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| 1 | Improving Joint Features and Mechanical Properties of Pinless Fiction Stir Welding of Alcald 2A12-T4 Aluminum Alloy显示文摘As a new solid state welding,pinless friction stir welding(PFSW) can be used to join thin-wall structures.In this study,four new pinless tools with different groove distributions were designed and manufactured in order to enrich technological storage of PFSW and obtain sound joint with high quality of alclad 2A12-T4 alloy.The results show that the small-obliquity tool is detrimental to the transfer of plasticized materials,resulting in the formation of kissing bond defect.For the through-groove tool or the large-curvature tool,bigger flashes form on the joint surface and alclad layer is observed in the nugget zone(NZ),deteriorating mechanical properties.Compared with the above-mentioned three tools,using the six-groove tool with rational curvature and obliquity can not only yield sound joint with small flashes and thickness reduction,but also prevent alclad from flowing into NZ,which has potential to weld thin alclad aluminum alloys.Meanwhile,the tensile strength and elongation of joint using the six-groove tool reach the maximum values of 362 MPa and 8.3%,up to 85.1% and 64% of BM. | Zhenlei Liu Hutao Cui Shude Ji Minqiang Xu Xiangchen Meng | 2016 | Journal of Materials Science & Technology2016，32，12： | 7 |
| 2 | UPF based autonomous navigation scheme for deep space probe显示文摘The autonomous 'celestial navigation scheme' for deep space probe departing from the earth and the autonomous 'optical navigation scheme' for encountering object celestial body are presented. Then, aiming at the conditions that large initial estimation errors and non-Gaussian distribution of state or measurement errors may exist in orbit determination process of the two phases, UPF (unscented particle filter) is introduced into the navigation schemes. By tackling nonlinear and non-Gaussian problems, UPF overcomes the accuracy influence brought by the traditional EKF (extended Kalman filter), UKF (unscented Kalman filter), and PF (particle filter) schemes in approximate treatment to nonlinear and non-Gaussian state model and measurement model. The numerical simulations demonstrate the feasibility and higher accuracy of the UPF navigation scheme. | Li Peng Cui Hutao Cui Pingyuan | 2008 | Journal of Systems Engineering and Electronics2008，19，3： | 7 |
| 3 | Anti-unwinding attitude maneuver control of spacecraft considering bounded disturbance and input saturation显示文摘The attitude maneuver control of spacecraft under bounded disturbance and input saturation is investigated in this paper.Using the Lyapunov stability theory,an anti-saturation sliding mode control algorithm is given by designing a time-varying sliding mode to solve the input saturated attitude control problem without disturbance.Then combining the merit in anti-saturation of time-varying sliding mode controller with the merit in anti-disturbance of time-invariant sliding mode controller,a switching strategy between the two controllers is designed to solve the attitude maneuver control problem under input saturation and bounded disturbance.However,double value of quaternions makes the attitude slewing unwinding.To solve the problem,an attitude error vector is designed.Based on the error vector,a modified sliding mode control algorithm is proposed which simultaneously has the ability of anti-saturation,anti-disturbance and anti-unwinding.Simulation results show that the algorithm in this paper is feasible and effective. | CUI HuTao CHENG XiaoJun | 2012 | Science China(Technological Sciences)2012，55，9： | 5 |
| 4 | Disturbance observer-based robust guidance for Mars atmospheric entry with input saturation显示文摘With low-lifting capability taken into account,a robust guidance law for Mars entry vehicles with low lift-to-drag ratios,such as Mars Science Laboratory(MSL),is presented.Consider the nonlinear term in the drag dynamic equation and bounded disturbances as a lumped disturbance,and design a linear disturbance observer(DOB)to estimate it.With the consideration of the control input saturation,an innovative sliding surface and a virtual system are introduced to design the guidance law.Analyses of disturbance observer performance and Lyapunov-based transient performance are also presented.It is shown that the drag tracking error can be adjustable by explicit choices of design parameters.Simulation results confirm the effectiveness of the proposed guidance law. | Zheng Yiyu Cui Hutao | 2015 | Chinese Journal of Aeronautics2015，28，3： | 4 |
| 5 | Vision-aided inertial navigation for pinpoint planetary landing显示文摘 | Shuang Li Pingyuan Cui Hutao Cui | 2007 | Aerospace Science and Technology2007，，6： | 2 |
| 6 | An improved nonlinear control strategy for deep space formation flying spacecraft显示文摘This paper aims to provide further study on thenonlinear modeling and controller design of formation flyingspacecraft in deep space missions. First, in the Sun-Earthsystem, the nonlinear formation dynamics for the circularrestricted three-body problem (CRTBP) and elliptic restrictedthree-body problem (ERTBP) are presented. Then, with theFloquet mode method, an impulsive controller is developedto keep the Chief on the desired Halo orbit. Finally, anonlinear adaptive control scheme based on Nonzero set-point LQR and neural network is proposed to achieve highprecision formation maneuver and keeping. The simulationresults indicate that the proposed nonlinear control strategyis reasonable as it considers not only the orbit keeping of theChief, but also the formation modeling inaccuracy. Moreover,the nonlinear adaptive control scheme is effective toimprove the control accuracy of the formation keeping. | Peng Li Pingyuan Cui Hutao Cui Deep Space Exploration Research Center,Harbin Institute of Technology, 150080 Harbin, China | 2009 | Acta Mechanica Sinica2009，25，6： | 2 |
| 7 | Vision-aided inertial navigation for pinpoint planetary landing显示文摘 | LI Shuang CUI Pingyuan CUI Hutao | 2007 | Aerospace Science and Technology2007，11，6： | 1 |
| 8 | Vision-aided inertial navigation for pinpoint planetary landing 显示文摘 | LI Shuang CuI Pingyuan Cu: Hutao | 2007 | Aerospace Science and Technology2007，11，6： | 1 |
| 9 | Ivar asteroid rendezvous mission system scenario and trajectory design显示文摘 | CUI Pingyuan LI litao and CUI Hutao | 2003 | Joumal of Harbin Institute of Technology2003，10，3： | 1 |
| 10 | Vision- aided inertial navigation for pinpoint planetary landing 显示文摘 | Li Shuang Cui Pingyuan Cui Hutao | 2007 | Aerospace Science and Technology2007，，11： | 1 |
| 11 | Vision-aided inertial navigation for pinpoint planetary landing 显示文摘 | LIShuang CUI Pingyuan CUI Hutao | 2007 | Aerospace Scienee and Teehnology2007，11，6： | 1 |
| 12 | Vision-aided inertial navigation for pinpoint planetary landing 显示文摘 | Li Shuang Cui Pingyuan Cui Hutao | 2007 | Aerospace Science and Technology (S 1270-9638)2007，11，6： | 1 |
| 13 | Vision-aided in-ertial navigation for pinpoint planetary landing显示文摘 | Li Shuang Cui Pingyuan Cui Hutao | 2007 | Aerospace Science and Technology2007，11，6： | 1 |
| 14 | Autonomous navigation and guidance for landing on asteroids显示文摘 | Shuang Li Pingyuan Cui Hutao Cui | 2005 | Aerospace Science and Technology2005，，3： | 1 |
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