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Minimum-Fuel Fixed-Time Impulsive Elliptic Glide-Slope guidance algorithms Using Semidefinite Programming

JOURNAL OF guidance CONTROL AND DYNAMICS 2018年第9期41卷 1873-1887页

作者： Ariba, Yassine Arzelier, Denis Urbina-Iglesias, Laura Sofia Univ Toulouse LAAS CNRS ICAM F-31031 Toulouse France ICAM F-31300 Toulouse France

A new minimum-fuel glide-slope guidance algorithm for approaching autonomously a target evolving on an elliptic orbit is proposed in this paper. Assuming chemical propulsion, the present work aimed at enhancing seminal methods. Although this reference method is efficient and easy to implement, there is no direct control on the fuel consumption and the guidance error. By identifying some relevant degrees of freedom, a new formulation of the glide-slope guidance algorithm is proposed to address these issues. For a fixed-time rendezvous and a given number of maneuvers, the fuel-optimal multipulse glide slope is expressed as a semidefinite programming problem. A solution to this optimization problem provides an impulsive control sequence that guarantees a minimal consumption and makes sure the chaser trajectory remains inside a user-defined corridor. Besides, if trajectory constraints are removed, or if a specific direction is considered (V-bar or R-bar), then the formulation is reduced to a simple linear programming problem. Three realistic scenarios of rendezvous are simulated to illustrate the benefit of the proposed methodology.

关键词： guidance algorithms Fuels Fuel Consumption Quadratic Programming Chemical Propulsion State Space Representation Elliptical Orbit Velocity Profiles Propellant Glideslope

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Combined and Cooperative Minimum-Effort guidance algorithms in an Active Aircraft Defense Scenario

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JOURNAL OF guidance CONTROL AND DYNAMICS 2017年第5期40卷 1241-1254页

作者： Weiss, Martin Shima, Tal Castaneda, David Rusnak, Ilan Technion Israel Inst Technol Dept Aerosp Engn IL-31000 Haifa Israel Rafael Adv Def Syst Ltd IL-31021 Haifa Israel

The paper proposes two guidance algorithms for the target-attacker-defender scenario. The first is a combined guidance algorithm for the attacker that simultaneously achieves evasion from the defender and pursuit of the target. The second is a cooperative guidance algorithm for the target to evade the attacker and for the defender to pursue the evader. Both algorithms are derived under the assumption that performance is prescribed in the sense of the required maximum miss distance for pursuit and the required minimum miss distance for evasion, and the algorithms are minimizing the effort to achieve the requirements. It turns out that both the combined guidance algorithm and the cooperative guidance algorithm share a very similar structure. The performance of the proposed algorithms is tested in numerical simulations.

关键词： guidance algorithms Aircrafts Numerical Simulation Control guidance Engagement Kinematics Command to Line of Sight Proportional Navigation Lagrange Multipliers Optimal Control Pursuit guidance

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Minimum Effort Intercept and Evasion guidance algorithms for Active Aircraft Defense

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JOURNAL OF guidance CONTROL AND DYNAMICS 2016年第10期39卷 2297-2311页

作者： Weiss, Martin Shima, Tal Castaneda, David Rusnak, Ilan Technion Israel Inst Technol Dept Aerosp Engn IL-31000 Haifa Israel RAFAEL IL-31021 Haifa Israel

The paper proposes a new approach to guidance algorithm design for the target-attacker-defender problem based on the idea of specifying the desired performance in terms of miss distance and of optimizing the effort required to achieve it. Using this approach, guidance algorithms are designed separately for the defender and the target. The pursuit guidance algorithm for the defender uses the fact that the attacker is pursuing the target in order to improve the prediction of the attacker motion and thus its guidance performance. The evasion guidance algorithm for the target weighs in the fact that aggressive evasion maneuver will determine aggressive interception maneuvering from the part of the attacker, making the task of the defender more difficult. The guidance design problems are formulated as optimal control problems, and the solutions of these optimal control problems are used as guidance laws that use variables that are either directly obtainable from sensor measurements or estimates obtained from filtering these measurements. Using simulation results, the performance of the proposed guidance laws is demonstrated under perfect information assumption as well as in the presence of estimation errors.

关键词： guidance algorithms guidance Laws Optimal Control Sensors Aircrafts Proportional Navigation Numerical Simulation Autopilot Engagement Kinematics Pursuit guidance

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Descent & Landing Trajectory and guidance algorithms with Divert Capabilities for Moon Landing

Descent & Landing Trajectory and Guidance Algorithms with Di...

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AIAA SciTech Forum

作者： Capolupo, Francesco Rinalducci, Antonio European Space Agcy Estec Guidance Nav & Control Sect NL-2201 AZ Noordwijk Netherlands

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

This paper presents the preliminary design of the descent and landing trajectory and guidance algorithms of the ESA Argonaut lunar lander. The mission scenario and driving system constraints are presented and accounted for in the design of a fuel-optimal trajectory that includes divert capabilities, as required to achieve a safe landing. A sub-optimal descent and landing trajectory is then presented and computed from the optimal one, and the related on-board guidance algorithms are derived. The proposed end-to-end guidance solution represents an easily implementable alternative to on-board optimization, minimizing the verification & validation effort, computational footprint, and programmatic risk in the development of the related GN&C capabilities. A dedicated off-line optimization process is also outlined, and exploited to optimize the propellant consumption of the sub-optimal trajectory and to ensure the fulfilment of system constraints despite the use of simple algorithms on-board. The sub-optimal trajectory is compared to the optimal baseline, and conclusions are drawn on the applicability of the proposed approach to the Argonaut mission.

关键词： guidance algorithms Space Missions Propellant Lunar Lander Pontryagin's Maximum Principle Thrust Vectoring Closed Loop Terrain Relative Navigation Steering Law Attitude Control System

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A COMPARATIVE STUDY OF PATH-FOLLOWING guidance algorithms FOR AN AUTONOMOUS UNMANNED AERIAL VEHICLE

A COMPARATIVE STUDY OF PATH-FOLLOWING GUIDANCE ALGORITHMS FO...

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The Third International Conference on Dynamics, Vibration and Control

作者： M.Idres H.Mazhar R.Kafafy W.Faris Department of Mechanical Engineering International Islamic University Malaysia53100 Kuala LumpurMalaysia Department of Mechatronics Engineering International Islamic University Malaysia53100 Kuala LumpurMalaysia

Unmanned aerial vehicle(UAV) has many applications such as military defense and surveillance, weather forecast,terrain surveying,and civilian search and *** this paper,the autonomous UAV is commanded to follow a path defined by a series of *** tracking performance of different guidance algorithms for horizontal path tracking is *** algorithms are tested using nonlinear 6-DOF simulations of a model *** comparison study considers stability,accumulated tracking error,tracking time,and control power *** tracking performance is evaluated in windy and non-windy *** algorithms should allow the UAV to smoothly converge to change in course with minimal overshoot or undershoot, which is an important capability for tactical *** parameters which affect tracking performance are identified.

关键词： Unmanned Aerial Vehicle UAV guidance algorithms Path following Autonomous

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Flight-Path Angle guidance for Aerogravity-Assist Maneuvers on Hyperbolic Trajectories

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JOURNAL OF guidance CONTROL AND DYNAMICS 2015年第2期38卷 238-248页

作者： Mazzaracchio, Antonio Univ Roma La Sapienza Astronaut Elect & Energet Engn Dept I-00138 Rome Italy

This paper presents an original flight-path angle guidance algorithm using lift modulation for aerogravity-assist maneuvers on hyperbolic trajectories. The lift coefficient is tuned according to a three-stage guidance law, in which a linear flight-path angle guidance is assumed for both the ascending and descending atmospheric flight branches with a different gain coefficient in the feedback control form. The reference flight-path angle is linear with altitude and the closed-loop guidance attempts to track this reference. Between the descent and ascent phases, the guidance scheme provides a segment trajectory that is flown at a constant altitude. The developed algorithm was verified by comparing the obtained suboptimal results with data from previous studies on aerogravity-assist trajectory designs. A case study regarding a maneuver on a hyperbolic trajectory to Venus performed by a waverider, which is a spacecraft characterized by a high lift-to-drag ratio, is presented. The analysis provides the ranges of feasibility for the maneuver by varying the hyperbolic excess velocity and the periapsis altitude of the incoming orbit, as well as the angle flown at a constant altitude. The viability of the solutions in the presence of a number of thermal and dynamic constraints is also verified. The maneuver can be extremely effective in terms of the high values obtained for the angular deflection and the variation in velocity magnitude when appropriate values are selected for the input variables. The analysis indicates that the total heat load is the more stringent constraint.

关键词： Flight Path Angle Hyperbolic Trajectories Aerogravity Assist Orbital Eccentricity guidance algorithms Lift Coefficient guidance Laws Waverider Feedback Control Closed Loop

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Design of fuzzy logic guidance law against high-speed target

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JOURNAL OF guidance CONTROL AND DYNAMICS 2000年第1期23卷 17-25页

作者： Lin, CL Chen, YY Feng Chia Univ Inst Automat Control Engn Taichung 40724 Taiwan Natl Tsing Hua Univ Inst Elect Engn Hsinchu 30043 Taiwan

An advanced guidance law is developed against very high-speed targets. Preliminary studies have shown that the aspect angle of the interceptor at lock-on near 180 deg is a fundamental requirement for achieving small miss distance against a very high-speed target. To meet this requirement, a fuzzy guidance law in midcourse phase that is more similar to human decision making is designed. In terminal phase, a proportional and derivative-type fuzzy terminal guidance law is explored. It is shown that the integrated guidance scheme offers a near head-on homing condition before the missile enters terminal phase and provides better final results (smaller miss distance and wider defensible volume) than the conventional guidance law A complete simulation study is performed to show the effects of the proposed design.

关键词： guidance Laws Fuzzy Control System Midcourse guidance Proportional Derivative Angle of Attack Aerodynamic Force Proportional Navigation Inertial Reference Unit guidance algorithms Energy Consumption

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Stochastic Entry guidance

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JOURNAL OF guidance CONTROL AND DYNAMICS 2022年第2期45卷 320-334页

作者： Ridderhof, Jack Tsiotras, Panagiotis Johnson, Breanna J. Georgia Inst Technol Sch Aerosp Engn Atlanta GA 30332 USA Georgia Inst Technol Inst Robot & Intelligent Machines Atlanta GA 30332 USA NASA Johnson Space Ctr Houston TX 77058 USA NASA Flight Mech & Trajectory Design Branch JSC EG5 Houston TX USA

In this paper, closed-loop entry guidance in a randomly perturbed atmosphere, using bank angle control, is posed as a stochastic optimal control problem. The entry trajectory and the closed-loop controls are both modeled as random processes with statistics determined by the entry dynamics, the entry guidance, and the probabilistic structure of altitude-dependent atmospheric density variations. The entry guidance, which is parameterized as a sequence of linear feedback gains, is designed to steer the probability distribution of the entry trajectories while satisfying bounds on the allowable control inputs and on the maximum allowable state errors. Numerical simulations of a Mars entry scenario demonstrate improved range targeting performance with approximately 50% lower 1st and 99th percentile final range errors when using the developed stochastic guidance scheme as compared to the existing Apollo final phase algorithm.

关键词： Aerodynamic Coefficients Stochastic Optimal Control Atmospheric Density Probability Distribution Numerical Simulation Earth Flight Path Angle Angle of Attack Linear Quadratic Gaussian guidance algorithms

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Minimum-Effort Intercept Angle guidance with Multiple-Obstacle Avoidance

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JOURNAL OF guidance CONTROL AND DYNAMICS 2018年第6期41卷 1355-1369页

作者： Kumar, Shashi Ranjan Weiss, Martin Shima, Tal Indian Inst Technol Dept Aerosp Engn Bombay 400076 Maharashtra India Technion Israel Inst Technol Fac Aerosp Engn IL-32000 Haifa Israel

This paper presents an intercept angle guidance law against moving targets in an environment with several static obstacles. The guidance law is derived based on linearized kinematics model. By minimizing the guidance effort subjected to the conditions where the target is intercepted at the specified impact angle and the obstacles are avoided by specified minimum distances, the basic guidance algorithm is obtained. The special cases of one and two obstacles are separately considered. The proposed guidance law has a form similar to that of augmented proportional navigation guidance with some additional bias terms. These bias terms correspond to the correction for the impact angle error and the generation of the required maneuvers to avoid the obstacles. Finally, numerical simulations are used to illustrate the efficacy of the proposed guidance law.

关键词： Sliding Mode Control guidance Laws Engagement Kinematics Intercept Angle guidance Law Proportional Navigation Numerical Simulation guidance algorithms Optimal Control Target Missiles Computing

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AN OPTIMAL Q-guidance SCHEME FOR SATELLITE LAUNCH VEHICLES

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JOURNAL OF guidance CONTROL AND DYNAMICS 1987年第1期10卷 53-60页

作者： BHAT, MS SHRIVASTAVA, SK Indian Institute of Science Bangalore India

A closed-loop steering logic based on an optimal Q-guidance is developed. The guidance system drives the satellite launch vehicle along a two- or three-dimensional trajectory for placing the payload into a specified circular orbit. The modified Q-guidance algorithm makes use of the optimal required velocity vector, which minimizes the total impulse needed for an equivalent two-impluse transfer from the present state to the final orbit. The required velocity vector is defined as velocity of the vehicle on the hypothetical transfer orbit immediately after the application of the first impulse. For this optimal transfer orbit, a simple and elegant expression for the Q-matrix is derived. A working principle for the guidance algorithm in terms of the major and minor cycles, and also for the generation of the steering command, is outlined.

关键词： Satellite Launch Vehicle Elliptical Orbit guidance algorithms Closed Loop guidance System Perigee Thrust Vectoring Orbital Elements Perturbation Analysis Earth

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