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MISSILE guidance ALGORITHM AGAINST HIGH-G BARREL ROLL MANEUVERS

JOURNAL OF guidance CONTROL AND DYNAMICS 1994年第1期17卷 123-128页

作者： IMADO, F MIWA, S TOKYO DENKI UNIV FAC ENGNTOKYOTOKYO 101JAPAN

The features of high-g barrel rolls for an aircraft and the countermeasures for a proportional navigation guidance missile against this maneuver are studied. First, the features of the barrell roll maneuver, and the effects of the parameters on the miss distance are discussed. The simulation results show that a high-g barrel roll maneuver generally produces a larger miss distance than a split-S (a sustained maximum g turn) and the miss distance does not critically depend on the maneuver initiation time, if the aircraft has a certain Length of ''time-to-go'' and maneuvers with an appropriate roll rate. Second, the inference is made that the provision of a phase lead in the pitch-yaw plane in the missile guidance loop and adoption of the augmented proportional navigation guidance may be effective. It is also proven that a large phase shift (but less than pi/2) results in a smaller miss distance and that the combination of the phase lead and the augmented proportional navigation produces better results.

关键词： guidance algorithms Rudder Proportional Navigation Missile guidance Lift Coefficient Zero Lift Drag Coefficient Air to Air Missiles Mathematical Models Kalman Filter Boundary Value Problems

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Practical dual-control guidance using adaptive intermittent maneuver strategy

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JOURNAL OF guidance CONTROL AND DYNAMICS 2001年第5期24卷 1009-1015页

作者： Lee, HI Tahk, MJ Sun, BC Korea Adv Inst Sci & Technol Div Aerosp Engn Taejon 305701 South Korea Korea Aerosp Res Inst Guidance & Control Dept Taejon 305333 South Korea

A new adaptive intermittent maneuver strategy is proposed, which has switching threshold levels dependent on the estimated time-to-go for dual-control guidance of passive homing missiles. guidance performance in terms of control effort and target observability for the adaptive intermittent maneuver strategy are also analyzed, as well as proportional navigation guidance. With intermittent maneuvers the guidance command is occasionally disabled to intentionally increase guidance errors. When provided with suitable switching threshold levels, this intermittent maneuver strategy improves target observability and, consequently, intercept performance. Statistical simulations for an atmospheric engagement demonstrate the effectiveness of the proposed intermittent maneuver strategy.

关键词： Control guidance Proportional Navigation Homing Missile guidance algorithms Homing guidance Stochastic Dynamic Programming Polar Coordinate System Switching Mechanisms Stochastic Control Command Missile

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EVALUATION OF OPTIMAL-guidance ALGORITHM FOR AEROASSISTED ORBIT TRANSFER

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JOURNAL OF guidance CONTROL AND DYNAMICS 1995年第4期18卷 718-722页

作者： MELAMED, N CALISE, AJ Georgia Inst. of Technology Atlanta

In this paper we perform an evaluation of a guidance algorithm for aeroassisted orbit transfer based on the method of matched asymptotic expansions (MAEs). It is shown that, by exploiting the structure of the matched asymptotic expansion solution procedure, the original problem, which requires the solution of a set of 20 implicit algebraic equations, can be reduced to a problem of 6 implicit equations in 6 unknowns. guidance law implementation entails treating the current state as a new initial state and repetitively solving the MAE problem to obtain the feedback controls.

关键词： guidance algorithms Feedback Control guidance Laws Lift to Drag Ratio Closed Loop Hamilton Jacobi Bellman Equation Aerodynamic Force Lift Coefficient Earth Orbit Transfer Vehicle

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NOISY SATELLITE PURSUIT-EVASION guidance

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JOURNAL OF guidance CONTROL AND DYNAMICS 1989年第6期12卷 901-905页

作者： MERZ, AW Lockheed Research Laboratory Palo Alto California

guidance laws are developed for both pursuer and evader satellites, using a simplified dynamic model of the one-on-one satellite encounter. Dynamic symmetry is assumed: both have noisy azimuth-elevation data, the criterion for each is the expected miss, and both satellites have on-off thrust inputs of controllable direction. Sample times and control times are simultaneous, and the known time of minimum range is independent of the controls. Under a set of plausible assumptions, the expected miss is minimized by the pursuer and maximized by the evader. Typical solutions are illustrated, and refinements are discussed.

关键词： Satellites guidance Laws Bang Bang Control Kalman Filter Discrete Control Statistical Distributions Boundary Value Problems guidance algorithms Control Algorithm

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OPTIMAL guidance OF AEROASSISTED TRANSFER VEHICLES BASED ON MATCHED ASYMPTOTIC EXPANSIONS

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JOURNAL OF guidance CONTROL AND DYNAMICS 1995年第4期18卷 709-717页

作者： CALISE, AJ MELAMED, N Georgia Institute of Technology Atlanta Georgia 30332

In this paper we address and clarify a number of issues related to matched asymptotic expansion analysis of skip trajectories or any class of problems that give rise to inner layers that are not associated directly with satisfying boundary conditions. The procedure for matching inner and outer solutions and using the composite solution to satisfy boundary conditions is developed and rigorously followed to obtain a set of algebraic equations for the problem of inclination change with minimum energy loss. Repeated solution of these algebraic equations along the trajectory, treating each current state as an initial state, constitutes a feedback guidance algorithm. The solution is uniformly valid to zero order in an expansion parameter.

关键词： guidance algorithms Hamilton Jacobi Bellman (HJB) Equations Flight Path Angle Aerodynamic Force Perturbation Analysis guidance Laws Earth Aerospace Engineering Hamiltonian Functions Aerodynamic Heating

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Linear Quadratic Minimum-Effort, Specify-Performance Approach to Missile guidance

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JOURNAL OF guidance CONTROL AND DYNAMICS 2021年第3期44卷 559-571页

作者： Weiss, Martin Shima, Tal Technion Israel Inst Technol Dept Aerosp Engn IL-32000 Haifa Israel

A generic guidance design framework is proposed that is based on the idea of minimizing the guidance effort expressed as the quadratic integral of the guidance command and imposing performance constraints on various trajectory parameters at arbitrary points in time during the flight. This framework extends previous work on guidance algorithms for active aerial defense and for obstacle avoidance. Using some concrete examples it is shown that the proposed framework is flexible enough to tackle interesting guidance problems related to multiple targets scenarios. It is also shown that the same framework offers a practical solution for the optimal intercept guidance problem with constraints on the lateral missile acceleration.

关键词： Missile guidance guidance algorithms Obstacle Avoidance guidance System Linearized Kinematics Flight Control Proportional Navigation Optimal Control Numerical Simulation Structural Damage

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Optimal Aerocapture guidance

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JOURNAL OF guidance CONTROL AND DYNAMICS 2015年第4期38卷 553-565页

作者： Lu, Ping Cerimele, Christopher J. Tigges, Michael A. Matz, Daniel A. Iowa State Univ Dept Aerosp Engn Ames IA 50011 USA NASA Lyndon B Johnson Space Ctr Flight Mech & Trajectory Design Branch Houston TX 77058 USA NASA Lyndon B Johnson Space Ctr Houston TX 77058 USA

Aerocapture is the maneuver by an interplanetary spacecraft to fly through the atmosphere of a planet with the aim of attaining a specified orbit around the planet. By appropriately controlling the aerodynamic lift and/or drag force vectors, the spacecraft can exit the atmosphere and enter the target orbit without the need for large propellant consumption in post-atmospheric orbital correction burns. The focus of this paper is to develop an algorithm to guide the spacecraft accurately and reliably during the aerocapture maneuver with lift vector control while ensuring the least possible post-atmospheric propellant expenditure for inserting into the target orbit. The analysis of optimal aerocapture flight in this work shows that the optimal aerocapture trajectory in general has a bang-bang control structure in which the spacecraft first flies with the largest possible vertical lift up, then the largest possible vertical lift down. Based on this understanding, a two-phase numerical predictor-corrector guidance algorithm is developed. It is demonstrated that this algorithm not only exhibits the strengths of adaptivity and high accuracy of predictor-corrector guidance algorithms, but also produces an optimal performance in terms of propellant consumption that is significantly better than existing aerocapture numerical predictor-corrector guidance algorithms.

关键词： Aerobraking Aerodynamic Coefficients guidance algorithms Propellant Mass Fraction Trajectory Optimization Earth Interplanetary Spacecraft Orbital Inclination Flight Path Angle Angle of Attack

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Route guidance for Satisfying Temporal Logic Specifications on Aircraft Motion

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JOURNAL OF guidance CONTROL AND DYNAMICS 2017年第2期40卷 390-401页

作者： Cowlagi, Raghvendra V. Zhang, Zetian Worcester Polytech Inst Aerosp Engn Program Worcester MA 01609 USA

A new technique for aircraft route guidance subject to linear temporal logic specifications is presented. The proposed approach is based on workspace partitioning, and it relies on the idea of so-called lifted graphs. Briefly, edges in a lifted graph are successions of adjacent edges in the topological graph associated with the workspace partition. Edges of the lifted graph are associated with certain reachability properties of the aircraft model. The main result of this paper is the precise characterization of acceptable routes (namely, sequences of cells) that are guaranteed to be traversable by admissible state trajectories of the aircraft model while satisfying the given linear temporal logic specifications. The proposed approach incorporates nonholonomic kinematic constraints, does not require complete controllability in the presence of workspace constraints, and does not require linearization of the aircraft model. Numerical methods to implement the proposed route-planning algorithm are discussed. The proposed algorithm is illustrated with numerical simulation examples that reflect the practical significance of linear temporal logic specifications in aircraft guidance.

关键词： Aircrafts Numerical Simulation UAV Dijkstra's Algorithm Trajectory Optimization MATLAB guidance algorithms Search Algorithm Nonlinear Systems Open Source Software

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EXPLICIT guidance ALONG AN OPTIMAL SPACE CURVE

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JOURNAL OF guidance CONTROL AND DYNAMICS 1989年第4期12卷 495-504页

作者： HOUGH, ME Textron Defense Systems Wilmington Massachusetts

An explicit guidance theory is developed for maneuvering to a prescribed destination with terminal constraints on velocity vector direction. Motion is constrained to an optimal, three-dimensional space curve by constraint forces perpendicular to velocity (lift). Lift components are derived by twice differentiating functions specifying radial distance and geocentric latitude as functions of longitude. An optimal space curve is determined by solving a two-point boundary-value problem in the calculus of variations. Necessary conditions for an extremum are 1) a set of coupled, fourth-order, Euler-Lagrange differential equations for the space curve functions;2) a single, first-order differential equation for the adjoint variable;and 3) boundary conditions specified at two ends of the trajectory. Although energy is not conserved because of drag, motion along the space curve is integrable because lift-induced drag is determined by trajectory curvature. Velocity along the space curve may be expressed by a quadrature evaluated by the method of successive approximation to refine the accuracy of the compressibility drag slowdown. © 1980 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Aerodynamic Configurations Boundary Value Problems Kinematic Viscosity Lift Coefficient Flight Path Angle Earth guidance algorithms Hamiltonian Functions Transversality Condition Autopilot

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guidance SCHEME FOR A MACH-3 STAGED GLIDING BOOSTER

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JOURNAL OF SPACECRAFT AND ROCKETS 1991年第5期28卷 567-573页

作者： NAFTEL, JC POWELL, RW NASA Langley Research Center Hampton VA

One of the promising launch concepts that could replace the current Space Shuttle launch system is a two-stage, winged, vertical-takeoff, parallel-burn, fully reusable launch vehicle comprised of a manned orbiter and an unmanned booster. During the boost phase of ascent, the booster provides propellant for the orbiter engines through a cross-feed system. When the vehicle reaches Mach 3, the booster propellants are depleted and the booster is staged and glides to a horizontal landing al a launch site runway. One of the major design issues for this class of vehicle is the unpowered glide back of the booster after the staging maneuver is completed. A guidance algorithm was developed for the glide-back maneuver and verified using a three-degree-of-freedom trajectory simulation that included static trim in pitch. The guidance algorithm was tested using off-nominal atmospheric, staging, and booster aerodynamic characteristics.

关键词： Runways guidance algorithms Aerodynamic Characteristics Propellant Launch System Reusable Launch Vehicle Three Degrees of Freedom Vertical Takeoff Space Shuttle Lift Coefficient

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