Stabilization of the F-8 Fighter Aircraft Using Model-Based Predictive Control
Mohammad
Veysi
author
Mohammadreza
Soltanpour
author
Jafar
Khalilpour
author
text
article
2018
per
The aircraft stabilizer stabilizes the aircraft utilizing non-fixed and controllable aerodynamic surfaces. Thispaper presents a model-based predictive control for F-8 fighter aircraft stabilization. In the proposedcontrol method, meanwhile the real-time optimization, the cost-function is minimized by means of thelinearized model of F-8 fighter and the output is predicted in future interval times based on the recedinghorizon strategy. The cost-function is defined as the aggregate of terminal cost and summation of stagecosts, that the quadratic form of cost-function is utilized in control algorithm, eventually. The costfunctionminimization is giving rise to stable control input. The extracted stable control input stabilizedthe states of the nonlinear F-8 fighter system under the various initial conditions. The considerations aretaken into account in the controller designing steps, to reduce the computational load. Mathematical proofinvestigates that the closed-loop system with the proposed control has asymptotic stability. Thesimulation results well demonstrate the favorable efficiency of the proposed controller in F-8 fighteraircraft stabilization.
Journal of Aeronautical Engineering
Shahid Sattari Aeronautical University of Science and Technology-Iranian Aerospace Society
Director-in-Charge:
Dr. Akbar Cheraqi
Editor-in-Chief:
Dr. Farhad Javidrad
Associate Editor:
Dr. Vahid Khalafi
Website Manager:
Amir Ehsan Zamanian
Eng. Nima Mansour Lakouraj
English Text Editor:
Dr. Roohollah Maleki
17359449
20
v.
2
no.
2018
1
15
https://www.joae.ir/article_121875_f3fc38a8efbe10beae9bac358ddaa05c.pdf
Strength analysis of aluminum matting plates welded by TIG welding process for airfield repair
Ehsan
Barati
author
Mohsen
Kalateh
author
Mohammad
Rashtbarian
author
text
article
2018
per
One of the fastest ways to repair a damaged airfield, is using the matting plates. These plates are manufactured with various size and materials. If there is no way to continuously manufacture the plates, one can produce two separately parts of them and weld to each other. In this paper, the strength of a matting plate namely AM-2 welded by TIG welding process has been analyzed. For determination of the landing loads, Hercules C-130 aircraft has been considered. Various values of subgrade CBR have been studied. The joining plan of plates has been considered in such a way that the strength in the weld region be greater than before. The results showed that by using the matting plate welded by TIG welding process, the value of the subgrade CBR should be at least 15. Simulating test with crane has been carried out in this paper and good agreement was found in the results obtained by experimental tests and that evaluated by numerical analyses.
Journal of Aeronautical Engineering
Shahid Sattari Aeronautical University of Science and Technology-Iranian Aerospace Society
Director-in-Charge:
Dr. Akbar Cheraqi
Editor-in-Chief:
Dr. Farhad Javidrad
Associate Editor:
Dr. Vahid Khalafi
Website Manager:
Amir Ehsan Zamanian
Eng. Nima Mansour Lakouraj
English Text Editor:
Dr. Roohollah Maleki
17359449
20
v.
2
no.
2018
16
26
https://www.joae.ir/article_121876_1ca8f8d55beb9cb24a4bf11009014da8.pdf
Reduction of wing-related incidents and aircraft fuselage by replacing riveting process with friction stir spot welding process
Mohammad
Kazemi Nasrabadi
author
Kazem
Sadeghpour
author
text
article
2018
per
Friction stir spot welding has been considered as one of the superior manufacturing processes with variousapplications which nowadays draw the attention of aerospace industries. The main goal of the current study is tocompare the shear tensile-shear strength of dissimilar aluminum alloy sheets of 7075-T6 and 2024-T3 in thefriction stir spot welding process with the riveting process commonly used in the wing and body structures of theaircraft. In addition, the influence of various parameters such as the influence of tool penetration speed, toolrotational speed, and the arrangement of aluminum alloy sheets on the tensile-shear strength of the joining zone havebeen investigated and compared with that of rivet joining process. By properly choosing these parameters, theoptimum tensile-shear strength of the joint can be attainable. Results obtained during the current research can beconsidered to replace the riveting process with the stir spot welding process in the aerospace industries, and inparticular for some portions of the wing and body of the aircraft in order to achieve higher strength for the desiredjoints. As a result, the damage related to the joints used in aircraft structures could be efficiently reduced.
Journal of Aeronautical Engineering
Shahid Sattari Aeronautical University of Science and Technology-Iranian Aerospace Society
Director-in-Charge:
Dr. Akbar Cheraqi
Editor-in-Chief:
Dr. Farhad Javidrad
Associate Editor:
Dr. Vahid Khalafi
Website Manager:
Amir Ehsan Zamanian
Eng. Nima Mansour Lakouraj
English Text Editor:
Dr. Roohollah Maleki
17359449
20
v.
2
no.
2018
27
38
https://www.joae.ir/article_121877_3b45837c6b81423b7d505853f273b1d2.pdf
Adaptive Fuzzy Slide Mode Control Design with Asymptotic Sliding Surface for
MEMS Vibrational Gyroscope System in the Presence of Uncertainty
Mohammadreza
Soltanpour
author
Reza
Khaki
author
text
article
2018
per
Electromechanical Gyroscopes are based on vibrational systems. To control the driving mode of such small vibrationalsystem is of pivotal importance for researchers. A sliding-mode control system is proposed for MEMS gyroscopes. At first,for decreasing the uncertainties existed in dynamical equations, utilizing the Inverse Dynamics method known dynamics ofthe gyroscope system are eliminated. To make the controller robust against the remaining uncertainties, sliding-modecontrol is applied. Sliding mode control will add undesired chattering on the control input, which result in a reduction indriving mode actuator's lifetime. In order to preclude the chattering problem in the control input, two approaches arepresented. In the first approach, an adaptive fuzzy approximator is used to estimate the uncertainty bound in dynamicalequations. The application of proposed adaptive fuzzy sliding mode control in reducing the undesirable chattering in thecontrol input is impressive. In the second approach, by adjusting the Adaptive fuzzy sliding mode control designing process,a new variable is presented, which finally leads to designing the control input derivative. The mathematical proof shows thatthe proposed control method will cause the sliding surface to converge to zero asymptotically in the presence ofuncertainties. Since it is imperative for implementation purposes to take integral from the control input, the chatteringphenomenon will disappear completely in practice. To demonstrate the function of the proposed controllers, four simulationsteps have been implemented on MEMS gyroscopes. Simulation results indicate desired operation of adaptive fuzzy slidingmode control with the asymptotical sliding surface.
Journal of Aeronautical Engineering
Shahid Sattari Aeronautical University of Science and Technology-Iranian Aerospace Society
Director-in-Charge:
Dr. Akbar Cheraqi
Editor-in-Chief:
Dr. Farhad Javidrad
Associate Editor:
Dr. Vahid Khalafi
Website Manager:
Amir Ehsan Zamanian
Eng. Nima Mansour Lakouraj
English Text Editor:
Dr. Roohollah Maleki
17359449
20
v.
2
no.
2018
39
55
https://www.joae.ir/article_121879_df5b14a357298885f6bc6c585c367efe.pdf
Robust compensation of radome error using μ-synthesis technique
Mahdi
Khosravi Samani
author
Mahdi
Nikusokhan
author
Iman
Mohammadzaman
author
text
article
2018
per
Because of refraction of the incoming wave in the radar-guided interceptors, the radome can cause large miss distance and even having a destabilizing effect on the guidance system. On the other hand, the radome imposes an unwanted feedback that is not similar to the conventional feedback loops, in which output must follow a desired control signal. In this paper, the destructive effect of radome in guidance loop stability and performance is analyzed at first. Then, proposing a virtual integrator operator, the problem is transformed to a conventional tracking control problem so that the performance indexes can be defined in control aspect. Regarding the parametric uncertainty of the radome slope, μ-synthesis approach is used to design a robust compensator. Simulation results and stability analysis show that the designed compensator improves the guidance system performance in the presence of the radome, while the stability is guaranteed.
Journal of Aeronautical Engineering
Shahid Sattari Aeronautical University of Science and Technology-Iranian Aerospace Society
Director-in-Charge:
Dr. Akbar Cheraqi
Editor-in-Chief:
Dr. Farhad Javidrad
Associate Editor:
Dr. Vahid Khalafi
Website Manager:
Amir Ehsan Zamanian
Eng. Nima Mansour Lakouraj
English Text Editor:
Dr. Roohollah Maleki
17359449
20
v.
2
no.
2018
56
66
https://www.joae.ir/article_121881_c456a1b7089279736340db96752d6c22.pdf
Reliability analysis of flutter threshold for an isotropic panel with different boundary conditions
Mohammad Ali
Farsi
author
Vahid
Khalafi
author
text
article
2018
per
Reliability and uncertainty effect on aeroelasticity problems have been less respected by researchers.Reliability defines the ability of an item to perform the desired function during a specified time. In thispaper, the flutter threshold for a panel has been studied; uncertainty in some parameters such as the elasticmodel, Poisson's ratio, density, thickness, and plane length is investigated. The plane is an Isotropicmaterial considered in supersonic flow regime with three boundary conditions (SS, CS, CC). Thestructural model is considered based on the classical plate theory; also to determine the supersonicaerodynamic loads on the plate the first order piston theory is applied. The Generalized DifferentialQuadrature Method (GDQM) is used to discrete and analysis the aeroelastic equations of the panel. Thenthe equations are analyzed and eigenvalues are calculated. Then the threshold of the panel flutter isdetermined. Finally, to calculate the threshold of panel flutter reliability based on the first order reliabilitymethod, the Monte Carlo (MC) simulation is used.
Journal of Aeronautical Engineering
Shahid Sattari Aeronautical University of Science and Technology-Iranian Aerospace Society
Director-in-Charge:
Dr. Akbar Cheraqi
Editor-in-Chief:
Dr. Farhad Javidrad
Associate Editor:
Dr. Vahid Khalafi
Website Manager:
Amir Ehsan Zamanian
Eng. Nima Mansour Lakouraj
English Text Editor:
Dr. Roohollah Maleki
17359449
20
v.
2
no.
2018
67
74
https://www.joae.ir/article_121882_f3409abe46ef22d3c0cf7dbbb8db7921.pdf