Wen Bao

Harbin Institute of Technology

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Juntao Chang

Harbin Institute of Technology

112

Silong Zhang

Harbin Institute of Technology

Daren Yu

Fourth Affiliated Hospital of Harbin Medical University

Jiang Qin

Harbin Institute of Technology

Junlong Zhang

Harbin Institute of Technology

Jingying Zuo

Harbin Institute of Technology

Jiang Qin

Harbin Institute of Technology

Hongchao Qiu

Harbin Institute of Technology

Qingchun Yang

Beihang University

Weixing Zhou

Harbin Institute of Technology

Cooperative Institutions

Harbin Institute of Technology

206

Heilongjiang Institute of Technology

Chinese Academy of Sciences

Zhejiang University

Ministry of Industry and Information Technology

Shanghai Jiao Tong University

Lanzhou University

Northwestern Polytechnical University

University of Chinese Academy of Sciences

Beijing Institute of Technology

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Dynamic bumpless transfer: An exact model matching approach

Chinese Control Conference (2011)

Yiwen Qi Wen Bao

This paper establishes a framework for candidate controller design and bumpless transfer compensator synthesis of uncertain controller switched systems. By dividing the design into two steps, a sufficient condition is firstly given for the existence of a robust multivariable proportional-integral (PI) controller. Then a novel bumpless transfer method is introduced based on exact model matching and H ∞ control theory. The method is especially well-suited to situations in which transfer is occurred in dynamic process. Existence conditions for a bumpless transfer compensator are derived in the form of an linear matrix inequality (LMI) and several linear matrix equations. Simulation results verify the effectiveness of the proposed method.

Linear matrix inequality

Transfer matrix

Matrix (chemical analysis)

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Safety protection control for a class of linear systems via switching strategy

Chinese Control Conference (2011)

Chao Chen Daren Yu Wen Bao Jun Zhao

For a class of linear systems, which can be considered as the simplified hypersonic air-breathing propulsion model, focusing on the safe boundaries existing during the working progressing, this paper studies the output regulation/ safety protection switching control problem. Several remarks are given to the switching control based on minimum switching law studied in our previous work, and to make the designing of the switching controller more systematic, a novel reference command switching strategy is proposed, where a discontinuous controller is adapted, and the asymptotic tracking problem is transformed into the asymptotic stability problem of the linear switched and impulsive system. The stability of the switching control system is illustrated, and the principle guaranteeing asymptotic tracking is given. Finally, impacts of switching condition and size of jumping step on the response performances are studied through simulation and it is pointed out that reference commands switching can improve both overshooting and setting time, the ability of tracking commands safely and quickly is enhanced. In addition, the design of PI controller and the switching law can be completed separately, and the switching control law is utility.

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Mathematical Representation of Liquid Jet Diffusion Characteristics Effected with Evaporation Process in Supersonic Crossflow

Guangjun Feng junlong zhang Muxin Cheng Jin Gao Wen Bao

The liquid jet diffusion characteristics effected with evaporation process and the mathematical representation of penetration depth in supersonic crossflow were discussed in this paper. A series of numerical simulations were carried out both in cold inflow (Tt=300K) and high enthalpy inflow (Tt=1680K) with the simulated flight condition of Ma=6. Based on the Euler-Lagrange method, the evaporation and diffusion process of liquid kerosene under different inflow conditions were studied. The mathematical representation of kerosene vapor penetration depth was obtained by convolution method. By analyzing the influence of different evaporation processes on the penetration depth of kerosene vapor, the penetration law of kerosene vapor with evaporation was revealed. The results show that the penetration process of kerosene is not only affected by the injection momentum ratio, but also the evaporation momentum ratio is an important factor affecting the penetration depth. The total penetration depth of kerosene vapor is composed of liquid kerosene penetration and penetration gain due to kerosene evaporation. And the mathematical expression of quantitative analysis was obtained by derivation. Making the local evaporation momentum of kerosene evenly distribute, extending the action distance and expanding the evaporation range are important ways to increase the penetration depth. The investigation in this paper plays an important role in explaining the diffusion mechanism and quantitative analysis of kerosene vapor with evaporation.

Representation

10.2139/ssrn.4326118

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Parametric numerical analysis of regenerative cooling in hydrogen fueled scramjet engines

International Journal of Hydrogen Energy (2016)

Silong Zhang Yu Feng Duo Zhang Yuguang Jiang Jiang Qin

Scramjet

Mass flow rate

Fin

Overall pressure ratio

Aspect ratio (aeronautics)

10.1016/j.ijhydene.2016.03.176

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Citations (54)

Event-Triggered and Self-Triggered $H_\infty$ Control of Uncertain Switched Linear Systems

IEEE Transactions on Systems Man and Cybernetics Systems (2018)

Yiwen Qi Pengyu Zeng Wen Bao

This paper studies the problem of event-triggered and self-triggered H _∞ controls for uncertain switched linear systems with exogenous disturbances whose magnitude is bounded by the system state's norm. With the proposed schemes, the control task is carried out only when the triggering condition is met. That leads to changing and adaptive interexecution intervals and can further reduce the system resource costs to a certain extent. Moreover, to ensure the H _∞ control performance of the event-triggered switched system, a proof which makes certain that the occurrence of Zeno problem can be prevented is first provided. Then, by adopting the average dwell time method, a set of sufficient conditions for H _∞ performance analysis is developed. Subsequently, the codesign of controller gains and event-triggering schemes is provided. On the basis of the eventtriggered control, a solution to the self-triggered control problem is then presented. It can only utilize the current sampled data to predict the next triggered instant. Finally, in order to test the effectiveness of the proposed methods, numerical simulations are performed.

Dwell time

10.1109/tsmc.2018.2801284

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Citations (146)

Influence of multi-strut interaction on flame propagation and combustion performance in a large aspect ratio combustor

Aerospace Science and Technology (2023)

Hongchao Qiu Libo Lin Junlong Zhang Shiqi Zhang Wen Bao

Aspect ratio (aeronautics)

Flame spread

10.1016/j.ast.2023.108193

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Citations (13)

Characteristic analysis of unstart/restart of hypersonic inlets caused by variations of attack angle of freestream

Journal of Aerospace Power (2008)

Wen Bao

Unstart/restart is one of most important phenomenon in hypersonic inlets,which affects the operation range and the restart capacity.A two-dimensional internal flow field of mixed-compression hypersonic inlets was simulated numerically.The flow characteristics of unstart/restart caused by variations of attack angle were also investigated.The reasons behind the formation of inlet unstart/restart was discussed from the viewpoint of hydrodynamic stability.The inlet performance parameters varying with angle of attack were analyzed.Finally,the condition of inlet restart was discussed.

Freestream

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Adaptive Heat Flux Control in Scramjet Cooling Channel

Wen Bao Yanjuan Duan Weixing Zhou Daren Yu

Scramjet

10.2514/6.2009-5269

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Citations (0)

Flow field characteristics analysis and combustion modes classification for a strut/cavity dual-mode combustor

Acta Astronautica (2017)

Chenlin Zhang Juntao Chang Yuanshi Zhang Youyin Wang Wen Bao

Ramjet

Scramjet

Isolator

10.1016/j.actaastro.2017.03.023

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Citations (47)

Feasibility and Performance Analysis of High-Energy-Density Hydrocarbon-Fueled Turboexpander Engine

Aerospace (2023)

Jin Gao Ziyi Kang Weiheng Sun Youyin Wang Junlong Zhang

With the in-depth research on hypersonic aerodynamics and hypersonic propulsion technology, humans are growing closer to space travel. Recent studies have shown that the pre-cooled air-turborocket (ATR) or turboexpander engines are some of the potential propulsion methods for reusable space vehicles and single stage-to-orbit (SSTO) missions because they have a high specific impulse at low Mach numbers, which can overcome the problem of the “thrust gap” in turbine-based combined-cycle (TBCC) engines. The ATR engine needs an additional oxidizing agent and the turboexpander engine usually uses hydrogen as fuel, which has low energy density and poor safety. To address this problem, this paper proposed a high-energy-density (HED) hydrocarbon-fueled turboexpander engine, and its feasibility has been proven through a simplified thermodynamic model. Through detailed thermodynamic analysis based on the energy and pressure balance, this paper analyzed the performance characteristics of the engine to evaluate its capacity to work in a wide speed range at low Mach numbers. The results show that the endothermic hydrocarbon-fueled turboexpander engine has good specific impulse in Mach 0∼4 at an equivalence ratio of 0.7∼1.3, and the turboexpander engine can be combined with the dual-mode scramjet and become an efficient acceleration method for SSTO missions and the reusable spacecraft.

Turboexpander

Specific impulse

10.3390/aerospace10090753

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Citations (1)