141 results about "Propulsive efficiency" patented technology

The invention discloses a muck treatment capacity monitoring method and a muck treatment capacity monitoring system, and relates to the technical field of shield construction and muck treatment capacity prediction treatment, and the method comprises the following steps: collecting operation parameters of a shield tunneling machine deslagging and conveying link, calculating a muck flow coupling index, evaluating a deslagging link coupling state, and carrying out optimization; the load coupling index of the shield tunneling machine is calculated, the energy distribution balance is judged, and dynamic adjustment is conducted according to the unbalance state; calculating the energy consumption deslagging propulsion efficiency, evaluating the matching degree, and optimizing the power and conveying parameters of each link; a CNN and LSTM combined multi-scale modeling method is adopted to predict the future muck handling capacity, and online correction is carried out through a sudden change adaptive network; and finally, fusing the standardized data set with the actual operation parameters to generate a unit time muck handling capacity sequence. By means of the method, the deslagging and propelling matching degree of the shield tunneling machine can be improved, the energy utilization efficiency is optimized, and high-precision prediction and real-time regulation and control of the muck handling capacity are achieved.

The invention provides an underwater running double-stator beam flow rim propeller structure which comprises a guide pipe, the interior of one end of the guide pipe is connected with a front propeller hub, a front propeller hub cap is installed at one end of a propeller shaft, a front deflection stator, a rim transmission device and a rear deflection stator are sequentially installed on the propeller shaft, and the front deflection stator is connected with the front deflection stator. The other end of the conduit is connected with the tail beam tube; the wheel flange transmission device comprises a wheel flange transmission ring, the wheel flange transmission ring is connected with a paddle, and the paddle is installed on the rotor inner shaft. The guide pipe is used as a connecting carrier of the stator, the rim and the beam tube, and the rim transmission device is used as a power source device of the propeller. The front torsion stator plays a role in enabling inflow of the rotor to generate prerotation, the rear torsion stator plays a role in adjusting the torsion angle of the blades according to the fluid speed so as to better absorb wake flow energy, and the beam barrel is used for restraining the wake flow and concentrating pressure at the tail of the propeller on beams in the same direction, so that the effect of improving the propelling efficiency is achieved.

The invention discloses a ship propeller energy-saving rectifying device with diversion wings, and particularly relates to the technical field of ships, the ship propeller energy-saving rectifying device comprises a ship body, a driving rod is arranged at the rear end of the ship body, a propeller is arranged at the rear end of the driving rod, and a plurality of diversion wings are fixedly installed on the outer wall of the driving rod in an annular array mode. An L-shaped fixing support is arranged above the driving rod, the L-shaped fixing support is installed on the rear side of the ship body, a rectifying mechanism is installed at the bottom end of the vertical position of the L-shaped fixing support, the rectifying mechanism comprises an annular flow guide cover, and the propeller is located on the inner side of the annular flow guide cover. According to the ship propeller energy-saving rectifying device with the flow guide wings, through the synergistic effect of the flow guide wings and the rectifying mechanism capable of being dynamically adjusted, the inflow condition of the disc face of the propeller is improved, pre-rotation and non-uniformity of water flow are effectively weakened, and therefore the propelling efficiency of the propeller is improved, and fuel consumption and operation cost are reduced.

The invention discloses a water jet propulsion boat low-speed working condition energy-saving device based on the coanda effect. The water jet propulsion boat low-speed working condition energy-saving device comprises a flow guide plate, a fixed connecting piece and an angle adjusting device. The guide plate is arranged behind a nozzle of the water-jet propeller and is an S-shaped curved surface, the front end is hinged with the fixed connecting piece, and the rear end is hinged with the angle adjusting device; under a low-speed working condition, the guide plate rotates to a folded state, the upper wall surface covers a nozzle of the water-jet propeller and can guide jet flow to flow in a manner of being attached to the guide plate by means of the coanda effect, and the lower wall surface guides circulating vortex in a boat rear wake flow field; under the medium-high speed working condition, the guide plate rotates to a put-down state, the upper wall face is far away from jet flow of the water-jet propeller, and the lower wall face does not generate additional flow field disturbance in the boat body wake flow field. The jet flow of the water-jet propeller and the circulating vortex of the wake flow field of the boat body are guided based on the coanda effect, adverse flow coupling between the jet flow of the water-jet propeller and the circulating vortex is restrained, recycling of effective momentum in the corresponding wake flow field vortex is synchronously improved, and therefore the propelling efficiency of the water-jet propelling boat under the low-speed working condition is improved.

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 purpose of the present invention is to provide a hull-direct-connection-type propulsion device of a contra-rotating propeller and a method for manufacturing the same, the propulsion efficiency of an electrically propelled ship being greatly improved by disposing the contra-rotating propeller attached to the electrically propelled ship so as to be directly connected to the hull. In order to achieve the purpose, the hull-direct-connection-type propulsion device of the contra-rotating thruster according to the present invention comprises: a contra-rotating thruster comprising a front propeller and a rear propeller; a dual-rotor motor for generating respective rotation directions of the front propeller and the rear propeller; and the double shafts are used for connecting the contra-rotating thruster and the double-rotor motor.

The invention relates to a turbofan engine based on a multi-stage fan, which belongs to the technical field of aviation turbofan engines and comprises an inner duct, an outer duct, a high-pressure compressor system, a low-pressure compressor system, a high-pressure turbine, a low-pressure turbine and a multi-stage fan module. The high-pressure turbine drives the high-pressure compressor through the first transmission shaft, and the low-pressure turbine drives the low-pressure compressor and the multi-stage fan module through the second transmission shaft. And the multi-stage fan module comprises at least three stages of fans, transmits power and performs speed regulation and direction conversion through a gear set arranged on a second transmission shaft, so that the rotation directions of the odd-stage fans and the even-stage fans are opposite, and the rotation speeds of the odd-stage fans and the even-stage fans meet a certain proportional relation. The thrust load of the fan is dispersed to multiple stages of fan blades, so that the load of the fan blades is effectively reduced, the total thrust and the propulsive efficiency of the engine are improved, and meanwhile, the noise is favorably reduced.

This invention discloses a high-efficiency, low-noise waterjet propulsion pump, belonging to the field of marine engineering technology. The propulsion pump includes a shroud, a nozzle, a drive shaft, a drive shaft casing, a hub, an impeller, and a guide vane. The shroud and nozzle are connected, and the drive shaft and hub are coaxially connected and supported by the drive shaft casing inside the shroud and nozzle. The impeller and guide vane are fixed to the hub. The inner surface of the constricted nozzle at the rear of the impeller and guide vane has recesses, which are evenly distributed on the inner surface. This invention can reduce the flow resistance of the waterjet propulsion pump and improve propulsion efficiency.

The application discloses a flow field stabilizing mechanism of a double-throat aerodynamic vector nozzle and a control method thereof, which comprises two groups of guide vane arrays arranged in the double-throat aerodynamic vector nozzle and a servo control mechanism located outside the double-throat aerodynamic vector nozzle. When the double-throat aerodynamic vector nozzle is in a working state, according to the profile and flow field structure of the flow channel in the nozzle, the opening angle of the guide vane is adjusted through the servo control mechanism, so that the main flow of the double-throat aerodynamic vector nozzle is stabilized, and the vector performance of the double-throat aerodynamic vector nozzle is ensured, and the propelling efficiency and stability of the double-throat aerodynamic vector nozzle are improved.

An aircraft and an aircraft control method. The aircraft comprises: a fuselage (100), a frame (200), front propellers (300) and rear propellers (400), wherein the frame (200) tilts relative to the fuselage (100) about a pitch axis (001), with a tilt angle being adjustable; and the front propellers (300) and the rear propellers (400) are spaced apart along a longitudinal axis (002), and at least one of the front propellers (300) and the rear propellers (400) tilts relative to the fuselage (100) about an axis parallel to the pitch axis (001), with a tilt angle being adjustable. The frame (200) can tilt relative to the fuselage (100) about the pitch axis (001), thereby preventing the fuselage (100) from tilting and improving the stability of the aircraft. In addition, the tilted frame (200) can enable the front propellers (300) and the rear propellers (400) that are tilted to a horizontal state to be offset in a horizontal direction, thereby reducing aerodynamic interference of the front propellers (300), the rear propellers (400) and the fuselage (100), and ensuring the propulsion efficiency of the aircraft.

To provide a hull direct connection type propulsion device for a reciprocal rotation propeller greatly improving propulsion efficiency of an electric propulsion vessel by being composed so that the reciprocal rotation propeller loaded on the electric propulsion vessel is directly coupled to a hull, and a manufacturing method of the same.SOLUTION: A hull direct coupling propulsion device includes: a relative rotation propeller composed of a front propeller and a rear propeller; a double rotor electric motor generating respective rotational directions in a front propeller and a rear propeller; and a double shaft coupling the relative rotation propeller and the double rotor electric motor.SELECTED DRAWING: Figure 1

The invention relates to the technical field of ducted fans, and provides a ducted fan and a ducted fan unmanned aerial vehicle for fire fighting. The ducted fan comprises a ducted body, a fan body and a fan body, the wheel hub, the stationary blade and the movable blade are arranged in the flow channel, the stationary blade is connected with the wheel hub and the duct body, and the movable blade is rotatably arranged on the wheel hub; wherein the duct body comprises a main body section and a lip section which are arranged in the axial direction and connected, an inlet of the duct body is formed in the end, away from the main body section, of the lip section in the axial direction, an outlet of the duct body is formed in the end, away from the lip section, of the main body section, the inner diameter of the lip section is gradually reduced in the direction from the inlet to the outlet, and the lip section is provided with a plurality of through holes; the multiple through holes are formed in the circumferential direction of the lip section at intervals. According to the technical scheme, the pressure difference between the windward side and the leeward side of the lip area of the duct body can be reduced, the lateral resistance borne by the ducted fan is reduced, and then the propelling efficiency of the ducted fan is improved.

The invention belongs to the technical field of motors, and particularly relates to a rotary exposed electrostatic motor with an embedded stator and an aircraft, the rotary exposed electrostatic motor comprises a stator module, a rotor module, a bearing assembly, a charge transfer assembly and a power supply assembly, the stator module is embedded in the inner side of a bearing, and the rotor module sleeves the outer side and is partially exposed; the rotor blades can directly drive an external load to rotate, the power supply assembly enables the adjacent stator blades to be electrified alternately to form a driving electric field, and the charge transfer assembly achieves charge exchange during rotation so as to drive the rotor module to rotate. According to the structure, direct output of energy is achieved through the layout that the stator is embedded and the rotor is exposed, mechanical transmission loss is reduced, energy conversion efficiency is improved, and when the structure is applied to an aircraft, a motor can directly drive a propeller to generate thrust, the gravity center of the aircraft is lowered, and attitude stability and propelling efficiency are improved.

The invention discloses a compressible fluid reducing vortex method and device, and belongs to the technical field of fluid machinery and jet propulsion. The problems that in the prior art, the energy loss is large, the efficiency is low, and the gas temperature is sharply increased in the compression process are solved. Efficient and controllable conversion among fluid pressure energy, internal energy and kinetic energy can be achieved, an air injection device based on the method can more fully convert heat energy into directional injection kinetic energy through the synergistic effect of acceleration and vortex elimination guide vanes, and the propelling efficiency is remarkably improved; and the stable recovery and conversion of kinetic energy are realized through vortex expansion, and an approximately isentropic mild pressurization process can be realized, so that the temperature rise is obviously inhibited, and the compression energy consumption and the cooling requirement are fundamentally reduced.

The utility model discloses a catamaran propelling device which comprises a catamaran body (1), a paddle propelling device (2), a deck (3), paddles (4), a gear (5), a chain (6), a roller (7), an inner chain plate (8), a sleeve (9), a pin shaft (10), an outer chain plate (11) with paddles and an outer chain plate (12) with paddles. The paddles are driven through rotation of the chain, and the catamaran is pushed to move through interaction of the paddles and water. Water flow between the two ship bodies can be adjusted and rectified, the flowing state of the water flow is changed, and resistance received by the catamaran is reduced. Due to the action characteristics of the paddles, cavitation bubbles can be reduced, the propulsion efficiency is improved, and the navigation stability and the operation performance of the ship are improved.

The utility model discloses a kind of ship body structure and ship of wave can be pressed, wherein a kind of ship body structure including wave can be pressed comprises: ship body and wave plate. The ship body includes stern plate and ship body, the stern plate is located in the tail of the ship body, the bottom of the ship body has propeller tunnel;The wave plate is set on the stern plate, the wave plate is located in the tail end of the propeller tunnel, part structure of the wave plate overlaps with the stern plate, another part of the wave plate is located in the tail end of the propeller tunnel. The wave plate is set on the stern plate of ship body, simultaneously part structure of the wave plate is located in the tail of propeller tunnel in the bottom of the ship body, so when ship starts, the wave plate can suppress the upward rolling wake formed by propeller rotation, to reduce the resistance formed by propeller rotation to tail wave, to effectively improve the propulsion efficiency of propeller.

The coupling propulsion structure comprises a propeller arranged at the tail end of the tail of an aircraft and the semicircular empennage, the semicircular empennage starts from the lower portion of a wing and extends upwards along an arc path to exceed the propeller at the tail end of the tail of the aircraft, and a semicircular pneumatic structure is formed in a vertical plane; wherein the highest point of the front edge of the semi-annular empennage is located in the vertical plane of the longitudinal axis of the fuselage, and the minimum vertical height L from the highest point of the front edge of the semi-annular empennage to the tip of the propeller is equal to 0.1-0.2 time of the radius R of the tip of the propeller. According to the coupling propelling structure special for the semi-annular empennage, the propelling efficiency of the propeller can be remarkably improved by optimizing the coupling relation between the propeller and the semi-annular empennage, and meanwhile the coupling propelling structure has the structural advantages of the semi-annular empennage.

The invention discloses a ship electric propulsion efficiency evaluation method and system based on multi-modal data fusion, and the method comprises the steps: obtaining a blade cavitation corrosion image of a propeller, and constructing a multi-modal propulsion state data set through space-time alignment in combination with ship state parameters and electric propulsion parameters; extracting structural dynamic characteristics and electric propulsion state characteristics of the propeller, and fusing to generate a real-time propulsion state characteristic vector; based on the real-time propulsion state feature vector and the multi-modal propulsion state data set, obtaining a real-time propulsion efficiency estimated value and a corresponding propulsion efficiency risk level through a pre-constructed efficiency evaluation model; performing risk association analysis in combination with an efficiency risk mode library, determining an efficiency risk mode and associated data, and further obtaining a data adjustment amount through efficiency trend association analysis; and finally, generating a ship evaluation result according to the data adjustment amount and the efficiency risk mode so as to improve the comprehensiveness of ship evaluation.

The invention relates to the technical field of robot manufacturing, in particular to an underwater robot motion performance optimization method, device and equipment and a medium. The structure of the robot is optimized according to fluid dynamics so as to research the hydrodynamic characteristics of the propulsion system, and reference is provided for optimizing the structure of the underwater robot propulsion system and improving the flexibility and efficiency of movement of the underwater robot propulsion system. The thrust, the lateral force and the total resistance of the underwater robot driving device are directly extracted, complex formula derivation is not needed, the performance of different working modes of the propeller is verified respectively, the open water performance of the underwater robot can be visually and conveniently observed from a simulated diagram, and the method has the advantages of being high in practicability and easy to popularize. In addition, the simulation result of the robot performance is compared with pool test data to correct the robot model, so that the structure of the underwater robot is visually optimized. The propulsive efficiency of the underwater robot in different modes is calculated, and the problems of fluid resistance and delayed maneuvering response are solved according to the propulsive efficiency.

This invention belongs to the field of electronic digital data processing and discloses a propulsion modeling method for FPSOs based on Modelica, comprising the following steps: S1: Modeling the propulsion coefficient model of the propeller, including calculating the following parameters: thrust coefficient, thrust torque coefficient, thrust gain coefficient, and thrust torque gain coefficient; S2: Modeling the propeller performance model, including calculating the following parameters: wake coefficient, advance number, thrust loss coefficient, and relative rotational efficiency; S3: Based on the results of steps S1 and S2, outputting the thrust and thrust torque of the propeller, thereby obtaining the propulsion efficiency of the propeller. This method can comprehensively simulate the thrust and torque variation characteristics of the propeller under different operating conditions through a discrete dynamic modeling approach, thus providing accurate simulation support for the dynamic response of FPSO systems in complex marine environments.

The invention discloses a bionic shaftless rim thruster and a full parametric modeling method thereof. The bionic shaftless rim thruster comprises a bionic conduit, an inner ring, a first bionic propeller blade, a second bionic propeller blade and a third bionic propeller blade, an inner ring is arranged in the bionic catheter and attached to the interior of the bionic catheter. A first bionic propeller blade, a second bionic propeller blade and a third bionic propeller blade are arranged in the middle of the long axis of the inner ring; the first bionic propeller blade, the second bionic propeller blade and the third bionic propeller blade are coaxially arranged; the first bionic propeller blade, the second bionic propeller blade and the third bionic propeller blade are arranged at intervals of 120 degrees. Blades of the bionic rim thruster are of a unique bionic whale fin structure, thrust is provided through a rotor, tip vortexes are effectively reduced due to the appearance characteristic, and the bionic rim thruster plays an important role in improving the thrusting efficiency of a propeller. And the edge of the propeller is also provided with a unique bionic structure, so that the hydrodynamic efficiency of the propeller can be effectively improved.

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.

A vortex inducer is applied to the pressure face of a propulsion rotor blade. The vortex inducer defines an aft face located forward of the trailing edge of the blade. In operation, the vortex inducer generates a primary vortex behind its apex, which induces a counterrotating secondary vortex through viscous coupling at the trailing edge. The secondary vortex accelerates and deflects the suction face wake, enhancing overall blade performance. The system is applicable to propellers, helicopter rotors, prop-rotors, fan blades, and marine propellers.

The invention discloses a high-degree-of-freedom eVTOL aircraft, and the aircraft comprises a fuselage which comprises a first wing and a second wing, and the first wing and the second wing are oppositely arranged; each of the first wing and the second wing is provided with a plurality of propellers, and the number of the propellers on the first wing is equal to that of the propellers on the second wing; the first control assembly is mounted on the fuselage and used for controlling the multiple propellers on the first wing; the second control assembly is mounted on the fuselage and used for controlling a plurality of propellers on the second wing; the propeller comprises a telescopic assembly installed on the first wing or the second wing; the steering assembly is connected to the movable end of the telescopic assembly; the rotor wing assembly is connected with the steering assembly, and the rotor wing assembly provides propelling power; the movable end of the telescopic assembly stretches out and draws back to drive the steering assembly and the rotor wing assembly to move. The steering assembly controls the rotor assemblies to rotate. The aircraft can be suitable for various flight states, aerodynamic interference is reduced, and the propelling efficiency is improved.

The invention relates to an energy-saving guide wheel design method, which comprises the following steps of: screening out an energy-saving guide wheel according with the use of a real ship through CFD (Computational Fluid Dynamics) analysis, determining the size and the mounting position of the energy-saving guide wheel according to a method that the energy-saving effect is equal to (a PDbelt energy-saving guide wheel / a PDbare ship)-1) * 100% and the maximum value of the energy-saving effect is selected as the optimal value, selecting a scheme with a good energy-saving effect, and performing test determination to improve the propulsive efficiency. The wake flow rotation energy loss of the propeller is reduced, and the efficiency is improved by about 3-8%; the energy-saving guide wheel with the matched structure can further reduce the fuel consumption, the comprehensive fuel-saving effect exceeds 2-5%, and the annual operation cost is reduced; cavitation bubbles and vibration are reduced, the water flow uniformity is optimized, propeller cavitation bubble corrosion and hull vibration are reduced, and the service life of equipment is prolonged; the angles of part of the self-adaptive guide wheels can be adjusted, so that the self-adaptive guide wheels are suitable for different drafts or navigational speeds.

The embodiment of the invention provides a mixing ratio adjusting method and system for a propellant of a liquid carrier rocket, and the method comprises the steps: obtaining the flight data of the liquid carrier rocket and the state data of the propellant; determining a flight stage of the liquid carrier rocket according to the flight data; according to the state data of the propellant, the mixing ratio and the mixing ratio change rate of the propellant are determined; according to the flight stage, the mixing ratio and the mixing ratio change rate, the valve adjusting strength of the propellant is determined; and adjusting the valve of the propellant according to the valve adjusting strength of the propellant. According to the invention, through intelligent sensing and self-adaptive adjustment, the mixing ratio in the whole flight process of the rocket can be accurately controlled, and the propulsion efficiency and the flight safety are improved.

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.

The application discloses a permanent magnet conical propelling motor and a vehicle. The permanent magnet conical propelling motor comprises a stator (2) and a rotor (3) installed in a casing (1), the stator (2) and the rotor (3) are matched with each other through a bearing (6), the rotor (3) is connected with one end of a transmission shaft (5), the other end of the transmission shaft (5) penetrates through the casing (1) and is connected with a propeller, the inner wall of the stator (2) and the outer wall of the rotor (3) are parallel to each other and form a certain angle with the motor axis, and air gaps are distributed between the inner wall of the stator (2) and the outer wall of the rotor (3). The permanent magnet conical propelling motor has the advantages of simple and compact structure, low bearing friction loss, high propelling efficiency, long cruising range and the like, and has stable operation performance, long service life and the like, is suitable for use in different pressure environments and has wide application prospects in various vehicles.

The application belongs to the technical field of underwater propeller, and discloses a control method for periodic swing of bionic hydrofoil, which controls the hydrofoil to swing according to the following periodic swing rule: each swing period of the periodic swing rule is composed of two half periods which are mirror-symmetric about the center position; each half period is sequentially composed of a recovery stroke and a power stroke, wherein the ratio of the maximum angular velocity of the power stroke to the maximum angular velocity of the recovery stroke, i.e. the speed ratio, satisfies the application. Through the provided periodic motion rule, the rigid impact is eliminated, the residence time of the hydrofoil at the center position is prolonged, the propulsion efficiency and the forward distance are effectively improved, and reliable technical support is provided for the engineering propulsion of rigid hydrofoil.

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.