Authors: None

Abstract:

Keywords:

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.90001

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: ---

Authors: Lumbar, Satja; Dolanc, Gregor; Vrecko, Darko; Strmcnik, Stanko; Matko, Drago

Abstract: In this paper we have designed and implemented a predictive automatic flight controller for an airplane that takes as input the estimated pose obtained from the visual data and provides control outputs for an inner-loop augmented aircraft. In order to make the predictive controller suitable for flight control, it had to be modified. The most important modification was the introduction of the short term reference trajectories, linking the time-based and the position-based control strategy. Furthermore a controller switching mechanism was introduced to enable the aircraft to fly at different flight conditions. The parameters of the controller have been derived by experimental optimization. The tests have shown good overall tracking and disturbance rejection properties; the aircraft is able to perform various maneuvers and the touchdown in all the tested weather (wind, turbulence) conditions.

Keywords: model predictive control,automatic landing,flight control,visual servoing

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00002

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 1-6

Authors: Sato, Masayuki

Abstract: This paper addresses the design problem of flight controllers for suppressing aircraft motions due to wind gust, i.e. Gust Alleviation (GA) problem. As LIght Detection And Ranging (LIDAR) system which can detect even clear air turbulences ahead of aircraft has recently been developed, flight controllers which exploit the prior gust information obtained using LIDAR systems have been desired. On this issue, we have already proposed flight controllers using Model Predictive Control (MPC) scheme; however, all the state variables in the aircraft motion model are assumed to be exactly available. In this note, we extend our previous result to more realistic situations in which there exist measurement errors in both the current state variables of aircraft motions and the prior gust data under some plant uncertainties. Using our proposed GA flight controllers, we show several examples which examine the feasibility of GA problem.

Keywords: flight control,gust alleviation,uncertain plant,measurement error

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00003

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 7-12

Authors: Kondo, Hiroyuki; Ochi, Yoshimasa

Abstract: This paper proposes a design method of a model-following PID controller which is an extension of the design method of a proportional and derivative preceded integral (I-PD) controller based on integral-type optimal servomechanism (IOS) and the ν-gap metric. This original method is simple, compared with conventional ones and consists of two stages. First, a given high-order plant is reduced to a second-order system in terms of the ν-gap metric, and next, the state feedback gains of the IOS for the second-order system are computed to obtain PID control gains. The I-PD controller is extended to a model-following type by adding a reference model and a feedforward compensator for a desirable output response. This design method has been applied to Mini Aerial Vehicle (MAV) flight controllers to demonstrate that the proposed design method has sufficient effectiveness.

Keywords: integral-type optimal servomechanism,ν-gap metric,I-PD control,model-following control,SISO,PID control

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00004

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 13-18

Authors: Westermayer, C.; Schirrer, A.; Hemedi, M.; Kozek, M.

Abstract: In this paper a linear parameter-varying (LPV) controller design approach is applied to the longitudinal dynamics of a large blended wing body aircraft. The method is based on parameter-dependent Lyapunov functions utilizing the information given by bounds for the maximum parameter rate of variation. The entire parameter space is approximated by a set of linearized models in trimmed operating points which leads to a finite-dimensional convex optimization problem. Typical design goals for flexible aircraft control such as handling qualities, loads and vibration reduction were considered with the Mach number as scheduling parameter. The obtained LPV controller is extensively tested, and the obtained results demonstrate the high potential of the methodology for flexible aircraft control.

Keywords: linear parameter-varying (LPV) systems,robust control,flexible aircraft control,gain scheduling

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00005

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 19-24

Authors: Borisov, V. G.; Nachinkina, G. N.; Pavlov, B. V.; Shevchenko, A. M.

Abstract: The purpose of this paper is elaboration of uniform technology for carrying out of all stages of flight control system designing. Proprietary components of this technology are the energy approach to flight control and the special version of modal synthesis. The classical structure of an energy control system has been modified by insertion of a correction loop. The version of modal control has been developed for calculation of optimum regulator parameters in the whole flight envelope. Modal control at an incomplete control vector is formed as the weighed sum of controls. Weighting coefficients reflect a degree of influence of any control on each controlled variable. All developments are integrated into the computerized research stands. Modeling of the maneuverable aircraft with the synthesized flight control system has shown excellent characteristics in whole operational area.

Keywords: flight control,energy approach,modal method,handling qualities,modeling

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00006

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 25-30

Authors: Carrillo, Luis Rodolfo Garcia; Rondon, Eduardo; Sanchez, Anand; Dzul, Alejandro; Lozano, Rogelio

Abstract: We present a vision system that deals with the problem of local estimation of the position and velocity of a UAV quad-rotor indoor. Our approach is based in the estimation of homographies from a visual landmark. Stabilizing the UAV locally, real time experiments demonstrate the effectiveness of our method.

Keywords: aerial robotics,localization,computer vision,sensor fusion,visual tracking

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00007

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 31-36

Authors: Suzuki, Satoshi; Nonami, Kenzo

Abstract: In this paper, the development of a quaternion-based navigation and autonomous control system for a small single-rotor helicopter is described. First, a quaternion-based small attitude sensor and an INS-GPS navigation system are constructed. The performance of the small attitude sensor is shown via a comparison with a commercial attitude sensor that is precise and heavy. A nonlinear attitude controller for a single-rotor helicopter is designed by using quaternion feedback, and a guidance controller is constructed with the attitude control system as an inner loop. Finally, a flight experiment is performed with a small electric helicopter, and the results indicate the effectiveness of the proposed navigation and control system.

Keywords: autonomous control,quaternion feedback,helicopter control,sensor systems,nonlinear control,inertial navigation,kalman filters

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00008

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 37-42

Authors: Achour, Walid; Piet-Lahanier, Hélène; Siguerdidjane, Houria

Abstract: This study addresses the problem of enhancing the safety of the helicopter flight in presence of atmospheric perturbation. The proposed approach is based on the coupled design of a wind estimator and a guidance law. A model of the UAV is first described, including potential effects of wind. A short description of the proposed strategy is then detailed. The design of a navigation law taking wind into account is after that addressed. The guidance and control laws are afterward described. Identification of the state vector representing the UAV is performed using a set estimation technique in order to characterize the variation boundaries of the flight induced by the presence of wind. Simulation results are presented to illustrate the obtained results.

Keywords: guidance law design,bounding approach state estimation,atmospheric turbulence estimation

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00009

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 43-48

Authors: Guerreiro, B. J.; Silvestre, C.; Cunha, R.

Abstract: This paper proposes a laser-based trajectory tracking control methodology for rotorcraft operation in environments where absolute position measurements are unavailable or unreliable. Laser-based nonlinear kinematics are formulated in three-dimensions space, and a trajectory-dependent error space is defined to express the dynamic model of the vehicle and the laser-based kinematics. A linear parameter varying (LPV) representation with piecewise affine dependence on the parameters is introduced to model the error dynamics over a set of predefined operating regions. The synthesis problem is stated as a continuous-time H2 control problem, solved using linear matrix inequalities (LMIs) and implemented within the scope of gain-scheduling control theory. The effectiveness of the proposed controller is assessed in simulation using the full nonlinear model of a small-scale helicopter.

Keywords: laser-based control,autonomous vehicles,helicopter control,disturbance rejection

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00010

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 49-54

Authors: Yamasaki, Takeshi; Balakrishnan, S. N.

Abstract: This study focuses on integrated guidance and control for a chasing UAV against a maneuvering target. A sliding mode approach is selected to develop the integrated guidance and control using a full model of nonlinear, rigid body, 6 Degree-Of-Freedom equations of motion including nonlinear aerodynamics for the target-following capability and maneuverability enhancement against uncertain target maneuvers. Intermediate control variables for the integrated guidance and control system are carefully selected and approximated time derivatives of a sliding surface are applied such that a sliding surface structure is simple and sufficient to propagate the actuator input to the sliding surface in order to make the design synthesis simple. The potential of the proposed method is demonstrated and discussed with some simulation results, comparing its performance with a system where the guidance law and the controller are designed independently.

Keywords: sliding mode,integrated guidance and control,pure pursuit guidance,UAV,chase

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00011

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 57-62

Authors: Kaynak, Okyay

Abstract: This paper is concerned with final approach and touch-down periods of UAVs and proposes a fuzzy logic based autonomous landing system controller. Three fuzzy logic modules are developed under the main landing system for the control of the horizontal and the vertical positions of the aircraft against the runway under a TACAN (Tactical Air Navigation) approach. The performance of the fuzzy logic based controllers is evaluated using MATLAB's standard configuration and the Aerosim Aeronautical Simulation Block Set which provides a complete set of tools for rapid development of 6 degree-offreedom nonlinear generic manned/unmanned aerial vehicle models. Additionally, FlightGear Flight Simulator and GMS aircraft instruments are deployed in order to get visual outputs that aid the designer in evaluating the performance and the potential of the controllers. The simulated test flights on an Aerosonde indicate the capability of the approach in achieving the desired performance despite the simple design procedure.

Keywords: autonomous landing system for UAVs,fuzzy logic controller

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00012

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 63-68

Authors: Watanabe, Yoko; Fabiani, Patrick

Abstract: This paper addresses a vision-based air-to-ground target tracking problem of an unmanned aerial vehicle. A navigation filter is designed based on an extended Kalman filter to simultaneosly localize a moving target and an own-ship UAV by fusing vision-based measurements and other onboard sensors. Particularly, it is suggested to utilize sparse optical flow estimation to aid the inertial navigation when GPS signals are inaccessible. A guidance law aims at making a UAV pursue a target's horizontal position while vertically avoiding obstacles whose global positions are known. In order to achieve this guidance purpose, high accuracy in both the self and the target localizations is required. Since the vision-based navigation performance significantly depends on the camera motion relative to objects of interest, this paper proposes a stochastically optimized guidance law which attains target tracking and obstacle avoidance while maximizing the navigation accuracy. For real-time applicability, the one-stepahead optimization technique is applied to derive a suboptimal guidance solution. Simulation and flight test results are presented to demonstrate the advantage of using the suggested optimal guidance policy instead of a nominal linear guidance.

Keywords: unmanned aerial vehicle (UAV),vision-based navigation,optimal guidance,extended Kalman filter,autonomous flight system

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00013

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 69-74

Authors: Medagoda, Eran D. B.

Abstract: This paper examines the closed-loop stability characteristics of the Synthetic Waypoint Guidance (SWG) algorithm. Following the development of the underlying guidance laws, an analysis into the effect of guidance parameter variations on aircraft performance was conducted. The dynamics of the synthetic waypoint was integrated with the dynamics of the aircraft to develop an augmented state space model incorporating aircraft and guidance states. A linear stability analysis was performed and showed that guidance parameter variations had a significant effect on the overall stability of the system with the introduction of a new guidance mode. The properties of the guidance mode and its influence on the state response of the aircraft are illustrated by simulation.

Keywords: guidance systems,dynamic stability,dynamic behaviour,flight control

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00014

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 75-80

Authors: Voelker, A.; Dördelmann, M.; Kouramas, K.; Pistikopoulos, E. N.; Shanmugavel, M.; Tsourdos, A.; White, B. A.; Zbikowski, R.

Abstract: In this paper we present an integrated framework for the control of unmanned aerial vehicles (UAV) that consists of three hierarchical layers: 1) the path-planner, 2) the intermediate guidance law, and 3) the autopilot. Our objective is to investigate and demonstrate how the three different layers for the control of an unmanned aerial vehicle can be integrated into one hierarchical control structure and how these layers interact with each other. We employ Dubins path on the path-planner level, a P-controller for the guidance and investigate for the autopilot the use and implementation of advanced model-based control methods, here Model Predictive Control (MPC). The proposed control framework is demonstrated for a small fixed-wing UAV, the Aerosonde.

Keywords: unmanned aerial vehicles,model predictive control,autopilot,guidance,path planning,cooperation,Dubins path

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00015

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 81-86

Authors: Regina, Niki; Zanzi, Matteo

Abstract: This paper describes a 2D target loitering problem addressed to UAV applications. While target tracking and loitering problems have been studied for long time in literature, here a new and particular type of loitering trajectory around the target (fix o moving) is considered: a Lemniscate-type trajectory. The proposed way to track this particular curve derives from the Lyapunov Vector Field theory, a recently developed methodology that has been used and tested for simpler cases before, such as circles or basin-like trajectory tracking. A stability analysis and preliminary simulation results are given in this paper.

Keywords: Lyapunov vector field,UAV,guidance,lemniscate,target tracking,trajectory

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00016

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 87-92

Authors: Niccolini, Marta; Innocenti, Mario; Pollini, Lorenzo

Abstract: The paper presents a preliminary application of a new methodology to the problem of task assignment, for a large number of unmanned vehicles operating in a cooperative and coordinated fashion. The proposed methodology uses the general concept of Descriptor Functions, to establish a relationship between tasks, their priority, and agents or groups of agents forming a large interconnected system. A bio-inspired model of the division of labor in colonies of social agents is used to derive a set of rules at the individual level that gives rise to agent specialization. Preliminary simulations show interesting results, and the potential of the proposed technique.

Keywords: task assignment,UAV,swarm,networked agents,cooperative control

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00017

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 93-98

Authors: Shah, M. A.; Tsourdos, A.; James, D.; Aouf, N.

Abstract: This paper deals with the problem of defining a frame along the curve at the point of inflection such that the intrinsic properties of the curve are reflected in the defined frame and the frame can be used as a local frame of the body moving on the curve. It is natural to use the Frenet Serret Frames of the curve whenever we need to define a local reference frame along the curve, but the problem with Frenet Serret Frame is that, it is not defined at the point of inflection. The problem gets serious if the point of inflection drags along for some times. i.e. if the direction of the unit tangent is not changing for some time. In such cases if we want to use the Frenet frame of the curve as the local reference frame of a body (a local frame for some sensor e.g camera reference frame) moving along the same curve, it will suffer from the problem of indeterminacy at the point of inflection. Therefore we have to define a frame which exists at all the points of the curve. This defined frame must retain the intrinsic properties of the curve. The Rotation Minimizing Frame is proposed as a solution to the problem in this paper.

Keywords: pythagorean hodograph curves,point of inflection,Frenet frame,rotation minimizing frame,rotation matrix,intrinsic properties of curve

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00018

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 99-105

Authors: Nebylov, Alexander V.

Abstract: Wing-in-Ground Effect vehicle (WIG-craft) or Ekranoplane as it is called in Russia could take the significant part of the projected air traffic growth. After the seventies-eighties when the first generation of heavy Ekranoplanes was developed under the order of Russian Navy, the numerous changes appeared in the concepts of WIG-craft design and application. The modern means of motion control automation has become applicable. The aim of such technologies development is to improve the operational performance of the vehicles of advanced design. The primary sensors and measuring systems for operation at low altitudes were designed to increase the accuracy of control and to provide the fault-tolerance properties. Methods of stability provision and solving other problems of WIG flight by means of automatic control are analyzed. The criteria and methods for control systems improving for large ekranoplanes are given. The experience and achievements in this field of high technology are described.

Keywords: flight control,low altitude flight,sea waves,sensors integration,control law design

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00019

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 106-111

Authors: Nebylov, Alexander; Sharan, Sukrit; Arifuddin, Farid

Abstract: In the paper a scientific and technological analysis has been presented for the viability, advantages and highly successful prospects for the realization of an Autonomous and Intelligent Wing-In-Ground Effect Vehicle mainly for Coastal Patrolling and Search & Rescue Operations. The necessary Autopilots and Automatic Control Systems have been proposed and described especially considering such vehicles for their various modes of motion. Also has been described the special Phase-Radioaltimeter created in IIAAT for such purposes and missions. Some alternate sources of power and energy for such systems for round the clock sea surveillance have also been suggested for such highly promising and highly advanced next generation intellectual amphibious vehicles.

Keywords: autonomous & intelligent vehicles,automatic control,integrated navigation systems and data fusion

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00020

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 112-117

Authors: Yamasaki, Takeshi; Balakrishnan, S. N.

Abstract: This paper focuses on missile guidance methods for a defense missile trying to protect a cooperative aircraft from guided munitions which have the same thrust and maneuvering capabilities as that of the defense missile. A novel guidance law for the missile-to-missile intercept is developed using two lines of sight: one line-of-sight is constructed from the protected aircraft to the threat missile, and the other is from the protecting missile to the threat missile. Potential of the guidance law is demonstrated and discussed with some simulation results; performance comparison with a conventional guidance law is also presented.

Keywords: aerial defense,missile guidance,missile VS missile,LOS,CLOS,PN

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00021

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 118-123

Authors: Shin, Hyo-Sang; Le Ménec, Stéphane; Tsourdos, Antonios; Markham, Keith; White, Brian; Zbikowski, Rafal

Abstract: In this paper, we proposed a cooperative guidance strategy to consider many on many engagements for maritime area air defence. The main idea is that a cooperative missile guidance law can defend the area as long as it guarantees that the keep out zone is always within the defended area defined by Earliest Intercept Geometry (EIG) or a No Escape Zone (NEZ). Since one of the most important issues for the cooperative guidance is to allocate attacking missiles to defending missiles, we focused on developing an allocation plan. The cooperative guidance algorithm proposed in this paper consists of two main parts: a pre allocation algorithm designed by using the EIG guidance law and Differential Geometry Guidance Law (DGGL); in flight target allocation proposed based on the differential game theory. Whilst the pre allocation plan is activated during the mid course and deactivated after the mid course, the in flight target allocation is activated during all in flight phases to refine the initial allocation. Mathematical analysis for the allocation algorithms is carried out to check their characteristics and the performance of the proposed strategy is verified by some numerical examples.

Keywords: cooperative guidance,pre allocation,target allocation,NEZ,DGL/1,EIG,DGGL

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00022

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 124-129

Authors: Tatiya, Mayuri; Bhatia, Namrata; Padhi, Radhakant

Abstract: A computationally efficient suboptimal Model Predictive Spread Acceleration Guidance (MPSAG) law is proposed for terminal phase of air defense missiles with impact angle constraint. This nonlinear guidance law provides closed form solution of lateral acceleration (latax) update. The latax demand is purposefully spread over the available time-to go (tgo), which is done by parameterizing it with respect to tgo as a straight line and parabola. It enables guidance law to avoid the latax saturation limits. A tgo adjustment mechanism is also proposed in this paper for enhancing the effectiveness of the proposed guidance law. Simulation studies have also been carried out incorporating autopilot lags in the loop to have a realistic evaluation of the proposed guidance design. Algorithm is tried to make online using iteration unfolding.

Keywords: model predictive spread acceleration guidance,MPSAG,model predictive static programming,MPSP,impact angle,air defence

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00023

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 130-135

Authors: Lee, Chang-Hun; Kim, Tae-Hun; Tahk, Min-Jea

Abstract: This paper provides the target observability analysis of advanced guidance laws such as the impact angle control guidance law and the time-to-go polynomial guidance law. The target observability condition for a constant-velocity target, which is given by the function of line-of-sight (LOS) angle, is considered. To analyze the target observability under advanced guidance laws, the closed-form solution of LOS angle produced by these laws is firstly derived and substituted into the predetermined observability condition. The analysis result shows that the target observability of advanced guidance laws is depending on the choice of guidance gain and the initial engagement geometry. Finally, this mathematical analysis result is evaluated and demonstrated by number of simulation.

Keywords: target observability,bearing-only measurement,advanced guidance law

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00024

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 136-141

Authors: Halbe, O.; Mathavaraj, S.; Sarmah, P.; Chawla, C.; Chethana, P.; Padhi, R.

Abstract: A nonlinear optimal guidance and control scheme for the atmospheric reentry of an RLV using pitch plane maneuver is presented. The guidance law generates an angle of attack control command that satisfies the terminal constraints (considered as hard constraints) and the path constraints (considered as soft minimizable constraints). The guidance update process is done rapidly and in closed form using model predictive static programming (MPSP), a technique that provides a finite time nonlinear suboptimal guidance law. A nonlinear optimal controller for the reaction control system (RCS) and aerodynamic controls has been designed using dynamic inversion (DI) and optimal dynamic inversion (ODI) respectively. A fusion logic for the RCS and aerodynamic control combination provides the total control action required. After each guidance cycle, the guidance command updates the trajectory using the actual states obtained from the control design. The control design is found to track the guidance commands well for perturbations in the initial reentry conditions.

Keywords: reentry guidance,optimal guidance,dynamic inversion,reusable launch vehicle

Digital Object Identifier (DOI): 10.3182/20100906-5-JP-2022.00025

Conference: 18th IFAC Symposium on Automatic Control in Aerospace (2010)

Location: Nara-ken Shinkokaido, Japan

Start Date: Mon Sep 06 2010 - End Date: Fri Sep 10 2010

Page Numbers: 142-147