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Root-mean-square miss distance of proportional navigation missile against sinusoidal target

JOURNAL OF guidance CONTROL AND DYNAMICS 1996年第3期19卷 563-568页

作者： Ohlmeyer, EJ U.S. Navy Naval Surface Warfare Center Dahlgren VA

The performance of a proportional navigation homing missile against a target performing a sinusoidal weave maneuver is evaluated. The missile's effectiveness is measured in terms of the root-mean-square miss distance over a set of engagements in which the initial phase of the target weave is uniformly distributed. Closed form solutions for the root-mean-square miss are derived for the case where the missile guidance system is modeled by a first order lag and the lateral acceleration is unlimited. The analysis is then extended to include the effects of acceleration saturation and higher order missile dynamics. Comparisons are made between a first-order and a fifth-order guidance system, and the root-mean-square miss is determined numerically as a function of the interceptor's effective navigation gain, time constant and acceleration limit, and the target's weave amplitude and frequency.

关键词： Proportional Navigation Homing Missile guidance System terminal guidance Missile Dynamics Monte Carlo Simulation Flight Control System Statistical Distributions Target Missiles Command Missile

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Analytical missile guidance laws with a time-varying transformation

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JOURNAL OF guidance CONTROL AND DYNAMICS 1996年第2期19卷 496-499页

作者： Balakrishnan, SN Missouri-Rolla Univ. Rolla

There is considerable scope for research in improving homing missile performance in terms of estimator, guidance, and autopilot in an intercept scenario. This study focuses on obtaining improvements in homing missile guidance with a properly posed controller for guidance. In this way it is possible to integrate the estimator in the loop in an optimal way. The central idea is that the polar coordinates present a natural coordinate system for a missile engagement. An attempt to minimize the control energy is sought, and a time-varying weight on the control to shape the relative kinematics is considered. To obtain a closed-form solution for the commanded accelerations, the radial and transverse coordinates are decoupled. This leads to a two-point boundary-value problem with linear time-varying coefficients. With a time-varying transformation, however, a class of closed-form solutions are obtained that yield several proportional guidance laws. (AIAA)

关键词： terminal guidance Sequential Quadratic Programming Thrust to Weight Ratio Spacecraft Mission Computing Earth Moon guidance Laws Proportional Navigation Linear Quadratic Gaussian

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AUTONOMOUS RENDEZVOUS USING ARTIFICIAL POTENTIAL FUNCTION guidance

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JOURNAL OF guidance CONTROL AND DYNAMICS 1995年第2期18卷 237-241页

作者： LOPEZ, I MCINNES, CR University of Glasgow Glasgow G12 8QQ Scotland United Kingdom

A novel methodology has been developed for the guidance and control of a maneuvering chase vehicle undergoing terminal rendezvous in the presence of path constraints and multiple obstructions. The method hinges on defining a suitable scalar function which represents an artificial potential field describing the locality of the target vehicle. Using a set of bounded impulses the chase vehicle is guided by the local topology of this potential function. Obstructions and path constraints are introduced by superimposing regions of high potential around these regions. Exact, analytical expressions are then obtained for the required control impulse magnitude, direction and switching times using the second method of Lyapunov. These control impulses ensure that the potential function monotonically decreases so that convergence of the chaser to the target is ensured analytically, without violating the path constraints. Since the components of the potential and control impulses may be represented analytically, the method appears suitable for autonomous, real-time control of complex maneuvers with a minimum of onboard computational power.

关键词： Artificial Potential Fields Propellant Clohessy Wiltshire Equation International Space Station Large Space Structures Vehicle Trajectories terminal guidance Space Stations Optimal Control Theory Rendezvous guidance

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BANK-TO-TURN OPTIMAL guidance WITH LINEAR EXPONENTIAL QUADRATIC GAUSSIAN PERFORMANCE CRITERION

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JOURNAL OF guidance CONTROL AND DYNAMICS 1995年第5期18卷 951-958页

作者： LIN, JM LEE, SW CHUNG HUA POLYTECH INST GRAD SCH AERONAUT & ASTRONAUT ENGNHSINCHU 30067TAIWAN CHUNG SHAN INST SCI & TECHNOL DIV ROCKETTAYUAN 32500TAIWAN

This paper presents an optimal guidance law for controlling the pitch acceleration and roll rate of a bank-to-turn missile with linearized plant dynamics and zero autopilot lag. The closed-form solution of the guidance law is derived by using the linear exponential quadratic Gaussian performance criterion and the corresponding Hamilton-Jacobi-Bellman equation. In addition, a constant acceleration bias is also introduced to prevent excessive roll rate command due to noise. It is shown that the optimal control gain can explicitly take both system and measurement noise covariances into consideration;therefore, the average, maximum, and standard deviation of miss distance can be reduced. Comparisons with those optimal guidance laws developed by the traditional linear quadratic Gaussian method are also made, which prove that the proposed guidance law is always better.

关键词： Bank to Turn Hamilton Jacobi Bellman (HJB) Equations guidance Laws Standard Deviation Autopilot Gaussian White Noise Target Missiles terminal guidance Riccati Equations Power Spectral Density

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ANALYTICAL SOLUTION OF OPTIMAL TRAJECTORY-SHAPING guidance

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JOURNAL OF guidance CONTROL AND DYNAMICS 1989年第4期12卷 600-601页

作者： RAO, MN Defence Research and Development Laboratory Hyderabad India

An analytical solution of the optimal trajectory-shaping guidance law is presented whose results yield superior estimates of the optimal gains of a closed-loop nonlinear system. Missiles employing this guidance law can achieve higher-than-conventional range, with excellent intercept performance; the solution will also furnish a smooth acceleration-time history, leading to better end-performance parameters. Surface-to-surface, surface-to-air, and air-to-air missile applications are foreseen. (O.C.)

关键词： guidance Laws Bessel Functions Closed Loop High Performance Aircraft Linearized Kinematics Dynamic Response terminal guidance Nonlinear Systems

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OPTIMAL-CONTROL AND ESTIMATION FOR STRAPDOWN SEEKER guidance OF TACTICAL MISSILES

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JOURNAL OF guidance CONTROL AND DYNAMICS 1982年第3期5卷 225-226页

作者： VERGEZ, PL MCCLENDON, JR U.S. Air Force Armament Laboratory Eglin Air Force Base Fla.

Most contemporary tactical guided weapons utilize proportional navigation as the terminal guidance law and an inertially stabilized grimballed seeker to provide guidance information. The proportional guidance law is most often used because it can be easily implemented. It has been shown that proportional navigation is most effective under restrictive engagement conditions, i. e. , small off-boresight angle launches, intercepting low-maneuverability targets;however, when employed in engagements that deviate from these conditions, proportional navigation's performance is degraded.

关键词： Linear Quadratic Gaussian Tactical Missiles guidance System Proportional Navigation terminal guidance Extended Kalman Filter Missile Body Air to Air Missiles Gaussian White Noise Electronic Component

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terminal guidance FOR SOFT AND ACCURATE LUNAR LANDING FOR UNMANNED SPACECRAFT

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JOURNAL OF SPACECRAFT AND ROCKETS 1968年第6期5卷 644-&页

作者： FENG, TY WASYNCZU.CA Hughes Aircraft Company El Segundo Calif.

Soft, precise landings of unmanned lunar spacecraft may be needed for logistic support of future manned missions. The terminal descent guidance concept proposed in this paper utilizes proportional navigation plus logarithmic deceleration in the initial guided phase of flight and switches at a predetermined range to an unguided gravity turn, thereby achieving a soft landing with vertical attitude at touchdown. guidance simulation studies have shown this concept to be effective in reducing the target miss distance resulting from dispersions in initial flight conditions caused by uncertainties in retro burnout and errors in instrument measurement and command execution. With the present technology and available spaceflight- proven instruments, this guidance concept can be easily implemented without exceeding practical design limitations. Moreover, it requires no knowledge of the local vertical throughout the terminal phase of flight. A landing accuracy of 500-ft circular error probability is achievable. © 1968 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

关键词： terminal guidance Lunar Landing Unmanned Spacecraft Flight Path Angle Thrust Vectoring Gravity Turn Doppler Velocity Sensor Flight Control System Proportional Navigation guidance System

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ORBITAL DOCKING DYNAMICS

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AIAA JOURNAL 1963年第6期1卷 1360-1364页

作者： WARD, JW WILLIAMS, HM Space Technology Laboratories Inc. Redondo Beach Calif.

A docking configuration and docking sequence are described for accomplishing an orbital refueling mission. The docking configuration consists essentially of matched conical surfaces, on the docking vehicles, and a latching device. A mathematical model for studying the collision dynamics is presented, and the effects of guidance errors, attitude errors, and various structural parameters on docking performance are discussed. Requirements for attitude control also are included. It is concluded that the proposed docking configuration is feasible and will accommodate reasonable system errors. © 1963 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

关键词： Attitude Control System Mathematical Models Yaw Structural Damping Propellant Friction Coefficient Rendezvous guidance Structural Members Energy Transfer terminal guidance

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RENDEZVOUS guidance WITH LIMITED ENGINE THROTTLING

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JOURNAL OF SPACECRAFT AND ROCKETS 1966年第10期3卷 1450-&页

作者： OBRIEN, RM SIEVERS, RF The Boeing Company Huntsville Ala.

The problem of performing an earth-orbital rendezvous with a Saturn-class payload is considered. Conventional closed-loop guidance techniques require more throttling capability than is available in existing high-thrust engines. A solution is provided by using analytical methods to choose among competing guidance laws and to select criteria and gains giving a smooth acceleration demand in the general situation while retaining fuel economy and low sensitivity to trajectory errors. A typical mission then is selected and digital simulation is used to optimize parameters for both a homing and homing-docking mission. For the ensemble of errors producing the worst expected case, rendezvous is achieved with less than 30% throttling for a propulsion system developing 30,000-lb thrust and carrying a Saturn V payload. A guidance method employing a new thrust-initiation criterion and time-varying gains is devised to eliminate the sudden increase in thrust requirements encountered in the transition from homing to docking. Readily sensed quantities are retained as control variables to reduce onboard computer complexity, computation error, and time delays. © 1966 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

关键词： Rendezvous guidance guidance System Hohmann Transfer Gain Scheduling Saturn terminal guidance Attitude Control System Propulsion System Fuel Consumption Rocket Engine

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Thermal conductive connection and method of making same Patent

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1967年

作者： c. a. harper

Supplemental catalog subcollection information: NASA Publication Collection; Astrophysics and Technical Documents; Thermal conductive, electrically insulated cleavable adhesive connection between electronic module and... 详细信息

关键词： conferences data processing equipment terminal guidance

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