Straight wing propeller simulation loading device and component size parameterization design method thereof

Abstract

The present application relates to a kind of straight wing propeller simulation loading device and its component size parameterization design method, belong to ship power propulsion field.The device is made of rotating shaft, stand, cross bar, longitudinal eccentric block and transverse eccentric block, can replace actual blade in land test, through the centrifugal force and inertial moment generated in operation process, the load equivalent with actual propeller hydrodynamic load is generated at the hinge point under control lever and propeller bearing.At the same time, the present application proposes a kind of parameterization design method, according to the structure parameters and load input of different models of actual propeller, by selecting design variable, constructing objective function, defining constraint condition and solving optimization model, the structure parameters of simulation loading device are quickly determined.The present application can realize the land substitution of straight wing propeller in-water test, greatly reduce test cycle, cost and difficulty, effectively complete the examination of propeller bearing carrying capacity, rotating box mechanism strength and hydraulic system distance adjusting and distance stabilizing performance.

Description

Technical Field

[0001] This invention relates to the field of marine propulsion technology, and in particular to a simulated loading device for a straight-wing propeller and a method for parameterizing the dimensions of its components. Background Technology

[0002] A straight-wing propeller is a special type of propulsion device with adjustable pitch, where the blades and main shaft are mounted perpendicular to the hull. The propeller blades are vertically inserted into the water, rotating around the center of a turntable while each blade oscillates around its own axis. Because the magnitude and direction of the thrust of a straight-wing propeller can be flexibly adjusted, it enables functions such as agile maneuverability and attitude control for ships.

[0003] A straight-wing propeller consists of a propeller mechanical body, a hydraulic system, and a control system. The propeller mechanical body comprises a blade 1, a blade actuator 2, a control rod 5, a hydraulic cylinder 4, a transmission gear set 6, a bearing assembly 3, a rotating housing 8, and a propeller base 7, etc. Figure 1 As shown. The propeller actuator 2 consists of five sets of cranks 24, a long connecting rod 21, a concentric rod 23, and a support rod 22, as follows. Figure 2A As shown. The structural relationship between the single crank 24, long connecting rod 21, concentric rod 23, and strut 22 is as follows. Figure 2B As shown, the components are connected by pins. The crank 24 is fixed to the shaft of the blade 1 and rotates together around the axis of the blade 1. The ends of the five concentric rods 23 are stacked together and hinged to the lower hinge point of the control lever 5, as shown. Figure 2C As shown.

[0004] The blade 1 and blade actuator 2 are installed in the rotating housing 8 of the straight-wing propeller and rotate together with the rotating housing 8 during operation. When the center position of the concentric rod 23 (i.e. the control point) is eccentric with the center of the turntable under the drive of the lower hinge point of the control rod 5, the blade 1 swings under the drive of the blade actuator 2 during the rotation of the rotating housing 8, and the angle of attack with the incoming flow direction is always positive, thereby generating thrust to drive the propeller forward.

[0005] The simplified model and coordinate system of the single-blade actuator of the straight-wing propeller are as follows: Figure 3A As shown. The load on a single blade includes the hydrodynamic thrust of the blade, the hydrodynamic rotation torque, the centrifugal force generated by the blade's revolution around the center of the entire blade, and the inertial torque generated by the blade's rotation around its own axis.

[0006] The hydrodynamic thrust and centrifugal force of the propeller blades create a bending moment relative to the propeller bearings. This bending moment is ultimately balanced by the reaction forces of the upper and lower bearing supports within the rotating housing 8. This bending moment serves as the load input for assessing the load-bearing capacity of the propeller bearings and the strength of the rotating housing mechanism.

[0007] The hydrodynamic torque and inertial torque of the five sets of blades are transmitted through the blade actuator 2, forming a resultant force at the hinge point at the end of the concentric rod 23. This resultant force is transmitted to the hydraulic cylinder 4 via the control rod 5, and is balanced by the oil pressure of the hydraulic system. This resultant force is the load input for evaluating the pitch adjustment and pitch stability performance of the hydraulic system.

[0008] The load-bearing capacity assessment of the propeller bearings, the strength assessment of the rotating housing mechanism, and the pitch adjustment and stabilization performance assessment of the hydraulic system are key and challenging aspects of the straight-wing propeller design process. Currently, the assessment methods typically involve full-scale ship testing on an experimental vessel or underwater loading tests on a test platform. These methods are time-consuming, costly, and extremely difficult. Summary of the Invention

[0009] To address the aforementioned issues, a simulated loading device for a straight-wing propeller is proposed. This device replaces the actual propeller blades in land-based tests of the straight-wing propeller. During the propeller's rotation, the centrifugal force and inertial torque generated can produce loads equivalent to those transmitted to the actual propeller's hydrodynamic loads at the lower hinge point of the control rod and the blade bearings. This allows for on-land assessments of the blade bearing's load-bearing capacity, the strength of the rotating housing mechanism, and the pitch adjustment and stability performance of the hydraulic system. Furthermore, a parametric design method is proposed for determining the component dimensions of this simulated loading device.

[0010] The technical solution of the present invention is: a straight-wing propeller simulation loading device, used to replace the actual blades for loading tests in land tests of straight-wing propellers, including a rotating shaft, a column, a crossbar, a longitudinal eccentric block and a transverse eccentric block; The structure of the rotating shaft is consistent with the end blade structure of the actual blade inserted into the crank. The crossbar is coaxially connected to the transverse eccentric block, and the end of the crossbar away from the transverse eccentric block is fixedly connected to the middle end of the column. The rotating shaft is coaxially and sequentially fixedly connected to the column and the longitudinal eccentric block, and the coaxial line of the crossbar is perpendicular to the coaxial line of the column. The transverse eccentric block, crossbar, longitudinal eccentric block, and column are all cylindrical, and the dimensions and connection relationships of each component are configured such that, during the rotation of the device with the rotating housing of the straight-wing propeller, the centrifugal force and inertial torque generated produce loads at the lower hinge point of the control rod and the blade bearing that are equivalent to the hydrodynamic load of the actual propeller transmitted to that part.

[0011] Preferably, the structural parameters of the device include: the radius of the lateral eccentric block. R H1 Length of the lateral eccentric block L H1 , crossbar radius R H2 Length of crossbar L H2Longitudinal eccentric block radius R L1 Length of longitudinal eccentric block L L1 Column radius R L2 Column length L L2 Distance between the lateral eccentric block and the bottom of the shaft L L3 and the angle between the axial direction of the transverse eccentric block and the upper EF of the crank. δ The simulation loading device preferably uses a manufacturing process of integral forging and machining.

[0012] Preferably, the rotating shaft is used to connect to the crank of the straight-wing propeller, so that the simulated loading device rotates together with the rotating housing, and transmits the load to the control rod and the blade bearing through the blade actuator.

[0013] Preferably, the distance between the overall center of mass of the simulated loading device and the central axis of the rotating shaft, as well as the distance between the overall center of mass and the bottom of the rotating shaft, are calculated and determined based on the mass of the lateral eccentric block, the mass of the crossbar, and the mass of the longitudinal eccentric block, wherein the mass of each component is based on the material density. ρ Based on the calculation of their respective geometric dimensions, alloy structural steel is the preferred material for the simulation loading device.

[0014] A parameterized design method for the component dimensions of a straight-wing thruster simulation loading device, used to determine the structural parameters of the straight-wing thruster simulation loading device, includes the following steps: Step S1: Determine the target load, including the hydrodynamic thrust of a single blade of a solid propeller, the hydrodynamic rotor torque, the centrifugal force, and the inertial torque; Step S2: Establish the kinematic model of the simulated loading device and the blade actuator, and solve for the angular displacement, angular velocity, angular acceleration and hinge acceleration of the components; Step S3: Establish a dynamic model of the simulated loading device and the blade actuator, list the dynamic static equilibrium equations of each component based on d'Alembert's principle, and solve for the load at the lower hinge point of the control rod and the load on the blade bearing. Step S4: Construct a parameter optimization model, select the structural parameters of the simulated loading device as design variables, construct the objective function, and define the constraints; Step S5: Solve the parameter optimization model to obtain the optimal solution of the structural parameters of the simulated loading device.

[0015] Further, in step S2, the simplified model of the simulated loading device and the blade actuator is transformed into a kinematic model, wherein component AE is a rotating box, component BC is a strut, component DG is a concentric rod, component EF is a crank, component GF is a long connecting rod, A is the rotation center of the rotating box, B is the hinge point connecting the end of the strut, C is the hinge point connecting the strut and the concentric rod, D is the hinge point connecting the control rod and the concentric rod, E is the hinge point connecting the crank and the end of the blade, F is the hinge point connecting the long connecting rod and the crank, and G is the hinge point connecting the concentric rod and the long connecting rod. Based on the geometric relationship of the components, the equations of quadrilateral ABCD and polygon AEFGD are established, the angular displacement of each component is solved, and the angular velocity and angular acceleration are obtained by differentiating with respect to time.

[0016] Furthermore, in step S3, the simulated loading device and the blade actuator linkage are decomposed, and corresponding inertial forces and inertial torques are added to the components according to D'Alembert's principle. The dynamic equilibrium equations of the rotating box, strut, concentric rod, long connecting rod and crank-simulated loading device are listed, and the loads at each hinge point are obtained by solving them simultaneously.

[0017] Furthermore, in step S4, the objective function is selected to be able to simulate both the same control rod lower hinge point load during actual propeller operation and the maximum load on the bearing during actual propeller operation; the constraint conditions include constraint conditions determined based on the geometric relationship of the components and constraint conditions determined based on the structural strength relationship of the components.

[0018] Furthermore, in step S4, the selected design variable is: the radius of the lateral eccentric block. R H1 Length of the lateral eccentric block L H1 , crossbar radius R H2 Length of crossbar L H2 Longitudinal eccentric block radius R L1 Length of longitudinal eccentric block L L1 Column radius R L2 Column length L L2 Distance between the lateral eccentric block and the bottom of the shaft L L3 And the angle between the axial direction of the transverse eccentric block and the upper EF of the crank. δ .

[0019] Furthermore, in step S1, the determination of the target load is based on a simplified model of a single-set blade actuator, wherein the load includes the blade hydrodynamic thrust, the hydrodynamic blade rotation torque, the centrifugal force generated by the blade revolving around the center of the entire blade, and the inertial torque generated by the blade rotating around its own axis.

[0020] The beneficial effects of this invention are as follows: The simulated loading device for a straight-wing propeller and its component dimension parameterized design method can generate a load at the relevant part of the straight-wing propeller through the inertial load produced during its operation. This load is equivalent to the load transferred to that part in the water by the actual propeller, thus enabling the assessment of the propeller bearing capacity, the strength of the rotating housing mechanism, and the functional performance of the hydraulic system on land. This achieves a land-based alternative to underwater propeller testing, significantly reducing the difficulty of the test. The parameterized design method can quickly design the structural parameters of the simulated loading device suitable for different propeller models based on their structural parameters and load inputs. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the mechanical structure of a straight-wing propeller. Figure 2A This is a schematic diagram of the paddle actuator structure; Figure 2B This is a schematic diagram of a single-stage blade actuator. Figure 2C A schematic diagram of the ends of the five concentric rods and the control rod structure; Figure 3A A simplified model and coordinate system for a single-blade actuator—the blade; Figure 3B A simplified model of the paddle actuator; Figure 3C To simplify the model of the blade system; Figure 4A This is a structural diagram of the simulation loading device of the present invention; Figure 4B This is a simulation of the assembly effect of the loading device and the blade actuator of the present invention; Figure 4C This is a simplified model of the simulated loading device—paddle actuator of the present invention; Figure 5 The structural parameters that need to be determined for the simulated loading device of this invention Figure 1 ; Figure 6 Figure 2 shows the structural parameters that need to be determined for the simulated loading device of this invention; Figure 7 This is a kinematic model diagram of the simulated loading device—paddle actuator of the present invention; Figure 8A This is a force diagram of the rotating housing (single blade section) of the simulated loading device—blade actuator of the present invention; Figure 8B This is a force diagram of the support rod of the simulated loading device—paddle actuator of the present invention; Figure 8C This is a force diagram of the concentric rod of the simulated loading device—paddle actuator of the present invention; Figure 8D This is a force diagram of the long connecting rod of the simulated loading device—paddle actuator of the present invention; Figure 8E This is a force diagram of the simulated loading device—paddle actuator crank—simulated loading device of the present invention; Figure 9 This is a diagram showing the hydrodynamic torque of a single-blade propeller. Figure 10 This is a diagram showing the hydrodynamic thrust of a single-blade propeller. Figure 11A This invention provides a simulation effect of the load at the lower hinge point of the control rod. Figure 1 ; Figure 11B Figure 2 shows the simulated load effect of the lower hinge point of the control rod in this invention; Figure 12 This is a simulation diagram of the bending moment load on the propeller bearing of the present invention. Detailed Implementation

[0022] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. These embodiments are based on the technical solution of the present invention and provide detailed implementation methods and specific operating procedures. However, the scope of protection of the present invention is not limited to the following embodiments.

[0023] This invention relates to a straight-wing propeller simulation loading device, which can achieve the loading effect of a real propeller in water during land-based tests. A parametric design method is proposed for determining the dimensions of the device's components. Details are as follows: 1. Determination of target load: Figure 3A In the simplified model of the single-blade actuator shown, components AE, BC, DG, GF, and EF are simplified models of the rotating housing, strut, concentric rod, long connecting rod, and crank, respectively. A~G are the connection hinge points of each component, where A is the rotation center of the rotating housing, B is the connection hinge point at the end of strut 22, C is the connection hinge point between strut 22 and concentric rod 23, D is the hinge point between control rod 5 and concentric rod 23, E is the connection hinge point between crank 24 and the end of blade 1, F is the connection hinge point between long connecting rod 21 and crank 24, and G is the connection hinge point between concentric rod 23 and long connecting rod 21.

[0024] Single blade loads include blade hydrodynamic thrust. F tx , F ty Hydrodynamic rotor torque M cz And the centrifugal forces in the X and Y directions generated by the blades revolving around the center of the propeller. , and the inertial torque generated by the rotation of the blades around their own axis .in, For the blade mass, , These are the accelerations of the blade's center of mass in the X and Y directions, respectively. Let be the moment of inertia of the blade about its center of mass. It represents the rotational angular acceleration of crank 24 and blade 1.

[0025] Figure 3A The simplified model can be decomposed into a simplified model of the paddle actuator (such as...). Figure 3B ) and simplified models of blade systems (such as Figure 3C It consists of two parts. Figure 3B During the operation of the propeller blades, the hydrodynamic rotor torque... M cz and inertial torque A support reaction force is formed at hinge point D. and The resultant force at hinge point D of the five sets of propeller actuators is obtained by vector superposition of the loads at hinge point D of the entire device: , The load is transmitted from control lever 5 to hydraulic cylinder 4, and is balanced by the oil pressure of the hydraulic system. Therefore, and This is one of the loads that need to be simulated during the operation of this simulation loading device.

[0026] Figure 3C In the middle, the propeller's hydrodynamic thrust F tx , F ty and centrifugal force , The bending moment load generated at the lower bearing of the blade is: In the formula, and These represent the distances between the points of application of the hydrodynamic thrust and centrifugal force and the lower bearing of the propeller blade, respectively. This bending moment is ultimately balanced by the reaction forces of the upper and lower bearing supports within the rotating housing 8. Therefore, This is another load that needs to be simulated during the operation of this simulation loading device.

[0027] 2. Structure and working principle of the simulated loading device: The structure of the simulated loading device is as follows Figure 4AAs shown, the device consists of a rotating shaft 30, a column 40, a crossbar 20, a longitudinal eccentric block 50, and a transverse eccentric block 10. The rotating shaft 30 has the same structure as the end blade of the actual blade inserted into the crank 24. The column 40, crossbar 20, longitudinal eccentric block 50, and transverse eccentric block 10 are all cylinders. The crossbar 20 is coaxially connected to the transverse eccentric block 10, and the end of the crossbar 20 away from the transverse eccentric block 10 is fixedly connected to the middle end of the column 40. The rotating shaft 30 is coaxially and sequentially fixedly connected to the column 40 and the longitudinal eccentric block 50, and the two axes of the crossbar 20 and the column 40 are perpendicular. A manufacturing process of integral forging and machining is recommended for the simulated loading device.

[0028] The single-unit simulated loading device, used as a replacement for blade 1 in the simulation experiment, and its assembly effect with the blade actuator are as follows: Figure 4B As shown, its simplified model and coordinate system are as follows: Figure 4C As shown, the simulated loading device generates centrifugal forces in the X and Y directions when it rotates with the propeller. , and the moment of inertia .in, To simulate the mass of the loading device, , These represent the accelerations of the center of mass of the simulating loading device in the X and Y directions, respectively. To simulate the rotational inertia of the loading device about its center of mass, The angular acceleration is the rotational speed of the crank and the simulated loading device.

[0029] Choose the appropriate , , and This allows the obtained centrifugal force and inertial torque to generate an equivalent load at the lower hinge point of control lever 5, which is then transmitted to the propeller hydrodynamic rotor torque and propeller inertial torque. and Simultaneously, centrifugal force can generate an equivalent bending moment at the lower bearing of the propeller blade, which is equivalent to the hydrodynamic thrust and centrifugal force of the propeller at that location. .

[0030] 3. Simulated loading device structural parameters: The structural parameters that need to be determined for the simulation loading device are as follows: Figure 5 , 6 As shown, it includes: 1) R H1 1) Radius of the lateral eccentric block; 2) L H1 The length of the lateral eccentric block is 10; 3) R H2 The crossbar has a radius of 20; 4) L H2 The crossbar is 20 units long; 5) RL1 For the longitudinally eccentric block with a radius of 50; 6) L L1 The longitudinal eccentric block is 50 mm long; 7) R L2 The column has a radius of 40; 8) L L2 The column is 40mm long; 9) L L3 The distance between the lateral eccentric block 10 and the bottom of the rotating shaft 30; 10) δ It is the angle between the axial direction of the transverse eccentric block 10 and the upper EF of the crank 24.

[0031] 4. Simulate the mass and moment of inertia of the loading device: 1) Quality: Mass of the lateral eccentric block: ; Crossbar mass: ; Longitudinal eccentric block mass: ; Column quality: ; in: ρ The material density is [not specified]. The simulated loading device can be made of alloy structural steel, therefore... ρ Take 7800 kg / m 3 ; Overall mass of the simulated loading device: ; The distance between the overall center of mass of the simulated loading device and the central axis of the rotating shaft 30 can be expressed as: , The distance between the overall center of mass of the simulated loading device and the bottom of the rotating shaft 30 can be expressed as: .

[0032] 2) Moment of inertia: According to the parallel axis theorem, the moment of inertia of each component relative to the overall center of mass can be expressed as: Moment of inertia of the lateral eccentric block 10: , Moment of inertia of crossbar 20: , Moment of inertia of longitudinal eccentric block 50: , Moment of inertia of column 40: , The moment of inertia of the simulated loading device relative to the overall center of mass is: .

[0033] 5. Simulation of loading device—kinematic solution of blade actuator: 1) Kinematic model: Will Figure 4C The simplified model of the single-unit simulated loading device and blade actuator is transformed into a kinematic model, such as Figure 7 As shown. Among them, L 1~ L 8 represents the distances between hinge points A~B, B~C, C~D, D~A, B~E, E~F, F~G, and G~C, respectively. Component AE (rotating box 8) is the driving component. φ 1 represents its angular displacement. φ 2~ φ 5 represents the angular displacements of components BC (strut 22), DG (concentric rod 23), EF (crank 24), and GF (long connecting rod 21), respectively.

[0034] 2) Angular displacement of components: Based on the geometric relationships of the components, for quadrilateral ABCD, we have: (1), Solving the equation, we get: , , in: , , , .

[0035] For polygon AEFGD, we have: (2), Solving the equation, we get: , , in: , , , .

[0036] 3) Component angular velocity: The angular velocities of the rotating box 8, strut 22, and concentric rod 23 are respectively defined as follows: ω 1. ω 2. ω 3; The crank-simulated loading device and the angular velocity of the long connecting rod 21 are respectively defined as... ω 4. ω 5.

[0037] Differentiating equation (1) with respect to time and solving the equation, we get: , , Differentiating equation (2) with respect to time and solving the equation, we get: , .

[0038] 4) Component angular acceleration: The angular accelerations of strut 22 and concentric strut 23 are defined as follows: α 2. α 3; The crank-simulated loading device and the angular acceleration of the long connecting rod 21 are respectively defined as... α 4. α 5. Taking the second derivative of equation (1) with respect to time and solving the equation, we get: , , Taking the second derivative of equation (2) with respect to time and solving the equation, we get: , .

[0039] 5) Acceleration at the hinge point of the component: In the propeller actuator, the hinge point accelerations of each component are as follows: Acceleration at hinge point B: , E-hinge acceleration: , C-hinge acceleration: , G-hinge acceleration: .

[0040] 6) Component center of mass acceleration: Acceleration of the center of mass of the concentric rod: , acceleration of the strut's center of mass: , Acceleration of the center of mass of the long connecting rod: , Crank—simulating the acceleration of the center of mass of the loading device: , In the formula L 3_1 , L 2_1 , L2_2 , L 7_1 The location of the centroid of each component; Centrifugal force generated during the operation of the simulation loading device , Inertial torque That is, the source of the simulated load it generates.

[0041] 6. Simulation of loading device—dynamic solution of blade actuator: 1) Simulation of the load at the lower hinge point of control lever 5: The simulated loading device—paddle actuator linkage is decomposed. Based on d'Alembert's principle, corresponding inertial forces and moments are applied to the components, and the dynamic-static equilibrium equations for each component are derived. The forces acting on each linkage of the simulated loading device—paddle actuator are as follows: Figures 8A-8E As shown.

[0042] The dynamic equilibrium equations for the rotating box are as follows: (3) In the formula, T 驱 The driving torque on the rotating box.

[0043] The dynamic equilibrium equations of the strut are as follows: (4) In the formula, m 2 represents the mass of the strut; J L2 Let be the moment of inertia of the strut about its center of mass.

[0044] The dynamic equilibrium equations of the concentric rods are as follows: (5) In the formula, m 3 represents the mass of the concentric rod; J L3 Let be the moment of inertia of the concentric rods about their center of mass.

[0045] The dynamic equilibrium equations for a long connecting rod are as follows: (6) In the formula, m 7 represents the mass of the long connecting rod; J L7 Let be the moment of inertia of the long connecting rod about its center of mass.

[0046] The dynamic equilibrium equations of the crank-simulated loading device are as follows: (7) In the above formula, F AX , FAY , F BX , F BY , F CX , F CY , F DX , F DY , F EX , F EY , F FX , F FY , F GX , F GY The loads at hinge points A through G are respectively.

[0047] By combining formulas (3) to (7), the loads at each hinge point can be obtained. F DX , F DY This refers to the load at the end of the concentric rod. Based on the 72° phase difference between the loads of each blade actuator, the loads at the end of the concentric rod in the other four sets of simulated loading devices—blade actuators—can also be calculated.

[0048] After vector superposition, the load at the lower hinge point of the control rod in the entire device can be obtained: This is one of the loads generated during the operation of this simulated loading device.

[0049] 2) Simulation of blade bearing load: The bending moment load generated by the centrifugal force of the simulated loading device at the lower bearing of the blade can be expressed as: In the formula, L B — The distance between the bottom of the shaft and the lower bearing of the blade. This is another load generated during the operation of this simulated loading device.

[0050] 7. Parameter optimization design of simulated load device: Step 1: Select design variables: The design variables for the simulated load device are selected as follows: .

[0051] Step 2: Construct the objective function: The objective of optimizing the parameters of the simulated load device is to simulate both the same control rod lower hinge point load during actual propeller operation and the maximum bearing load during actual propeller operation. Therefore, the objective function is selected as follows: , in, , , The target load for the actual propeller condition to be simulated; k 1. k 2. k 3 is the importance weighting factor, which is selected in this optimization design. k 1 = 0.4 k 2 = 0.4, k 3 = 0.2.

[0052] Step 3: Define constraints: Based on the geometric relationships of the components, the constraints include: ; ; ; ; Based on the structural strength relationship of the components, the constraints include: .

[0053] Step 4: Solve the above optimization model to obtain the optimal solution for the parameters of the simulated load device. Take the design of a simulated loading device for a certain type of ship's straight-wing propeller as an example.

[0054] 1. Design inputs are as follows: 1) The distance parameters between each hinge point of its propeller actuator are known:

[0055] 2) Mass, moment of inertia, and speed parameters of each component of the propeller actuator:

[0056] 3) The hydrodynamic torque and hydrodynamic thrust of a single-bladed propeller are as follows: Figure 9 , Figure 10 As shown.

[0057] 2. Design Output: The structural parameters of the simulated loading device obtained through the above optimization method are as follows:

[0058] Simulation results show that the simulated load effect at the lower hinge point of the control rod under the operating conditions of the simulated loading device is as follows: Figure 11A, 11B As shown in the figure, the frequency and amplitude of the load at the lower hinge point of the control lever generated by the figure are in good agreement with the load generated under actual water conditions, thus it can be used to assess the pitch adjustment and pitch stabilization capabilities of the hydraulic system.

[0059] The simulated bearing bending moment load effect is as follows Figure 12 As shown in the figure, the generated bearing bending moment can reach the maximum value of the bearing bending moment under actual propeller water conditions, thus serving as an assessment tool for the bearing capacity of the propeller blades and the strength of the rotating housing mechanism.

[0060] The embodiments described above merely illustrate specific implementations of the present invention, and while the descriptions are detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the protection scope of the present invention. Therefore, the protection scope of this invention patent should be determined by the appended claims.

Claims

1. A simulated loading device for a straight-wing propeller, used to replace actual propeller blades for loading tests during land-based trials of a straight-wing propeller, characterized in that, It includes a rotating shaft (30), a column (40), a crossbar (20), a longitudinal eccentric block (50), and a transverse eccentric block (10); the structure of the rotating shaft (30) is consistent with the end blade structure of the actual blade insertion crank (24); the crossbar (20) is coaxially connected to the transverse eccentric block (10), and the end of the crossbar (20) away from the transverse eccentric block (10) is fixedly connected to the middle end of the column (40); the rotating shaft (30) is coaxially connected to the column (40) and the longitudinal eccentric block (50). The shafts are fixedly connected in sequence, and the coaxial line of the crossbar (20) is perpendicular to the coaxial line of the column (40); the transverse eccentric block (10), crossbar (20), longitudinal eccentric block (50) and column (40) are all cylinders, and the size and connection relationship of each component are configured as follows: during the rotation of the device with the rotating box (8) of the straight wing propeller, the centrifugal force and inertial torque generated generate loads at the lower hinge point of the control rod (5) and the blade bearing that are equivalent to the hydrodynamic load of the actual propeller transmitted to this part.

2. The straight-wing propeller simulation loading device according to claim 1, characterized in that, The structural parameters of the device include: the radius of the transverse eccentric block (10). R H1 Length of the transverse eccentric block (10) L H1 , radius of the crossbar (20) R H2 Length of crossbar (20) L H2 Longitudinal eccentric block (50) radius R L1 Length of longitudinal eccentric block (50) L L1 Column (40) radius R L2 Length of column (40) L L2 The distance between the lateral eccentric block (10) and the bottom of the rotating shaft (30) L L3 And the angle between the axial direction of the transverse eccentric block (10) and the upper EF of the crank (24). δ The simulation loading device preferably uses a manufacturing process of integral forging and machining.

3. The straight-wing propeller simulation loading device according to claim 1, characterized in that, The rotating shaft (30) is used to connect the crank (24) of the straight-wing propeller, so that the simulated loading device rotates together with the rotating housing (8) and transmits the load to the control rod (5) and the blade bearing through the blade actuator (2).

4. The straight-wing propeller simulation loading device according to claim 1, characterized in that, The distance between the center of mass of the simulated loading device and the central axis of the rotating shaft (30), and the distance between the center of mass of the simulated loading device and the bottom of the rotating shaft (30), are calculated based on the mass of the transverse eccentric block, the mass of the crossbar, and the mass of the longitudinal eccentric block. The mass of each component is determined based on the material density. ρ Based on the calculation of their respective geometric dimensions, alloy structural steel is the preferred material for the simulation loading device.

5. A method for parameterizing the dimensions of a straight-wing propeller simulation loading device, used to determine the structural parameters of the straight-wing propeller simulation loading device according to any one of claims 1 to 4, characterized in that, The process includes the following steps: Step S1: Determine the target load, including the hydrodynamic thrust of the single blade of the real propeller, the hydrodynamic rotor torque, the centrifugal force, and the inertial torque; Step S2: Establish the kinematic model of the simulated loading device and the blade actuator, and solve for the angular displacement, angular velocity, angular acceleration, and hinge acceleration of the components; Step S3: Establish the dynamic model of the simulated loading device and the blade actuator, list the dynamic static equilibrium equations of each component based on the d'Alembert principle, and solve for the hinge load of the control rod (5) and the blade bearing load; Step S4: Construct a parameter optimization model, select the structural parameters of the simulated loading device as design variables, construct the objective function, and define the constraints; Step S5: Solve the parameter optimization model to obtain the optimal solution of the structural parameters of the simulated loading device.

6. The method for parameterizing the dimensions of components of a straight-wing propeller simulation loading device according to claim 5, characterized in that, In step S2, the simplified model of the simulated loading device and the blade actuator is transformed into a kinematic model, wherein component AE is the rotating box (8), component BC is the strut (22), component DG is the concentric rod (23), component EF is the crank (24), component GF is the long connecting rod (21), A is the rotation center of the rotating box, B is the hinge point connecting the end of the strut (22), C is the hinge point connecting the strut (22) and the concentric rod (23), D is the hinge point connecting the control rod (5) and the concentric rod (23), E is the hinge point connecting the crank (24) and the end of the blade (1), F is the hinge point connecting the long connecting rod (21) and the crank (24), and G is the hinge point connecting the concentric rod (23) and the long connecting rod (21). Based on the geometric relationship of the components, the equations of quadrilateral ABCD and polygon AEFGD are established, the angular displacement of each component is solved, and the angular velocity and angular acceleration are obtained by differentiating with respect to time.

7. The method for parameterizing the dimensions of components of a straight-wing propeller simulation loading device according to claim 5, characterized in that, In step S3, the simulated loading device and the blade actuator linkage are decomposed, and corresponding inertial forces and inertial torques are applied to the components according to D'Alembert's principle. The dynamic equilibrium equations of the rotating box, strut, concentric rod, long connecting rod and crank-simulated loading device are listed, and the loads at each hinge point are obtained by solving them simultaneously.

8. The method for parameterizing the dimensions of components of a straight-wing propeller simulation loading device according to claim 5, characterized in that, In step S4, the objective function is selected to be able to simulate both the load at the lower hinge point of the control rod (5) during actual propeller operation and the maximum load on the bearing during actual propeller operation; the constraint conditions include constraint conditions determined based on the geometric relationship of the components and constraint conditions determined based on the structural strength relationship of the components.

9. The method for parameterizing the dimensions of components of a straight-wing propeller simulation loading device according to claim 2, characterized in that, In step S4, the selected design variable is: the radius of the lateral eccentric block (10). R H1 Length of the transverse eccentric block (10) L H1 , radius of the crossbar (20) R H2 Length of crossbar (20) L H2 Longitudinal eccentric block (50) radius R L1 Length of longitudinal eccentric block (50) L L1 Column (40) radius R L2 Length of column (40) L L2 The distance between the lateral eccentric block (10) and the bottom of the rotating shaft (30) L L3 And the angle between the axial direction of the transverse eccentric block (10) and the upper EF of the crank (24). δ .

10. The method for parameterizing the dimensions of components of a straight-wing propeller simulation loading device according to claim 5, characterized in that, In step S1, the determination of the target load is based on a simplified model of a single-set blade actuator, wherein the load includes the blade hydrodynamic thrust, the hydrodynamic blade rotation torque, the centrifugal force generated by the blade revolving around the center of the blade, and the inertial torque generated by the blade rotating around its own axis.

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