A direct adaptive neural command controller design for an unstable helicopter

Kumar, M. Vijaya; Sundaram, Suresh; Omkar, S. N.; Ganguli, Ranjan; Sampath, Prasad

doi:10.1016/j.engappai.2008.07.004

Cited by 39 publications

(8 citation statements)

References 23 publications

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“…It was shown that both these methods resulted in periodic control gains being expressed as explicit functions of time which permit a realtime control scheme to be implemented. (Vijayakumar et al, 2006(Vijayakumar et al, , 2009) have explored the development of a feedback error-learning neural controller for an unstable research helicopter. Three different neural aided controllers were designed to satisfy the ADS-33 handling qualities specifications in pitch, roll and yaw axes.…”

Section: Helicopter Rotor Design Optimizationmentioning

confidence: 97%

Rotorcraft research in India: recent developments

Ganguli

2010

Aircraft Eng & Aerospace Tech

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If you would like to write for this, or any other Emerald publication, then please use our Emerald for Authors service information about how to choose which publication to write for and submission guidelines are available for all. Please visit www.emeraldinsight.com/authors for more information. About Emerald www.emeraldinsight.comEmerald is a global publisher linking research and practice to the benefit of society. The company manages a portfolio of more than 290 journals and over 2,350 books and book series volumes, as well as providing an extensive range of online products and additional customer resources and services.Emerald is both COUNTER 4 and TRANSFER compliant. The organization is a partner of the Committee on Publication Ethics (COPE) and also works with Portico and the LOCKSS initiative for digital archive preservation. AbstractPurpose -The purpose of this paper is to discuss published research in rotorcraft which has taken place in India during the last ten years. The helicopter research is divided into the following parts: health monitoring, smart rotor, design optimization, control, helicopter rotor dynamics, active control of structural response (ACSR) and helicopter design and development. Aspects of health monitoring and smart rotor are discussed in detail. Further work needed and areas for international collaboration are pointed out. Design/methodology/approach -The archival journal papers on helicopter engineering published from India are obtained from databases and are studied and discussed. The contribution of the basic research to the state-of-the-art in helicopter engineering science is brought out. Findings -It is found that strong research capabilities have developed in rotor system health and usage monitoring, rotor blade design optimization, ACSR, composite rotor blades and smart rotor development. Furthermore, rotorcraft modeling and analysis aspects are highly developed with considerable manpower available and being generated in these areas. Practical implications -Two helicopter projects leading to the "advanced light helicopter" and "light combat helicopter" have been completed by Hindustan Aeronautics Ltd These helicopter programs have benefited from the basic research and also provide platforms for further basic research and deeper industry academic collaborations. The development of well-trained helicopter engineers is also attractive for international helicopter design and manufacturing companies. The basic research done needs to be further developed for practical and commercial applications. Originality/value -This is the first comprehensive research on rotorcraft research in India, an important emerging market, manufacturing and sourcing destination for the industry.

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Section: Helicopter Rotor Design Optimizationmentioning

confidence: 97%

Rotorcraft research in India: recent developments

Ganguli

2010

Aircraft Eng & Aerospace Tech

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“…Uçuş dinamiğinde doğrusal olmama ve belirsizlik gibi etkenlerden dolayı geleneksel kontrolörlerin kullanımı istenen performans ve kararlılığı sağlayamamaktadır. Bu yüzden geleneksel kontrolörleri kullanmak yerine H [3], temel radyal fonksiyonlu sinirsel [4], uyarmalı sinirsel [5], kendinden ayarlı bulanık PID [6], bulanık mantık [7] ve kayan kipli [8] gibi kontrolörler kullanılmaktadırlar.…”

Section: Introductionunclassified

Henry Gaz Çözünürlük Optimizasyonu ile Uçak Eğim Kontrol Sistemi için Etkin Kontrolör Tasarımı

Kaçti¹,

Ekinci²,

İzci³

2020

DÜMF Mühendislik Dergisi

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Sezgisel-üstü algoritmalar, uçak eğim kontrol sistemi, PID kontrolör ÖZET Bu çalışma ile sezgisel-üstü algoritmalardan olan Henry gaz çözünürlük optimizasyonu (HGSO) kullanılarak oransal, integral ve türevsel (PID) bir kontrolöre ait parametreler bir uçağın alçalma/yükselme (eğim) açısına ait sistemin kontrolü için optimum olacak şekilde ayarlanmıştır. Kullanılan bu yaklaşım literatürde ilk defa önerilmekte olup, sistemin performans analizi için istatistiksel test, geçici hal cevabı, kutup-sıfır haritası ve bode gibi analizler gerçekleştirilmiştir. Söz konusu bu analizler aynı zamanda literatürde son beş yıl içinde yayınlanmış ve oldukça etkili olduğu gösterilmiş olan sinüs kosinüs algoritması (SCA) ve çekirge optimizasyon algoritması (GOA) gibi diğer sezgisel-üstü algoritmalar ile ayarlanmış PID kontrolörler ile de kıyaslanmıştır. Karşılaştırmalar neticesinde, bu çalışma ile önerilen HGSO ayarlı PID kontrolörün uçak eğim açısı kontrol sistemi için diğer güncel ve etkili olan sezgisel-üstü algoritmalar ile ayarlanmış PID kontrolörlerine göre daha etkili olduğu ve iyi bir performansa sahip olduğu görülmüştür.

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“…For helicopters, NN adaptive controls have been utilized for various purposes. NNs are used to stabilize an unstable helicopter and track a pitch rate command [11], to track an altitude command using rotor speed [12], to track a pitch angle command [13], and to increase the performance of the attitude control and the trajectory control of a helicopter [14]. In reference [15], NNs are employed to reject external disturbance while linear quadratic regulator and proportional and derivative (PD) controllers are used for speed and position control of an unmanned helicopter.…”

Section: Introductionmentioning

confidence: 99%

Trajectory tracking controller design using neural networks for a tiltrotor unmanned aerial vehicle

Kim

2010

Proceedings of the Institution of Mechanical Engineers, Part G:

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This article presents a design of trajectory tracking controller for a tiltrotor unmanned aerial vehicle (UAV). The objective of this design is to control the tiltrotor aircraft with one fixed controller architecture for all flight modes, viz. helicopter mode, conversion mode, and aeroplane mode. The controller is implemented using two time-scale separations, and thus comprises an inner loop for attitude control and an outer loop for trajectory control. The dynamic model inversion (DMI) technique is applied to both the control loops such that the inner-loop and the outer-loop DMIs are driven using the angular equations of motion and the translational equations of motion, respectively. In addition, online adaptive neural networks are employed to compensate for the model inversion errors of the inner loop and the outer loop due to the lack of complete knowledge of tiltrotor aircraft dynamics. The pseudo-control hedging algorithm is adopted to reduce the instability problem caused by the time-delay of control loops, saturation, and rate limit of actuators. The trajectory tracking controller is evaluated using a sophisticated six-degree-of-freedom non-linear simulation programme with an approach and landing scenario including all flight modes of a smart UAV, a tiltrotor UAV.

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A direct adaptive neural command controller design for an unstable helicopter

Cited by 39 publications

References 23 publications

Rotorcraft research in India: recent developments

Rotorcraft research in India: recent developments

Henry Gaz Çözünürlük Optimizasyonu ile Uçak Eğim Kontrol Sistemi için Etkin Kontrolör Tasarımı

Trajectory tracking controller design using neural networks for a tiltrotor unmanned aerial vehicle

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