Seid H. Pourtakdoust

@sharif.ir

Aerospace Engineering
Sharif University of Technology



                 

https://researchid.co/pourtakdoust

EDUCATION

1- PhD. in Aerospace Engineering , University of Kansas , 1989, USA.
2- M.S. in Aerospace Engineering, University of Kansas, 1984, USA.
3- B.S. in Aerospace Engineering, University of Kansas, 1982, USA.
4- B.S. in Civil Engineering, University of Kansas, 1982, USA.
5- FAA Private Pilot License, 1981, USA.

RESEARCH INTERESTS

• Aerospace Flight Dynamics and Control,
• Stochastic Optimal Control and Nonlinear Filtering,
• Spacecraft Orbit and Attitude determination and Control,
• Motion Planning and Trajectory Optimization,
• Aeroelastic/Statistical Analysis/Simulation of Dynamic Systems,
• Reliability Based and Multidisciplinary Design Optimization.

108

Scopus Publications

Scopus Publications

  • Composite learning-based prescribed-time control for time-varying nonlinear systems
    Mostafa Ezabadi, Seyyed Ali Emami, Seid H. Pourtakdoust, and Nima Assadian
    Elsevier BV

  • Global energy-participative prescribed performance control for spacecraft attitude control
    Mostafa Ezabadi, Seyyed Ali Emami, Seid H. Pourtakdoust, and Paolo Castaldi
    Elsevier BV

  • Development of a Hybrid Force Balance and Gimbal System for Virtual Flight Testing of Flapping-Wings
    Seid M.S. Mousavi and Seid H. Pourtakdoust
    Institute of Electrical and Electronics Engineers (IEEE)


  • Optimal spacecraft trajectory and formation control for asteroid deflection using pseudo-spectral methods and halo orbits
    Seid H. Pourtakdoust, M. H. Hajkarim, and A. H. Khodabaksh
    Springer Science and Business Media LLC

  • Prescribed-time fault-tolerant control of a spacecraft with time-varying moments of inertia and input constraint
    Mostafa Ezabadi, Seyyed Ali Emami, Seid H. Pourtakdoust, and Nima Assadian
    Elsevier BV

  • Model predictive control of a flared folding wingtip for gust load alleviation
    Mohammad Narimani, Hassan Haddadpour, and Seid H. Pourtakdoust
    Elsevier BV

  • A neural-metaheuristic kalman filter for moving microburst wind shear identification
    E. Mohajeri, Seid H. Pourtakdoust, and F. Pazooki
    Elsevier BV

  • An improved Multi-State Constraint Kalman Filter for Visual-Inertial Odometry
    M.R. Abdollahi, Seid H. Pourtakdoust, M.H. Yoosefian Nooshabadi, and H.N. Pishkenari
    Elsevier BV


  • Design and Development of a Miniaturized Roto-Translational Motion Platform for Micro Aerial Vehicle Identification
    Mohammad R. Abdollahi, Seid H. Pourtakdoust, and Seid M. S. Mousavi
    Institute of Electrical and Electronics Engineers (IEEE)

  • Reliability-based multidisciplinary design optimization of an aeroelastic unpowered guided aerial vehicle
    Seid H Pourtakdoust and Amir H Khodabakhsh
    SAGE Publications
    Most Aeronautical and Astronautical Systems (AAS) are inherently complex, multidisciplinary, nonlinear, and computationally intensive for design and analysis. Utilizing the Reliability-Based Multidisciplinary Design Optimization framework can address the multidisciplinary nature of these systems while accounting for inherent uncertainties. In this paper, an efficient methodology for Reliability-Based Multidisciplinary Design optimization of an aerial vehicle is developed. The computational burden of reliability assessment could make its integration within a Multidisciplinary Design Optimization cycle a formidable task. In this respect, a multilevel Multidisciplinary Design Optimization architecture is proposed in which the computational cost is reduced by considering the reliability analysis, as needed only for critical subsystems. To this end, a single-level Reliability-Based Multidisciplinary Design Optimization is derived using the Performance Measure Analysis and the Karush-Kuhn-Tucker condition. The work demonstrates the integration of this formulation into the proposed multilevel Reliability-Based Multidisciplinary Design Optimization architecture. The proposed design architecture is implemented for an aeroelastic Unpowered Guided Aerial Vehicle whose outcomes are compared with previous results obtained via a mono-level Uncertainty-Based Multidisciplinary Design Optimization architecture.

  • Radiation based satellite attitude and thermal parameters estimation considering conduction effect
    Marjan Moghanipour, Maryam Kiani, and Seid H. Pourtakdoust
    Elsevier BV

  • Advanced fault detection and diagnosis in spacecraft attitude control systems: Current state and challenges
    Seid H Pourtakdoust, Mohamad Fakhari Mehrjardi, Mohammad Hossein Hajkarim, and Forough Nasihati Gourabi
    SAGE Publications
    A review of advanced fault detection and diagnosis (FDD) techniques in attitude control systems (ACSs) of spacecraft is presented. In the first part of the paper, several types of ACS failure scenarios with their practical solutions are presented. Next, the existing approaches to FDD are considered and classified based on different criteria, including applications and design techniques. The literature of this part showed that to enhance ACS operational safety, predictability of failure of an ACS and/or of its components as well as reducing the possibility of failure occurrence is imperative. In addition, fast FDD of various kinds of failures is necessary to guarantee the required reliability of an ACS. The second part of this study highlights challenges involved with different FDD approaches, emphasizing their practical applicability. Current research gaps in FDD techniques such as insensitive residual signal, process monitoring methods, accurate plant model design, easy-to-use software development, FDD tuning process, dealing with noisy sensor measurements, time taken for fault management, the sensitivity of FDD system to faults, and FDD robustness are further elaborated on. Subsequently, the state-of-the-art FDD and its future needs are reflected on. The results of this study could direct spacecraft manufacturers and ACS providers to focus on future needs and improve ground testing for enhanced operational reliability and redundancy.

  • Model-based microburst identification using a hybridized extended Kalman filter with genetic algorithm
    E. Mohajeri, Seid H Pourtakdoust, and Farshad Pazooki
    SAGE Publications
    Microburst (MB) wind shear is one of the most important meteorological dangers threatening the aircraft (AC) safety and the life of passengers. Though there are some ground-based 3D Lidar systems to detect low-level MB wind shears to alert the pilots, there have been fewer scientific attempts to identify model-based MB parameters via AC onboard air and position data. The latter refers to the development and identification of an acceptable MB model upon which an automatic flight control (AFC) system can be designed to control the AC through wind shear microburst. In essence, accurate knowledge of MB model is an essential prerequisite for design and analysis of AFC systems that can safely fly the AC against microbursts, especially in crucial phases of flight such as takeoff and landing. The present study focuses on online estimation of MB parameters whose results pave the way for effective MB autopilot designs for safe flights through MB. The proposed task is accomplished via a model-based approach using the AC six degrees of freedom (6 DoF) equations of motion (EOM) integrated with the latest verified model of the MB utilizing the extended Kalman filter (EKF). In addition to a sensitivity analysis to determine the key MB model parameters, the performance of the estimation process is enhanced via a hybridization of the genetic algorithm (GA) with the EKF. The results are promising and indicate that the proposed scheme can identify the MB model parameters with sufficient accuracy needed for online applications with AFC design.

  • A modified unsteady-nonlinear aeroelastic model for flapping wings
    Seid H Pourtakdoust, Hadi Zare, and Arian Bighashdel
    SAGE Publications
    A novel integrated aeroelastic model of flapping wings (FWs) undergoing a prescribed rigid body motion is presented. In this respect, the FW nonlinear structural dynamics is enhanced via a newly proposed modification of implicit condensation and expansion (MICE) method that better considers the structural nonlinear effects. In addition, the unsteady aerodynamic model is also an extension of the widely utilized modified strip theory (MST) in which the flexibility effects are accounted for (MST-Flex). The integrated utility of the proposed generalized MICE and MST-Flex is demonstrated to be more realistic for elastic FW flight simulation applications. The prescribed rigid body motion is produced via a servo motor whose dynamics is also considered for the analysis. A special case study is also performed whose combined aeroelastic solution is determined and validated under a sinusoidal flapping motion. To this end, an experimental setup is designed and tested in order to validate the proposed integrated approach for aeroelastic modeling of FWs. There is very good agreement between the numerical and experimental results for elastic FW aerodynamics. It should be noted that the proposed integrated aeroelastic approach is readily adaptable to all kinds of elastic wings with arbitrary geometry and various combination of structural elements.

  • Improved Neural Adaptive Control for Nonlinear Oscillatory Dynamic of Flapping Wings
    Seid M. S. Mousavi and Seid H. Pourtakdoust
    American Institute of Aeronautics and Astronautics (AIAA)
    Modeling uncertainties and oscillatory dynamics are control challenges for flapping vehicles. Flapping-wing aerial vehicles are nonlinear time-varying oscillatory systems with flexible multibody dynamics. As such, accurate modeling of these complex systems considering unsteady aerodynamics is a formidable task. Though adaptive controllers can work well with uncertain approximate models, inherent oscillation of flapping systems can degrade their control performance and create undesired control actuations. This paper addresses improvements of neural adaptive dynamic inversion controller toward efficient performance for flapping flight via effective utility of actuator capacity. In this respect, first an assumptive model of a bird-mimetic flapping-wing is considered for simulation and analysis. It is shown that the usage of oscillatory feedback data produces additional error in trajectory tracking and unnecessary oscillatory control actuations. Subsequently, the control loop is modified by adding an adaptive notch filter for real-time estimation, tracking, and removal of dominant oscillatory modes from the feedback data and consequently from the controller output. As a result, the required control effort is effectively reduced and the controller performance is significantly improved. Simulations are provided to demonstrate the efficiency of the proposed scheme in presence of noise, variation of system frequency, disturbances, as well as delay in the control loop.


  • Satellite pose estimation using Earth radiation modeled by artificial neural networks
    Forough Nasihati Gourabi, Maryam Kiani, and Seid H. Pourtakdoust
    Elsevier BV



  • Reliability analysis of composite anisogrid lattice interstage structure
    N. Raouf, A. Davar, and Seid H. Pourtakdoust
    Informa UK Limited
    Application of composite lattice structures in aerospace application can bring about considerable weight savings, thus allowing for increased payload weight. This study is devoted to reliability an...

  • Wind-tolerant optimal closed loop controller design for a domestic atmospheric research airship
    Sasan Amani, Seid H. Pourtakdoust, and Farshad Pazooki
    Informa UK Limited

  • On-Line Orbit and Albedo Estimation Using a Strong Tracking Algorithm via Satellite Surface Temperature Data
    Forough Nasihati Gourabi, Maryam Kiani, and Seid H. Pourtakdoust
    Institute of Electrical and Electronics Engineers (IEEE)

  • Time-varying structural reliability assessment method: Application to fiber reinforced composites under repeated impact loading
    S. Saraygord Afshari, Seid H. Pourtakdoust, B.J. Crawford, R. Seethaler, and A.S. Milani
    Elsevier BV
    Abstract Reliability evaluations play a significant role in engineering applications to ensure the serviceability and safety of advanced structures such as those made of composites. Here, a dynamic reliability evaluation analysis based on the probability density evolution Method (PDEM) has been adapted to assess the reliability of composite structures under uncertainties within the material properties and the external loadings. A Back-Propagation Neural Network approach is employed to identify the system's nonlinear structural response, which is often the case under large deformations. To exemplify, a split Hopkinson pressure bar system was employed to mimic the mechanical behavior of a polypropylene/fiberglass woven composite plate structure under repeated high-strain rate impacts. Subsequently, the reliability prediction was performed offline via the system model and integration of uncertainties, as well as via an online SHM-based approach, and compared to full-scale (direct) experimental reliability values by repeating the impact tests on a population of samples. A material degradation factor has been introduced within the PDEM approach to account for surface damage induced during impacts. Results clearly showed the accuracy of the PDEM in predicting the remaining reliability of the composite after each impact. The method is generic and may be applied to other types of loadings and structures.

RECENT SCHOLAR PUBLICATIONS

    Publications

    1. Shakouri A., Kiani M., Pourtakdoust Seid H., “A New Shape -Based Multiple-Impulse Strategy for Coplanar Orbital Maneuvers”, Acta Astronautica, Volume 161, pp. 200-208, , Elsevier, 11th, May 2019.
    2. Nasihati Gourabi F., Kiani M., Pourtakdoust Seid H., “Autonomous temperature-based orbit estimation”, Aerospace Science and Technology, No. 86, pp. 671-682, , Elsevier, January 2019.
    3. Shakouri A., Kiani M., Pourtakdoust Seid H., “Covariance-Based Multiple-Impulse Rendezvous Design”, accepted for publication in IEEE Transactions on Aerospace and Electronic Systems, DOI 10.1109/, IEEE, November 2018.
    4. Raouf N., Pourtakdoust Seid H., S. Samiei Paghaleh, “Reliability and Failure analysis of jet vane TVC system”, Journal of Failure Analysis and Prevention, Volume 18, Issue 6,pp. 1635-1642,Springer, October 2018.
    5. Labibian A., Pourtakdoust Seid H., A. Alikhani, H. Fourati, “Development of a Radiation Based Heat Model for Satellite Attitude Determination”, Aerospace Science and Technology, No. 82-83, pp. 479-486, , Elsevier, September 27th , 2018.
    6. Afshari S. S. , Pourtakdoust Seid H., “Probability Density Evolution For Time-Varying Reliability Assessment Of Wing Structures”, Aviation Journal, ISSN: 1648-7788 /, Volume 22, Issue 2,pp. 52-61, , May 2018.
    7. Afshari S. S. , Pourtakdoust Seid H., “Utility of Probability Density Evolution Method for Experimental Reliability Based Active Vibration Control”, Structural Control & Health Monitoring, DOI: 10.1002/, Wiley, April 2018.
    8. Bighashdel A., Zare H., Pourtakdoust Seid H., “An Analytical Approach in Dynamic Calibration of Strain Gauge Balances for Aerodynamic Measurements”, IEEE Sensors Journal , DOI 10.1109/, March 2018.
    9. Zare H., Bighashdel A., Pourtakdoust Seid H., “Analytical Structural Behavior Of Elastic Flapping Wings Under The Actuator Effect”, The Aeronautical Journal ,Vol. 122, Issue 1254, pp. 1176-1198, Royal Aeronautical Society, U.K , August 2018.

    RESEARCH OUTPUTS (PATENTS, SOFTWARE, PUBLICATIONS, PRODUCTS)

    1- Implementation of satellite attitude determination process via nonlinear filtering of thermal data. Patent No. 90141, Intellectual Property Center, Tehran-Iran, October 2016.
    2- Development of a 3 DOF Dynamic Force/Moment Measurement System for Flapping Robots. Patent No. 94817, Intellectual Property Center, Tehran-Iran, January 2018.
    3- Advanced UAV aerodynamics, flight stability and control: Novel concepts, theory and applications. John Wiley & Sons Inc, December 2016.ISBN-10: 1118928687, ISBN-13: 978-1118928684.
    Chapter 17: Constrained Motion Planning and Trajectory Optimization for Unmanned Aerial Vehicles.
    Chapter 18: Autonomous Space Navigation Utilizing Nonlinear Filters with MEMS Technology.

    4- Recent Advances in Multisensor Attitude Estimation: Fundamental Concepts and Applications.
    CRC Press- Taylor and Francis Group, August 2016. ISBN 9781498745710
    Chapter 11: Recent Advances in Nonlinear Attitude Estimation Algorithms.