ORIGINAL_ARTICLE
Dynamic Terminal Sliding Mode Control for an Aerospace Launch Vehicle
Tracking guidance commands for a time-varying aerospace launch vehicle during the atmospheric flight is considered in this paper. Hence, the dynamic terminal sliding mode control law is constructed for this purpose and dynamic sliding mode control is utilized. The terminal sliding manifold causes the dynamic sliding mode to converge asymptotically to zero in finite-time. The actuator and rate gyro dynamics are included in the model of launch vehicle. Dynamic sliding mode control accommodates unmatched disturbances, while the terminal sliding mode control is used to accelerate the system to reach the dynamic sliding manifold. Finally, the effectiveness of the proposed control is demonstrated in the presence of unmatched disturbances and is compared with the dynamic sliding mode.
https://jsst.ias.ir/article_15234_1e91ad3fbd9a6588e4d839a5b212614e.pdf
2016-01-01
1
7
Terminal sliding mode
Dynamic sliding mode
Unmatched disturbance
Finite-time convergence
علیرضا
علیخانی
aalikhani@ari.ac.ir
1
پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران
LEAD_AUTHOR
سیدعلی اکبر
کسائیان
2
پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران
AUTHOR
[1] Bahrami, M., Roshanian, J. and Ebrahimi, B., “Aerospace Launch Vehicle Robust Control: A Variable Structure Approach,” Institute Superior Técnico, 7th Portuguese Conference on Automatic Control, Lisboa, Portugal, 2006 .
1
[2] Shtessel, Y. B. and Shkolnikov, I. A., “Aeronautical and Space Vehicle Control in Dynamic Sliding Manifolds,” International Journal of Control, Vol. 76, No. 9-10, 2003, pp. 1000-1017(18).
2
[3] Mezghani, N., Romdhane, B. and Damak, T. “Terminal Sliding Mode Feedback Linearization Control,” International Journal of Sciences and Techniques of Automatic Control & Computer Engineering, Vol. 4, No. 1, 2010, pp. 1174-1178.
3
[4] Sira-Ramirez, H. “Dynamic Second-Order Sliding Mode Control of Hovercraft Vessel,” IEEE Transaction on Control Systems Technology, Vol. 10, No. 6, NOV. 2002, pp. 860-865.
4
[5] Shuai, G. and Jin-bao, H., “Adaptive Dynamic Terminal Sliding Mode Control Method,” IEEE, Second International Conference on Intelligent Computation Technology and Automation, 2009.
5
[6] Krupp, D. R., Shkolnikov, I. A. and Shtessel, Y. B., “High Order Sliding Modes in Dynamic Sliding Manifolds: SMC Design with Uncertain Actuator,” Proceeding of the American Control Conference, Chicago, Illinois, Jun. 2000.
6
[7] Ansarifar, G.R., Talebi, H.A. and Davilu, H., “An Adaptive-Dynamic Sliding Mode Controller for Non-minimum Phase Systems,” Commun Nonlinear Sci Numer Simulat, Vol. 17, Issue 1, 2012, pp. 414-425.
7
[8] Kim, J., Ryu, J., Baek, J., Kim, K. and Kim, S., “Terminal Sliding Mode Control in Reaching and Sliding Dynamics with Input Limit,” International Conference on Control, Automation and Systems 2010, Kintex, Gyeonggi-do, Korea, 2010.
8
[9] Blakelock, J.H., Automatic Control of Aircraft and Missiles, Second Edition, A Wiley-Interscience Publication, John Wiley & Sons, 1991.
9
[10] Hong, Y., Yang, G., Cheng, D. and Spurgeon, S. “A New Approach to Terminal Sliding Mode Control Design,” Asian Journal of Control, Vol. 7, No. 2, 2005, pp. 177-181.
10
[11] Bahrami, M., Roshanian, J. and Ebrahimi, B. “Robust Integral Sliding-Mode Control of an Aerospace Launch Vehicle,” JAST, Vol. 3, No. 3, 2006, pp 143-149.
11
[12] Slotine, J. J. E. and Li, W., Applied Nonlinear Control, Prentice-Hall, 1991.
12
[13] Roshanian, J., Ebrahimi, B., Esfahanian, M. and Bahrami, M., “Dynamic Sliding Mode Autopilot for an Aerospace Launch Vehicle,” The 7th Iranian Aerospace Society Conference, Sharif University of Technology, 2008.
13
[14] Bahrami, M., Ebrahimi, B. and Ansarifar, G.R. “Sliding Mode Observer and Control Design with Adaptive Parameter Estimation for a Supersonic Flight Vehicle,” International Journal of Aerospace Engineering, Vol. 2010, Article ID 474537, 2010, p. 9.
14
[15] Shuai, G. and Jin-Bao, H., “Adaptive Dynamic Terminal Sliding Mode Control Method”, IEEE, 2th International Conference on Intelligent Computation Technology and Automation, 2009.
15
[16] Wang, Y., Feng, Y. and Yu, X., “High-order Nonsingular Terminal Sliding Mode Control of Uncertain Multivariable Systems,” The 33rd Annual Conference of the IEEE Electronics Society (IECON), Taipei, Taiwan, Nov. 2007.
16
[17] Shtessel, Y.B., “Nonlinear Output Tracking in Conventional and Dynamic Sliding Manifolds,” IEEE Transactions On Automatic Control, Vol. 42, No. 9, 1997, pp. 1282-1286.
17
ORIGINAL_ARTICLE
A New Backstepping Sliding Mode Guidance Law Considering Control Loop Dynamics
In this paper, a new procedure for designing the guidance law considering the control loop dynamics is proposed. The nonlinear guidance loop entailing a first order lag as the control loop dynamics is formulated. A new finite time and smooth backstepping sliding mode control scheme is used to guarantee the finite time convergence of relative lateral velocity. Also in the proposed algorithm the chattering is removed and a smooth control signal is produced. Moreover, the target maneuver is considered as an unmatched uncertainty. Then a robust guidance law is designed without requiring the precise measurement or estimation of target acceleration. Simulation results show that the proposed algorithm has better performance as compared to the proportional navigation, augmented PN and the other sliding mode guidance law.
https://jsst.ias.ir/article_15236_3df76c834ee785c1f62dbc47f0af52c0.pdf
2016-01-01
9
17
Guidance law
Control loop dynamics
Sliding mode control
Chattering
وحید
بهنام گل
vahidbehnamgol@yahoo.com
1
دانشکدة کنترل، دانشگاه صنعتی مالک اشتر، تهران، ایران
LEAD_AUTHOR
احمدرضا
ولی
ar.vali@aut.ac.ir
2
دانشکدة کنترل، دانشگاه صنعتی مالک اشتر، تهران، ایران
AUTHOR
علی
محمدی
ali_mohammadi@yahoo.com
3
دانشکدة کنترل، دانشگاه صنعتی مالک اشتر، تهران، ایران
AUTHOR
[1] Zarchan, P., Tactical and Strategic Missile Guidance, AIAA Series, Vol. 199, 2002, pp. 143–152.
1
[2] Siouris, G. M., Missile Guidance and Control Systems, Springer, 2005, pp. 194–228.
2
[3] Moon, J., Kim, K., and Kim, Y., “Design of Missile Guidance Law via Variable Structure Control,” Journal of Guidance, Control, and Dynamics, Vol. 24, No. 4, 2001, pp. 659 - 664.
3
[4] Zhou, D., Mu, C., and Xu, W., “Adaptive Sliding-Mode Guidance of a Homing Missile,” Journal of Guidance, Control, and Dynamics, Vol. 22, No. 4, 1999, pp. 589-594.
4
[5] Babu, K. R., Sarma, I. G., and Swmy, K. N., "Switched Bias Proportional Navigation for Homing Guidance Against Highly Maneuvering Target," Journal of Guidance, Contro1, and Dynamics, Vol. 17, No. 6, 1994, pp. 1357-1363..
5
[6] Innocenti, M., “Nonlinear guidance techniques for agile missiles,” Control Engineering Practice 9, 2001, pp. 1131–1144
6
[7] Lum, K. Y., Xu, J. X., Abidi, K., and Xu, J., “Sliding Mode Guidance Law for Delayed LOS Rate Measurement,” AIAA Guidance, Navigation, and Control Conference and Exhibit, Honolulu, Hawaii, 18 - 21 August, 2008.
7
[8] Zhanxia, Z., Feng, X., Huai, G., “The Application of Sliding Mode Control on Terminal Guidance of Interceptors,” IEEE, Third International Conference on Intelligent Networks and Intelligent Systems, 2010
8
[9] Harl, N., and Balakrishnan, S. N., “Impact Time and Angle Guidance with Sliding Mode Control,” IEEE Transactions on Control Systems Technology, 2011
9
[10] Shtessel, Y.B., Shkolnikov, I.A., and Levant, A., “Smooth Second-Order Sliding Modes: Missile Guidance Application,” Automatica, Vol. 43, Issue 8, 2007, pp. 1470 – 1476.
10
[11] Der, R.T, “A Sliding Mode Nonlinear Guidance with Navigation Loop Dynamics of Homing Missiles,” AIAA Guidance, Navigation and Control Conference, Toronto, Ontario Canada, 2010.
11
[12] Dongk young, C. and JIN, Ch., “Adaptive Nonlinear Guidance Law Considering Control Loop Dynamics,” IEEE Transactions on Aerospace and Electronics Systems, Vol. 39, No. 4, 2003, pp. 1134-1143.
12
[13] Khalil, H. K., Nonlinear Systems, Prentice-Hall, Upper Saddle River, NJ, 1996, pp. 601-617.
13
[14] Slotine, J. J. E. and Li, W., Applied Nonlinear Control, Prentice-Hall, Upper Saddle River, NJ, 1991, pp. 276-309.
14
[15] Fridman, L., Moreno, J. and Iriarte, R. Sliding Modes after the First Decade of the 21st Century, Springer, 2011.
15
[16] Min-Shin Ch., Yean-Ren H. and Tomizuka, M., “A State-Dependent Boundary Layer Design for Sliding Mode Control,” IEEE Transaction On Automatic Control, Vol. 47, No. 10, 2002, pp. 1677-1681.
16
[17] Kim, K. J., Park, J. B. and Choi, Y. H., “Chattering Free Sliding Mode Control,” SICE-ICASE International Joint Conference 2006, Busan, Korea,2006, pp.732-735
17
[18] Behnamgol, V., Mohammadzaman, I., Vali, A.R. and Ghahramani, N. A., “Guidance Law Design using Finite Time Second Order Sliding Mode Control,” Journal of Control, K.N. Toosi University of Technology, Vol. 5, No. 3, 2011, pp. 36-45.
18
[19] Behnamgol, V., Mohamma dzaman, I., Vali, A. R. and Fattahi, E., “Design of Sliding Mode Guidance Law using PI Sliding Surface,”20th Iranian Conference on Electrical Engineering, Tehran, Iran, 2012
19
[20] Zhang, H. and Zhang, G., “Adaptive Backstepping Sliding Mode Control for Nonlinear Systems with Input Saturation,” Transactions of Tianjin University, Vol. 18, No. 1, 2012, pp 46-51.
20
[21] Rana, M., Wanga, Q., Houa, D. and Dong, Ch., “Backstepping Design of Missile Guidance and Control Based on Adaptive Fuzzy Sliding Mode Control,” Chinese Journal of Aeronautics, Vol. 27, No. 3, 2014, pp. 634–642.
21
[22] Basri, M., Ariffanan, M., Husain, R. and Kumeresan, A., “Robust Chattering Free Backstepping Sliding Mode Control Strategy for Autonomous Quadrotor Helicopter,” International Journal of Mechanical and Mechatronics Engineering, Vol. 14,Issue 3, 2014, p. 36.
22
[23] Zhou, D., Sun, Sh. and Teo, K. L., “Guidance Laws with Finite Time Convergence,” Journal of Guidance, Control and Dynamics, Vol. 32, No. 6, 2009, pp. 1838-1846.
23
ORIGINAL_ARTICLE
Equilibrium Effects on the Hypersonic Laminar Boundary Layer Flow over Axisymmetric Bodies
An accurate and efficient computational procedure is developed to predict the laminar hypersonic flowfield for both the perfect gas and equilibrium air around the axisymmetric blunt body configurations. To produce this procedure, the boundary layer equations utilize the integral matrix solution algorithm for the blunt nose and after body region by using a space marching technique. The integral matrix procedure enables us to create accurate and smooth results using the minimum grid in the boundary layer and to minimize the computational costs. This algorithm is highly appropriate for the design of hypersonic reentry vehicles. The effects of real gas on the flowfield characteristics are also studied in boundary layer solutions. Comparisons of the results with experimental data demonstrate that accurate solutions are obtained.
https://jsst.ias.ir/article_15237_e736b7dcdd631efaa3aeba5112e79686.pdf
2016-01-01
19
27
Hypersonic Flow
Equilibrium air
Boundary Layer
Integral matrix method
رامین
کمالی مقدم
rkamali@ari.ac.ir
1
پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران
LEAD_AUTHOR
محمدرضا
سلیمی
mohammadsalimi@ari.ac.ir
2
دانشکدة مهندسی هوافضا، دانشگاه صنعتی شریف، تهران، ایران
AUTHOR
[1] Shlichting, H. and Gersten, K., Boundary-Layer Theory, Springer, New York, 2000.
1
[2] Bartlett E.P. and Kendall R.M., Nonsimilar Solution of the Multicomponent Laminar Boundary Layer by an Integral Matrix Method, NASA CR-1062, Part III, 1967.
2
[3] Wood, W.A., Eberhardt, S., “Dual-code Solution Strategy for Chemically Reacting Hypersonic Flows,” 33rd Aerospace Sciences Meeting and Exhibit, Aerospace Sciences Meetings (AIAA Paper), 1995, pp.95-0158.
3
[4] Wood, W.A., Thompson, R.A. and Eberhardt, S., “Dual-Code Solution Strategy for Hypersonic Fows,” Journal of Spacecraft and Rockets, Vol. 33, No. 3, 1995, pp. 449–451.
4
[5] Hejranfar, K., Kamali-Moghadam, R. and Esfahanian, V., “Dual-code Solution Procedure for Efficient Computing Equilibrium Hypersonic Axisymmetric Laminar Flows,” Aerospace Science and Technology, Vol. 12, Issue 2, 2008, pp. 135–149,
5
[6] Thompson R.A., Zoby E.V., Wurster K.E. and Gnoffo P.A., An Aero Thermodynamic Study of Slender Conical Vehicles, AIAA Paper 87-1475, 1987.
6
[7] Cheatwood, F.M. and Dejarnette, F.R., “Approximate Viscous Shock Layer Technique for Calculating Hypersonic Flows About Blunt-Nosed Bodies,” Journal of Spacecraft and Rockets, Vol. 31, No. 4, 1994, pp. 621-629.
7
[8] Noori S., Ghasemloo S. and Mani M., “A New Method for Solution of Viscousshock-Layer Equations,” Proceeding of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering, Vol. 224, No.1, 2008, pp.719-729,.
8
[9] Gnoffo, P.A., Gupta, R.N. and Shinn, J.L., Conservation Equations and Physical Models for Hypersonic Air Flows in Thermal and Chemical Non-equilibrium, NASA TP 2867, 1989.
9
[10] Buelow, P.E., Tannehill, J.C., Ievalts, J.O. and Lawrence, L.S., “Three Dimensional, Upwind, Parabolized Navier–Stokes Code for Chemically Reacting Flows,” Journal of Thermophysics and Heat Transfer, Vol. 5, No. 3, 1991, pp. 274–283.
10
[11]Esfahanian, V. and Hejranfar, K., Accuracy of parabolized Navier–Stokes Schemes for Stability Analysis of Hypersonic Axisymmetric Flows, AIAA Journal, Vol. 40, No. 7, 2002, pp. 1311–1322.
11
[12]Kendall, R. M., Bartlett, E. P., Rindall, R. A. and Moyer, C.B., “An Analysis of Chemically Reacting Boundary Layer,” Issued by Originator as Aerotherm Report No. 66-7, Part 1, 1961.
12
[13] Kopriva, D.A., “Spectral Solution of the Viscous Blunt Body Problem II: Multidomain Approximation,” ICASE Report No. 94-73, 1994.
13
[14] Kamali-Moghadam R., Dual-code TLNS-PNS Solution Procedure for Efficient Computing Equilibrium Hypersonic Axisymmetric Flows, (M.Sc. Thesis), The Sharif University of Technology, Tehran, Iran, December 2005.
14
[15] Tannehill, J.C. and Mugge, T.L., “Improved Curve-Fits for the Thermodynamic Properties of Equilibrium Air Suitable for Numerical Computation Using Time Dependent or Shock-Capturing Methods, NASA CR-2470, 1974.
15
[16] Srinivasan, S., Tannehill, J.C. and Weilmuenster, K.J., Simplified Curve Fits for the Thermodynamic Properties of Equilibrium Air, NASA RP-1-313, 1986.
16
[17] Srinivasan, S., Tannehill, J.C. and Weilmuenster, K.J., Simplified Curve Fits for the Transport Properties of Equilibrium Air, NASA RP-1181, 1987.
17
[18] Bhutta, B.A. and Lewis, C.H., “Comparison of Hypersonic Experiments and PNS Predictions, Part I: Aerothermodynamics,” Journal of Spacecraft and Rockets, Vol. 28, No. 4, 1991, pp. 376-386.
18
[19] Miller, C.G., Micol, J.R. and Gnoffo, P.A., Laminar Heat-Transfer Distribution on Biconics at Incidence in Hypersonic-Hypervelocity Flows, NASA, TP-2213, 1985.
19
ORIGINAL_ARTICLE
Hot Air Gun Identification by Inverse Heat Transfer
The aim of this paper is to identify the unknown properties of an industrial hot air gun using inverse heat transfer approach. A combination of experiments and numerical analyses is used to define the convection coefficient and the produced temperature of this device. A numerical solver is developed by employment of a straightforward and powerful inverse heat transfer method: “The conjugate gradient method for parameter estimation”. The variation of temperature versus time in a fixed point of a steel-304 rod is sensed by a thermocouple and is given as an input to the numerical solver. The produced temperature of the hot air gun and the variation of convection heat transfer coefficient of this device as a function of distance between gun and rod are estimated in this research. Two non-dimensional distances between hot air gun and head of rod, H/D, are considered in this research: 2 and 6. These distances are chosen based on the hot jet potential core, the former is inside the potential core and the latter is outside it. The identifications of this gun are used in the process of determining unknown thermal properties of insulating and ablative materials, which are essential components of ablative heat shields, by inverse heat transfer methods.
https://jsst.ias.ir/article_15238_410302085ff81e2646929f64d626bb8b.pdf
2016-01-01
29
34
Inverse Heat Transfer
Conjugate Gradient Method
Forced Convection
thermal properties
Numerical analysis
امیر مهدی
تحسینی
am_tahsini@iust.ac.ir
1
پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران
LEAD_AUTHOR
سمانه
تدین موسوی
sam.tadayyon@gmail.com
2
پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران
AUTHOR
Ozisik, M.N. and Orlando, H.R.B., Inverse Heat Transfer, Taylor & Francis, 2000.
1
Beck, J.V., Blackwell, B. and JR. C.R.ST. Clair, Inverse Heat Conduction, Ill-Posed Problem, Wiley, 1985.
2
Beck, J.V., “Surface Heat Flux Determination using an Integral Method,” Nuclear Engineering and Design, Vol. 7, 1968, pp. 170-178.
3
Weber, C.F., “Analysis and Solution of the Ill-Posed Inverse Heat Conduction Problem,” International Journal of Heat and Mass Transfer, Vol. 24, No.11, 1981, pp. 1783-1792.
4
J.L. Battaglia, O. Cois, L. Puigsegur L., and A. Oustaloup, “Solving an Inverse Heat Conduction Problem using a Non-Integer Identified Model,” International Journal of Heat and Mass Transfer, Vol. 44, 2001, pp. 2671-2680.
5
Beck, J.V., Litkouhi, B. and Clair Jr., R. St., “Efficient Sequential Solution of the Nonlinear Inverse Heat Conduction Problem,” Numerical Heat Transfer, Vol. 5, 1982, pp. 275-286.
6
Huang, C. H. and Yan, J.Y., “An Inverse Problem in Simultaneously Measuring Temperature-Dependent Thermal Conductivity and Heat Capacity,” International Journal of Heat and Mass Transfer, Vol. 38, No. 18, 1995, pp. 3433-3441.
7
Huan, C. H. and Wang, S.P., “A Three-Dimensional Inverse Heat Conduction Problem in Estimating Surface Heat Flux by Conjugate Gradient Method,” International Journal of Heat and Mass Transfer, Vol. 42, 1999, pp. 3387-3403.
8
Molavi, H., Hakkaki-Fard, A., Pourshaban, I., MahbubiFard, M. and Rahmani, R.K., “Estimation of Temperature-Dependent Thermo physical Properties of Noncharring Ablators,” Journal of Thermo physics and Heat Transfer, Vol. 23, No. 1, 2009.
9
Molavi, H., Rahmani, R.K., Pourshaghaghy, A., Tashnizi, E.S. and Hakkaki-Fard, A., “Heat Flux Estimation in a Nonlinear Inverse Heat Conduction Problem with Moving Boundary,” Journal of Heat Transfer, 132, 2010.
10
Molavi, H., Pourshaban, I., Hakkaki-Fard, A., Molavi, M., Ayasoufi, A. and Rahmani, R.K., “Inverse Identification of Thermal Properties of Charring Ablators,” Numerical Heat Transfer, 56, 2009, pp. 478-501.
11
Yang, Y.C., Chu, S.S., Chang, W.J. and Wu, T.S. “Estimation of Heat Flux and Temperature Distributions in a Composite Strip and Homogenous Foundation,” International Communications in Heat and Mass Transfer, 37, 2010, pp. 495-500.
12
Bahramian, A.R. and Kokabi, M. “Ablation Mechanism of Polymer Layered Silicate Nanocomposite Heat Shield,” Journal of Hazardous Materials, Vol. 166, 2009, pp. 445-454.
13
ORIGINAL_ARTICLE
Optimal Control of a Tri-axial Spacecraft Simulator Test bed Actuated by Reaction Wheels
This article describes the details of a Tri-axial Spacecraft Simulator Testbed (TSST) that has been developed as part of a research program on spacecraft multi-body rotational dynamics and control in Space Research Laboratory (SRL) at K. N. Toosi University of Technology. This dumbbell style simulator includes a variety of components: spherical air-bearing, inertial measurement unit (IMU), rechargeable battery, reaction wheels (RW), on-board computer (OBC) and balancing masses. In this paper, an attitude control problem for the spacecraft simulator actuated by three reaction wheels is studied. Under the assumption of uniform gravity and frictionless air-bearing environment, reaction wheels generate control moments about the roll, pitch and yaw axes of the base body. The control objective is to perform attitude commands sent from users with the least power consumption and a high precision. To handle the non-linear model, a Linear Quadratic Ricatti (LQR) controller has been programmed and it efficaciously controlled the computer-modeled simulator for any given slewing maneuver. This control approach has been developed to facilitate the system to accomplish large-angle, three-axis slewing maneuvers using RWs as effective actuators.
https://jsst.ias.ir/article_15239_a48b868a47f4d4087fa9dc764d44e0a9.pdf
2016-01-01
35
44
spacecraft simulator
air-bearing
Reaction wheel
LQR
حجت
طائی
hojattaie@gmail.com
1
دانشکدة مهندسی هوافضا، دانشگاه صنعتی مالک اشتر، تهران، ایران
LEAD_AUTHOR
مهران
میرشمس
mirshams@kntu.ac.ir
2
صنعتی خواجه نصیرالدین طوسی
AUTHOR
مهدی
قبادی
mahdi_ghobadi@ut.ac.ir
3
دانشکدة فنی، دانشگاه تهران
AUTHOR
محمد امین
وحید دستگردی
4
آزمایشگاه تحقیقات فضایی، دانشگاه صنعتی خواجه نصیرالدین طوسی
AUTHOR
حسن
حقی
5
آزمایشگاه تحقیقات فضایی، دانشگاه صنعتی خواجه نصیرالدین طوسی
AUTHOR
[1] Kim, B., Velenis, E., Kriengsiri, P. and Tsiotras, P., "Designing a Low-Cost Spacecraft Simulator, Control Systems," IEEE, Vol. 23, No. 4, 2003, pp. 26-37.
1
[2] Schwartz, J. L., Peck, M. A. and Hall, C. D., "Historical Review of Air-Bearing Spacecraft Simulators," Journal of Guidance, Control, and Dynamics, Vol. 26, No. 4, 2003, pp. 513-522.
2
[3] Liu, Y., Zhou, J., Chen, H. and Mu, X., "Experimental Research for Flexible Satellite Dynamic Simulation on Three-Axis Air-Bearing Table," Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, Vol. 227, No. 2, 2013, pp. 369-380.
3
[4] Mirshams, M., Taei, H., Ghobadi, M. and Haghi, H., "Spacecraft Attitude Dynamics Simulator Actuated by Cold Gas propulsion System," Proceeding of the Institution of Mechanical Engineering, Part G: Journal of Aerospace Engineering, Vol. 229, No. 8, 2015, pp. 1510-1530.
4
[5] Prado, J., Bisiacchi, G., Reyes, L., Vicente, E., Contreras, F., Mesinas, M. and Juárez, A., "Three-Axis Air-Bearing Based Platform for Small Satellite Attitude Determination and Control Simulation," Journal of Applied Research and Technology, Vol. 3, No. 3, 2005, pp. 222-237.
5
[6] Cho, S. and McClamroch, N. H., "Feedback Control of Triaxial Attitude Control Testbed Actuated by Two Proof Mass Devices," Decision and Control, Proceedings of the Conference on, USA, 2002, pp. 498-503.
6
[7] Saulnier, K., Pérez, D., Huang, R., Gallardo, D., Tilton, G. and Bevilacqua, R., "A Six-Degree-of-Freedom Hardware-in-the-Loop Simulator for Small Spacecraft, Acta Astronautica," Vol. 105, No. 2, 2014, pp. 444-462.
7
[8] Kinnett, R. L., System Integration and Control of a Low-Cost Spacecraft Attitude Dynamics Simulator, (M. Sc. Thesis) Aerospace Engineering, California Polytechnic State University, 2010.
8
[9] Wilson, W. R., Jones, L. L. and Peck, M. A., "A Multimodule Planar Air Bearing Testbed for CubeSat-Scale Spacecraft," Journal of Dynamic Systems, Measurement, and Control, Vol. 135, No. 4, 2013, pp. 1-10.
9
[10] Li, J., Post, M. A. and Lee, R., "Nanosatellite Attitude Air Bearing System Using Variable Structure Control," Proceeding of Electrical & Computer Engineering (CCECE), China, 2012.
10
[11] Peck, M. A., Miller, L., Cavender, A. R., Gonzalez, M. and Hintz, T., "An Airbearing-Based Testbed for Momentum Control Systems and Spacecraft Line of Sight," Advances in the Astronautical Sciences, Vol. 114, 2003, pp. 427-446.
11
[12] Aghalari, A., Kalhor, S. A., Dehghan, M. M. and Cheheltani, S. H., "Manufacturing and Test of an Attitude Dynamics Simulator for Microsatellites Based on CMG," Journal of Aerospace Science and Technology, Vol. 7, No. 3, 2013, pp. 51-67 (In Persian).
12
[13] Kim, J. J. and Agrawal, B. N., "Automatic Mass Balancing of Air-Bearing-Based Three-Axis Rotational Spacecraft Simulator," Journal of Guidance, Control, and Dynamics, Vol. 32, No. 3, 2009, pp. 1005-1017.
13
[14] Jung, D. and Tsiotras, P., "A 3-dof Experimental Test-Bed for Integrated Attitude Dynamics and Control Research," AIAA Guidance, Navigation and Control Conference, USA, 2003.
14
[15] Mirshams, M., Taei, H. and Vahid, M., A Systems Engineering for Satellite Simulator Design, ASME Conference on Systems Engineering, Turkey, 2010.
15
[16] Sidi, M.J., Spacecraft Dynamics and Control: A Practical Engineering Approach, UK: Cambridge University Press, 2000.
16
[17] Shen, J., McClamroch, N. H. and Bloch, A. M., "Local Equilibrium Controllability of the Triaxial Attitude Control Testbed," Proceedings of 41st IEEE Conference on Decision and Control, USA, 2002.
17
[18] Williams, R. and Lawrence, D., Linear State-Space Control Systems, USA: Ohio University, 2007.
18
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ORIGINAL_ARTICLE
INS Alignment Improvement Using Rest Heading and Zero-Velocity Updates
In this paper the feasibility of rapid alignment and calibration of a static strapdown inertial navigation system (INS) is evaluated. Resting conditions including zero-velocity update and a known initial heading direction as virtual external measurement data are integrated with INS data. By comparing the virtual external measurements with the estimates of those generated by the aligning INS, estimates of the velocity and heading errors can be obtained and these errors will be propagated in the INS as a result of alignment inaccuracies. An extended Kalman filter based on an augmented process model and a measurement model is designed to estimate alignment attitudes and biases of inertial sensors. Monte Carlo simulation results show that the integration of INS with rest conditions is very effective in rapid and fine leveling and azimuth alignment of INS, but this type of data fusion due to poor acceleration and angular rates of static condition has no chance of valuable calibration of all inertial sensor biases.
https://jsst.ias.ir/article_15240_d36e073d05994f6419ac2639a2995cdc.pdf
2016-01-01
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Aided inertial navigation system
INS
Alignment
Kalman Filter
ZUPT
مهدی
فتحی
mahd.fathi@irost.ir
1
مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر، تهران، ایران
LEAD_AUTHOR
علی
محمدی
ali_mohammadi@yahoo.com
2
دانشکده مهندسی برق، دانشگاه صنعتی مالک اشتر، تهران، ایران
AUTHOR
نعمت الله
قهرمانی
ghahremani@mut.ac.ir
3
دانشکده مهندسی برق، دانشگاه صنعتی مالک اشتر، تهران، ایران
AUTHOR
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