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2011 Chinese Control and Decision Conference（CCDC）

作者： CHEN Jie,Naval Aeronautical and Astronautical University,Yantai,Shandong Province,China,PAN Changpeng,Naval Aeronautical and Astronautical University,China,ZHAO Hongchao,Naval Aeronautical and Astronautical University,Yantai,Shandong Province,China

A novel sliding surface observer and controller is designed based on Lyapunov function for hypersonic aircraft nonlinear dynamitic *** output sliding surface to construct Lyapunov function to guarantee the astringency of *** surface adaptive backstepping is adopted designed to ensure control law,and multi-layers neural network adjust function is used to compensate the influence from the uncertain,which designs the robust terms to solve the problem from approach *** stability analysis and simulations demonstrate the good performance of the controller.

关键词： Dynamic surface adaptive backstepping Observer Uncertain hypersonic aircraft Multi-layers neural network

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Nonlinear Modelling and Adative backstepping control Design for One hypersonic aircraft

Nonlinear Modelling and Adative backstepping control Design ...

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2011 Chinese Control and Decision Conference（CCDC）

作者： CHEN Jie,Naval Aeronautical and Astronautical University,Yantai,Shandong Province,China, PAN Changpeng,Naval Aeronautical and Astronautical University,China, WU Jinhua,Naval Aeronautical and Astronautical University,Yantai,Shandong Province,China

A six degree-of-freedom nonlinear model of the near space hypersonic aircraft is founded and modified according to the series of literatures of Winged-Cone offered by America NASA Langly *** model can meet the demand of strongly nonlinear,highly coupled,rapidly time variation,and be applied to theory study and simulate validation of hypersonic aircraft control *** backstepping control to design the nonlinear control system.

关键词： hypersonic aircraft A six degree-of-free domnonlinear model highly coupled Adative backstepping control

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CALCULATING METHOD OF AERODYNAMIC HEATING FOR hypersonic aircraftS

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Transactions of Nanjing University of Aeronautics and Astronautics 2013年第3期30卷 237-242页

作者：季卫栋王江峰 College of Aerospace Engineering Nanjing University of Aeronautics and Astronautics

A new calculating method of aerodynamic heating for unsteady hypersonic aircrafts with complex configuration is *** method,which considers the effects of high temperature chemical non-equilibrium and the heat transfer process in thermal protection structure,is based on the combination of the inviscid outerflow solution and the engineering method,where the Euler solver provides the flow parameters on boundary layer edge for engineering method in aerodynamic heating calculation.A high efficient interpolation technique,which can be applied to the fast computation of longtime aerodynamic heating for hypersonic aircraft,is developed for flying *** this paper,three hypersonic test cases are calculated,and the heat flux and temperature distribution of thermo-protection system are *** numerical results show the high efficiency of the developed method and the validation of thermal characteristics analysis on hypersonic aerodynamic heating.

关键词： hypersonic aircraft aerodynamic heating fluid-structure coupled analysis chemical non-equilibrium effects coupling of numerical and engineering methods

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Dynamic Surface Control for Nonlinear hypersonic Air Vehicle Using Neural Network

Dynamic Surface Control for Nonlinear Hypersonic Air Vehicle...

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第二十九届中国控制会议

作者： Waseem Aslam BUTT Amezquita S.KENDRICK School of Automation Beijing University of Aeronautics and Astronautics

In this paper dynamic surface control（DSC）technique is combined with neural network based adaptive control design framework to design the longitudinal dynamics controller for a nonlinear generic hypersonic air vehicle（HSAV）.Detailed stability analysis is carried out to prove the uniform ultimate boundedness of all the signals in the closed loop *** effectiveness of the proposed strategy is demonstrated by simulation of the longitudinal model of the HSAV for trimmed cruise conditions of 110,000 ft and Mach 15 where the responses of the vehicle to a step change in altitude and airspeed are evaluated.

关键词： Adaptive Control Dynamic Surface Control hypersonic aircraft Neural Networks

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20 ppm Anhydrous Ammonia Odor Agent Proposed for Hydrogen Fuel for Safe Detection of Leaks

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Detection 2023年第1期10卷 1-6页

作者： Daniel Nelson Russell Independent Research Consultation Anchorage USA

Preferably 20 ppm anhydrous ammonia (NH3) is proposed to be added to hydrogen fuel (H) made from renewable energy sources (green hydrogen), so that H leaks may be easily detectable by smell, but not dangerously toxic. Including this odor agent, would allow H to be distributed safely in pipes, as required by law, and it would allow H to be safely stored, transported, and exported for sale, and widely commercialized. Further research is suggested to identify optimum pressure, temperature, and automated technique for injecting NH3 into H, and to chart the minimum concentration needed, as a function of temperature and humidity. An application to make hypersonic H burning aircraft safer for ground maintenance crews is proposed. An ability to make, store and distribute H, made from local sources of renewable energy, would reduce a need for fossil fuels, especially in poor, remote communities, where it could improve their economy by creating an export product for sale, while reducing pollution.

关键词： Hydrogen Renewable Energy Anhydrous Ammonia Hydrogen Gas Distribution System Odorant Odor Agent Green Hydrogen hypersonic aircraft

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Battlefield Situation Deduction and Maneuver Decision Using Deep Q-Learning

Battlefield Situation Deduction and Maneuver Decision Using ...

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第40届中国控制会议

作者： Minghui Shi Xiwang Dong Liang Han Qingdong Li Zhang Ren School of Automation Science and Electrical Engineering Science and Technology on Aircraft Control Laboratory Beihang University Key Laboratory of Dependable Service Computing in Cyber Physical Society (Chongqing University) Ministry of Education of ChinaChongqing University School of Sino-French Engineer Beihang University

As the pace and complexity of modern warfare accelerates, it is of great significance to apply intelligent technology to defense decision-making. Due to the high dynamics and randomness of the aircraft, traditional methods are difficult to solve the optimal control strategy. The characteristics of reinforcement learning match the difficulty of the problem. In this paper, the situation of hypersonic aircraft is deduced, and the deep reinforcement learning method is used to make autonomous penetration decisions in the reentry phase. The model of aircraft and environment is established, and the maneuvering decision-making model is established based on deep Q-learning and its optimization algorithm. Through a large number of simulation training,this method can effectively give the real-time decision output of the agent and make a good prediction of the situation. It has the ability of short-range accurate operation and long-term planning and prediction. This method can improve the probability of successful penetration, and can be used as the decision-making basis of glider penetration.

关键词： hypersonic aircraft situational deduction maneuver decision-making reinforcement learning deep Q-learning

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Numerical Study and Flight Control of Active Flow Control Based on Plasma Synthetic Jet

Numerical Study and Flight Control of Active Flow Control Ba...

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第43届中国控制会议

作者： Chunzhi Li Sheng Zhai Jianying Yang LandSpace Technology Co. Ltd. State Key Laboratory for Turbulence and Complex Systems Department of Mechanics and Engineering Science College of Engineering Peking University

Rapid response control technology has become a key aspect in the development of hypersonic aircraft. Plasma synthetic jet technology, characterized by its extremely fast response and zero-mass properties, has shown promising control capabilities in hypersonic flow control. It holds significant potential for application in the rapid response control of hypersonic aircraft. Leveraging the rapid response characteristics of plasma synthetic jets, this paper proposes a plasma synthetic jet rapid response control technology for hypersonic aircraft. By establishing a simplified model for controlling the flow field of hypersonic aircraft, numerical studies are conducted to investigate the control of hypersonic aircraft using plasma synthetic jets. Several controllers were designed to achieve the attitude control of the aircraft.

关键词： plasma synthetic jet hypersonic aircraft numerical simulation ESO

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