Trim and Stability Analysis of Parafoil/Payload System Using Bifurcation Methods

Prakash, Om; Daftary, Avani; Ananthkrishnan, N.

doi:10.2514/6.2005-1666

Cited by 16 publications

(4 citation statements)

References 4 publications

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“…The method is implemented for the 3DOF longitudinal hybrid airship model by applying SBA for the nonlinear dynamic model [4,7] and the state variables are given by x=[V, γ, α, θ, q, h]′. The states are further reduced for simplicity, considering constant velocity, V, constant height, ℎ and considering very small changes in γ, thus the state variable considered for the analysis is reduced and is given by x=[α, θ, q]′.…”

Section: Bifurcation Methods Analysismentioning

confidence: 99%

“…Although the hybrid airship is unique, its modelling and stability analysis were done according to the typical procedure of a conventional airship and aircraft. Analysis of parafoil system using trim and stability from researches [3][4][5] uses bifurcation technique and discusses the impact of the model constraints on the longitudinal dynamics with trim along with stability traits for 4DOF longitudinal dynamic flight model. 4DOF comes from 9DOF model of hybrid airship discussed in researches [6][7].…”

Section: Introductionmentioning

confidence: 99%

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Longitudinal Trim and Stability Analysis of Hybrid Airship with Suspended Payload for Single Body and Two Body Dynamics Using Bifurcation Method

Kumar¹,

Prakash²

2023

MMEP

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The paper deals with the nonlinear mathematical modelling of the longitudinal dynamics of a small sized hybrid airship with suspended payload vehicle. The modelling is done by considering the system as single body dynamic as well as two body dynamics. Bifurcation Analysis method is applied to do the trim and stability analysis of the system. MATLAB and AUTO bifurcation analysis tool is used for dynamic modeling and simulation of the system. Total five different simulation cases with different elevator deflection are discussed for 3DOF model. For each case Six output states as Vel, gamma, alpha, q, theta and range (h) is taken and one input parameter as dele i.e. elevator deflection is taken. In this paper 6DOF and 3DOF longitudinal conventional single body dynamic model of hybrid airship is discussed and an alternate method as 4DOF two body longitudinal dynamic model of hybrid airship is also considered. Simulation is done for all models on MATLAB and Alternate technique as bifurcation method is also used on AUTO software to study the dynamic analysis of the system. Eigen values is obtained from bifurcation method and is helpful to analyze the stability of the Hybrid airship with suspended payload vehicle.

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Section: Bifurcation Methods Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Longitudinal Trim and Stability Analysis of Hybrid Airship with Suspended Payload for Single Body and Two Body Dynamics Using Bifurcation Method

Kumar¹,

Prakash²

2023

MMEP

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“…The use of bifurcation methods can provide parafoil designers with a systematic procedure to pick the best rigging angle and also predict the system performance and stability. Prakash et al [57,58] carried out bifurcation analysis for a parafoil-payload system using aerodynamic data for the parafoil in tabular form over a range of angles of attack from -10 to +80 deg. The equations of motion for the parafoil-payload system have been listed in Appendix-C. Their computed trim states (parafoil angle of attack, system glide angle) for various choices of rigging angle μ are reproduced in Fig.…”

Section: Choice Of Rigging Angle For Parafoil-payload System Gliding ...mentioning

confidence: 99%

Use of Bifurcation And Continuation Methods For Aircraft Trim And Stability Analysis - A State-of-the-art

Paranjape,

Kumar Sinha,

Ananthkrishnan

2008

joast

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The bifurcation and continuation methodology has evolved over the last two decades into a powerful tool for the analysis of trim and stability problems in aircraft flight dynamics. Over the years, bifurcation methods have been employed to deal with a variety of problems in aircraft dynamics, such as predicting high angle of attack behavior, especially spin, and studying instabilities in rolling maneuvers. The bifurcation methodology has served as a tool for the design of flight control systems, and is promising to be a useful tool in the aircraft design, simulation, testing, and evaluation process. In the present paper, we describe the state-of-theart in the use of bifurcation and continuation methods for the analysis of aircraft trim and stability with a few illustrative examples. Both the standard and extended bifurcation analysis procedures are discussed and typical results for instabilities in high-α flight and inertia-coupled roll maneuvers are shown. This is followed by several problems in nonlinear flight dynamics where bifurcation and continuation methods have been fruitfully applied to yield effective solutions. Finally, the use of bifurcation theory to arrive at analytical instability criteria is demonstrated for the aircraft roll coupling and wing rock problems. 78 references have been cited in the text.

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“…The use of bifurcation methods can provide parafoil designers with a systematic procedure to pick the best rigging angle and also predict the system performance and stability. Prakash et al 56,57 carried out bifurcation analysis for a parafoil-payload system using aerodynamic data for the parafoil in tabular form over a range of angles of attack from −10 to +80 deg. Their computed trim states (parafoil angle of attack, system glide angle) for various choices of rigging angle µ are reproduced in Fig.…”

Section: B Choice Of Rigging Angle For Parafoil-payload System Glidimentioning

confidence: 99%

Use of Bifurcation and Continuation Methods for Aircraft Trim and Stability Analysis - A State-of-the-Art

Paranjape

Sinha

Ananthkrishnan

2007

45th AIAA Aerospace Sciences Meeting and Exhibit

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The bifurcation and continuation methodology has evolved over the last two decades into a powerful tool for the analysis of trim and stability problems in aircraft flight dynamics. Over the years, bifurcation methods have been employed to deal with a variety of problems in aircraft dynamics, such as predicting high angle of attack behavior, especially spin, and studying instabilities in rolling maneuvers. The bifurcation methodology has served as a tool for the design of flight control systems, and is promising to be a useful tool in the aircraft design, simulation, testing, and evaluation process. In the present paper, we describe the state-of-the-art in the use of bifurcation and continuation methods for the analysis of aircraft trim and stability with a few illustrative examples. Both the standard and extended bifurcation analysis procedures are discussed and typical results for instabilities in high-α flight and in inertia-coupled roll maneuvers are shown. This is followed by several problems in nonlinear flight dynamics where bifurcation and continuation methods have been fruitfully applied to yield effective solutions. Finally, the use of bifurcation theory to arrive at analytical instability criteria is demonstrated for the aircraft roll coupling and wing rock problems. 76 references have been cited in the text.

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Trim and Stability Analysis of Parafoil/Payload System Using Bifurcation Methods

Cited by 16 publications

References 4 publications

Longitudinal Trim and Stability Analysis of Hybrid Airship with Suspended Payload for Single Body and Two Body Dynamics Using Bifurcation Method

Longitudinal Trim and Stability Analysis of Hybrid Airship with Suspended Payload for Single Body and Two Body Dynamics Using Bifurcation Method

Use of Bifurcation And Continuation Methods For Aircraft Trim And Stability Analysis - A State-of-the-art

Use of Bifurcation and Continuation Methods for Aircraft Trim and Stability Analysis - A State-of-the-Art

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