Application of a Proportional Feedback Controller for Active Control of a Vibration Isolator

Liu, Yunhui

doi:10.1260/026309205775374442

Cited by 8 publications

(7 citation statements)

References 12 publications

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“…The above equations of motion can be written in the matrix form as (13) where, [M] is the mass matrix given by…”

Section: Full Aircraft Model Formulationmentioning

confidence: 99%

“…Oveisi and Gudarzi [12] presented a PID controller tuned with Ziegler-Nichols rules for both robustness and vibration suppression performance aspects. The application of proportional controller to active vibration control incorporated with a passive vibration isolator to suppress the resonant oscillation at its natural frequency was studied by Liu [13]. The present study analysed random vibration of full aircraft model with active landing gears under normal landing condition and dynamic response on different grades of random runways.…”

Section: Introductionmentioning

confidence: 99%

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Aircraft Random Vibration Analysis Using Active Landing Gears

Sivakumar

Haran

2015

Journal of Low Frequency Noise, Vibration and Active Control

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In this article, random vibration analysis of full aircraft with passive and active landing gears has been done by numerical simulations on random runway profile. The mathematical model of full aircraft with active landing gears and modelling of runway profiles have been developed for analysing the aircraft bounce, pitch, roll accelerations, displacement and shock strut travel while taxiing on random runways. The results show that vibration levels of the aircraft by the active landing gear system is less than the conventional landing gear system while taxiing on different grades of random runways. Comparison results also show that the active system improves the ride comfort and easiness of pilot handling and thus, increases the fatigue life of the aircraft. NOMENCLATURE MAircraft fuselage mass m 1Nose landing gear tire mass m 2 Rear left landing gear tire mass m 3 Rear right landing gear tire mass ks 1 Nose gear shock strut stiffness ks 2 Rear left gear shock strut stiffness ks 3 Rear right gear shock strut stiffness cs 1 Nose gear shock strut damping coefficient cs 2 Rear left gear shock strut damping coefficient cs 3 Rear right gear shock strut damping coefficient kt 1 Nose gear tire stiffness kt 2 Rear left gear tire stiffness kt 3 Rear right gear tire stiffness ct 1 Nose gear tire damping coefficient ct 2 Rear left gear tire damping coefficient ct 3 Rear right gear tire damping coefficient [M] Mass matrix [C] Damping INTRODUCTIONLanding gear is a critical component of the aircraft which transmits the ground loads to the aircraft structure. It provides ride comfort to the passengers during taxiing on the runways. It also improves the pilot's efficiency to control the aircraft and to read the instruments in the glass cockpits during ground manoeuvres. The landing gear fitted in the aircraft is not able to adjust the damping characteristics in real-time runway conditions. The focus on active landing gear system is essential to overcome the difficulties of passive landing gear. presented a PID controller tuned with Ziegler-Nichols rules for both robustness and vibration suppression performance aspects. The application of proportional controller to active vibration control incorporated with a passive vibration isolator to suppress the resonant oscillation at its natural frequency was studied by Liu [13]. The present study analysed random vibration of full aircraft model with active landing gears under normal landing condition and dynamic response on different grades of random runways. The designed PID controller generates the control force to reduce bounce, pitch, roll displacement and accelerations of fuselage body considerably. This article does not analyse the bank angle response by PID controller during flight. The PID controller requires the bank angle reference command to tackle the unknown banking for turn coordination. However, the bank angle reference is required by the PID controller during crosswind taxiing conditions. Runway roughness affects both the landing gear and the airframe. Nowada...

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“…The above equations of motion can be written in the matrix form as (13) where, [M] is the mass matrix given by…”

Section: Full Aircraft Model Formulationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Aircraft Random Vibration Analysis Using Active Landing Gears

Sivakumar

Haran

2015

Journal of Low Frequency Noise, Vibration and Active Control

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“…Thread gauge is manipulated conveniently and credibly and used to detect the quality of inner thread. It is allowable that limited gauges (less than two thread pitch) are screwed when thread gauge is used to detect the quality of inner thread [8].In this paper, the screwed depth of the gauge is used to judge the dilation of inner thread.…”

Section: Experiments Of Vibratory Tappingmentioning

confidence: 99%

A Compound Vibratory Mode in High Speed Vibratory Tapping

Wang

Zhu

et al. 2009

AMR

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Based on the investigation of two traditional vibratory modes, this paper puts forward a novel vibratory mode in high speed tapping. Vibratory tapping on stainless steel with all kinds of vibratory modes is carefully studied. Experimental results show that the new vibratory mode not only preserves the machining effect of the separable vibratory tapping, but also increases the life of tap. Therefore this study provides a new solution to increase the performance of high speed vibrat- ion tapping.

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“…Most of active suspension systems are required to use high cost actuators and transducers. 8,9 Moreover, they are not capable with low energy consumption requirements. 4,10 At this point, vibration isolation systems based on hybrid electromagnets have become a good alternative, 11–16 because in hybrid electromagnet structure, permanent magnets behave as if they were additional current-source equivalents.…”

Section: Introductionmentioning

confidence: 99%

Observer-based H₂ controller design for a vibration isolation stage having hybrid electromagnets

Yalçin

Sever

Erkan

2018

Journal of Low Frequency Noise, Vibration and Active Control

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Vibration isolation systems based on hybrid electromagnets, consisting of electromagnet and permanent magnet, have a potential usage in many industrial areas, such as clean room design, transportation, semiconductor manufacturing, suspension systems, and robotic surgery due to providing mechanical contact free vibration isolation. Using permanent magnets in the electromagnet structure has some crucial advantages, such as a minimized volume and a more compact structure. Furthermore, the essential force for levitation of vibration isolation stage can be generated by only the permanent magnet(s), which means, by using hybrid electromagnets, magnetic levitation can be achieved with considerably low energy consumption against possible vibrations. This property is called zero-power behavior. However, the main problems of magnetic levitation process are as follows: it has highly nonlinear nature even if it can be linearized; it has unstable pole(s), which makes the system vulnerable in terms of stability. In recent years, linear matrix inequality-based design of controllers has received considerable attention and become very popular due to their ability to satisfy multiobjective design requirements. However, an observer-based H2 controller design for a vibration isolation system having hybrid electromagnets has not been considered yet. Therefore, the linear matrix inequality-based controller is employed to minimize the effect of disturbances on the following objectives, such as vibration isolation, zero-power property, and protection of the levitation gap. The effectiveness of the proposed method is shown with the numerical simulation studies and compared with classical Linear Quadratic Regulator (LQR) approach.

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Application of a Proportional Feedback Controller for Active Control of a Vibration Isolator

Cited by 8 publications

References 12 publications

Aircraft Random Vibration Analysis Using Active Landing Gears

Aircraft Random Vibration Analysis Using Active Landing Gears

A Compound Vibratory Mode in High Speed Vibratory Tapping

Observer-based H₂ controller design for a vibration isolation stage having hybrid electromagnets

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Application of a Proportional Feedback Controller for Active Control of a Vibration Isolator

Cited by 8 publications

References 12 publications

Aircraft Random Vibration Analysis Using Active Landing Gears

Aircraft Random Vibration Analysis Using Active Landing Gears

A Compound Vibratory Mode in High Speed Vibratory Tapping

Observer-based H2 controller design for a vibration isolation stage having hybrid electromagnets

Contact Info

Product

Resources

About

Observer-based H₂ controller design for a vibration isolation stage having hybrid electromagnets