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第三十八届中国控制会议

作者： Dong Guo Xiwang Dong Dingdong Li Zhang Ren School of Automation Science and Electrical Engineering Beihang University Beijing Advanced Innovation Center for Big Data and Brain Computing Beihang University

This paper presents a feasibility analysis method for cooperative interception of hypersonic maneuvering target. Firstly, the dynamic model for cooperative interception is established. Secondly, for the characteristics of high-speed and bounded maneuverability of hypersonic targets, the analytical calculation methods for minimum and maximum flight time are proposed. Then, a coverage-based feasibility analysis method for cooperative interception is given, and the cooperative interception zone calculation method is illustrated. Finally, through numerical simulations, the reachable regions and the arrival time distribution for interceptors and target are calculated, and the cooperative interception zone is further obtained. The proposed method can also provide reference for the design of cooperative guidance method.

关键词： Cooperative interception cooperative attack zone feasibility analysis terminal guidance hypersonic

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Adaptive Fuzzy Sliding Mode guidance Law considering Available Acceleration and Autopilot Dynamics

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INTERNATIONAL JOURNAL OF AEROSPACE ENGINEERING 2018年第Pt.1期2018卷 10-10页

作者： Wang, Yulin Tang, Shengjing Shang, Wei Guo, Jie Beijing Inst Technol Sch Aerosp Engn Beijing 100081 Peoples R China Hubei Aerosp Technol Acad Syst Design Inst Wuhan 430040 Hubei Peoples R China

terminal guidance law for missiles intercepting high maneuvering targets considering the limited available acceleration and autopilot dynamics of interceptor is investigated. Conventional guidance laws based on adaptive sliding mode control theory were designed to intercept a maneuvering target. However, they demand a large acceleration for interceptor at the end of the terminal guidance, which may have acceleration saturation especially when the target acceleration is close to the available acceleration of interceptor. In this paper, a terminal guidance law considering the available acceleration and autopilot dynamics of interceptor is proposed. Then, a fuzzy system is utilized to approximate and replace the variable structure term, which can handle the unknown target acceleration. And an adaptive neural network system is adopted to compensate the effects caused by the designed overlarge acceleration of interceptor such that the interceptor with small available acceleration can intercept the high maneuvering target. Simulation results show that the guidance law with available acceleration and autopilot dynamics (AAADG) is highly effective for reducing the acceleration command and achieving a small final miss distance.

关键词： Automatic pilots milbemycin oxime Interceptor aircraft acceleration terminal guidance

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Planetary Defense Mission Using Guided Collision of Near-Earth Objects

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JOURNAL OF SPACECRAFT AND ROCKETS 2017年第5期54卷 985-992页

作者： Marcus, Matthew L. Sloane, Joshua B. Ortiz, Oliver B. Barbee, Brent W. Univ Maryland Dept Aerosp Engn 3179 Glenn L Martin Hall College Pk MD 20742 USA NASA Goddard Space Flight Ctr Nav & Mission Design Branch 8800 Greenbelt RdMail Stop 595 Greenbelt MD 20771 USA

The Baseline Instrumented Lithology Lander, Inspector, and Asteroid Redirection Demonstration System is a proposed demonstration mission to characterize a small asteroid less than 10m in diameter and redirect it to collide with a larger asteroid hundreds of meters in diameter. This collision will disrupt the larger asteroid or alter its trajectory, thereby demonstrating a capability to prevent such an asteroid from colliding with Earth. The concept of redirecting a smaller asteroid into a larger asteroid is attractive for this type of mission because it uses natural kinetic energy available beyond Earth's gravity well for the majority of the energy delivered to the larger asteroid. By contrast, a kinetic impactor launched directly from Earth to its target must have all of its mass lifted out of Earth's gravity well. The proposed architecture allows for an impact energy of several terajoules without the use of nuclear devices. This work presents a novel approach to this type of kinetic impactor mission. In the proposed concept of operations, a spacecraft performs a controlled rendezvous and capture of the smaller asteroid. It then uses solar electric propulsion to redirect the asteroid over time onto a collision course. A high-thrust terminal guidance system is used to perform final trajectory adjustments in the hours leading to collision with the larger asteroid, ensuring a successful interception.

关键词： Earth Asteroid Collisions terminal guidance Solar Electric Propulsion Kinetic Energy Minimum Orbit Intersection Distance Bipropellants Attitude Control System Orbital Elements Asteroid Redirect Mission

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Nonswitching guidance Law for Trajectory Shaping Control

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JOURNAL OF guidance CONTROL AND DYNAMICS 2017年第10期40卷 2721-2728页

作者： Ratnoo, Ashwini Indian Inst Sci Autonomous Vehicles Lab Dept Aerosp Engn Bangalore 560012 Karnataka India

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Impact Angle Constrained Integrated guidance and Control for Maneuvering Target Interception

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JOURNAL OF guidance CONTROL AND DYNAMICS 2017年第10期40卷 2653-2661页

作者： He, Shaoming Song, Tao Lin, Defu Beijing Inst Technol Inst UAV Autonomous Control POB 327 Beijing 100081 Peoples R China

study considers the problem of impact angle constraint and integrated guidance and control (IGC) law design in an integrated manner for maneuvering target interception without knowing target acceleration. To address this problem, the systematic backstepping technique is adopted in IGC law design, where the convergence of line-of-sight (LOS) rate and impact angle error are regulated by two independent virtual control laws. A new smooth second-order sliding mode (SSOSM) differentiator is developed to estimate the derivatives of the virtual control laws.

关键词： Control guidance Model Predictive Control Aerodynamic Coefficients Surface to Air Missile Flight Path Angle Autopilot terminal guidance Air to Ground Missile Angle of Attack Missile Dynamics

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Research on Intercepting Strategy of Multiple Kill Vehicle in Midcourse Defense Based on Multi-Sensors Fusion Method

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IFAC-PapersOnLine 2017年第1期50卷 15032-15037页

作者： Shi, Heng Zhu, Jihong Yuan, Xiaming Kuang, Minchi Wang, Wufan Deng, Zhihui State Key Laboratory of Intelligent Technology and Systems Department of Computer Science and Technology Tsinghua University Beijing100084 China

The multiple kill vehicle (MKV) interceptor consists of a carrier vehicle and some small kill vehicles which can intercept multiple targets independently. According to the mission of midcourse interception for multiple warheads of long-range ballistic missile, this paper focused on the design and optimization of cooperative detection and guidance strategy. Based on multi-sensors fusion technology, the method of high-accuracy position measurement and view expansion of infrared sensors are proposed. The terminal guidance law is analyzed based on the data obtained by the methods. A digital real-time simulation system is developed to verify the feasibility of the method. © 2017

关键词： Vehicles Ballistic missiles Data fusion Electronic guidance systems Guided missiles Infrared detectors Cooperative detection Design and optimization Digital real time Fusion technology guidance strategy Missile interception Multiple kill vehicles terminal guidance

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Aircraft Attitude Determination Algorithms Employing Gravity Vector Estimations and Velocity Measurements 14

Aircraft Attitude Determination Algorithms Employing Gravity...

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14th International Conference on Informatics in Control, Automation and Robotics (ICINCO)

作者： de Celis, Raul Cadarso, Luis Rey Juan Carlos Univ European Inst Aviat Training & Accreditat EIATA Madrid 28943 Spain

ISBN: (纸本)9789897583049

Precision on Navigation, guidance and Control of aircraft is dependent on the precision of the measurement system both for position and attitude. It is well known in aerospace engineering that the rotation of an aircraft or space vehicle can be determined measuring two vectors in two different reference systems. Velocity vector in an aerospace vehicle can be determined in an inertial reference frame directly from a GNSS-based sensor. Also this velocity vector can be determined by integrating the acceleration measurements in an aircraft body fixed reference frame. By estimating gravity vector in an inertial reference frame, which currently is perfectly tabulated, and in a body reference frame, and combining these measurements with the velocity vector, rotation of the body can be determined. Application of these concepts is especially interesting in order to substitute high-precision attitude determination devices, which are usually expensive as they are forced to bear high solicitations as for instance G forces.

关键词： IMU GNSS Attitude Determination Sensor Model Projectile terminal guidance

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Dtic Ada055992: Three-Beacon Projectile guidance Study

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2017年

Dtic Ada055992: Three-Beacon Projectile guidance Study by Defense Technical Information Center; Defense Technical Information Center; published by

关键词： beacons guided projectiles terminal guidance ada055992: army armament research and development center dover nj large caliber weapon systems lab circular error probable computerized simulation distance measuring equipment drag dtic archive equations of motion guidance guidance computers masly, john r projectile projectile trajectories study terminal ballistics three-beacon transponders

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NASA Technical Reports Server (Ntrs) 20050182052: Development of the Surface Management System Integrated with Ctas Arrival Tools

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2017年

NASA Technical Reports Server (Ntrs) 20050182052: Development of the Surface Management System Integrated with Ctas Arrival Tools by NASA Technical Reports Server (Ntrs); published by

关键词： (ntrs) 20050182052: air traffic control airline operations airport towers arrival automatic control development integrated jara, dave jung, yoon c. management systems nasa technical reports server (ntrs) radar approach control synchronous meteorological satellite terminal guidance

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NASA Technical Reports Server (Ntrs) 19910012401: Human Factors in Aviation: terminal Control Area Boundary Conflicts

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2017年

NASA Technical Reports Server (Ntrs) 19910012401: Human Factors in Aviation: terminal Control Area Boundary Conflicts by NASA Technical Reports Server (Ntrs); published by

关键词： (ntrs) 19910012401: air traffic control aircraft approach spacing airfield surface movements airline operations airports airspace aviation: boundary collision avoidance conflicts flight control flight safety human factors engineering human performance instrument flight rules monan, william p. nasa technical reports server (ntrs) terminal guidance

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