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

Identifier: 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

Authors: Miyatake, Katsumasa; Yoshikawa, Shoji; Shimoji, Haruhiko; Kawano, Hiroyuki; Suzuki, Takeshi; Kunii, Yoshinori; Hama, Kazumori; Oka, Noriaki

Abstract: We have developed a star sensor system with four heads as a prototype of a future small and low-priced satellite attitude controller. To reduce size and cost of the controller, we integrate attitude sensors into star sensors with medium resolution and medium sensitivity and adopt Commercial Off-The-Shelf (COTS) electrical parts for key parts such as CPU and CCD. Newly developed computer architecture is introduced for high reliability with COTS parts under the harsh space environment. In this paper, we will focus on the new star identification algorithm dedicated for the proposed four-head star sensor system and evaluate it with ground test and on-orbit check-out data.

Keywords: artificial satellites,attitude,estimation algorithms,test data adequacy

Identifier: 10.3182/20100906-5-JP-2022.00083

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

Authors: Miura, Masashi

Abstract: "Air Launch Rocket" is a promising launch system for small satellites. Air-launch rockets have potential to achieve low-cost and responsive missions. One of the biggest technical problems in air-launching is that the attitude of the separated rocket is very unstable and it is hard to predict its motion. The attitude motion and the angle at the ignition can stray far from the nominal. Therefore it is necessary to estimate the motion of the separated rocket and revise the trajectory program quickly to achieve reliable air-launching. Then I suggest taking approaches using the probability methods to these problems. In this research, particle filter was used for estimation and MCMC (Markov Chain Monte Carlo) method was used for optimization. These methods are new powerful techniques developed in mathematical statistics. This paper shows numerical simulation results of state estimation and trajectory optimization for air-launch rocket using these new methods.

Keywords: air-launch rocket,state estimation,parameter estimation,particle filter,trajectory optimization

Identifier: 10.3182/20100906-5-JP-2022.00026

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

Authors: Gabarrou, M.; Alazard, D.; Noll, D.

Abstract: We extend the concept of bundle methods to address non-convex and non-smooth optimization problems arising in the design of a feedback control law for the longitudinal flight control of a civil aircraft. Our novel approach has two advantages. It allows to handle the specific structure of the control law directly, and we can express control law specifications directly as band-limited frequency-domain mathematical programming constraints.

Keywords: optimization,structured controller,flight control,H∞,multi-objective

Identifier: 10.3182/20100906-5-JP-2022.00091

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

Authors: None

Abstract:

Keywords:

Identifier: 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

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

Identifier: 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

Authors: Panferov, Alexander I.; Nebylov, Alexander V.; Brodsky, Sergey A.

Abstract: The concept of a universal program for research into dynamic properties, calculation of comprehensive mathematical models, simulation of the flight motion and synthesis of smart control laws for different types of the flexible aerospace constructions (launchers and missiles) is considered. The basis of the program is the structure, which allows carrying out of the analysis of dynamic characteristics, simulation, and visual information representation. The software package is supplied with the library of program modules. These modules are designed on the base of mathematical models of separate vehicle elements and different physical effects, such as flexibility, sloshing, sluggishness of engines, local angle of attack values, etc. Selection of different sets of the mathematical models and program modules allows investigating different constructions for known and prospective vehicles. The interface of the program enables changing parameters of the vehicle in a wide range, to simulate flight at any trajectory and to output results of the analysis in a digital or graphical form. For synthesis of control laws, provides the usage of the smart control approach.

Keywords: mathematical model,smart control,flexible vehicle,simulation,bending,sloshing,local angle of attack,oscillations damping

Identifier: 10.3182/20100906-5-JP-2022.00027

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

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

Identifier: 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

Authors: Nakamura, Tsutomu

Abstract: As a case of asymmetric satellite with flexible appendages, it is known that there exists coupled vibration between rotational motion and translational motion. Therefore, when an asymmetric satellite rotates, elastic vibration excited by control input of rotational motion may be transmitted to translational motion. Reversely, suppression of such an excited vibration of translational motion would help realizing attitude maneuver with little vibration. From the reason mentioned above, in this paper, we propose translational motion control system using proof-mass actuators and co-located accelerometers for asymmetric satellite. Then, translational motion control law with consideration of actuator control loop was studied. The proposed translational motion control system was verified through numerical simulations.

Keywords: attitude control,flexible structure,actuators

Identifier: 10.3182/20100906-5-JP-2022.00039

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

Authors: Krɒger, Hans; Theil, Stephan

Abstract: Future exploration missions require advanced optical sensors for precise navigation and landing site evaluation. The Testbed for Robotic Optical Navigation (TRON) is a Hardware-in-the-Loop test environment, with the purpose to support the development of optical navigation technology, and to qualify breadboards to TRL 4, and to qualify flight models to TRL 5-6. In this paper the design and ongoing realization of TRON is discussed. The first application of TRON is to simulate relevant parts of the lunar landing. After illustrating the concept, the building blocks of the laboratory are explained in detail. These are the simulation of the scaled dynamics via a 7-DOF robot, the simulation of the optical environment via a black out system and a lighting system, and the simulation of the terrain geometry via scaled 3D terrain models. With modifications TRON can also provide relevant environments for Mars, asteroids and moons.

Keywords: hardware-in-the-loop test,optical navigation,safe and precise landing,spacecraft autonomy

Identifier: 10.3182/20100906-5-JP-2022.00046

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

Authors: Ahn, Jong-Sun; Park, Bong-Gyun; Tahk, Min-Jea

Abstract: In this paper, minimum-fuel, two-dimensional trajectory optimization from a parking orbit to the desired landing site is presented. The landing site is usually not considered when performing the trajectory optimization. However, to design the precise trajectories to land at the desired site, the landing site has to be considered as the terminal constraint. To convert the trajectory optimization problem into a parameter optimization problem, a pseudospcetral (PS) method is used, and CFSQP is used as a numerical solver. To check that the results obtained are good solutions, the feasibility check is performed.

Keywords: soft landing,trajectory optimization,legendre pseudospectral method,pseudospectral knotting method,sequential quadratic programming

Identifier: 10.3182/20100906-5-JP-2022.00031

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

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

Identifier: 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

Authors: Tsuda, Yuichi

Abstract: This paper derives a new batch sequential estimator utilizing "Unscented Transformation." It is a natural extension of the Unscented Batch Filter(UBF), and it inherits advantages of the UBF, such as being able to deal with nonlinear system equations directly, and providing a higher convergence capability starting from poorer initial guesses compared with conventional Bayesian filters. This paper applies the proposed filter to a relative orbit determination for a multiple spacecraft formation flight mission using relative range measurement information. A major challenge of this problem is that, since the available initial guess of estimation and the dynamic range of the relative orbital motion itself are of the same order, relatively higher convergence capability is required for the estimator to realize an accurate guess. The Bayesian filter, which is generally applied to this kind problem, is found to have an insufficient convergence performance. Numerical simulations show that the proposed "Unscented Batch Sequential Filter" provides a better convergence performance without taking longer computational time than other conventional filters.

Keywords: unscented transformation,batch sequential filter,orbital determination,formation flight

Identifier: 10.3182/20100906-5-JP-2022.00079

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

Authors: Nishida, Junichi; Matunaga, Saburo

Abstract: The Laboratory for Space Systems (LSS) at the Tokyo Institute of Technology has proposed a tether-controlled spinning solar sail. Three satellites at each corner of membrane are connected by tether and control the formation and attitude by controlling the lengths of the tethers. In this paper, the attitude maneuver by generating offset between center of mass (C.M.) and center of pressure (C.P.) is proposed and investigated by means of numerical simulation. Then the Virtual Structure method is applied to the control of attitude maneuver methodology. The results show that the Virtual Structure method improves the stability of the membrane and realizes sufficient attitude maneuver performance.

Keywords: solar sail,formation flight,virtual structure

Identifier: 10.3182/20100906-5-JP-2022.00061

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

Authors: Flandin, G.; Perrimon, N.; Polle, B.; Vidal, P.; Philippe, C.; Drai, R.

Abstract: As a passive light-weight system with a natural adaptation capacity to the environment, mimicking the human capacity for detecting hazards, vision-based navigation for space applications has been the subject of a sustained research effort in Europe for more than ten years. The "Navigation for Planetary Approach and Landing" (NPAL) ESA/Astrium Satellites project paved the way for a new European autonomous vision based navigation system called VisNAV, aiming at a proof of concept, with an elegant breadboard realization, preparing for the next step to flight demonstration. This paper presents the consolidated design, and HW/SW architecture of the real time implementation. It also addresses the validation strategy from simulation, making extensive use of virtual scene generation through a realistic modeling environment, to in-flight demonstration experiment, as well as the achievable performances.

Keywords: navigation,vision,space exploration,image processing

Identifier: 10.3182/20100906-5-JP-2022.00049

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

Authors: Hashimoto, Tatsuaki; Kubota, Takashi; Kawaguchi, Jun'ichiro; Uo, Masashi; Shirakawa, Kenichi; Kominato, Takashi; Morita, Hideo

Abstract: Hayabusa spacecraft performed approaching to and landing on the asteroid Itokawa from September to November in 2005 with sophisticated vision-based navigation and guidance. The spacecraft had some autonomous functions of station-keeping, descending, touching down and sampling. Since two of three reaction wheels for attitude control had malfunctions and the autonomous guidance did not work as designed, however, a ground-based landmark optical navigation system was developed. This paper presents the navigation, guidance and control system of Hayabusa spacecraft with some flight results.

Keywords: autonomous control,image processing,optical landmark navigation,teleoperation,MUSES-C,Itokawa,asteroid

Identifier: 10.3182/20100906-5-JP-2022.00045

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

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

Identifier: 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

Authors: Wang, Wenfei; Menon, Prathyush P.; Paulino, Nuno M. Gomes; Di Sotto, Emanuele; Salehi, Sohrab; Bates, Declan G.

Abstract: This paper describes the development and application of optimization-based worst-case analysis methods to the problem of verifying correct functionality of autonomous GNC systems in the terminal rendezvous phase. A number of different hybrid global/local optimisation algorithms based on evolutionary (Genetic Algorithms, Differential Evolution) and deterministic (DIviding RECTantles) approaches are employed to analyze the robustness of a GNC system in the presence of realistic levels of parametric uncertainty in the spacecraft simulation model with respect to a number of specified safety criteria. Parametric sensitivity analyses about the worst-case point in the uncertain parameter space provide additional important insights into the robustness of the autonomous GNC system with respect to the defined uncertainties. The study presents a rigorous comparison of the computational overheads associated with the different optimisation-based methods compared with traditional Monte-Carlo simulation approaches. The results of our study indicate potentially significant advantages for the proposed optimization-based approach when compared with traditional Monte Carlo simulations, in terms of both improved reliability and efficiency.

Keywords: hybrid optimization,worst-case analysis,autonomous rendezvous

Identifier: 10.3182/20100906-5-JP-2022.00055

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