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Dr. Haitao Luo
State Key Laboratory of Robotics, Shenyang Institute of Automation, Chinese Academy of Sciences (CAS)

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0 dynamics analysis
0 Lightweight Design
0 Vibration And Impact
0 Buffer Protection
0 Space Payload

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Buffer Protection

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Journal article
Published: 17 August 2021 in Acta Astronautica
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Deep space exploration technology is an important development direction for scientific exploration. The penetrator method has been proposed as an inexpensive method of studying planetary bodies. The basic principle of this method is that the detection equipment carried by the high-speed penetrator hits a planetary body at a high speed and is buried up to several meters below the surface to carry out detection work. During the frictional collision process with the planets crust, the instantaneous acceleration peaks of the scientific payload (electronic instrumentation) are large. Shock protection of these payloads is necessary to improve their survival and mission success. In this paper, with the goal of improving the survival rate of scientific loads inside a penetrator, a penetrator with a multilayer energy-absorbing structure is developed, in which cushioning protection measures, such as an aluminum foam-filled corrugated tube(AFFT) structure, polyurethane rubber, and epoxy resin potting, are applied to the penetrator. Since the analysis of this process is a highly nonlinear problem, a numerical modeling method is the main approach in this paper. The LS-DYNA software platform was used to simulate the penetrators penetration process on a moon soil medium. The results obtained using empirical formulas and theoretical derivations were compared with the results of numerical analysis to ensure the accuracy of the penetration simulation model. The finite element model of the penetrator was then verified and modified by conducting shock response spectral experiments and shock simulations. The results showed that the spacer scheme had a positive effect on the impact isolation and energy absorption. In addition, this scheme provides an important reference for the design of the penetrator prototype to guarantee the success of subsequent ground rocket sled experiments.

ACS Style

Haitao Luo; Yuxin Li; Chaohui Fan; Xingyuan Wu; Guangming Liu. Design and experimental research on buffer protection of high-g penetrator for deep space exploration. Acta Astronautica 2021, 189, 63 -78.

AMA Style

Haitao Luo, Yuxin Li, Chaohui Fan, Xingyuan Wu, Guangming Liu. Design and experimental research on buffer protection of high-g penetrator for deep space exploration. Acta Astronautica. 2021; 189 ():63-78.

Chicago/Turabian Style

Haitao Luo; Yuxin Li; Chaohui Fan; Xingyuan Wu; Guangming Liu. 2021. "Design and experimental research on buffer protection of high-g penetrator for deep space exploration." Acta Astronautica 189, no. : 63-78.

Journal article
Published: 28 June 2021 in Coatings
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At present, hard coating structures are widely studied as a new passive damping method. Generally, the hard coating material is completely covered on the surface of the thin-walled structure, but the local coverage cannot only achieve better vibration reduction effect, but also save the material and processing costs. In this paper, a topology optimization method for hard coated composite plates is proposed to maximize the modal loss factors. The finite element dynamic model of hard coating composite plate is established. The topology optimization model is established with the energy ratio of hard coating layer to base layer as the objective function and the amount of damping material as the constraint condition. The sensitivity expression of the objective function to the design variables is derived, and the iteration of the design variables is realized by the Method of Moving Asymptote (MMA). Several numerical examples are provided to demonstrate that this method can obtain the optimal layout of damping materials for hard coating composite plates. The results show that the damping materials are mainly distributed in the area where the stored modal strain energy is large, which is consistent with the traditional design method. Finally, based on the numerical results, the experimental study of local hard coating composites plate is carried out. The results show that the topology optimization method can significantly reduce the frequency response amplitude while reducing the amount of damping materials, which shows the feasibility and effectiveness of the method.

ACS Style

Haitao Luo; Rong Chen; Siwei Guo; Jia Fu. Topology Optimization of Hard-Coating Thin Plate for Maximizing Modal Loss Factors. Coatings 2021, 11, 774 .

AMA Style

Haitao Luo, Rong Chen, Siwei Guo, Jia Fu. Topology Optimization of Hard-Coating Thin Plate for Maximizing Modal Loss Factors. Coatings. 2021; 11 (7):774.

Chicago/Turabian Style

Haitao Luo; Rong Chen; Siwei Guo; Jia Fu. 2021. "Topology Optimization of Hard-Coating Thin Plate for Maximizing Modal Loss Factors." Coatings 11, no. 7: 774.

Journal article
Published: 24 January 2021 in Materials
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A finite element model for setting drilling conditions is established. The effect of feed speed and spindle speed on the drilling process was studied. In the test phase, drilling tests were conducted using three different feed speeds (60, 100, and 140 mm/min) and three different spindle speeds (800, 1000, and 1200 rpm). The correctness of the finite element model was verified by comparing the experimental and numerical simulation data. The results show that the axial force and torque increase significantly with the increase of feed speed, while the axial force and torque increase less as the spindle speed increases. The numerical simulation results show that the temperature of the cutting edge increases as the feed speed increases. Increasing the rotating speed increases the formation of chip curl. When the working conditions are high rotating speed and low feed, the tool wear is reduced, and the machining quality is better. The numerical simulation results obtained for the chip forming effect are similar to the experimental data. In addition, the simulation results show the generation of burrs. A comparison of the finite element simulation and experimental data leads to an in-depth understanding of the drilling process and ability to optimize subsequent drilling parameters, which provide reliable process parameters and technical guarantees for the successful implementation of drilling technology for space suspended ball structures.

ACS Style

Haitao Luo; Jia Fu; Tingke Wu; Ning Chen; Huadong Li. Numerical Simulation and Experimental Study on the Drilling Process of 7075-t6 Aerospace Aluminum Alloy. Materials 2021, 14, 553 .

AMA Style

Haitao Luo, Jia Fu, Tingke Wu, Ning Chen, Huadong Li. Numerical Simulation and Experimental Study on the Drilling Process of 7075-t6 Aerospace Aluminum Alloy. Materials. 2021; 14 (3):553.

Chicago/Turabian Style

Haitao Luo; Jia Fu; Tingke Wu; Ning Chen; Huadong Li. 2021. "Numerical Simulation and Experimental Study on the Drilling Process of 7075-t6 Aerospace Aluminum Alloy." Materials 14, no. 3: 553.

Research article
Published: 01 January 2021 in Composites and Advanced Materials
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Aiming at the problem that the vibration of the space science experimental cabinet is too large during the launch phase of the rocket, the viscoelastic constrained damping layer is used to suppress the vibration. Firstly, to explore the vibration suppression mechanism of the constrained damping layer, the dynamic model of the constrained damping layer is established and the modal loss factor is calculated. Secondly, the influence of the modulus, material thickness, and the position and the area of the damping layer on the loss factor of the structure is analyzed. Finally, the simulation and experiment methods are used to calculate and verify the space science experiment cabinet with additional constrained damping layer. The results show that the viscoelastic constrained damping can effectively reduce the vibration level of the space science experiment cabinet, and the acceleration response in the resonance region is reduced by more than 56%. The viscoelastic constrained damping structure is simple and easy to realize, which can suppress the vibration of the space payload design is of great significance.

ACS Style

Haitao Luo; Siwei Guo; Changshuai Yu; Jia Fu; Haochen Wang; Guangming Liu; Zhong Luo. Vibration suppression analysis and experimental test of additional constrained damping layer in space science experiment cabinet. Composites and Advanced Materials 2021, 30, 1 .

AMA Style

Haitao Luo, Siwei Guo, Changshuai Yu, Jia Fu, Haochen Wang, Guangming Liu, Zhong Luo. Vibration suppression analysis and experimental test of additional constrained damping layer in space science experiment cabinet. Composites and Advanced Materials. 2021; 30 ():1.

Chicago/Turabian Style

Haitao Luo; Siwei Guo; Changshuai Yu; Jia Fu; Haochen Wang; Guangming Liu; Zhong Luo. 2021. "Vibration suppression analysis and experimental test of additional constrained damping layer in space science experiment cabinet." Composites and Advanced Materials 30, no. : 1.

Research article
Published: 01 January 2021 in International Journal of Advanced Robotic Systems
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The friction stir welding robot for aerospace applications developed by the research group is subject to the effects of size, working conditions, and other conditions during the operation. The load conditions of the friction stir welding robot are harsh, and the strength and stiffness tests of the whole machine need to be carried out. Five typical working conditions of the friction stir welding robot are analyzed. By analyzing the system composition and configuration of the robot, the loading conditions of the robot stirring head during the welding process are accurately simulated, and this is used as the stiffness and strength check. The boundary conditions of the robot are simulated and analyzed under typical working conditions. The results show that the data of each part of the robot under load are obtained for a given size of the rocket cap welding. After analysis, the maximum normal displacement of the friction stir welding robot reached 0.6424 mm and the maximum stress was 79.21 MPa under the condition of melon flap welding.

ACS Style

Haitao Luo; Fengqun Zhao; Siwei Guo; Changshuai Yu; Guangming Liu; Tingke Wu. Mechanical performance research of friction stir welding robot for aerospace applications. International Journal of Advanced Robotic Systems 2021, 18, 1 .

AMA Style

Haitao Luo, Fengqun Zhao, Siwei Guo, Changshuai Yu, Guangming Liu, Tingke Wu. Mechanical performance research of friction stir welding robot for aerospace applications. International Journal of Advanced Robotic Systems. 2021; 18 (1):1.

Chicago/Turabian Style

Haitao Luo; Fengqun Zhao; Siwei Guo; Changshuai Yu; Guangming Liu; Tingke Wu. 2021. "Mechanical performance research of friction stir welding robot for aerospace applications." International Journal of Advanced Robotic Systems 18, no. 1: 1.

Journal article
Published: 24 December 2020 in Applied Sciences
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The Microgravity Platform (MP) of the Chinese Space Station is locked and released by Lock-or-Release (L/R) mechanism on both sides. In order to ensure the safety and reliability of the MP under the vibration environment during the rocket launch, the L/R mechanism must output the appropriate locking torque value. Based on the structural characteristics of the Scientific Experiment Cabinet (SEC), this paper proposes a method of evaluating locking torque by combining theory with experiment, and the relationship between locking force and locking torque of L/R mechanism is proved that the locking force on both sides can reach 2000 N at 25 Nm driving torque. Finally, it is verified by vibration test that the locking torque obtained by this method can effectively guarantee the safety and reliability of the MP under vibration environment.

ACS Style

Guangming Liu; Haitao Luo; Changshuai Yu; Haochen Wang; Lilu Meng. Simulation Analysis and Experimental Verification of the Locking Torque of the Microgravity Platform of the Chinese Space Station. Applied Sciences 2020, 11, 102 .

AMA Style

Guangming Liu, Haitao Luo, Changshuai Yu, Haochen Wang, Lilu Meng. Simulation Analysis and Experimental Verification of the Locking Torque of the Microgravity Platform of the Chinese Space Station. Applied Sciences. 2020; 11 (1):102.

Chicago/Turabian Style

Guangming Liu; Haitao Luo; Changshuai Yu; Haochen Wang; Lilu Meng. 2020. "Simulation Analysis and Experimental Verification of the Locking Torque of the Microgravity Platform of the Chinese Space Station." Applied Sciences 11, no. 1: 102.

Research article
Published: 25 July 2020 in Complexity
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The UAV/UGV heterogeneous system combines the air superiority of UAV (unmanned aerial vehicle) and the ground superiority of UGV (unmanned ground vehicle). The system can complete a series of complex tasks and one of them is pursuit-evasion decision, so a collaborative strategy of UAV/UGV heterogeneous system is proposed to derive a pursuit-evasion game in complex three-dimensional (3D) polygonal environment, which is large enough but with boundary. Firstly, the system and task hypothesis are introduced. Then, an improved boundary value problem (BVP) is used to unify the terrain data of decision and path planning. Under the condition that the evader knows the position of collaborative pursuers at any time but pursuers just have a line-of-sight view, a worst case is analyzed and the strategy between the evader and pursuers is studied. According to the state of evader, the strategy of collaborative pursuers is discussed in three situations: evader is in the visual field of pursuers, evader just disappears from the visual field of pursuers, and the position of evader is completely unknown to pursuers. The simulation results show that the strategy does not guarantee that the pursuers will win the game in complex 3D polygonal environment, but it is optimal in the worst case.

ACS Style

Xiao Liang; Honglun Wang; Haitao Luo. Collaborative Pursuit-Evasion Strategy of UAV/UGV Heterogeneous System in Complex Three-Dimensional Polygonal Environment. Complexity 2020, 2020, 1 -13.

AMA Style

Xiao Liang, Honglun Wang, Haitao Luo. Collaborative Pursuit-Evasion Strategy of UAV/UGV Heterogeneous System in Complex Three-Dimensional Polygonal Environment. Complexity. 2020; 2020 ():1-13.

Chicago/Turabian Style

Xiao Liang; Honglun Wang; Haitao Luo. 2020. "Collaborative Pursuit-Evasion Strategy of UAV/UGV Heterogeneous System in Complex Three-Dimensional Polygonal Environment." Complexity 2020, no. : 1-13.

Research article
Published: 13 July 2020 in Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science
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In an attempt to address the limitations of single function and the poor process flexibility of existing friction stir welding equipment, a new friction stir welding robot has been developed to address practical problems in three-dimensional surface welding. Based on an analysis of the components of the robotic system, a kinematics model was established, and the forward and backward kinematics solutions were derived for the robot. An iterative nearest point algorithm, iterative closest point based on point cloud matching, was used to plan the welding trajectory for the most complex petal welding conditions, and an experimental study was conducted. The results show that the kinematic and dynamic test results were consistent with the acquired simulation curves for specific sizes of the rocket cap flaps under appropriate welding conditions. The normal error of the weld was less than 85 µm, the average tensile strength was 359 MPa, and the elongation was 7.20%, 78.0%, and 72.0% of 2A14-T6 aluminum alloy. The friction stir welding robot exhibited robust performance, and the proposed trajectory planning method is practical and effective. The appearance, geometric dimension, and mechanical properties of the weld achieved the expected criteria, and high-precision welding of large complex thin-walled surfaces is possible.

ACS Style

Luo Haitao; Wu Tingke; Fu Jia; Zhao Fengqun. Analysis of typical working conditions and experimental research of friction stir welding robot for aerospace applications. Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 2020, 1 .

AMA Style

Luo Haitao, Wu Tingke, Fu Jia, Zhao Fengqun. Analysis of typical working conditions and experimental research of friction stir welding robot for aerospace applications. Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science. 2020; ():1.

Chicago/Turabian Style

Luo Haitao; Wu Tingke; Fu Jia; Zhao Fengqun. 2020. "Analysis of typical working conditions and experimental research of friction stir welding robot for aerospace applications." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science , no. : 1.

Review article
Published: 01 January 2020 in Advanced Composites Letters
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Due to the difficulty of direct finite-element modeling for honeycomb sandwich panels, it is more common to apply equivalent modeling theories. It is necessary to compare their equivalent precision and then to determine the method with the best equivalent performance so as to prepare for the application in satellite solar arrays. The first 10 natural frequencies are obtained by analyzing the dynamic characteristics of sandwich panel theory model, honeycomb panel theory model, and equivalent panel theory model. The equivalent errors of different equivalent methods are obtained by comparison with the analysis results of real honeycomb panel model. Then, the sandwich panel theory and the Hoff theory with high precision are used to simulate the solar array panel. The two methods are further verified and compared by simulation and experiment. Finally, the sandwich panel theory with the highest accuracy is selected to simulate the vibration response of the solar array panel based on the above work. By comparing the frequency response analysis results with the test results, it is found that the maximum acceleration response error is within 7%, and the corresponding frequency error of the main direction is within 3%. The comparison between random analysis results and test results shows that the root mean square response errors of acceleration in three directions are within 13.7%. It is proved that the sandwich panel theory has high accuracy in the honeycomb structure. Based on the background of a specific space project, this study innovatively applies the test results to compare several typical equivalent theories of honeycomb sandwich panels so as to get a theory with the highest equivalent precision. The final conclusion has been applied to the design of related space products and proved to be feasible. This provides important reference and basis for the structural design of the satellite.

ACS Style

Wei Wang; Haitao Luo; Jia Fu; Haochen Wang; Changshuai Yu; Guangming Liu; Qiming Wei; Shufan Wu. Comparative application analysis and test verification on equivalent modeling theories of honeycomb sandwich panels for satellite solar arrays. Advanced Composites Letters 2020, 29, 1 .

AMA Style

Wei Wang, Haitao Luo, Jia Fu, Haochen Wang, Changshuai Yu, Guangming Liu, Qiming Wei, Shufan Wu. Comparative application analysis and test verification on equivalent modeling theories of honeycomb sandwich panels for satellite solar arrays. Advanced Composites Letters. 2020; 29 ():1.

Chicago/Turabian Style

Wei Wang; Haitao Luo; Jia Fu; Haochen Wang; Changshuai Yu; Guangming Liu; Qiming Wei; Shufan Wu. 2020. "Comparative application analysis and test verification on equivalent modeling theories of honeycomb sandwich panels for satellite solar arrays." Advanced Composites Letters 29, no. : 1.

Research article
Published: 26 November 2019 in Shock and Vibration
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High-speed penetrators carrying detection equipment impact planetary bodies at high speeds, and they are therefore buried at depths of up to several meters beneath the surface. During the friction and collision with the crust of the planet, the acceleration of the scientific instrumentation is significantly large. The vibration protection structure for scientific instrumentation is necessary for the reduction of the peak value of the acceleration response and the improvement of the survival rate. In this study, a penetrator with a multilayered energy absorbing structure was developed to improve the survival rate of the penetrator, of which the foam-filled thin-walled structure (FTS) was applied to the penetrating vibration-damping structure. The penetration process of the penetrator into the planetary medium was simulated using the LS-DYNA software platform. The results obtained using empirical formulas and theoretical derivations were compared with the results of the numerical analysis. The reliability of the penetrator limit element model was then verified by conducting an impulse response experiment and simulation. The results suggest that FTS has a positive influence on the isolation impact and energy absorption. Moreover, the vibration isolation effects of nine different FTSs were evaluated with respect to the following six factors: impact isolation efficiency, load efficiency, peak of acceleration, peak impact force, total energy absorption, and specific energy absorption. Furthermore, the design of the damping structure provides an indispensable solution for penetrator detection.

ACS Style

Haitao Luo; Yuxin Li; Guangming Liu; Changshuai Yu; Shipeng Chen. Buffering Performance of High-Speed Impact Space Penetrator with Foam-Filled Thin-Walled Structure. Shock and Vibration 2019, 2019, 1 -15.

AMA Style

Haitao Luo, Yuxin Li, Guangming Liu, Changshuai Yu, Shipeng Chen. Buffering Performance of High-Speed Impact Space Penetrator with Foam-Filled Thin-Walled Structure. Shock and Vibration. 2019; 2019 ():1-15.

Chicago/Turabian Style

Haitao Luo; Yuxin Li; Guangming Liu; Changshuai Yu; Shipeng Chen. 2019. "Buffering Performance of High-Speed Impact Space Penetrator with Foam-Filled Thin-Walled Structure." Shock and Vibration 2019, no. : 1-15.

Journal article
Published: 17 October 2019 in Materials
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Aiming at the problems that the temperature in the welding area of friction stir welding (FSW) is difficult to measure and the joints are prone to defects. Hence, it is particularly important to study the material flow in the welding area and improve the welding quality. The temperature of the tool shoulder and the tool pin was monitored by the wireless temperature measuring system. The finite element model of friction stir welding was established and the welding conditions were numerically simulated. The flow law of material of the friction stir welding process was studied by numerical simulation. The material flow model was established by combining the microstructure analysis results, and the forming mechanism of the defects was analyzed. The results show that the temperature in the welding zone is the highest at 1300 rpm, and the temperature at the tool shoulder is significantly higher than that at the tool pin in the welding stage. When high-rotation speeds (HRS) are chosen, the material beneath the tool shoulder tends to be extruded into the pin stirred zone (PSZ) after flowing back to the advancing side. This will cause turbulence phenomenon in the advancing side of the joint, which will easily lead to the formation of welding defects. In the future, temperature monitoring methods and the flow model of material can be used to optimize the welding parameters.

ACS Style

Tingke Wu; Fengqun Zhao; Haitao Luo; Haonan Wang; Yuxin Li. Temperature Monitoring and Material Flow Characteristics of Friction Stir Welded 2A14-t6 Aerospace Aluminum Alloy. Materials 2019, 12, 3387 .

AMA Style

Tingke Wu, Fengqun Zhao, Haitao Luo, Haonan Wang, Yuxin Li. Temperature Monitoring and Material Flow Characteristics of Friction Stir Welded 2A14-t6 Aerospace Aluminum Alloy. Materials. 2019; 12 (20):3387.

Chicago/Turabian Style

Tingke Wu; Fengqun Zhao; Haitao Luo; Haonan Wang; Yuxin Li. 2019. "Temperature Monitoring and Material Flow Characteristics of Friction Stir Welded 2A14-t6 Aerospace Aluminum Alloy." Materials 12, no. 20: 3387.

Research article
Published: 24 July 2019 in Advances in Mechanical Engineering
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The mechanical configuration, structural composition, and five typical working conditions of a newly developed friction stir welding robot are introduced. The kinematics model of the friction stir welding robot is established and the forward kinematics equations, inverse kinematics equations, and the Jacobian matrix are solved. In addition, the dynamics model of the friction stir welding robot is also built by using the Lagrange method. The centroid position coordinate and inertia matrix of each part are obtained. Finally, the dynamic equation of friction stir welding robot is determined. According to the kinematics and dynamics model of robots, simulation analysis for friction stir welding robot based on virtual prototyping technology was carried out. The trajectory equation of the weld joint under the condition of melon petal welding is established, the spline trajectory is fitted by many discrete points measured by the contact probe, and the trajectory planning of each joint and the changing laws of motion parameters under the friction stir welding robot melon petal welding condition are obtained. The movement laws and the loading conditions of each joint can be better controlled by designers, and provide solid theoretical support for the static and dynamic characteristics analysis and structural optimization of the friction stir welding robot.

ACS Style

Haitao Luo; Jia Fu; Lichuang Jiao; Guangming Liu; Changshuai Yu; Tingke Wu. Kinematics and dynamics analysis of a new-type friction stir welding robot and its simulation. Advances in Mechanical Engineering 2019, 11, 1 .

AMA Style

Haitao Luo, Jia Fu, Lichuang Jiao, Guangming Liu, Changshuai Yu, Tingke Wu. Kinematics and dynamics analysis of a new-type friction stir welding robot and its simulation. Advances in Mechanical Engineering. 2019; 11 (7):1.

Chicago/Turabian Style

Haitao Luo; Jia Fu; Lichuang Jiao; Guangming Liu; Changshuai Yu; Tingke Wu. 2019. "Kinematics and dynamics analysis of a new-type friction stir welding robot and its simulation." Advances in Mechanical Engineering 11, no. 7: 1.

Research article
Published: 27 June 2019 in Mathematical Problems in Engineering
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Double-nut ball screws bear the action of bidirectional pretightening force, leading to the deformation of the contact area between the ball and the raceway. Under this condition, it is important to analyze and calculate the static stiffness of the ball screw. However, the conventional calculation method is inaccurate. Hence, a new method for the static stiffness analysis of a double-nut ball screw is proposed. Through the structural analysis of the ball screw and internal load distribution, a load deformation model was established based on the Hertzian contact theory. Through the load analysis of the ball screw, a static stiffness model of the ball screw was established and applied to a case study and a finite element simulation. The rigidity of THK double-nut ball screws used in the X-axis feed system of a high-stiffness heavy-duty friction stir welding robot (developed by the research group) was calculated. When the workload was lower than 1.1 × 104 N, the slope of the double-nut static stiffness curve increased significantly with the increase in the workload, and when the workload was greater than 1.1 × 104 N, its upward slope tended to stabilize. The simulated and experimental stiffness curves were in good agreement; when the external axial load was greater than 2.8 × 104 N, the stiffness value calculated using the finite element method gradually converged to the theoretical value; and when the axial load reached 3.0 × 104 N, the simulation and test curves matched well. The analysis method of the double-nut ball screw was found to be concise and accurate, and the stiffness curves calculated using the two methods were consistent. The simulation analysis of the static stiffness presented herein is expected to aid the design of double-nut ball screws of high-rigidity heavy-duty equipment.

ACS Style

Haitao Luo; Jia Fu; Lichuang Jiao; Fengqun Zhao. Theoretical Calculation and Simulation Analysis of Axial Static Stiffness of Double-Nut Ball Screw with Heavy Load and High Precision. Mathematical Problems in Engineering 2019, 2019, 1 -11.

AMA Style

Haitao Luo, Jia Fu, Lichuang Jiao, Fengqun Zhao. Theoretical Calculation and Simulation Analysis of Axial Static Stiffness of Double-Nut Ball Screw with Heavy Load and High Precision. Mathematical Problems in Engineering. 2019; 2019 ():1-11.

Chicago/Turabian Style

Haitao Luo; Jia Fu; Lichuang Jiao; Fengqun Zhao. 2019. "Theoretical Calculation and Simulation Analysis of Axial Static Stiffness of Double-Nut Ball Screw with Heavy Load and High Precision." Mathematical Problems in Engineering 2019, no. : 1-11.

Journal article
Published: 28 May 2019 in Metals
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Friction stir welding (FSW) material flow has an important influence on weld formation. The finite element model of the FSW process was established. The axial force and the spindle torque of the welding process were collected through experiments. The feasibility of the finite element model was verified by a data comparison. The temperature field of the welding process was analyzed hierarchically. It was found that the temperature on the advancing side is about 20 °C higher than that on the retreating side near the welding seam, but that the temperature difference between the two sides of the middle and lower layers was decreased. The particle tracking technique was used to study the material flow law in different areas of the weld seam. The results showed that part of the material inside the tool pin was squeezed to the bottom of the workpiece. The material on the upper surface tends to move downward under the influence of the shoulder extrusion, while the material on the lower part moves spirally upward under the influence of the tool pin. The material flow amount of the advancing side is higher than that of the retreating side. The law of material flow reveals the possible causes of the welding defects. It was found that the abnormal flow of materials at a low rotation speed and high welding speed is prone to holes and crack defects. The forming reasons and material flow differences in different regions are studied through the microstructure of the joint cross section. The feasibility of a finite element modeling and simulation analysis is further verified.

ACS Style

Haitao Luo; Tingke Wu; Peng Wang; Fengqun Zhao; Haonan Wang; Yuxin Li; Luo; Wu; Zhao; Wang; Li. Numerical Simulation of Material Flow and Analysis of Welding Characteristics in Friction Stir Welding Process. Metals 2019, 9, 621 .

AMA Style

Haitao Luo, Tingke Wu, Peng Wang, Fengqun Zhao, Haonan Wang, Yuxin Li, Luo, Wu, Zhao, Wang, Li. Numerical Simulation of Material Flow and Analysis of Welding Characteristics in Friction Stir Welding Process. Metals. 2019; 9 (6):621.

Chicago/Turabian Style

Haitao Luo; Tingke Wu; Peng Wang; Fengqun Zhao; Haonan Wang; Yuxin Li; Luo; Wu; Zhao; Wang; Li. 2019. "Numerical Simulation of Material Flow and Analysis of Welding Characteristics in Friction Stir Welding Process." Metals 9, no. 6: 621.

Conference paper
Published: 10 April 2019 in IOP Conference Series: Materials Science and Engineering
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In order to improve the numerical calculation accuracy of the hexagonal aluminum honeycomb panel, the influence of the length-thickness ratio on the dynamic calculation accuracy of the equivalent models is studied. The modal frequencies of the equivalent models and the entity model are compared to analyse the influence of the length-thickness ratio on the dynamic calculation accuracy of the equivalent models. The results show that the first 10 order errors of sandwich panel theory model and honeycomb panel theory model are less than 20% for medium thickness panel with length-thickness ratio less than 10.3, so the equivalent effect is ideal. When the ratio of length to thickness of Reissner theory model and honeycomb panel theory model is about 10.3 and 13.7 respectively, the calculation accuracy is low and the error peak appears. The sandwich panel theory model has lower accuracy than other equivalent models for thick panel.

ACS Style

Haitao Luo; Wei Wang; Tingke Wu; Haonan Wang. Effects of length-thickness ratio on the dynamic calculation accuracy of the honeycomb panel equivalent models. IOP Conference Series: Materials Science and Engineering 2019, 490, 052034 .

AMA Style

Haitao Luo, Wei Wang, Tingke Wu, Haonan Wang. Effects of length-thickness ratio on the dynamic calculation accuracy of the honeycomb panel equivalent models. IOP Conference Series: Materials Science and Engineering. 2019; 490 (5):052034.

Chicago/Turabian Style

Haitao Luo; Wei Wang; Tingke Wu; Haonan Wang. 2019. "Effects of length-thickness ratio on the dynamic calculation accuracy of the honeycomb panel equivalent models." IOP Conference Series: Materials Science and Engineering 490, no. 5: 052034.

Research article
Published: 21 March 2019 in Shock and Vibration
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The modal analysis of a satellite sailboard finite element model is carried out to accurately investigate the response of a satellite sailboard in a complex loaded space environment through simulation. The basic excitation vibration test of the satellite sailboard is used to perform model matching and a correlation test. Appropriate design variables are selected through sensitivity analysis. Modal analysis data and vibration table excitation test response data are used to modify the finite element model. After optimization, the orthogonality of the simulated vibration mode and experimental vibration mode is good. The low-order frequency errors in the simulation model are less than 5%, the high-order errors are less than 10%, and the modal confidence MAC values are above 0.8. The modal frequency and mode shape are closer to the experimental modal frequency and mode shape, respectively. The simulation and test acceleration response of the modified finite element model of a honeycomb panel are compared under the two conditions of sine sweep and random vibration. The acceleration response curves of reference points are consistent, and amplitude and frequency errors are within acceptable limits. The model updating effect is evident, which provides good reference for research on satellites and other aerospace products.

ACS Style

Haitao Luo; Wei Wang; Jia Fu; Lichuang Jiao. Finite Element Model Updating of Satellite Sailboard Based on Sensitivity Analysis. Shock and Vibration 2019, 2019, 1 -12.

AMA Style

Haitao Luo, Wei Wang, Jia Fu, Lichuang Jiao. Finite Element Model Updating of Satellite Sailboard Based on Sensitivity Analysis. Shock and Vibration. 2019; 2019 ():1-12.

Chicago/Turabian Style

Haitao Luo; Wei Wang; Jia Fu; Lichuang Jiao. 2019. "Finite Element Model Updating of Satellite Sailboard Based on Sensitivity Analysis." Shock and Vibration 2019, no. : 1-12.

Research article
Published: 13 March 2019 in Advances in Mechanical Engineering
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Kinematics and dynamics are the most important and basic tool for robot research. With the help of computer technology and the respective advantages of three kinds of software, a new method of co-simulation of parallel robot based on multi-platform is proposed, and the mechanical model of multi-body system of 3-revolute-prismatic-spherical parallel robot is established. According to the mechanical analysis of the parallel robot, the rigid-flexible coupling analysis method is adopted. The displacement error shows a periodic change with a period of 4.2 s and the maximum error is [Formula: see text]. The dangerous part of the structure is the root of the lower link, and its maximum stress is 202.64 MPa less than the yield strength of the material. The multi-software platform co-simulation improves the accuracy of the dynamic response analysis of the part under dynamic load, and provides an important theoretical basis for the design and optimization of the parallel robot.

ACS Style

Haitao Luo; Jia Fu; Lichuang Jiao; Ning Chen; Tingke Wu. Rigid-flexible coupled dynamics analysis of 3-revolute-prismatic-spherical parallel robot based on multi-software platform. Advances in Mechanical Engineering 2019, 11, 1 .

AMA Style

Haitao Luo, Jia Fu, Lichuang Jiao, Ning Chen, Tingke Wu. Rigid-flexible coupled dynamics analysis of 3-revolute-prismatic-spherical parallel robot based on multi-software platform. Advances in Mechanical Engineering. 2019; 11 (3):1.

Chicago/Turabian Style

Haitao Luo; Jia Fu; Lichuang Jiao; Ning Chen; Tingke Wu. 2019. "Rigid-flexible coupled dynamics analysis of 3-revolute-prismatic-spherical parallel robot based on multi-software platform." Advances in Mechanical Engineering 11, no. 3: 1.

Journal article
Published: 04 February 2019 in Materials
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According to the actual size parameters, the finite element model (FEM) of friction stir welding (FSW) was established, and the FEM was updated by experiments. The FSW of the 2A14-T6 high-strength aluminum alloy was simulated under a reasonable welding process parameter range, and the welding process parameters with good simulation effect were determined. The test was carried out under the same parameters, and the axial force of the FSW tool and temperature of the workpiece measuring point were collected. The comparison between the simulated data and the experimental data is reasonable, indicating the correctness of the FEM. The microstructure analysis of the welded joint shows that the grain size in the upper part of the weld nugget was smaller than that in the middle and lower parts, and there are obvious boundaries of grain size in each region of the joint. The hardness of the joint in the upper layer is higher than that in the middle and lower layers, and the minimum Vickers hardness value of the joint appears near the interface between the thermo-mechanically affected zone and the heat-affected zone on both sides of the weld. Tensile testing shows that the strength coefficient of the joint reaches 82.5% under this process parameter, and the sample breaks at the intersection of the material flow during stretching. After analyzing the final mechanical properties of the joint, we found that a degree of aerospace application can be achieved. Under this parameter, the welding test was carried out on the top cover of the rocket fuel tank. Firstly, melon valve welding, which is relatively difficult in welding conditions, was carried out, and a high-quality joint with good surface and no defects was obtained.

ACS Style

Haitao Luo; Tingke Wu; Jia Fu; Wei Wang; Ning Chen; Haonan Wang. Welding Characteristics Analysis and Application on Spacecraft of Friction Stir Welded 2A14-T6 Aluminum Alloy. Materials 2019, 12, 480 .

AMA Style

Haitao Luo, Tingke Wu, Jia Fu, Wei Wang, Ning Chen, Haonan Wang. Welding Characteristics Analysis and Application on Spacecraft of Friction Stir Welded 2A14-T6 Aluminum Alloy. Materials. 2019; 12 (3):480.

Chicago/Turabian Style

Haitao Luo; Tingke Wu; Jia Fu; Wei Wang; Ning Chen; Haonan Wang. 2019. "Welding Characteristics Analysis and Application on Spacecraft of Friction Stir Welded 2A14-T6 Aluminum Alloy." Materials 12, no. 3: 480.

Journal article
Published: 24 January 2019 in DEStech Transactions on Computer Science and Engineering
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In order to obtain higher equivalent accuracy in the dynamics study of satellite sailboard using sandwich panel theory, the cell size of satellite sailboard is optimized. By comparing the changes of modal frequency equivalent errors of different structures, the equivalent accuracy of satellite sailboard structure is the best when the wall thickness is 0.02 mm and the wall length is 6 mm. The section size parameter with the smallest equivalent error is applied to the honeycomb sandwich plate structure of satellite sailboard. By comparing the modal analysis results of the equivalent theoretical model with the modal test results, the modal frequency equivalent errors are within 11% and the fundamental frequency error is as low as 0.1%. The equivalent theory can be well applied to the simulation of dynamic response of honeycomb sandwich panels of this size, which provides a new verification method for the rational application of equivalent theory in honeycomb structures and a new reference for the subsequent design and research of honeycomb sandwich panel.

ACS Style

Wei Wang; Li-Xin Guo; Hai-Tao Luo; Jia Fu; Li-Chuang Jiao. Influence of Cell Size on Equivalent Calculation Accuracy of Satellite Sailboard. DEStech Transactions on Computer Science and Engineering 2019, 1 .

AMA Style

Wei Wang, Li-Xin Guo, Hai-Tao Luo, Jia Fu, Li-Chuang Jiao. Influence of Cell Size on Equivalent Calculation Accuracy of Satellite Sailboard. DEStech Transactions on Computer Science and Engineering. 2019; (msota):1.

Chicago/Turabian Style

Wei Wang; Li-Xin Guo; Hai-Tao Luo; Jia Fu; Li-Chuang Jiao. 2019. "Influence of Cell Size on Equivalent Calculation Accuracy of Satellite Sailboard." DEStech Transactions on Computer Science and Engineering , no. msota: 1.

Original article
Published: 01 January 2019 in Mechanics of Advanced Materials and Structures
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This paper proposes a method for designing the ram structure of friction stir welding (FSW) robots using finite element analysis. Under the given working condition, force analysis for the ram structure is performed. By analyzing the boundary and load cases on the ram structure, we optimize the topology and size. Through ram-structure optimization considering the static and dynamic characteristics, we can achieve lightweight design of the ram structure and effectively improve the FSW robot’s welding precision. The optimization flow and method can be applied to heavy-load robots and high-stiffness structure.

ACS Style

Haitao Luo; Jia Fu; Peng Wang; Jinguo Liu; Weijia Zhou. Design optimization of the ram structure of friction stir welding robot. Mechanics of Advanced Materials and Structures 2019, 27, 108 -118.

AMA Style

Haitao Luo, Jia Fu, Peng Wang, Jinguo Liu, Weijia Zhou. Design optimization of the ram structure of friction stir welding robot. Mechanics of Advanced Materials and Structures. 2019; 27 (2):108-118.

Chicago/Turabian Style

Haitao Luo; Jia Fu; Peng Wang; Jinguo Liu; Weijia Zhou. 2019. "Design optimization of the ram structure of friction stir welding robot." Mechanics of Advanced Materials and Structures 27, no. 2: 108-118.