31 results about "Propulsive efficiency" patented technology

The application provides a variable impulse method for manta ray-like vehicle attitude control through bypass internal flow distribution, a propeller serving as a propelling system and a flow distributor with adjustable position arranged at an outlet end of a power duct module are fused and designed, axial water flow generated by the single propeller is directly used as propelling power and attitude control direct power, the flow of each jetting outlet can be adjusted without changing the propeller rotating speed through position adjustment of the flow distributor arranged at the outlet end of the power duct module, the impulse of water flow of upper and lower jetting outlets is quickly changed, upper and lower thrust difference is formed on the bionic body, the pitching moment is changed without changing the propelling process, the attitude adjustment of the bionic vehicle is accurately realized, and the system efficiency, dynamic response and task adaptability are coordinately improved on the basis of keeping the original propelling efficiency advantage.

The application provides a kind of propulsive efficiency calculation method of aircraft, by obtaining the first target parameter of orbit transfer thruster, and determine the first ignition duration of orbit transfer thruster;Obtain the second target parameter of attitude control thruster, and determine the second ignition duration of attitude control thruster;According to the interference moment and control moment in the first target parameter and the second target parameter, determine the function relationship between the first ignition duration and the second ignition duration based on angular momentum conservation;According to the function relationship, the flow of orbit transfer thruster and the flow of attitude control thruster, calculate the consumption propellant proportion of the orbit transfer thruster and the attitude control thruster during the n time ignition;According to the consumption propellant proportion, calculate the thruster efficiency value during the n time ignition;According to the thruster efficiency value calculated during each ignition, obtain the total thruster efficiency value during total ignition.

The application provides a bulk carrier main engine power prediction method and system, and relates to the technical field of green ships and intelligent shipping. The method realizes high-precision and high-robustness prediction of the bulk carrier main engine power through the following steps: sister ship operation big data collection preprocessing, Pearson correlation feature screening, wave resistance explainable separation based on the two-factor Froude method and the iteration of resistance and propulsion efficiency, fusion of SVM to build a physically mechanism-constrained grey-box prediction model, and comparison and optimization of a black-box model. The method has physical explainability, can meet the consistency verification of the Minimum Propulsion Power Guidelines, can be quickly modeled and calculated online in real time relying on conventional operation data, can be reused for the same series of ship types, and has outstanding engineering practicability and maritime compliance.

This invention discloses a method for optimizing the propulsion performance of a biomimetic flapping wing under multiple operating conditions, relating to the fields of biomimetic fluid mechanics and propulsion technology. The method includes steps such as selecting the airfoil of the biomimetic flapping wing, setting the distance between the pitch axis and leading edge of the biomimetic flapping wing, setting the motion mode of the biomimetic flapping wing, adjusting the phase difference and pitch amplitude to match the motion mode of the biomimetic flapping wing under different operating conditions, setting the pitch frequency to be equal to the heave frequency, adjusting the pitch motion mode according to the pitch amplitude, and calculating the propulsion power coefficient and propulsion efficiency of the biomimetic flapping wing. This invention achieves precise control of different propulsion directions by optimizing the phase difference under different operating conditions; it determines the optimal frequency matching relationship to avoid propulsion performance degradation caused by frequency mismatch, ensuring stable and efficient operation of the flapping wing under all operating conditions; and it optimizes non-harmonic motion parameters for large pitch amplitudes, increasing propulsion efficiency to 24.10%, a 71% improvement compared to harmonic motion, significantly reducing energy loss.

The application discloses a variable airfoil propeller design and optimization method of a water-air cross-medium vehicle, and belongs to the field of artificial intelligence. The method comprises the following steps: coupling CST parameterized variables and a GAN generator to obtain a CST-GAN airfoil generation model; defining a chord length and a pitch angle distribution function and an airfoil transformation position, and generating a three-dimensional propeller geometric model; calculating aerodynamic force and hydrodynamic characteristics by using different resolution grids, and constructing a multi-precision data set; establishing a multi-precision neural network, and training a surrogate model by using a transfer learning method; and taking water-air propulsion efficiency as a multi-objective optimization function, and searching for a Pareto optimal solution by using a multi-objective optimization algorithm. The application expands the design space by using the CST-GAN, and effectively solves the cross-medium performance balance problem while reducing the calculation cost by combining a multi-precision transfer learning strategy, so that the efficient design and optimization of the propeller are realized.

This invention provides an integrated propeller wheel for amphibious transport vehicles, belonging to the technical field of amphibious transport vehicle technology. The invention designs an integrated propeller wheel structure comprising a hub base, spoke supports, blade bending bodies, and an annular outer ring. It configures an angle adjustment mechanism consisting of an adjustment ring and push-pull rods, and combines this with a spoke adjustment module within a control chip. A seven-step closed-loop control algorithm based on a state matrix, adjustment command matrix, resistance correction matrix, and interference compensation matrix is ​​established to achieve real-time adaptive adjustment of the angles of the eight spoke supports. By sensing changes in operating conditions through speed sensors and environmental detection sensors, the optimal geometric parameters are automatically calculated based on a preset optimization model, and precise adjustments are executed. This eliminates fluid interference between adjacent spokes, solving the technical problem of existing technologies that struggle to adaptively adjust propeller wheel geometric parameters to achieve optimal propulsion efficiency during the operation of amphibious transport vehicles.

The application provides a cruise ship shafting propulsion system, which comprises a shafting, a propeller connected to an output end of the shafting, a driving device for providing rotary driving force to the propeller, and a shaft coupling connecting the shafting and the driving device, wherein the rotation speed of the driving device is the same as that of the propeller; and the system further comprises a thrust bearing assembly, which comprises an outer shell and a thrust bearing, the outer shell is fixed to a ship body, an inner cavity is formed in the inner shell, and the thrust bearing is arranged in the inner cavity and sleeved on the outside of the shafting and used for bearing at least axial force of the shafting. The application can improve the propulsion efficiency of the cruise ship, reduce noise and vibration, save engine room space, and reduce maintenance cost.

The utility model belongs to life-saving equipment technical field, specifically disclose a kind of modularization pump spray propeller and lifesaving equipment.The utility model's modularization pump spray propeller, impeller of propeller operates in the uniform flow field in fairing, can effectively utilize inflow ram, so that it can better improve anti-cavitation performance at high speed, reach higher propelling efficiency, and not susceptible to water flow condition and sailing speed influence;The motor speed of propeller is changed by electronic speed regulator, to change the water velocity of fairing water outlet jet, and then the propelling force of propeller can be quickly changed;The motor speed of lifesaving equipment two sides propeller is changed by electronic speed regulator, to change the water velocity of two sides fairing water outlet jet and produce speed difference, that is, the quick steering of lifesaving equipment can be realized;Even if lifesaving equipment overturns, because the upper end and lower end of lifesaving equipment stern are all provided with propeller, the normal propelling use of lifesaving equipment is not affected.

This invention belongs to the field of ship propulsion efficiency prediction technology, and discloses a method and system for predicting ship propeller efficiency. The method includes constructing an autoencoder and pre-training it on data; using the trained autoencoder as input, constructing a physical information neural network using the relevant physical equations of propeller propulsion efficiency; introducing a regularization term to determine the final loss function; predicting propeller efficiency using the trained neural network; and iterative optimization and application of the model. This invention, by introducing an autoencoder and a regularized loss function, effectively improves the accuracy and reliability of propeller efficiency prediction under complex sea conditions, and overcomes the limitations of traditional prediction models in handling nonlinear dynamic responses.

The utility model discloses a kind of efficient low-noise bionic annular conduit propeller based on multi-biometric feature cooperation, including annular conduit and annular propeller assembly, annular conduit adopts round tube structure, and the cross section along its axial direction is two airfoil sections.Annular conduit front end has wavy leading edge array, and annular conduit rear end is sawtooth array, the number of wavy protrusion is equal to the number of sawtooth, and respectively one-to-one correspondence.Annular propeller assembly is located annular conduit inside, and it includes central shaft and multiple annular blades.The circumference outer wall of annular conduit has multiple wavy grooves continuously distributed along its circumferential direction, and wavy groove extends along the axial direction of annular conduit.The utility model constructs annular conduit by area to three kinds of bionic characteristics of whale forefin node, owl feather split and long-eared owl wing surface groove, break through traditional blade tip vortex energy dissipation bottleneck in combination with annular propeller, and comprehensive propulsion efficiency is improved, cavitation critical coefficient is improved, and wideband noise is significantly reduced.

This invention discloses a propulsion efficiency improvement device. An embodiment of this invention includes: a duct disposed in front of a propeller, formed in an arc shape and used to generate thrust; and a plurality of pre-spin stators supporting the duct to a stern boss portion for generating a swirling flow in the opposite direction to the propeller's rotation direction.

This invention belongs to the field of ship propulsion efficiency prediction technology, and discloses a method and system for predicting ship propeller efficiency. The method includes constructing an autoencoder and pre-training it on data; using the trained autoencoder as input, constructing a physical information neural network using the relevant physical equations of propeller propulsion efficiency; introducing a regularization term to determine the final loss function; predicting propeller efficiency using the trained neural network; and iterative optimization and application of the model. This invention, by introducing an autoencoder and a regularized loss function, effectively improves the accuracy and reliability of propeller efficiency prediction under complex sea conditions, and overcomes the limitations of traditional prediction models in handling nonlinear dynamic responses.

The application discloses an anti-icing channel propeller and belongs to the technical field of ship and ocean engineering equipment. The anti-icing channel propeller comprises an inlet section, a first curved section, a curved connection section, a second curved section and an outlet section which are sequentially connected, a propeller is arranged in the outlet section, the shape of the first curved section is variable, a curvature adjusting device is arranged on the first curved section, the curvature adjusting device is used for adjusting the curvature of the first curved section, an inertia locking cavity is further arranged in the first curved section, and the inertia locking cavity is used for making high inertia ice blocks collide and break. Through the collaborative design of the curvature adjusting device and the inertia locking cavity, the application realizes smooth flow guiding in an ice-free area and active deformation interception in an ice area, thereby completely solving the structural conflict between propelling efficiency and anti-icing capability and greatly improving the all-weather survival capability and economic benefits of a polar ship.

The present application relates to the technical field of aviation, and in particular to a supersonic civil aircraft configuration. In the supersonic civil aircraft configuration of the present application, engine nacelles are mounted above a rear fuselage between wings and horizontal stabilizers; the lower portions of inlets are shielded by the trailing edges of the wings, and the lower portions of outlets are shielded by the leading edges of the horizontal stabilizers; by means of the shielding effect of the wings and the horizontal stabilizers, shock waves generated by engines are prevented from propagating to the ground, effectively reducing the ground sonic boom loudness of such an aircraft; the engines and pylons can perform small-angle pitch deflection around pivot shafts in the pylons, thereby adjusting mounting angles of the engines and improving the propulsive efficiency of the engines under off-design operating conditions; during supersonic cruising, the tips of the horizontal stabilizers can be folded upward to provide an additional vertical stabilizer volume, so as to compensate for the loss of vertical stabilizer efficiency during supersonic cruising, and preventing expansion waves generated by engine exhaust nozzles and the horizontal stabilizers from propagating to the ground; and during low-speed takeoff / landing, the tips are unfolded to ensure a large vertical stabilizer area, so as to meet the requirements of trim in takeoff / landing configuration.

A propulsion system includes a drive turbine connected to a drive shaft movable in rotation about an axis of rotation, a fan section including a fan rotor connected to a fan shaft, and a reduction structure coupling the drive shaft and the fan shaft in order to drive the fan shaft at a rotation speed lower than the rotation speed of the drive shaft. In the propulsion system, a rotation speed of the drive shaft complies with a formula defining a relationship among the rotation speed of the drive shaft, an inlet temperature of the drive turbine when the propulsion system is stationary in a take-off rating in a standard atmosphere and at sea level, and an inlet section of the drive turbine, in square meters.

The invention provides a propeller blade and a ship propeller, relates to the technical field of propellers, and solves the problems that the working efficiency of the propeller blade is reduced, the energy consumption of a ship engine is increased by increasing the length of the propeller blade to improve the efficiency, and the collision risk is high. The propeller blade comprises a small blade structure and a blade body with an upstream blade surface and a blade following edge, the small blade structure is only fixedly arranged at the blade tip end of the blade body, or the small blade structure is only fixedly arranged at the blade tip end of the blade body and a connecting section of the blade following edge and the blade tip end; the small paddle structures extend in the direction away from the water facing blade surface; a non-zero included angle is formed between the upstream face of the small paddle structure and the upstream surface of the paddle body, so that a container structure for containing water flow is formed. Water flow is held under the action of centrifugal force and is fully accelerated in the container structure, and under the condition that the size of the propeller is kept unchanged, the propelling efficiency is effectively improved, the energy consumption is reduced, and the risk of colliding with underwater obstacles is reduced.

The utility model relates to propeller fishing net cutter mechanism technical field, disclose a propeller fishing net cutter mechanism, including propeller body and flow guide cap, the tail outer wall of propeller body is provided with propeller blade, the back of propeller body and the inside of flow guide cap are provided with cutter assembly, the cutter assembly includes driving pulley, the outer wall of flow guide cap is provided with cutting groove, when propeller body rotates, can drive driving pulley synchronous rotation through the cutter assembly of setting, through the meshing drive of driving pulley and driven pulley, drive cutter head and cutter body high -speed rotation, such design can cut in advance the fishing net, rope and so on sundries of entering the flow guide cap area, effectively prevent its winding to propeller blade root part or wheel hub gap, avoid the propelling efficiency decline or propeller damage risk caused by sundries winding, significantly improved the ship navigation safety and reliability.

This invention relates to a small tandem biplane unmanned aerial vehicle (UAV) configuration with ducted thrust reduction at the wingtip, comprising: a fuselage; a main wing fixedly connected to the middle or front of the fuselage; a horizontal tail fixedly connected to the rear of the fuselage, arranged in tandem with the main wing; and a ducted propulsion unit disposed at the wingtip of the main wing and / or the horizontal tail, the ducted propulsion unit comprising a duct body, ducted blades rotatably disposed within the duct body, and a motor for driving the ducted blades to rotate; wherein the axial direction of the duct body extends in the same direction as the average incoming flow direction at the corresponding wingtip. This invention solves the problems of wingtip drag reduction, propulsion efficiency, and structural adaptability in existing small tandem biplane UAVs, achieving synergistic effects of drag reduction and propulsion, and improving aerodynamic efficiency, endurance, and flight safety.

The utility model relates to the technical field of side thruster fairing and discloses a fairing structure of bulk carrier bow side thruster, including the fairing body, the mounting block of fixed mounting in the lateral wall of fairing body and set up in the fairing body side position's fairing subassembly, the fairing subassembly includes the fairing mechanism of setting up in the inner wall position of fairing body, the side position of fairing body is provided with auxiliary mechanism, the fairing mechanism includes stable frame, stable frame fixed mounting is in the inner wall of fairing body, the inner wall of stable frame is rotatably installed with the fairing board through the bearing, the inner wall sliding installation of the top of fairing board is provided with the adjusting rod of chute. The utility model solves the problem that the existing fairing mostly adopts simple cylindrical or conical design, has big water flow resistance, and the fairing effect is not good, leads to the low side thruster propulsion efficiency, thereby influences the steering stability of ship.

The application discloses a kind of active arc excitation type linear track electromagnetic propulsion device, it is related to electromagnetic propulsion field, and the device mainly includes track pair, armature projectile, pulse power supply and active arc device;By configuring active arc device with sharp contact in the inside of track, and according to the set order, main pulse power supply is turned on, active arc device is excited, so that closed loop is formed between armature projectile and track pair by arc, armature projectile is propelled by electromagnetic force in the magnetic field generated by electrified track, and keeps non-contact suspension state with track in the whole acceleration process.The application replaces traditional physical contact with controllable arc, fundamentally eliminates the friction loss between armature projectile and track, significantly improves track life, propulsion efficiency and motion controllability, realizes efficient, low-loss electric energy-kinetic energy conversion.

The present invention relates to a controllable pitch propeller capable of changing the pitch of the blade according to the navigation conditions of the ship, and particularly, to a controllable pitch propeller having an optimum hub to tip diameter ratio, which is capable of reducing the size of the hub in order to have a high efficiency close to the propulsive efficiency of a fixed pitch propeller (FPP). In order to achieve the above-mentioned object, the present invention relates to a controllable pitch propeller comprising a hub mounted at the propulsion shaft of the ship and a blade mounted at the circumference of the hub and having a variable pitch, and is technically characterized by an H / D ratio of the diameter (H) of the propeller to the diameter (D) of the hub of 0.170-0.2.

The application discloses a motion control system for a near space antenna unmanned aerial vehicle, comprising a duct attitude adjustment system, a laser anemometer system and a Beidou satellite navigation system. The laser anemometer system monitors the wind speed and direction in the wind field and transmits the interference signals in real time; the Beidou satellite navigation system positions the antenna unmanned aerial vehicle in real time and transmits the position information; the duct attitude adjustment system comprises a sensor module, a controller module and a propulsion device, and adjusts the attitude of the propulsion device according to the interference signals and the position information. The propulsion device comprises eight duct propellers based on 3-RPS parallel structures and arranged in a cross shape, the design of the duct makes the airflow more stable and efficient, which helps to improve the propulsion efficiency and reduce the noise. The controller module adopts a strategy combining feedback linearization and terminal sliding mode control to generate control signals. The application realizes high-precision fixed-point hovering control of the antenna unmanned aerial vehicle in the complex wind field environment of the near space.

A single-crystal titanium-aluminum blade for aerospace applications based on precision electrolytic machining includes a blade root, a blade-direction synchronous conical shaft, a blade seat, a blade body, and a blade crown. The blade root is characterized by comprising acute-angled root branches, root branch grooves, inner root branches, obtuse-angled root branch grooves, obtuse-angled root branches, a vertical parallel plane, and a slanted transverse parallel corrugated surface. The beneficial effects are: 1. The reduction in the volume and mass of the blade root reduces the weight of the aero-engine; this weight reduction improves the propulsion efficiency of the aero-engine; the reduced load decreases the failure rate and extends the service life of the aero-engine; it also reduces fuel consumption, saves energy, and reduces pollution. 2. This advanced technology replaces the cumbersome process of bolting the spindle carriage to the workpiece during electrolytic machining, requiring the bolts to be removed and the spindle carriage reset after machining before installing the next workpiece. It provides a convenient and quick way to position the spindle carriage assembly and the workpiece; it also increases machining speed and efficiency.

A propulsion system includes a drive shaft movable in rotation about an axis of rotation, a fan shaft, a fan section including an unducted fan rotor driven in rotation by the fan shaft, the fan rotor including plural blades, and a reduction mechanism coupling the drive shaft and the fan shaft in order to drive the fan shaft at a rotation speed lower than the rotation speed of the drive shaft. A thrust density per blade of the fan rotor of the propulsion system being greater than or equal to 5.0×104 N / m2 and less than or equal to 10.0×104 N / m2, where the thrust density per blade is defined based on a thrust generated by the fan rotor and measured when the propulsion system is stationary in take-off rating, a number of blades in the fan rotor, and a diameter of the fan rotor in meters.

This invention provides a ducted passive air bleed structure and aircraft based on a micro-pore array, relating to the field of aircraft technology. The ducted passive air bleed structure includes a duct body and a downstream nozzle section; an air bleed channel is provided within the duct wall, connecting an array of inlet micro-pores at the lip to an array of outlet micro-pores offset towards the inner side of the nozzle in the nozzle junction area. This structure is purely passive, with no moving parts and zero power consumption, relying on the natural airflow redistribution driven by the pressure difference inside and outside the duct under flight conditions: during hovering / takeoff, it enhances lip suction to suppress backflow and separation; during cruise, it improves boundary layer control and jet mixing inside the nozzle, enhancing thrust vector efficiency and total pressure recovery. The micro-pore array design significantly enhances pressure difference response sensitivity, stress dispersion, acoustic vibration suppression, and improves tolerance tolerance and mass production consistency; the fully rigid structure completely avoids jamming risks, significantly improving long-term reliability and flight safety margins, and achieving a balanced optimization between propulsion efficiency, aerodynamic stability, lightweight design, and operational economy.

A multi-mode underwater-aerial inspection robot and its control method are disclosed. The robot comprises a fuselage, an arm, and an underwater-aerial propulsion system. The arm is connected to the fuselage, and the propulsion system is mounted on the arm. The propulsion system includes a first drive unit, a rotating frame, an angle control mechanism, and multiple propeller assemblies. Each propeller assembly includes blades capable of rotating about their spanwise axis. The first drive unit connects to and drives the rotating frame to rotate. The multiple propeller assemblies are evenly distributed circumferentially around the axis of the rotating frame. The propulsion system has multiple operating modes, including a multi-rotor mode and a submersible mode. The angle control mechanism adjusts the spanwise direction of the propellers to switch operating modes. In multi-rotor mode, the spanwise direction of the propellers is radially outward along the rotating frame for aerial flight. In submersible mode, the spanwise direction of the propellers is parallel to the axis of the rotating frame for underwater or surface translation. This invention significantly improves cross-medium propulsion efficiency and simplifies system structure, belonging to the field of aircraft technology.

The application discloses an electric propulsion ducted fan internal and external flow integration design method, and belongs to the technical field of electric aircrafts, which comprises the following steps: (1) fan blade model simplification; (2) establishing a ducted fan geometry based on a momentum source term; (3) internal and external flow reasoning distribution law exploration; (4) fan blade design; and (5) ducted fan internal and external flow coupling calculation verification. In the initial design stage of the ducted fan, the aerodynamic coupling effect between the fan and the duct is fully considered, so that the effective coupling of the duct additional thrust and the fan thrust is realized, the problems that the existing method is difficult to quantize the duct additional thrust and cannot clearly determine the influence law of various design parameters on the duct additional thrust are solved, the overall propulsion efficiency of the ducted fan is effectively improved, the design process complexity is reduced, the design iteration number is reduced, and a ducted fan design scheme with excellent aerodynamic performance can be quickly obtained.