韋常柱:人物經歷,研究方向,學術成果,科研項目,論文專著,科研專著,主講課程,榮譽

韋常柱，男，漢族，1982年出生，博士，哈爾濱工業大學航天學院航天工程系教授，博士生導師。

基本介紹

中文名：韋常柱
學位/學歷：博士
職業：教師
專業方向：飛行器控制理論及套用
任職院校：哈爾濱工業大學
性別：男

人物經歷,研究方向,學術成果,科研項目,論文專著,科研專著,主講課程,榮譽獎項,主要任職,

人物經歷

工作經歷

2021.12 - 至今哈爾濱工業大學教授

2015.12 - 2021.11 哈爾濱工業大學副教授

2013.06 - 2015.12 哈爾濱工業大學講師

2010.12 - 2012.12 韓國延世大學博士後

教育經歷

2001.09-2005.07 哈爾濱工業大學飛行器設計與工程工學學士

2005.09-2010.07 哈爾濱工業大學飛行器設計工學博士

研究方向

飛行器控制理論及套用

先進制導與彈道最佳化

人工智慧理論及套用

學術成果

科研項目

緊密結合國家航空航天發展需求，以國家縱向項目和科研院所橫向課題為依託，對精確制導武器、再入飛行器、垂直起降可重複使用運載器、類X37B重複使用飛行器、重型運載火箭等飛彈、火箭的飛行器控制、先進制導與彈道最佳化、人工智慧理論及套用問題進行了深入研究，共負責科研項目百餘項，年均科研經費2200餘萬元。

合作對象：

國家、部委下屬20餘家科研院所。

合作領域：

飛行器制導與控制：垂直起降重複使用運載器、重型運載火箭、CZ-××子級、類X37B重複使用飛行器、飛彈、無人機、制飛彈藥等

彈道設計與最佳化：重大專項工程項目、CZ-××子級、可重複使用運載器、天地往返運輸系統、高超聲速飛行器等

人工智慧理論及套用：軍兵種預研項目、飛行器智慧型控制、智慧型彈道規劃、智慧型氣動參數辨識、智慧型飛行能力預示等

系統平台開發與半實物仿真：可重複使用運載器半實物仿真系統、小型固體火箭制導控制地面驗證平台、新一代運載火箭設計平台、制導控制綜合最佳化設計評估系統、舵機載入系統等

空間飛行器動力學與控制：上面級、空間機械臂、天梯等

論文專著

SCI源：

[1]Ju Xiaozhe, Wei Changzhu, Zhang Liang, et al. Semi-globally smooth control for VTVL reusable launch vehicle under actuator faults and attitude constraints[J]. Acta Astronautica, 2021.

[2]Wei Changzhu,Wang Ruiming,Zheng Wei,Pu Jialun. Equivalent dynamic modeling of flexible morphing aircraft.[J]. Science progress,2021,104(2):

[3]Zhang Chenxin,Zhang Yankun,Wei Changzhu,Pecora Rosario. Onboard Trajectory Generation of Hypersonic Morphing Aircraft[J]. International Journal of Aerospace Engineering,2021,2021:

[4]Li Yuan,Wei Changzhu,He Yanfeng,Hu Renyi. A convex approach to trajectory optimization for boost back of vertical take-off/vertical landing reusable launch vehicles[J]. Journal of the Franklin Institute,2021,358(7):

[5]Jing Liang,Wei Changzhu,Zhang Liang,Cui Naigang,Ben Makhlouf Abdellatif. Cooperative Guidance Law with Predefined-Time Convergence for Multimissile Systems[J]. Mathematical Problems in Engineering,2021,2021:

[6]Chenxin Zhang, Yankun Zhang, Changzhu Wei, et al. Onboard Rocket Landing Guidance Using Convex Optimization and Model Predictive Control.[J]. International Journal of Aerospace Engineering,Volume 2021. (SCI 檢索)

[7]Wei Chang Zhu,Zhang Ze,Li Yuan,Li Yongyuan. Multi-Process Integrated Planning and Guidance for Return of Reusable Aircraft Under Time Constraint[J]. IEEE ACCESS,2020,8:

[8]Yuan Li ,Baojun Pang , Changzhu Wei, et al. Online trajectory optimization for power system fault of launch vehicles via convex programming [J]. Aerospace Science and Technology, 98: 105682, 2020. (SCI 檢索)

[9]Yuan Li ,Wei Changzhu,Baogang Lu , et al.Improved guidance algorithm considering terminal attitude constraints for spacecrafts via optimal control theory [J]. Optimal Control Applications & Methods, 2020. (SCI 檢索)

[10] Huibing Shao ,Yepeng Han ,Changzhu Wei , et al.A Novel Recurrent Convolutional Neural Network-Based Estimation Method for Switching Guidance Law [J]. Ieee Access, 10159-10168,2020. (SCI 檢索)

[11]Chenhao Zhu ,Wei Chang zhu, Guodong Xu , et al.Impact-Time-Control Guidance Law for Hypersonic Missiles in Terminal Phase [J]. Ieee Access, 8, 44611-44621,2020. (SCI 檢索)

[12]Changzhu Wei ,Ju Xiaozhe, Rong Wu , et al. Geometry and time updaters-based arbitrary-yaw iterative explicit guidance for fixed-thrust boost back of vertical take-off/vertical landing reusable launch vehicles [J].Aerospace Science and Technology, 95: 105433, 2019. (SCI 檢索)

[13]Liang Zhang , Changzhu Wei ,Rong Wu ,et al. Adaptive fault-tolerant control for a VTVL reusable launch vehicle [J]. Engineering Aerospace, AEROSPACE, 159: 362-370, 2019. (SCI 檢索)

[14]Liang Zhang, Changzhu Wei, Rong Wu , et al. Fixed-time adaptive model reference sliding mode control for an air-to-ground missile [J]. Chinese Journal Of Aeronautic, 32(5): 1268-1280, 2019. (SCI 檢索)

[15]Jinbo Wang ,Naigang Cui , Changzhu Wei, et al. Optimal Rocket Landing Guidance Using Convex Optimization and Model Predictive Control [J]. Chinese Journal Of Aeronautic, 42(5): 1078-1092, 2019. (SCI 檢索)

[16] Jinbo Wang , Naigang Cui , Changzhu Wei ,et al. Optimal Rocket Landing Guidance Using Convex Optimization and Model Predictive Control[J]. Journal of Mathematics,2019.(SCI檢索)

[17]JinboWang ,Naigang Cui , Changzhu Wei, et al. Rapid trajectory optimization for hypersonic entry using a pseudospectral-convex algorithm [J]. Proceeding Of The Institution Of Mechanicak Engineers Part G-Journal Of Aerospace Engineering, 233(14): 5227-5238, 2019. (SCI 檢索)

[18]Yuan Li, Yingzi Guan , Wei Changzhu, et al.

Optimal Control of Ascent Trajectory for Launch Vehicles: A Convex Approach [J]. Ieee Access, 7: 186491-186498, 2019. (SCI 檢索)

[19]Liang Zhang, Changzhu Wei, Yin Diao ,et al.

On-line orbit planning and guidance for advanced upper stage [J]. Aircraft Engineering And Aerospace Technology, 91(4): 634-647, 2019. (SCI 檢索)

[20]Jinbo Wang ,Naigang Cui ,Changzhu Wei, et al.

Rapid trajectory optimization for hypersonic entry using convex optimization and pseudospectral method [J]. Aircraft Engineering And Aerospace Technology, 91(4): 669-679, 2019. (SCI 檢索)

[21] Changzhu Wei, Yepeng Hanet al. Fifth-Degree Cubature Kalman Filter Estimation of Seeker Line-of-Sight Rate Using Augmented-, Naigang Cui, Dimensional Model [J]. Journal of Guidance, Control, and Dynamics, 40(9): 2355-2362, 2017. (SCI 檢索)

[22] Changzhu Wei, Sang-Young Park. Dynamic optimal output feedback control of satellite formation reconfiguration based on an LMI approach[J]. Aerospace Science and Technology, 63: 214-231, 2017. (SCI 檢索)

[23] Liang Zhang, Changzhu Wei, Liang Jing, et al. Fixed-time sliding mode attitude tracking control for a submarine-launched missile with multiple disturbances[J]. Nonlinear Dynamics, 93(4): 2543-2563, 2018. (SCI 檢索)

[24] Liang Zhang, Changzhu Wei, Rong Wu, et al. Fixed-Time Extended State Observer Based Non-Singular Fast Terminal Sliding Mode Control for a VTVL reusable launch vehicle[J]. Aerospace Science and Technology, 82-83: 70-79, 2018. (SCI 檢索)

[25] Rong Wu, Changzhu Wei, Feng Yang, et al. FxTDO-based non-singular terminal sliding mode control for second-order uncertain systems[J]. IET Control Theory and Applications, 12(18): 2459-2467, 2018. (SCI檢索)

[26] Feng Yang, Changzhu Wei, Rong Wu, et al. Non-recursive fixed-time convergence observer and extended state observer[J]. IEEE Access, 6: 62339-62351, 2018. (SCI檢索)

[27] Panxing Huang, Changzhu Wei, Yuanbei Gu, et al. Hybrid optimization approach for rapid endo-atmospheric ascent trajectory planning[J]. Aircraft Engineering and Aerospace Technology, 88(4): 473-479, 2016. (SCI 檢索)

[28] Naiming Qi, Yong Yang, Changzhu Wei, et al. Two-Dimensional Dynamics of a New Configuration of Continuous Cislunar Payloads Transfer System[J]. Transactions of the Japan Society for Aeronautical and Space Sciences, 59(2): 71-80, 2016. (SCI 檢索)

[29] Changzhu Wei, Jifeng Guo, Sang-Young Park, et al. IFF Optimal Control for Missile Formation Reconfiguration in Cooperative Engagement[J]. Journal of Aerospace Engineering, 28(3): 04014087, 2015. (SCI 檢索)

[30] Changzhu Wei, Sang-Young Park, Chandoek Park. Optimal H-infinity Robust Output Feedback Control for Satellite Formation in Arbitrary Elliptical Reference Orbits[J]. Advanced in Space Research, 54(6), 969-989, 2014. (SCI 檢索)

[31] Changzhu Wei, Sang-Young Park, Chandeok Park. Linearized Dynamics Model for Relative Motion under a J(2)-Perturbed Elliptical Reference Orbit[J]. International Journal of Non-Linear Mechanics, 55: 55-69, 2013. (SCI 檢索)

[32] Changzhu Wei, Yi Shen, Xiaoxiao Ma, et al. Optimal formation keeping control in missile cooperative Engagement[J]. Aircraft Engineering and Aerospace Technology, 84(6): 376-390, 2012. (SCI 檢索)

[33] Naigang Cui, Changzhu Wei, Jifeng Guo, Biao Zhao. Study on Missile Formation Reconfiguration Optimized Trajectory Generation and Control[J]. Journal of Applied Mechanics, 77(5):144-153,2010. (SCI 檢索)

EI源及其他：

[1]Naigang Cui, Rong Wu, Changzhu Wei, et al. Double-order power finxed-time convergence sliding mode control method for launch vehicle vertical returning

[C].Harbin Gongye Daxue Xuebao/Journal of Harbin Institute of Technology, 2020: 15-24. (EI 檢索)

[2]Changzhu Wei, Xiaozhe Ju, Dafu Xu, et al. Guidance and control for return process of vertical takeoff vertical landing reusable launching vehicle [C].Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica, 2019: 322782. (EI 檢索)

[3]Changzhu Wei, Xiaozhe Ju, Rong Wu, et al. Geometry and time updaters-based arbitrary-yawiterative explicit guidance for fixed-thrust boost back of vertical take-off/vertical landing reusable launch vehicles [C]Aerospace Science and Technology, 2019: 105433. (EI 檢索)

[4]Liang Zhang ,Changzhu Wei, Rong Wu, et al. Adaptive fault-tolerant control for a VTVL reusable launch vehicle [C]Acta Astronautica, 2019: 362-370. (EI 檢索)

[5]Hao Lee ,Changzhu Wei, et al. A trajectory design method for RLV via artificialmemory-principle optimization [C]MATEC Web of Conferences, 2018: 10019. (EI 檢索)

[6]Ruisong Huang ,Hao Lee ,Changzhu Wei, et al. Integrated optimization method of trajectory/system parameters for sub-orbital reusable launch vehicles [C] Zhongguo Guanxing Jishu Xuebao/Journal of Chinese Inertial Technology, 2018: 261-267. (EI 檢索)[7]Jinbo Wang ,Naigang Cui ,Changzhu Wei, et al. A Two-stage Rapid Trajectory Optimization Algorithm for Hypersonic Entry [C] IEEE CSAA Guidance, 2018: 9018689. (EI 檢索)

[8]Cheng Chen ,Changzhu Wei, Xiaozhe Ju, et al.Robust dynamic inversion control for quad-rotors unmanned vehicle based on sliding mode disturbance observation and compensation [C] Xi Tong Gong Cheng Yu Dian Zi Ji Shu/Systems Engineering and Electronics, 2018: 119-126. (EI 檢索)

[9] Hao Lee, Naigang Cui, Changzhu Wei, et al. Integrated Guidance and Control for Reusable Launch Vehicles with Actuator Failures[C]. 21st AIAA International Space Planes and Hypersonics Technologies Conference, 2017: 2407. (EI 檢索)

[10] Changzhu Wei, Xiaozhe Ju, Feiyi He, et al. Research on Non-stationary Control of Advanced Hypersonic Morphing Vehicles[C]. 21st AIAA International Space Planes and Hypersonics Technologies Conference, 2017: 2405. (EI 檢索)

[11] Liang Zhang, Rong Wu, Changzhu Wei, et al. Quaternion-Based Reusable Launch Vehicle Composite Attitude Control via Active Disturbance Rejection Control and Sliding Mode Approach[C]. 21st AIAA International Space Planes and Hypersonics Technologies Conference, 2017: 2320. (EI 檢索)

[12] Liang Zhang, Changzhu Wei, Liang Jing, Naigang Cui. Heavy Lift Launch Vehicle Technology of Adaptive Augmented Fault Tolerant Control[C]. Proceedings of the 2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC), 2016: 1587-1593 (EI 檢索)

[13] Rong Wu, Yingzi Guan, Changzhu Wei, et al. Fixed-Time Disturbance Observer Based Nonsingular Fast Terminal Sliding Mode Guidance with Impact Angle Constraint [C]. Proceedings of the 2018 IEEE/CSAA Guidance, Navigation and Control Conference, Xiamen, China, 2018: 1908-1913. (EI 檢索)

[14] Feng Yang, Changzhu Wei, Naigang Cui, Jiangtao Xu. Adaptive generalized super-twisting algorithm based guidance law design. 14th International Workshop on Variable Structure Systems (VSS), 47-52, 2016. (EI 檢索)

[15] Chao Cheng, Changzhu Wei, Naigang Cui, Zhiyong She. A measurement method of nonlinear strength for dynamical model of SRLV. International Journal of Modelling, Identification and Control, 24(2): 89-99, 2015. (EI 檢索)

[16] Panxing Huang, Changzhu Wei, Yuanbei Gu, Naigang Cui. A symplectic optimisation method for rapid endo-atmospheric ascent trajectory planning. International Journal of Modelling, Identification and Control, 24(3): 196-205, 2015. (EI 檢索)

[17] Changzhu Wei, Jifeng Guo, Libin Zhang, Yi Shen, and Naigang Cui. Adaptive Control for Missile Formation Keeping under Leader Information Unavailability. The 10th IEEE International Conference on Control & Automation, Hangzhou, China, 12-14 June 2013: 902-907. (EI 檢索)

[18] Naigang Cui, Changzhu Wei, Jifeng Guo and Biao Zhao. Research on Missile Formation Control System. Proceedings of the 2009 IEEE International Conference on Mechatronics and Automation, August 9 – 12. pp: 4197-4202. Changchun, China, 2009. (EI 檢索)

[19] Panxing Huang, Yuanbei Gu, Changzhu Wei, Naigang Cui. Reconfigurable Control System Design Based on Control Allocation or HLV. 27th Chinese Control and Decision Conference (CCDC), 3584-3590, 2015.

[20] Naigang Cui, Feng Yang, Changzhu Wei. Three-Dimensional Hit-to-Kill Guidance Law for Direct Thrust Controlled Interceptor. 27th Chinese Control and Decision Conference (CCDC), 4494-4499, 2015.

[21] Changzhu Wei, Naigang Cui, Jifeng Guo. Missiles formation Reconfiguration Optimized trajectory generation and control. The 25th International Symposium on Ballistics, Beijing, China, 2010. No. ISB’10 02-002.

[22]崔乃剛,郭冬子,李坤原,韋常柱.飛行器軌跡最佳化數值解法綜述[J].戰術飛彈技術,2020(05):37-51+75+5.

[23]崔乃剛,郭冬子,王瑞鳴,王銘澤,韋常柱.飛航飛彈智慧型故障診斷與容錯控制[J].戰術飛彈技術,2020(04):125-134.

[24]崔乃剛,吳榮,韋常柱,徐大富.火箭垂直返回雙冪次固定時間收斂滑模控制方法[J].哈爾濱工業大學學報,2020,52(04):15-24.

[25]韋常柱,琚嘯哲,何飛毅,潘豪,徐世昊.運載火箭主動段自適應增廣控制[J].宇航學報,2019,40(08):918-927.

[26]韋常柱,琚嘯哲,徐大富,吳榮,崔乃剛.垂直起降重複使用運載器返回制導與控制[J].航空學報,2019,40(07):197-220.

[27]邵會兵,崔乃剛,韋常柱.滑翔飛彈末段多約束智慧型彈道規劃[J].光學精密工程,2019,27(02):410-420.

[28]徐世昊,崔乃剛,韋常柱.基於RBF神經網路的飛彈智慧型控制系統設計[J].宇航總體技術,2018,2(06):19-26.

[29]高興,張璐,韋常柱.面向禁飛區約束的再入滑翔飛行器快速軌跡規劃[J].戰術飛彈技術,2018(05):62-67+94.

[30] 楊峰, 韋常柱, 吳榮, 等. 一階不確定系統的固定時間收斂擾動觀測器[J]. 控制與決策. (published online, EI 檢索)

[31] 韋常柱, 琚嘯哲, 何飛毅, 等. 運載火箭主動段自適應增廣控制研究[J]. 宇航學報. (published online, EI檢索)

[32] 陳誠, 韋常柱, 琚嘯哲, 等. 基於滑模觀測補償的四旋翼飛行器魯棒動態逆控制[J]. 系統工程與電子技術, 2018, 40(1): 119-126. (EI 檢索)

[33] 崔乃剛, 李浩, 盧寶剛, 韋常柱. 可重複使用飛行器制導控制一體化技術[J]. 光學精密工程, 2017, 25(12z): 52-58. (EI 檢索)

[34] 黃瑞松, 李浩, 韋常柱, 等. 亞軌道可重複使用飛行器軌跡/總體參數一體化最佳化方法[J]. 中國慣性技術學報, 2018, 26(2): 261-267. (EI 檢索)

[35] 崔乃剛, 張亮, 韋常柱, 等. 可重複使用運載器大姿態機動自抗擾控制[J]. 中國慣性技術學報, 2017, 25(03): 387-394. (EI 檢索)

[36] 單永志, 韋常柱, 孟秀雲, 等. 基於最優解析解的機載布撒武器彈道最佳化[J].北京理工大學學報（自然科學版）, 2016, (12):1228-1232. (EI 檢索)

[37] 崔乃剛, 黃盤興, 路菲, 黃榮, 韋常柱. 基於混合最佳化的運載器大氣層內上升段軌跡快速規劃方法[J]. 航空學報, 2015, 36(6): 1915-1923. (EI 檢索)

[38] 崔乃剛, 黃盤興, 韋常柱, 等. 基於混合最佳化的運載器大氣層內閉環制導方法[J]. 中國慣性技術學報, 2015, 23(3): 328-333. (EI 檢索)

[39] 黃榮, 崔乃剛, 韋常柱, 等. 基於 RRT-GPM 兩階策略的飛彈編隊協同突防最優軌跡快速設計[J]. 中國慣性技術學報, 2015, 23(3): 356-362. (EI 檢索)

[40] 崔乃剛, 韋常柱, 郭繼峰. 飛彈協同作戰飛行時間裕度[J]. 航空學報, 2010, 31(7): 1351-1360. (EI 檢索)

[41] 韋常柱, 郭繼峰, 崔乃剛. 飛彈協同作戰編隊隊形最優保持控制器設計[J]. 宇航學報, 2010, 31(4): 1043-1050. (EI 檢索)

[42] 韋常柱, 郭繼峰, 趙彪. 飛彈協同作戰編隊飛行控制系統研究[J]. 系統工程與電子技術, 2010, 32(9): 1968-1972. (EI 檢索)

[43] 浦甲倫, 韋常柱, 榮思遠. 修正增益卡爾曼濾波算法在被動測距問題中的套用[J]. 宇航學報, 2008, 28(4): 886-889. (EI 檢索)

[44] 許江濤, 崔乃剛, 路菲, 韋常柱. 無人機非方陣系統解耦控制[J]. 航空學報, 2008, 29(5): 157-162. (EI 檢索)

[45] 韋常柱, 張立佳, 崔乃剛. 布撒器對機場跑道的封鎖方式及機率分析[J]. 彈道學報, 2008, 20(2): 32-36. (EI 檢索)

[46] 張亮, 黃盤興, 徐大富, 韋常柱, 黃榮. 垂直起降火箭垂直返回段自適應容錯控制算法[J]. 戰術飛彈技術, 2015 (2): 63-69.

[47] 崔乃剛, 韋常柱, 郭繼峰. 利用彈上器件測風方法[J]. 中國慣性技術學報, 2009, 17(5): 520-524. (EI 檢索)

[48] 崔乃剛, 韋常柱, 郭繼峰. 飛彈協同作戰四維制導控制研究[J]. 飛行力學, 2010, 28(2): 63-66.

[33] 崔乃剛, 曹春泉, 韋常柱. 潛射飛彈水下運動過程仿真分析[J]. 彈道學報, 2009, 21(2): 95-99.

[49] 韋常柱, 郭繼峰, 崔乃剛, 等. 飛彈對跑道封鎖機率及進入角偏差計算方法研究[J]. 兵工學報, 2008, 29(6): 764-768.

科研專著

[1] Changzhu Wei, Yi Shen, Naigang Cui, Sang-Young Park and Jifeng Guo. Chapter 11: Missile Cooperative Engagement Formation Configuration Control Method. In "Recent Advances in Robust Control – Theory and Applications in Robotics and Electromechanics", INTECH Open Access Publisher, 2012, ISBN 978-953-307-421-4.