate is a semicircular arc shape which is arched upward; the square flow channel section is a cuboid cavity, and an upper variable structure geometry throat and a lower variable structure geometry throat which are consistent with the size of corresponding holes are embedded in the holes at the upper part and the lower part; the upper variable structure geometry throat and the lower variable structure geometry throat are both plate bodies in the shape of an inclined wedge, the tip of the inclined wedge faces the rear, and the inclined surface sides of the inclined wedge both face the cavity; the upper variable structure geometry throat and the lower variable structure geometry throat are used for changing the flow channel geometry throat area in the square flow channel section. The engine is matched with the flight state by reducing the throat area with the increase of the flight Mach number, the engine performance is improved, and the engine thrust vector adjustment can be realized.

The invention belongs to the technical field of prediction and control of a supersonic air inlet channel global flow field of a ramjet engine, and particularly relates to a prediction method and a prediction system for a wide-speed-domain variable-geometry air inlet channel global flow field. The method comprises the steps that 1, wide-speed-domain variable-geometry air inlet channel flow field information is obtained; 2, based on the information obtained in the step 1, a variable geometry air inlet channel global flow field prediction data set is constructed; 3, a variable geometry air inlet channel wall surface sensor configuration scheme is constructed, and the pressure value of the variable geometry air inlet channel is collected; and 4, designing a global flow field prediction model structure of the air inlet channel based on the variable geometry air inlet channel acquired in the step 3, and realizing prediction of the global flow field of the wide-speed-domain variable geometry air inlet channel. The method is used for solving the problem that the accurate perception of the hypersonic flow field is in the future development of hypersonic velocity.

A shape forming tool for pre-carbonization shaping of a fibrous preform is provided, comprising a rounded preform and an inner die to fit within the preform. The rounded preform may be a cylindrical, conical, or frustoconical shape. The inner die may be of a non-uniform diameter and / or have complex features. The preform may shrink to conform to the inner die.

This invention discloses a method, apparatus, computer equipment, and computer-readable storage medium for correcting an adjustable guide vane clearance leakage loss model, relating to the field of variable geometry turbine adjustable guide vane technology. The method includes: constructing a database of multiple clearance flow fields for the blade tip / root clearance and structures containing a rotating shaft based on CFD experimental flow field data of a variable geometry turbine, obtaining independent leakage losses. A machine learning method, primarily using neural networks, is used to fit the corrected AMDCKO model, obtaining blade tip and root clearance loss models, which are then superimposed into a total clearance loss model without a rotating shaft. A rotation shaft correction coefficient KZ is introduced, and its diameter and position are used as variables to model the leakage loss at the tip of the adjustable guide vane containing the rotating shaft. Embedding this model into a one-dimensional performance prediction program can improve the accuracy and reliability of loss calculation, providing a scientific theoretical basis and technical support for the aerodynamic optimization design and parameter matching of variable geometry turbines.

This invention relates to the field of multibody system dynamics, specifically a dynamic modeling method for simulating the flight motion of a morphing aircraft with an arbitrary number of rotating components. The method first abstracts the morphing aircraft as a tree-like multibody system containing virtual rigid bodies and virtual hinges. Rigid bodies and hinges are uniformly numbered using a depth-first traversal search, with the relative rotation angles between rigid bodies used as generalized coordinates. Then, a path matrix is ​​used to describe the system topology, and the center-of-mass velocity, center-of-mass acceleration, angular velocity, and angular acceleration of each rigid body are derived using the generalized coordinates. Next, based on the above kinematic parameters, the deflection velocity, deflection angular velocity, generalized active force, and generalized inertial force are calculated and substituted into the Kane equations to establish the multibody system dynamic equations. Finally, the dynamic equations are solved, and the motion state is updated according to a set time step, repeating the process until the simulation of the set duration is completed. This invention has strong versatility and good scalability, and is applicable to the flight motion simulation of morphing aircraft with an arbitrary number of rotating components.

A road vehicle having a roll axis, a pitch axis and a yaw axis and comprising a rear aileron; characterized in that the rear aileron comprises two airfoils coupled to each other in a rotary manner around a pivoting pin with an axis parallel to the yaw axis so that the aileron can assume a variable geometry between an opening configuration, in which the airfoils are in series to each other along an axis parallel to the pitch axis, and a closing configuration, in which the airfoils are in parallel to each other along an axis parallel to the roll axis, going through a plurality of semi-opening configurations, in which the airfoils define a non-zero negative sweep angle toward the front portion of the vehicle.

The invention belongs to the field of aero-engine design, and particularly relates to a variable geometry two-stage low-pressure turbine aerodynamic design method which comprises the steps that a typical state point with the maximum flow and a typical state point with the minimum flow are selected respectively, through-flow design and turbine one-dimensional aerodynamic design are conducted, and a one-dimensional design result is obtained; determining turbine element blade profiles according to a one-dimensional design result, and establishing adjustable blade configurations of each stage of turbine through three-dimensional modeling; and establishing and operating a three-dimensional model of each stage of turbine, collecting turbine working parameters of each stage of turbine at typical state points of maximum flow and minimum flow, and carrying out turbine characteristic calculation of the turbine at different rotating speeds along with the change of the expansion ratio to obtain the turbine working parameters of each stage of turbine. Compared with a single-stage variable geometry turbine, the efficiency of the turbine is improved under the limited geometric size, the efficiency of the turbine is improved by 3-4% at the typical state point with the minimum flow compared with a single-stage variable geometry turbine, the variable geometry low-pressure turbine design with the wide flow adjusting range and high efficiency is achieved, and the overall performance of an engine is improved.

The application belongs to the technical field of aero-engines, and particularly relates to a variable-geometry diffuser adjustable device, which comprises a diffuser, a casing, a flame tube, an adjustable structure fixing disc, an adjustable structure rotating disc and a driving mechanism. The casing forms an annular space for mounting the flame tube. The diffuser is mounted at the front end of the casing to pass air into the annular space. The adjustable structure fixing disc and the adjustable structure rotating disc are mounted between the diffuser and the flame tube to adjust the air flow between the diffuser and the flame tube. The adjustable structure fixing disc is fixed on the casing. The adjustable structure fixing disc is provided with circumferentially distributed first air inlet holes. The adjustable structure rotating disc is rotatably and concentrically mounted on the end face of the adjustable structure fixing disc. The driving mechanism drives the adjustable structure rotating disc to rotate relative to the adjustable structure fixing disc. The adjustable structure rotating disc is provided with second air inlet holes. The angle between the adjustable structure fixing disc and the adjustable structure rotating disc is changed, and then the communication area of the first air inlet holes and the second air inlet holes is changed.

The present invention relates to methods and systems for managing engines in a low power state. Methods and systems for operating an aircraft having two or more engines are described. One method includes operating the two or more engines of the aircraft in an asymmetric operating regime, wherein a first one of the engines is in an active mode to provide power to the aircraft and a second one of the engines is in a standby mode to provide substantially no power to the aircraft; managing the first engine in the active mode using first management logic; and managing the second engine in the standby mode using second management logic, the second management logic based on a target compressor speed adjusted using a trim value and a variable geometry mechanism (VGM) setting, the trim value dependent on at least one parameter of the second engine in the standby mode.

The application belongs to the field of aero-engine design, and particularly relates to a variable-geometry two-stage low-pressure turbine aerodynamic design method, a flow maximum and a flow minimum typical state point are respectively selected to perform through-flow design and turbine one-dimensional aerodynamic design, and one-dimensional design results are obtained; turbine base element blade profiles are determined according to the one-dimensional design results, and three-dimensional modeling is respectively performed to establish adjustable blade configurations of each stage of turbine; three-dimensional models of each stage of turbine are established and run, turbine working parameters of each stage of turbine at the flow maximum and flow minimum typical state points are collected, turbine characteristic calculation of the turbine under different rotating speeds with changes in expansion ratio is performed, and turbine working parameters of each stage of turbine are obtained. The efficiency of the turbine is improved under limited geometric dimensions, compared with a single-stage variable-geometry turbine, the turbine efficiency at the flow minimum typical state point is improved by 3-4%, wide flow regulation range and high-efficiency variable-geometry low-pressure turbine design are achieved, and the overall performance of the engine is improved.

The invention provides a variable geometry non-axisymmetric elastic device for actively controlling a turbine blade tip clearance. The variable geometry non-axisymmetric elastic device is composed of an elastic retaining ring, a micro motor, a lead screw, a clearance sensor and a displacement plate. The execution unit and the controller jointly form a control part, the elastic retaining rings are evenly arranged on the inner wall of the air cylinder, and the control part is connected with the movable ends of the retaining rings and used for controlling the displacement of the movable ends of the retaining rings in the radial direction so as to adjust the turbine blade tip gap size under different working conditions, and therefore the turbine blade tip gap size is always close to the optimal blade tip gap size. The deformation of the elastic retaining ring enables the whole annular surface formed by the elastic retaining ring and the inner wall of the air cylinder to present different non-axisymmetric space curved surface shapes. The variable geometry non-axisymmetric elastic retaining ring for actively controlling the turbine blade tip clearance has the following advantages of being high in response speed, simple in structure, convenient to install, low in cost, light in weight, high in reliability, easy to maintain, long in service life of components and the like.

The invention discloses a multi-constraint anti-saturation attitude control method for a variable-shape aircraft, and belongs to the field of aircraft guidance and control. The implementation method comprises the following steps: establishing a variable shape aircraft dynamics model, and writing the model in a control matrix form; considering attitude angle constraint, giving a state tracking error, constructing an asymmetric obstacle Lyapunov function, and introducing the attitude angle constraint into controller design; giving a state tracking error by considering an attitude angular rate constraint, constructing a symmetric obstacle Lyapunov function, and introducing the attitude angular rate constraint into controller design; a composite Lyapunov function is designed, control input constraints are considered, and an attitude angular rate subsystem virtual control law is designed; and realizing the multi-constraint anti-saturation attitude control of the variable shape aircraft according to the anti-saturation attitude control law under multiple constraints. According to the invention, under strict constraints of the attitude angle, the attitude angular rate and the control input, accurate tracking of the attitude angle and the attitude angular rate can be realized, and effective suppression of control buffeting can be realized.

The invention discloses a variable geometry bulge air inlet channel adjusting device based on cam copying, and belongs to the technical field of aircraft air inlet channel adjustment. The device comprises a driving system, five sets of segmented grating cam transmission systems, a flexible skin execution system, a supporting system and a fuselage integrated supporting structure. The transmission system is arranged in a segmented mode along the length of the bump, a crossed grating layout and a transition curved surface design are adopted, the supporting system takes a symmetric point at the lower end of the bump as a rotating axis, and a shaft body and fuselage integrated structure is adaptive to a stealth design. According to the device, through the unique segmented grating cam and an integrated supporting structure, wide speed range adaptation of a bulge profile is achieved, the structure is compact, adjustment is smooth, the problem that an existing adjusting structure is insufficient in adaptability and compatibility is solved, and the requirement for an air inlet channel of an advanced aircraft is met.

The application discloses a variable-structure wave-adaptive catamaran, which comprises two floating cylinder hulls (1) symmetrically distributed along a rolling axis of the catamaran, a deck platform (4) located between the two floating cylinder hulls (1) and a power propeller (5) installed at the tail of the floating cylinder hull (1), wherein the deck platform (4) is installed on the two floating cylinder hulls (1) through a hydraulic deformation mechanism (3), so that the height of the deck platform (4) and the distance between the two floating cylinder hulls (1) can be adjusted.

The application provides a variable geometry propeller with adjustable chord and span linkage and a regulating method, and belongs to the technical field of variable geometry propellers and mechatronic actuating mechanisms. The propeller comprises a hub, a plurality of fixed main blades, a movable blade segment, and an actuating drive device. The fixed main blades are fixedly installed on the hub, and the movable blade segment is connected with a chord and span linkage regulating device. The upper and lower ends of a follow-up pin of the chord and span linkage regulating device are slidably installed in a driving sliding groove and a composite guide sliding groove of a driving regulating ring, respectively. The driving regulating ring is rotatably installed on the actuating drive device. When the driving regulating ring rotates, the movable blade segment is driven to sequentially complete radial displacement and chord displacement through cooperation of the follow-up pin and the composite guide sliding groove. The application can realize linkage regulation of the chord and span lengths with a single actuating input, and significantly improves multi-working-condition adaptability and long-term reliability.

The invention discloses a design method of a variable geometry bulge air inlet channel adjusting mechanism based on cam copying, and belongs to the technical field of aircraft air inlet channel control. The method comprises the following steps: extracting a bump cross section profile curve; curve and structure parameters of five groups of segmented grating cams are designed, wherein the parameters comprise cross grating layout and transition curved surface size; driving, supporting and flexible skin parameters are matched and designed; the structure is optimized through simulation verification; and testing a trial sample machine. According to the method, through collaborative design of the segmented cam and the cross grating, precise adaptation of the adjusting structure and the bump profile is achieved, the design process is systematic and innovative, and the adjusting performance and stability of the structure are guaranteed.

(title) TURBOMACHINE COMPRESSOR WITH A VARIABLE GEOMETRY INLET BLADE Turbomachine compressor, particularly for an aircraft or helicopter, the compressor comprising: an inlet blade (26) having a foot (30) and a head (32), the foot (30) and the head (32) defining a twist of the blade (26); and a blade orientation adjustment mechanism, the compressor being notable in that the blade orientation adjustment mechanism comprises: a first actuator (36), for pivoting the foot (30); and a second actuator (38) for pivoting the head (32), said actuators (36, 38) allowing the orientation of the blade (26) to be adjusted together, and said actuators (36, 38) being configured to be controlled independently of each other in order to vary the twist of the blade (26). (Figure to be published with the abbreviation: Figure 5)

The invention discloses a self-adaptive turbine pump system capable of repeatedly using a liquid rocket engine and a control method of the self-adaptive turbine pump system. The self-adaptive turbine pump system comprises a variable geometry inducer, an information acquisition unit composed of a pressure sensor, a temperature sensor, a rotating speed sensor and a displacement sensor is arranged on the inducer, and an execution mechanism corresponding to the inducer is arranged in a turbine pump shell; and the execution mechanism and the information acquisition unit are in common electric signal connection with a controller. The optimal flow form is adjusted in real time through the variable geometry inducer, so that the turbine pump always keeps the highest efficiency and the stable working state in the whole flight mission profile, cavitation is thoroughly inhibited, the service life is remarkably prolonged, and the harsh requirement of a reusable liquid rocket engine is met.

The invention is a traction device for a vehicle, such as a wheel or a track, comprising one or more traction accessories that can change position to transition from a position enabling traction on the ground to a position ensuring traction in or on the surface of a fluid, or even to traction on a slippery surface. The main applications are land vehicles capable of traveling on roads as well as on uneven or muddy terrain and of navigating on or in water, such as a motor vehicle, a boat capable of operating on shallow waters, a submarine, or an aircraft capable of landing on a beach or on the water.

The invention relates to a reel comprising a drum (12) with axis X and two side flanges (14) which, in an assembled position of the reel, are fixed coaxially to said drum, each side flange having a cheek extending perpendicularly to the axis X in said assembled position, the cheeks of the two side flanges defining a winding surface for a cable, at least one of said side flanges, referred to as the "reversible flange", being assemblable onto the drum in first and second configurations in which the position of the cheek (20) of said reversible flange along the axis X is different. Abstract figure: Figure 4

Gearbox with a universal self-centering system with variable geometry, having an input shaft (22) and an output shaft (19), characterized in that the universal self-centered system includes a medial foundation (1) with rollers or gears (3-5), an outer foundation (2) with rollers or gears (9-11) and a variable geometry of the outer foundation (2), wherein the geometric changes of the outer foundation (2) are realized by means of a displacement of rollers or gears (10, 11) of the outer foundation (2), wherein the rollers or gears (9-11, 3-5) attached to the foundations (1, 2) are connected to each other by a belt, rope or chain (15), wherein the movable rollers or gears (10, 11) on the outer base (2) are cushioned and movable with respect to a center of rotation of the outer base (2) under the effect of a load on the gearbox.