Dynamics analysis and simulation of six DOF parafoil system

Zhang, Zhixiang; Zhao, Zining; Fu, Yongling

doi:10.1007/s10586-018-1720-3

Cited by 13 publications

(5 citation statements)

References 19 publications

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“…Several works devoted to the development of control models, guidance systems, and trajectory optimization can be found in the literature [9][10][11][12][13][14][15]. Further, a representative number of computational fluid dynamics (CFD)-based aerodynamic characterization is available [6,[16][17][18][19][20].…”

Section: Structural Aspectsmentioning

confidence: 99%

“…Such an approach is scientifically relevant but moves away from the objective of minimizing instrumentation to deliver a suitable on-board system. An alternative way of separating the effects of internal flow using only differential pressure is to rely on computational simulations, setting averaged parameters (a, b) for Equations ( 13) and (14). Considering airflow speed of 10 m/s and AOA varying from 5 • to 15 • , simulation data revealed that, where the thickness is maximum (x = 0.21), the inner bottom pressure coefficient should be near 80 ± 5%, and the upper-pressure coefficient should be around 10 ± 5%.…”

Section: Pressure Coefficient (Cp) Distribution and Lift Estimationmentioning

confidence: 99%

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Wind-Tunnel Measurement of Differential Pressure on the Surface of a Dynamically Inflatable Wing Cell

Benedetti

Veras

2021

Aerospace

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An instrumentation system for in-situ measurement of the inner-outer pressure differential at the upper and lower surfaces of dynamically inflatable wings is designed and tested, revealing important insights into the aerodynamic characteristics of inflatable airfoils. Wind tunnel tests demonstrated full capability of low-pressure differential readings in the range of 1.0–120 Pa, covering speeds from 3 to 10 m/s at angles of attack from −20 to +25°. Readings were stable, presenting coefficients of variation from 2% to 7% over the operational flight envelope. The experimental data confirmed the occurrence of a bottom leading-edge recirculation bubble, linked to the low Reynolds regime and the presence of an air intake. It supported the proposition of a novel approach to aerodynamic characterization based on local pressure differentials, which takes in account the confined airflow structure and provides lift forces estimations compatible with practical observation. The results were also compatible with data previously obtained following different strategies and were shown to be effective for parameterizing the inflation and stall phenomena. Overall, the instrumentation may be applied straightforwardly as a flight-test equipment, and it can be further converted into collapse alert and prevention systems.

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Section: Structural Aspectsmentioning

confidence: 99%

Section: Pressure Coefficient (Cp) Distribution and Lift Estimationmentioning

confidence: 99%

Wind-Tunnel Measurement of Differential Pressure on the Surface of a Dynamically Inflatable Wing Cell

Benedetti

Veras

2021

Aerospace

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“…Currently, there are numerous ways to express models of powered parafoils. From a dynamics standpoint, this includes three-degree-offreedom (DOF) modeling [2], four-DOF modeling [3], six-DOF modeling [4], eight-DOF modeling [5], and nine-DOF modeling [6]. Among them, the eight-DOF model takes into account the slew, sway, yaw, heave, pitch, and roll motions, as well as the relative pitch and relative yaw motion between the parafoil canopy and the payload, which effectively describe the motion state of the actual parafoil [7].…”

Section: Introductionmentioning

confidence: 99%

Intelligent Trajectory Tracking Linear Active Disturbance Rejection Control of a Powered Parafoil Based on Twin Delayed Deep Deterministic Policy Gradient Algorithm Optimization

Zheng,

Fei,

Tao

et al. 2023

Applied Sciences

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Powered parafoils, known for their impressive load-bearing capacity and extended endurance, have garnered significant interest. However, the parafoil system is a highly complex nonlinear system. It primarily relies on the steering gear to change flight direction and utilizes a thrust motor for climbing. However, achieving precise trajectory tracking control presents a challenge due to the interdependence of direction and altitude control. Furthermore, underactuation and wind disturbances bring additional difficulties for trajectory tracking control. Consequently, realizing trajectory tracking control for powered parafoils holds immense significance. In this paper, we propose a trajectory tracking method based on Twin Delayed Deep Deterministic Policy Gradient (TD3) algorithm-optimized Linear Active Disturbance Rejection Control (LADRC). Our method addresses the underactuation issue by incorporating a guiding law while utilizing two LADRC methods to achieve decoupling and compensate for disturbances. Moreover, we employ the TD3 algorithm to dynamically adjust controller parameters, thus enhancing the controller performance. The simulation results demonstrate the effectiveness of our proposed method as a trajectory tracking control approach. Additionally, since the control process is not reliant on system-specific models, our method can also provide guidance for trajectory tracking control in other aircraft.

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“…But the trajectories generated through RRT usually are not smooth enough, which brings difficulty in guidance design. Some planning methods integrated with flight dynamics were used to produce continuous and smooth trajectories [12], [13], [14], [15]. Fowler and Rogers [16] designed the guidance path composed of multiple cubic Bézier curves, where the turn rate in each segment is limited within its maximum and the descent rate varies with the current yaw rate instead of being constant.…”

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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Dynamics analysis and simulation of six DOF parafoil system

Cited by 13 publications

References 19 publications

Wind-Tunnel Measurement of Differential Pressure on the Surface of a Dynamically Inflatable Wing Cell

Wind-Tunnel Measurement of Differential Pressure on the Surface of a Dynamically Inflatable Wing Cell

Intelligent Trajectory Tracking Linear Active Disturbance Rejection Control of a Powered Parafoil Based on Twin Delayed Deep Deterministic Policy Gradient Algorithm Optimization

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

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