Applied Mechanics and Materials Vol. 455

Abstract: This paper approaches the rules of curvature mode and curvature mode difference about a simply supported beam. On the basis of the theory of curvature mode, through numerical simulation analysis of simply supported beam on four conditions, the result of simply supported beam with curvature mode and curvature mode difference were obtained. The results show that for the damaged beam information with numerical simulation, the curvature mode and curvature mode difference index calculated by difference method at the unit length unevenly is with strong noise, which can even submerge the beam damage information, and for different damage index of the beam, damage information from curvature mode difference curve is stronger and effected by unit length weaker than those from curvature mode curve, and damage information from curvature mode curve and curvature mode difference curve decrease with the increasing mode order.

Abstract: Based on the existing cable failure problems, two features of cable failure problems areput forward. The cablescannot be measured precisely and their characteristics cannot be predicted certainly. In order toanalyze the reliability of cables more reasonably, non-probabilistic reliability theory and its development status are introducedin this article. And the theory of modified one dimensional optimization algorithm is appliedto thereliability analysis of stayed-cable. Its results are comparedwith the results of the probabilistic reliability analysis of stayed-cable. Then the parameters analyses of cableare taken, as a result, the main factors that haveobviouslyinfluence on the reliability of the cable are presented in the article.

Abstract: The purpose of conventional counterbalance mechanism featuring a fixed counterbalance torque is to balance the nonuniformity of polished rod load. Therefore, it cannot satisfy the demand of polish rod load which changes with well-condition and then leads to increase of power cost for decreasing quality of balance. This paper presents a new dynamic adjusting mechanism of counterbalance in beam-pumping unit that can adjust the counterbalance torque automatically without stopping the unit according to the new balance parameters derived by analyzing the variation of well-condition and increase productivity at the same time. A data comparison based on the corresponding kinetic model of transmission mechanism is also discussed.

Abstract: The thin-walled shell axial impact deformation of one-leg electric detonator with different density charge was studied. The impact stress was analyzed, and on the basis of kinetic theory the impact deformation model was established for the thin-walled shell filled with explosive. The experiments were verified at 60 000g, 80 000g, 100 000g and 120 000g by gas gun. The results show that shell length decreases and the plastic deformation zone diameter increases after impact. Damage deformation degree decreases with increased shell strength, reduced shell and internal charging mass summation and reduced impact velocity square. The model calculated value agrees well with the test data. The deformation model can be used to predict overload damage deformation for such detonator.

Abstract: Focus on the performances of ASU, this paper utilized Lagrange equations to build the modeling of ASU and comprehensively analyze the work performances including shock resistance, synchronization and stability by use of orthogonal experiment methods under nine different operating conditions of coupling horizontal, rolling and pitching movements. From simulations of the work system in the velocity of 5~15(m/s), rolling angular velocity of 0~12 (rad/s), pitching angular velocity of 0~6 (rad/s), the results can be obtained under combined 3-factor and 3-level work conditions: the optimized combination is the speed in range of 10~15 (m/s), rolling angular velocity of 4~8 (deg/s) and pitching angular velocity of 4~6 (deg/s) and whole work performances fulfill the designed requirements.

Abstract: In order to research the problem of Aeolian vibration occurred on single conductor in this paper, ADINA program was applied to set up the model of fluid domain and structure domain. Fluid-structure interaction (FSI) analysis was taken based on the coupling models, from which the property result of Aeolian vibration numerical simulation was acquired. Meanwhile the method taken to analyze the question of conductors Aeolian vibration was testified to be correct in the paper.

Abstract: Static temperature model identification and compensation of vibrating beam accelerometer (VBA) are studied in this paper. The relationships between scale factor K₁, zero bias K₀ with temperature are obtained through static rolling test in 1g-gravitational field. The accelerometer static temperature model between-40°C to 60°C is established using the least square method. The error model is used for temperature compensation of VBA. Results show that the precision of fitting RMS error is improved by an order of magnitude.

Abstract: Distinguished quadrotor , the research of tricopter is still in undeveloped state. This paper focuses on torque analysis and mathematical modeling for attitude control of the tricopter aircraft. The simulation of controller shows that the PID method can not achieve the desired states, so the research of building the mathematical model provides some theoretical foundation for controlling the tricopter.

Abstract: In order to study the random vibration responses of satellite-borne equipment, the finite element model of satellite-borne equipment was established and its random vibration analysis was performed by ANSYS. The results showed that the stress of key part was too large to meet the strength requirement. The structural design was modified based on the stress analysis results. At the cost of adding 1.03% weight, we find the fundamental frequency of the modified model is increased by 14% and the maximum 1˰σ von Mises stress is decreased by 30%, which verify the correctness of the modification method. This analysis and modification method also can be applied to modify other satellite-borne equipments to shorten the development period and reduce the design cost.

Abstract: According to the structure of the airfoil, cantilever plate is made to substitute airfoil. The function of load is fit by using the primary function sequence. The load identification is transformed into solution of the fitting coefficients; numerical simulation shows the method is effective. Finally, the factors of effecting precision are studied.