The feasibility of utilizing molybdenum tailing and diatomite as siliceous materials to prepare calcium silicate board was explored.The influences of molybdenum tailing/diatomite proportion on hydration characteristic...The feasibility of utilizing molybdenum tailing and diatomite as siliceous materials to prepare calcium silicate board was explored.The influences of molybdenum tailing/diatomite proportion on hydration characteristics,thermal conductivity,water absorption,flexural strength and moisture adsorption-desorption property of calcium silicate board were investigated in detail.The experimental results reveal that molybdenum tailing is environmentally friendly to prepare building materials.The main hydration products in calcium silicate board under autoclaved condition are C-S-H with low crystallinity and tobermorite.Molybdenum tailing is favorable to the formation of tobermorite.The flexural strength and bulk density of the calcium silicate board gradually increase when the content of molybdenum tailing increases.Netlike C-S-H is formed with the increase of diatomite content during autoclaved curing process,resulting in the enhancement of moisture adsorptiondesorption performance and the reduction of thermal conductivity.The optimal content of molybdenum tailing is 20%,furthermore,the flexual strength and thermal conductivity of calcium silicate board at this content meet the Chinese standard JC/T564.1-2008.展开更多
To study the rolling control characteristics of a canard-controlled missile, a series of wind tunnel experiment is conducted. The experimental method, the structure features of wind tunnel model and the experimental r...To study the rolling control characteristics of a canard-controlled missile, a series of wind tunnel experiment is conducted. The experimental method, the structure features of wind tunnel model and the experimental results are introduced in this paper. The experimental data show that the canard is an inefficient rolling control device for canard-controlled missile with fixed tail fins; but for the free-spinning tail fin configuration, the canard can conduct rolling control of the missile, and even have higher controlling efficiency under larger canard deflection angle.展开更多
Vibration of structures is often an undesirable phenomena and should be avoided or controlled. There are two techniques to control the vibration of a system, that is, active and passive control techniques. In this pap...Vibration of structures is often an undesirable phenomena and should be avoided or controlled. There are two techniques to control the vibration of a system, that is, active and passive control techniques. In this paper, a negative feedback velocity is applied to a dynamical system, which is represented by two coupled second order nonlinear differential equations having both quadratic and cubic nonlinearties. The system describes the vibration of an aircraft tail. The system is subjected to multi-external excitation forces. The method of multiple time scale perturbation is applied to solve the nonlinear differential equations and obtain approximate solutions up to third order of accuracy. The stability of the system is investigated applying frequency response equations. The effects of the different parameters are studied numerically. Various resonance cases are investigated. A comparison is made with the available published work.展开更多
This paper proposes a novel composite dual-control bycombing the integral sliding mode control （ISMC） method basedon the finite time convergence theory with extended state observer（ESO） for a tracking problem of a...This paper proposes a novel composite dual-control bycombing the integral sliding mode control （ISMC） method basedon the finite time convergence theory with extended state observer（ESO） for a tracking problem of a missile with tail fins and reactionjetcontrol system （RCS）. First, the ISMC method based on finitetime convergence is utilized to design the control law of tail fins andthe pulse control of RCS for the dual-control system, ensuring thesystem with rapid response and high accuracy of tracking. Then,ESO is employed for the estimation of aerodynamic disturbancesinfluenced by the airflow of thruster jets. With the characteristicof high accuracy estimation of ESO, the chattering free trackingperformance of the attack angle command and the robustnessof the control law are achieved. Meanwhile, the stability of thedual-control system is analyzed based on finite time convergencestability theorem and Lyapunov’s theorem. Finally, numerical simulationsdemonstrate the effectiveness of the proposed design.展开更多
This paper adds a negative velocity feedback to the dynamical system of twin-tail aircraft to suppress the vibration.The system is represented by two coupled second-order nonlinear differential equations having both q...This paper adds a negative velocity feedback to the dynamical system of twin-tail aircraft to suppress the vibration.The system is represented by two coupled second-order nonlinear differential equations having both quadratic and cubic nonlinearities.The system describes the vibration of an aircraft tail subjected to both multi-harmonic and multi-tuned excitations.The method of multiple time scale perturbation is adopted to solve the nonlinear differential equations and obtain approximate solutions up to the third order approximations.The stability of the proposed analytic solution near the simultaneous primary,combined and internal resonance is studied and its conditions are determined.The effect of different parameters on the steady state response of the vibrating system is studied and discussed by using frequency response equations.Some different resonance cases are investigated numerically.展开更多
The main advantage of tail-sitter unmanned aerial vehicle (UAV) are introduced. Three design solutions of rotor tail-sitter lift system of UAV have been presented and the respective control strategies and characterist...The main advantage of tail-sitter unmanned aerial vehicle (UAV) are introduced. Three design solutions of rotor tail-sitter lift system of UAV have been presented and the respective control strategies and characteristics of three solutions are also analyzed in the paper, through the related experiments the design of twin-rotor lift system is verified, and its feasibility is proved. The characteristics and the applying background of the twin-rotor tail-sitter UAV are described in detail. Some useful conclusions of the lift system for tail-sitter UAV are obtained.展开更多
基金Funded by the National Key R&D Program of China(No.2017YFC0703206).
文摘The feasibility of utilizing molybdenum tailing and diatomite as siliceous materials to prepare calcium silicate board was explored.The influences of molybdenum tailing/diatomite proportion on hydration characteristics,thermal conductivity,water absorption,flexural strength and moisture adsorption-desorption property of calcium silicate board were investigated in detail.The experimental results reveal that molybdenum tailing is environmentally friendly to prepare building materials.The main hydration products in calcium silicate board under autoclaved condition are C-S-H with low crystallinity and tobermorite.Molybdenum tailing is favorable to the formation of tobermorite.The flexural strength and bulk density of the calcium silicate board gradually increase when the content of molybdenum tailing increases.Netlike C-S-H is formed with the increase of diatomite content during autoclaved curing process,resulting in the enhancement of moisture adsorptiondesorption performance and the reduction of thermal conductivity.The optimal content of molybdenum tailing is 20%,furthermore,the flexual strength and thermal conductivity of calcium silicate board at this content meet the Chinese standard JC/T564.1-2008.
文摘To study the rolling control characteristics of a canard-controlled missile, a series of wind tunnel experiment is conducted. The experimental method, the structure features of wind tunnel model and the experimental results are introduced in this paper. The experimental data show that the canard is an inefficient rolling control device for canard-controlled missile with fixed tail fins; but for the free-spinning tail fin configuration, the canard can conduct rolling control of the missile, and even have higher controlling efficiency under larger canard deflection angle.
文摘Vibration of structures is often an undesirable phenomena and should be avoided or controlled. There are two techniques to control the vibration of a system, that is, active and passive control techniques. In this paper, a negative feedback velocity is applied to a dynamical system, which is represented by two coupled second order nonlinear differential equations having both quadratic and cubic nonlinearties. The system describes the vibration of an aircraft tail. The system is subjected to multi-external excitation forces. The method of multiple time scale perturbation is applied to solve the nonlinear differential equations and obtain approximate solutions up to third order of accuracy. The stability of the system is investigated applying frequency response equations. The effects of the different parameters are studied numerically. Various resonance cases are investigated. A comparison is made with the available published work.
基金supported by the National Natural Science Foundation of China(11202024)
文摘This paper proposes a novel composite dual-control bycombing the integral sliding mode control （ISMC） method basedon the finite time convergence theory with extended state observer（ESO） for a tracking problem of a missile with tail fins and reactionjetcontrol system （RCS）. First, the ISMC method based on finitetime convergence is utilized to design the control law of tail fins andthe pulse control of RCS for the dual-control system, ensuring thesystem with rapid response and high accuracy of tracking. Then,ESO is employed for the estimation of aerodynamic disturbancesinfluenced by the airflow of thruster jets. With the characteristicof high accuracy estimation of ESO, the chattering free trackingperformance of the attack angle command and the robustnessof the control law are achieved. Meanwhile, the stability of thedual-control system is analyzed based on finite time convergencestability theorem and Lyapunov’s theorem. Finally, numerical simulationsdemonstrate the effectiveness of the proposed design.
基金the support of the author community in using REVTEX, offering suggestions and encouragement, testing new versions
文摘This paper adds a negative velocity feedback to the dynamical system of twin-tail aircraft to suppress the vibration.The system is represented by two coupled second-order nonlinear differential equations having both quadratic and cubic nonlinearities.The system describes the vibration of an aircraft tail subjected to both multi-harmonic and multi-tuned excitations.The method of multiple time scale perturbation is adopted to solve the nonlinear differential equations and obtain approximate solutions up to the third order approximations.The stability of the proposed analytic solution near the simultaneous primary,combined and internal resonance is studied and its conditions are determined.The effect of different parameters on the steady state response of the vibrating system is studied and discussed by using frequency response equations.Some different resonance cases are investigated numerically.
文摘The main advantage of tail-sitter unmanned aerial vehicle (UAV) are introduced. Three design solutions of rotor tail-sitter lift system of UAV have been presented and the respective control strategies and characteristics of three solutions are also analyzed in the paper, through the related experiments the design of twin-rotor lift system is verified, and its feasibility is proved. The characteristics and the applying background of the twin-rotor tail-sitter UAV are described in detail. Some useful conclusions of the lift system for tail-sitter UAV are obtained.
