Research on parafoil stability using a rapid estimate model

Hua, Yi; Song, Lei; Chen, Weifang

doi:10.1016/j.cja.2017.06.003

Cited by 9 publications

(3 citation statements)

References 21 publications

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“…The parafoil dynamics model is the research basis of an autonomous control system. There are some dynamics models presented according to the rigid body and the multibody methodologies [2], [3], [4]. For the rigid body model, the parafoil and the payload are considered as a whole, and the relative distance between the canopy and the payload The associate editor coordinating the review of this manuscript and approving it for publication was Halil Ersin Soken .…”

Section: Introductionmentioning

confidence: 99%

Dynamics Modeling and Autonomous Landing for Flexible Parafoil-Vehicle Multibody System

et al. 2023

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In this paper, the autonomous landing of the parafoil used for aerial vehicles is investigated through the numerical approach. The coupled parafoil-vehicle dynamics model is developed based on the multibody method. The transition process from aircraft flight to parafoil glide is designed in a global system framework. To deal with large flexible deformations during the deployment process, the parafoil canopy is approximated as interacting symmetric subparts using the geometric division method. The pseudo-spectral method is employed to generate a reference trajectory for the landing target. As the system dynamics are introduced into constraint conditions, the generated trajectory is beneficial to improve landing precision. In addition, other optimization objectives, including minimal energy consumption and obstacle avoidance, are considered in trajectory planning. The enhanced proportional integral control is designed to follow the reference trajectory. The neural network inversion model is used to reduce the coupling effect between the longitudinal and the directional control channels. There is a coupling effect that the two controls both are implemented through left and right trailing-edge deflections. An adaptive output allocation method is proposed to ensure that the directional control always is effective in particular when one side reaches saturation. Finally, simulations for autonomous landing under different conditions are carried out to validate the integrated system.INDEX TERMS Flexible parafoil model, multi-body system, trajectory optimization, flight control.

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Section: Introductionmentioning

confidence: 99%

Dynamics Modeling and Autonomous Landing for Flexible Parafoil-Vehicle Multibody System

et al. 2023

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“…Theoretical studies were carried out to investigate the performance of gliding parachutes (20)(21)(22) . In addition, several studies on the longitudinal and lateral stability characteristics of gliding parachutes performed in which the effects of varying significant design parameters on the static or dynamic stability were investigated (23)(24)(25)(26) . Nowadays, there are many canopies, basically designed for personnel applications.…”

Section: Introductionmentioning

confidence: 99%

A novel algorithm for conceptual design and optimisation of an affordable gliding airdrop platform using TCOMOGA

Nosratollahi

Ghapanvary

2018

Aeronaut. j.

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Unlike conventional ballistic parachutes, gliding parachutes have been extensively used as guided precision aerial delivery system (GPADS) platforms in recent years. The reasoning may be found in gliding and manoeuvering capabilities, which make this kind of ram-air parachutes superior for precision aerial delivery application. In contrast, wing-shaped configuration along with more design variables create a cumbersome design procedure for this type of parachute. Especially, when an affordable configuration is demanded, the design procedure will be a more important problem. In this respect, an innovative integrated design framework is proposed in which significant design aspects are considered so that the gliding parachute configuration can be optimiseoptimised through a bi-objective optimisation problem to find optimum cost for achievable gliding ranges. To do so, the configuration is defined with minimum required parameters and design space is constrained by performance and stability as significant design requirements to guarantee the feasibility of the solutions in practice. The objective functions are defined in terms of gliding characteristics and amount of materials for fabrication which are representative for maximum reachable stand-off distance and unit cost, respectively. As an effective numerical optimisation method, a niched multi-objective genetic algorithm (MOGA) is used to generate a pareto-optimal set for a specific payload mass whereas constraints are handled through a tournament selection process. Based on results, the provided pareto front can aid the designers in decision-making and trade-off between demanded objectives for a payload weight. The underlying design problem is solved using an all-at-once (AAO) approach and the design loop converges to favourable results in a reasonable time. Finally, as a comparative study, an optimiseoptimised affordable cargo parachute is proposed for the GPADS application in which the material cost is reduced by at least 25% with respect to an available low-cost gliding parachute with the same glide ratio.

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“…The parachute systems had two modes of short period and phugoid in longitudinal channels and roll, duch roll and spiral modes in lateraldirectional channel. In recent studies, using a 6-DOF linearized model discussed in litrature [23,24], a dynamic stability study was carried out for a powered low anhedral canopy parachute. The eigenvalues of longitudinal and lateral-directional channels were obtained whereas the trim points were extracted through a static 4-DOF model of straight trimmed flight in which the effect of relative pitching motion of the payload on the dynamic modes was considered.…”

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confidence: 99%