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An optimal trajectory design for the lunar vertical landing

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING 2016年第11期230卷 2077-2085页

作者： Leeghim, Henzeh Cho, Dong-Hyun Kim, Donghoon Chosun Univ Dept Aerosp Engn Gwangju South Korea KARI IT Convergence Technol Team Daejeon South Korea LG Elect Seoul South Korea

A research for designing the optimal lunar vertical landing trajectory to reduce the total energy or mass of propellant is addressed in this paper. Most of these problems can be divided into two phases: breaking and approach phase. The optimal landing trajectory in general does not consider the pitch-up motion so that the landing problem has been only solved in the breaking phase. For this reason, there are some attempts to find the optimal trajectory including the final vertical landing phase by including the equations of angular motion of the vehicle. However, the optimal solution using this approach depends on the scale factor of a cost function because the cost function consists of two different mechanical parameters such as the final mass and total control torque. The final control constraints are augmented for vertical lunar landing instead of the equations of angular motion. The obtained optimal trajectory has an additional positive effect of the image acquisition as well as the final vertical landing.

关键词： Optimal trajectory lunar vertical landing powered descent phase terminal guidance soft landing

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Impact Time and Angle Control Based on Constrained Optimal Solutions

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JOURNAL OF guidance CONTROL AND DYNAMICS 2016年第10期39卷 2445-U2451页

作者： Erer, Koray S. Tekin, Raziye Roketsan Missiles Inc TMS Guidance Syst Design Dept TR-06780 Ankara Turkey Aselsan Inc MGEO Nav & Guidance Syst Design Dept TR-06750 Ankara Turkey

A study proposes a technique which differs in that the problem of trajectory shaping is addressed by considering the full extent of the available resources in the form of look angle and acceleration constraints. This is made possible by the use of the nonlinear optimal control framework where the cost function is made up of an endpoint cost aiming to extremize the impact time or the impact angle against a stationary target. Based on the constrained optimal control solutions obtained in this way, practical guidance laws to control the impact time or the impact angle without violating the constraints are derived by realizing that optimality, which dictates the familiar PN guidance law with specific values of the navigation gain.

关键词： guidance Laws Sliding Mode Control Linear Quadratic Control Problem Autopilot Proportional Navigation terminal guidance Feedback Linearization guidance Algorithms MATLAB

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Adaptive Dynamic Surface guidance Law with Input Saturation Constraint and Autopilot Dynamics

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JOURNAL OF guidance CONTROL AND DYNAMICS 2016年第5期39卷 1152-1159页

作者： Zhou, Di Xu, Biao Harbin Inst Technol Dept Control Sci & Engn Mailbox 327 Harbin 150001 Peoples R China

A novel guidance law with input saturation constraint and autopilot dynamics is designed using block dynamic surface control. Different from conventional dynamic surface control, which employs n-1 low-pass filters to avoid the complexity arising from the explosion of terms, in the designing process of the guidance law, n low-pass filters have been used, where the extra auxiliary low-pass filter is able to compensate for the effect of input saturation. The guidance command is derived by regarding the target maneuvers as bounded disturbance inputs whose upper bound can be estimated online by an adaptation law. The guidance law is able to provide a high guidance precision on intercepting either a non-maneuvering target or a maneuvering target because it is robust against disturbances. Numerical simulations show that the proposed guidance law offers better performance than some other advanced guidance laws, which have not taken autopilot dynamics into account.

关键词： guidance System Autopilot terminal guidance Lyapunov Stability Theory Interceptor Missile Proportional Navigation Heading Angle Numerical Simulation Control Algorithm Interceptor guidance

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Fast Nonsingular terminal Sliding Mode to Attenuate the Chattering for Missile Interception with Finite Time Convergence

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IFAC-PapersOnLine 2016年第17期49卷 34-39页

作者： Lyu, Shi Zhu, Zheng H. Tang, Shuo Yan, Xiaodong School of Astronautics Northwestern Polytechnical University Xi'anShaanxi710072 China Department of Earth and Space Science and Engineering York University TorontoOntarioM3J 1P3 Canada

This paper proposed a new fast nonsingular terminal sliding mode to design terminal angle constraint guidance for intercepting maneuvering targets with attenuating the chattering of the command in the guidance law. A fast nonsingular terminal sliding mode (FNTSM) is established for dealing with the relationship between Line of sight (LOS) angle and the rate of LOS angle, the disturbance observer (DOB) is set up to calculate the compensation amount for counteracting the time-varying uncertainty produced by the design of guidance and targets’ maneuver. Combining with FNTSM and DOB, an adaptive law and a compensated parameter are adopted to ease the coupling relationship between the convergence rate of sliding variable and initial parameters design. Furthermore, the chattering amplitude can be reduced, even can be eliminated in some cases. Theoretical analysis and numerical simulations verify the effectiveness of the proposed method. © 2016

关键词： Missiles Numerical methods attenuating the chattering Coupling relationships Finite time convergence Missile interception Non singular terminal sliding modes Sliding modes terminal guidance Time varying uncertainties

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Sub-optimal Ground-Strike guidance based on Perturbation Method 13

Sub-optimal Ground-Strike Guidance based on Perturbation Met...

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IEEE International Conference on Mechatronics and Automation

作者： Meng, Jingwei Chen, Wanchun Yu, Wenbin Beihang Univ Sch Astronaut Beijing Peoples R China

ISBN: (纸本)9781509023967

An analytical guidance law based on perturbation method is proposed for ground strike mission. Letting the angle of attack (AOA) zero and considering the effects of gravity and drag force, the analytical expression of Zero Effort Miss (ZEM) is developed using perturbation method. In the development, the nonlinear flight dynamics is divided into the zeroth-order dynamics considering the major impact of gravity and drag force and the first-order dynamics compensating the remaining impact. To analytically solve the problem, an intermediate variable is innovatively introduced and some coefficients are fitted by Lagrange Polynomials. The simulation results show that the analytical ZEM expression has nearly the same high accuracy as the numerical integration, but the former has a much higher computation efficiency than the latter. Compared with the traditional guidance laws, the proposed guidance law can achieve a zero final AOA and requires less maneuvering load.

关键词： Regular perturbation method Zero Effort Miss terminal guidance analytic solution

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Research on Algorithm of counter Target lost for Maneuvering Reentry Vehicle using Infrared Imaging terminal guidance

Research on Algorithm of counter Target lost for Maneuvering...

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第八届IEEE信息与自动化国际会议(ICIC 2011)

作者： Tao Xu Xiao-feng Zhang Xiao-ping Zhu College of Astronautics Northwestern Polytechnical University Xi'an Shannxi710072China The UAV Research Institute Northwestern Polytechnical University Xi'an Shannxi710072China

ISBN: (纸本)9781457702686

Maneuvering Reentry Vehicle using Infrared(IR)imaging terminal guidance is vulnerable to interference which cause the seeker lost *** to this problem,first,this paper presents a new counter target lost Algorithm which combined extended state variable dimension passive location based on Extended Kalman Filter(EKF)and virtual guidance method to rebuild guidance *** the passive location accuracy of extended state variable dimension EKF and normal EKF algorithm is compared throughout simulation,at last,guidance accuracy of fore mentioned two algorithm and acceleration command memory algorithm are compared by circular error probable(CEP) simulation which based on six degree of freedom (6DoF) guidance and control *** results show the validity of the algorithm presented in this paper.

关键词： Extended Kalman Filter Extended State Variable Dimension Infrared Imaging guidance Maneuvering Reentry Vehicle Passive Location passive location terminal guidance Extended Kalman filters accuracy of guidance seekers guidance information algorithms RE-ENTRY VEHICLE six degrees of freedom Counters State variable

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NASA Technical Reports Server (Ntrs) 20120015510: a Framework for Probabilistic Evaluation of Interval Management Tolerance in the terminal Radar Control Area

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2016年

NASA Technical Reports Server (Ntrs) 20120015510: a Framework for Probabilistic Evaluation of Interval Management Tolerance in the terminal Radar Control Area by NASA Technical Reports Server (Ntrs); NASA Technical Re... 详细信息

关键词： (ntrs) 20120015510: air traffic control airspace control evaluation flight crews framework hagen, george e. hercencia-zapana, heber herencia-zapana, heber nasa technical reports server (ntrs) neogi, natasha safety factors spacing systems engineering terminal guidance workloads (psychophysiology)

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Dtic Adb024885: a Method for Estimating Target Acceleration and Its Use in a Missile guidance Law

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2016年

Dtic Adb024885: a Method for Estimating Target Acceleration and Its Use in a Missile guidance Law by Defense Technical Information Center; published by

关键词： algorithms terminal guidance acceleration adb024885: bednar, richard a. computerized simulation digital simulation dtic archive equations of motion estimates estimating flight maneuvers guidance guided missile trajectories inertial measurement units input output processing line of sight method miss distance missile naval weapons center china lake ca proportional navigation target angle velocity

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NASA Technical Reports Server (Ntrs) 20140010279: a User Guide for Smoothing Air Traffic Radar Data

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2016年

NASA Technical Reports Server (Ntrs) 20140010279: a User Guide for Smoothing Air Traffic Radar Data by NASA Technical Reports Server (Ntrs); NASA Technical Reports Server (Ntrs); published by

关键词： (ntrs) 20140010279: accuracy air traffic control algorithms applications programs (computers) bach, ralph e. data smoothing estimates ground speed ground tracks guide nasa technical reports server (ntrs) paielli, russell a. position errors radar radar approach control radar data real time operation reports surveillance terminal guidance

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NASA Technical Reports Server (Ntrs) 19810003557: a Mathematical Model of the Ch-53 Helicopter

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2016年

[Auto Generated] SYMBOLS................................. v SUMMARY................................. 1 INTRODUCTION .............................. 1 MATHEMATICAL MODEL . . . . Coordinate Systems . . . . General Model Description Fuselage Aerodynamics . . Rotor Models . . . . . . . Engine and Governor Model Control System . . . . . . Equations of Motion . . . MODELVALIDATION ............................ 19 Time History Comparisons . . . . . . . . . . . . . . . . . . . . . . 19 Pilot Comments . .

关键词： (ntrs) 19810003557: aerodynamic characteristics automatic flight control ch-53 flight simulation fuselages h-53 helicopter helicopter mathematical mathematical models nasa technical reports server (ntrs) phillips, j. d. real time operation rotor aerodynamics sturgeon, w. r. terminal guidance

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