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terminal guidance algorithm for ramjet-powered missiles

JOURNAL OF guidance CONTROL AND DYNAMICS 1998年第6期21卷 862-866页

作者： Aggarwal, RK Moore, CR Raytheon Syst Co Syst Design Lab Tewksbury MA 01876 USA

The terminal guidance design problem for a long-range bank-to-turn (BTT) ramjet missile involves a completely coupled pitch-yaw-roll nonlinear dynamics model. Because of these nonlinear dynamics, an optimal solution for acceleration and roll rate commands can be found only by numerical methods for solving two point boundary value problems. Because the roll-rate dynamics of the state-of-the-art missiles is much faster than the rest of the system states, a near-optimal solution is obtained to the BTT guidance problem using multiple timescale techniques. Nonlinear feedback solutions for the acceleration command and roll-rate command are derived. The zero-order slow solution obtained by treating roll rate as infinitely fast, is exactly the optimal guidance law for a skid-to-turn missile. The zero-order fast solution provides the roll-rate command. A first-order analysis corrects the acceleration command for the finite dynamics behavior in bank angle. Simulation results are presented for a representative terminal engagement using this algorithm. Near-zero miss distances are obtained in a noise-free environment.

关键词： Missiles Ramjet guidance Algorithms Bank to Turn terminal guidance guidance System Boundary Value Problems Nonlinear Feedback Roll Control Nonlinear Dynamics

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Analytical solution of missile terminal guidance

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JOURNAL OF guidance CONTROL AND DYNAMICS 1998年第2期21卷 342-348页

作者： Takehira, T Vinh, NX Kabamba, PT Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA

A new guidance law that combines pursuit guidance and proportional navigation is proposed. This guidance law depends on two parameters that determine the relative importance of pursuit guidance and proportional navigation. Numerical simulations of the nonlinear equations of motion suggest that the parameters of this law can be chosen to reduce the peak value of the missile acceleration or the duration of the engagement. When the engage ment ends in a tail chase, and linearization is valid, the linearized equations of motion lead to a confluent hypergeometric equation. This equation is solved in closed form, in the general case where tare target performs maneuvers such that its heading angle is a polynomial function of time. The analytical solution based on linearization and the numerical simulation of the nonlinear equations show good agreement.

关键词： Missiles terminal guidance guidance Laws Proportional Navigation Pursuit guidance Nonlinear Equation Numerical Simulation Heading Angle Second Order Differential Equations Mach Number

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Impact angle control for planar engagements

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IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS 1999年第4期35卷 1439-1444页

作者： Song, TL Cho, H Hanyang Univ Dept Control & Instrumentat Engn Ansan 425791 Kyunggi Do South Korea Agcy Def Dev Daejeon 305600 South Korea

A new and practical terminal guidance law is presented for impact angle control for two-dimensional active homing engagement scenarios. Impact angle control is required to enhance terminal effectiveness of antitank and antiship missile systems in particular. The proposed guidance law is developed to cope with missile velocity reduction due to aerodynamic drag and target maneuver. In actual applications, the proposed guidance law is combined in cascade with a target tracking filter under the certainty equivalence principle. The proposed guidance law in conjunction with the target tracking filter is shown to be effective in antiship active homing engagement scenarios by a series of Monte Carlo simulation runs.

关键词： engagement guidance aerodynamic drag Impact angle Target tracking engaging Monte Carlo technique EQUIVALENCE PRINCIPLE Filters terminal guidance

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Feedback control for spacecraft rendezvous and docking

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JOURNAL OF guidance CONTROL AND DYNAMICS 1999年第4期22卷 609-611页

作者： Kluever, CA Univ Missouri Dept Mech & Aerosp Engn Kansas City MO 64110 USA

A feedback control law for performing planar rendezvous and docking maneuvers is presented. The control law uses a feedback linearization approach and guarantees tracking along an arbitrary fixed docking direction with a desired approach speed. Although the control scheme is based on the linear CW equations, simulation of the nonlinear system shows that the control law results in accurate rendezvous and docking conditions. The feedback control law is relatively simple and therefore may be a potential onboard guidance scheme for autonomous docking manuevers. (AIAA)

关键词： Feedback Linearization Spacecraft Rendezvous Target Spacecraft State Space Representation Second Order Differential Equations terminal guidance Nonlinear Systems Lightly Damped Structures Satellites Boundary Value Problems

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Propulsion system sizing for orbital inspection vehicles

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JOURNAL OF guidance CONTROL AND DYNAMICS 1999年第2期22卷 375-378页

作者： Williams, T Tanygin, S Univ Cincinnati Dept Aerosp Engn Cincinnati OH 45221 USA Analyt Graph Inc Malvern PA 19355 USA

Low-thrust proximity operations of the type occurring with the new class of remotely piloted orbital inspection vehicles is studied. Closed-form expressions are derived for the trajectory of a spacecraft that is acted upon by a continuous thrust. These are used as the basis for a numerical procedure for generating a rest-to-rest acceleration/coast/deceleration trajectory that takes a vehicle with a specified acceleration level between two desired points in a specified time. It is concluded that increasing vehicle acceleration by an order of magnitude above the theoretical minimum leads to significantly reduced propellant consumption. (AIAA)

关键词： Propulsion System Propellant Numerical Optimization Space Stations Clohessy Wiltshire Equation Numerical Interpolation Mass Spring System Aerospace Engineering Rigid Body Dynamics terminal guidance

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Minimizing interceptor size using neural networks for terminal guidance law synthesis

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JOURNAL OF guidance CONTROL AND DYNAMICS 1996年第3期19卷 557-562页

作者： Cottrell, RG Vincent, TL Sadati, SH UNIV ARIZONA TUCSONAZ 85721 NICHOLS RES CORP NAVY PROGRAMS DIVCAMARILLOCA 93012

Several initiatives are underway to miniaturize the size and weight of kinetic energy kill vehicles employed as interceptors In theater missile defense, It is demonstrated that using a neural network for terminal guidance law synthesis can further reduce kill vehicle weight when the divert incremental velocity change along the intercept trajectory is minimized. Neural networks allow for the implementation of closed-loop optimal guidance laws that cannot be obtained from linear optimal control theory. A simplified but representative engagement scenario is analyzed for a kinetic energy interceptor against a target with constant acceleration. The intercept accuracy and the divert incremental velocity resulting from implementation of the neural network guidance law are compared to the results obtained from the implementation of augmented proportional navigation. The neural network guidance law yielded increased weight savings with increasing engagement range and with increasing error in the estimate of target acceleration.

关键词： terminal guidance Feedforward Neural Network guidance Laws Closed Loop Control Proportional Navigation Pontryagin's Maximum Principle Kinetic Energy Missile Defense Propellant MATLAB

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Fuel/time optimal control of spacecraft maneuvers

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JOURNAL OF guidance CONTROL AND DYNAMICS 1997年第2期20卷 394-397页

作者： Liu, SW Singh, T State University of New York at Buffalo Buffalo New York 14260

A modified STO algorithm to solve the weighted fuel/time optimal control problem has been developed. An inertially symmetric spacecraft undergoing a rest-to-rest reorientation maneuver with three independent bounded impulsive controls is investigated. Results illustrate the variation of the switch-time of the control profile from a 5-switch for the time-optimal case to a 10-switch for small α. Increasing α beyond 0.053 results in a transition from the 10-switch profile to a 9-switch profile. For α > 0.063, it is shown that the eigenaxis control with two switches is the optimum.

关键词： Time Optimal Control Spacecraft Maneuvers terminal guidance Aerospace Engineering Lunar Landing Control System Design Bernoulli's Equation Nonlinear Dynamics Spacecraft System Space Technology

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Integral relations for disturbance isolation

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JOURNAL OF guidance CONTROL AND DYNAMICS 1997年第3期20卷 614-615页

作者： Lurie, BJ Jet Propulsion Laboratory California Institute of Technology Pasadena California 91109-8099

The design methods for high order passive and active dynamic systems used in disturbance isolation could benefit from the design theory of active electrical networks. A Bode integral is here applied in order to estima... 详细信息

关键词： GPS Receivers Satellites World Geodetic System Airborne Warning and Control System Electrical Impedance Modern Weapon Systems terminal guidance Systems Engineering Reaction Wheels Capacitance

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terminal area navigation using a relative global positioning system correction vector scheme

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JOURNAL OF guidance CONTROL AND DYNAMICS 1997年第3期20卷 615-617页

作者： Krempasky, J Hughes Missile Systems Co. Tucson AZ

A relative GPS correction vector scheme is presented which virtually eliminates pseudorange bias and absolute target location errors. It thereby yields target accuracies higher than those afforded by GPS-only navigati... 详细信息

关键词： GPS Area Navigation GPS Receivers Satellites World Geodetic System Inertial Navigation System Airborne Warning and Control System terminal guidance Monte Carlo Simulation Modern Weapon Systems

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Midcourse guidance for a short-range attack missile using error compensation

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JOURNAL OF SPACECRAFT AND ROCKETS 1996年第2期33卷 191-197页

作者： Muzumdar, DV Hull, DG UNIV TEXAS DEPT AEROSP ENGN & ENGN MECH AUSTIN TX 78712 USA

Midcourse guidance laws are developed for a short-range, bank-to-turn attack missile with a high thrust-to-weight ratio, The trajectory optimization formulation is to minimize the flight time from a low-altitude, subsonic launch to a fixed target 100-300 n mile from the launch aircraft at any azimuth. After the thrust phase, the missile coasts in a vertical plane at zero angle of attack. For guidance, optimal guidance is selected, and two guidance laws are developed by formulating an equivalent optimal control problem over the thrust phase. The analytical guidance law is obtained by making approximations in the optimal control problem. It performs well for midcourse guidance but needs terminal guidance to hit the target. The error compensation (EC) guidance law is obtained by replacing the approximation terms by bounded controls, where the bounds are handled indirectly by adding penalty terms to the performance index. The EC weights are determined by using the EC control in the trajectory optimization problem and minimizing the flight time with respect to the weights. On board, weights can be stored for an array of target ranges and azimuths and obtained at launch by table lookup. The EC guidance law enables the missile to hit the target without terminal guidance.

关键词： midcourse guidance zero angle of attack trajectory optimization Optimal control azimuth TIME OF FLIGHT guidance vertical plane terminal guidance SHOOTING RANGE bounded control

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