Cong Wang

Beijing Aerospace Flight Control Center

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Zhengyu Song

Beijing Jiaotong University

David J. Hill

University of Hong Kong

Guopeng Zhou

Hubei University of Science and Technology

Weizhou Su

South China University of Technology

Jianming Li

Hohai University

Zhijiang Shao

State Key Laboratory of Industrial Control Technology

Shuzhi Sam Ge

National University of Singapore

Jinglin Li

Beijing University of Posts and Telecommunications

Ma Yuguang

Yuan He

Beijing Forestry University

Cooperative Institutions

Zhejiang University

Sun Yat-sen University

Fudan University

Zhongshan Hospital

Beijing University of Posts and Telecommunications

Beijing Aerospace Flight Control Center

Chinese Academy of Sciences

The First Affiliated Hospital, Sun Yat-sen University

China Aerospace Science and Technology Corporation

Peking University

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An ISS-modular approach for neural control of pure-feedback systems

Cong Wang David J. Hill Guanrong Chen Shuzhi Sam Ge

Feedback Control

10.1109/icca.2002.1229385

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Citations (9)

Nonlinear Output Regulation Based on RBF Neural Network Approximation

International Conference on Control and Automation (2005)

Guopeng Zhou Cong Wang Weizhou Su

The regulator equations arising from the nonlinear output regulation problem are a set of mixed partial differential and algebraic equations. Due to the nonlinear nature, it is difficult to obtain the exact solution of the regulator equations. In this paper, an approximation method based on a class of radial basis function (RBF) neural networks was investigated for solving the regulator equations. It is shown that the RBF neural networks can solve the regulator equations up to a prescribed arbitrarily small error, and this small error can be translated into a guaranteed steady-state tracking error for the closed-loop system. Simulation studies, which are conducted to compare with MNN method, show that the RBF NN method has good properties such as rapid training speed and overcoming local minimal value.

Algebraic equation

Tracking error

10.1109/icca.2005.1528210

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Simultaneous trajectory optimization for reusable payload fairing recovery via an initialization-enhanced hp-adaptive pseudospectral method

AIAA SCITECH 2022 Forum (2024)

Zhenyu Wei Cong Wang Zhijiang Shao

Recovery of payload fairings (PLF) is an innovative technology in the space industry with the potential to reduce launch costs and reshape rocket design. This paper proposes a trajectory optimization approach to determine the optimal recovery trajectory of the PLF. Firstly, a simultaneous trajectory optimization problem is established to characterize the entry, deceleration, and homing phases of the PLF flight process. To reduce the penalty of payload transportation capacity, minimum control effort is used as the performance index. Then, the formulated trajectory optimization problem is solved by the hp-adaptive pseudospectral method (hpPM) to obtain the optimized trajectory. To improve the convergence property of the hpPM, the particle swarm optimization algorithm is modified by the parametrization approach and the constraint handling method to generate an initial guess of the PLF recovery trajectory. On this basis, the density function theory is utilized to distribute the initial mesh points of hpPM, which improves the problem discretization quality and further enhances the convergence property. Simulation results demonstrate the optimized trajectory of the PLF recovery mission and the improved convergence of the proposed initialization-enhanced hpPM approach.

Payload (computing)

Initialization

Trajectory Optimization

10.2514/6.2024-2389

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Static Mechanical Characteristics Analysis of Aircraft Tire Under Extreme Weather Conditions

International Journal of Aeronautical and Space Sciences (2024)

K. B. Lei Jingtao Wu Zhanpeng Ren Wenliang Deng Cong Wang

Extreme Weather

10.1007/s42405-024-00719-3

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An Operational Semantics for UML Activity Diagrams

Journal of Computer Research and Development (2007)

Cong Wang

Activity diagram

10.1360/crad20071024

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Citations (3)

2次元アルミナ小板添加によって生成された熱的に安定な導電性と難燃性ナイロン612複合材料【Powered by NICT】

Composites Part A Applied Science and Manufacturing (2017)

Song Pingan Cong Wang Chen Lei Yiqi Zheng Liu Lina

Source

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Powered soft landing guidance method for launchers with non-cluster configured engines

Acta Astronautica (2021)

Zhengyu Song Cong Wang

Soft landing

Rocket engine

Collocation (remote sensing)

Rocket (weapon)

Throttle

10.1016/j.actaastro.2021.09.003

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Citations (11)

Nonlinear FE Centric Approach for Vehicle Structural Integrity Study

SAE technical papers on CD-ROM/SAE technical paper series (2004)

Cong Wang Narendra Kota

10.4271/2004-01-1344

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Requirements for the Accreditation of a Nondestructive Testing Laboratory and the Control of Testing Process

Nondestructive Testing (2007)

Cong Wang

Impartiality

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Reviews and Challenges in Reliability Design of Long March Launcher Control Systems

AIAA Journal (2021)

Zhengyu Song Hao Pan Yingxin Zhao Wengang Yao Yong He

This paper reviews the development of reliability design technology as well as challenges encountered thus far regarding control systems for long march launch vehicles (LMLVs). Along with the high frequency of space launches, the target of "increasing the success rate by one percentage point" has been proposed by the China Academy of Launch Vehicle Technology for LMLVs. In this context, the features of the representative launchers in the reliability design of control systems are reviewed first, especially from an industrial perspective. Thereafter, the techniques applied by LMLV control systems are presented using a five-level hierarchical architecture: fundamentals, self-repair, multiple module redundancy, fault-tolerant control, and fault-tolerant guidance. This is followed by a detailed discussion on the reliability design in LMLV navigation, guidance, control, and avionics subsystems. Finally, the challenges are addressed, which encompass the cost-oriented reliability design, the fault-tolerant control to suppress out-of-tolerance behaviors, and the fault-tolerant guidance to replan the mission autonomously under critical faults. The techniques under development for LMLVs in these areas are also summarized.

10.2514/1.j060640

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Citations (7)