A 6DOF mathematical model of parachute in Mars EDL

Shen, Ganghui; Xia, Yuanqing; Sun, Haoran

doi:10.1016/j.asr.2015.01.029

Cited by 10 publications

(3 citation statements)

References 17 publications

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“…The aerodynamic force of the parachute is at the geometric center of the parachute canopy. The drag area of the main parachute increases with time and is a function of time [6]. Ignoring the inflation process of the guide parachute, only the aerodynamic parameter identification of the test parachute is considered.…”

Section: Modelingmentioning

confidence: 99%

Flight Trajectory Simulation and Aerodynamic Parameter Identification of Large-Scale Parachute

Cao

Wei

2020

International Journal of Aerospace Engineering

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In this paper, the multibody parachute-payload system is simplified and analyzed. A six-degree-of-freedom rigid body flight dynamic model is established to calculate the flight trajectory, attitude, velocity, and drop point of the parachute-payload system. Secondly, the random interference factors that may be encountered in the actual airdrop test of the parachute system are analyzed. According to the distribution law of the interference factors, they are introduced into the flight dynamic model. The Monte Carlo method is used to simulate the target and predict the flight trajectory and landing point distribution of the parachute system. The simulation results can provide technical support and theoretical basis for the parachute airdrop test. Finally, the genetic algorithm is used to identify the aerodynamic parameters of the large-scale Disk-Gap-Band parachute. The simulation results are in good agreement with the test results, which shows that the research method proposed in this paper can be applied to study practical engineering problems.

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Section: Modelingmentioning

confidence: 99%

Flight Trajectory Simulation and Aerodynamic Parameter Identification of Large-Scale Parachute

Cao

Wei

2020

International Journal of Aerospace Engineering

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“…The calculated snatch force was equal to the actual situation. Shen Guanghui et al [18] established a 6-DOF mathematical model of the Mars deceleration system. Ortega Enrique et al [19] accurately calculated the structural load and stress during parachute inflation based on the filling-time expansion model and Ludtke's area law.…”

Section: Introductionmentioning

confidence: 99%

Dynamic Simulation and Parameter Analysis of Weaved Composite Material for Unmanned Aerial Vehicle Parachute Recovery in Deployment Phase

Shi

Yue

et al. 2022

Crystals

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Aiming at the parachute recovery of fixed-wing unmanned aerial vehicles, a method of parachute deployment by tractor rocket is proposed. First, the tensile tests were carried out on high-strength polyethylene and brocade silk-weaved composite materials. The dynamic property parameters of the materials were obtained, which was the input for the dynamic model of the parachute deployment phase. Second, the model was verified by the experiment results. Finally, parachute weight and rocket launch temperature during the deployment phase were studied. The results showed that the dynamic model has good accuracy; as the parachute weight increases, the maximum snatch force of the extraction line and the sling decreases as the force on the suspension lines increases and the deployment effect worsens. With the temperature rise, the maximum snatch force on the extraction line, sling, and suspension lines increases and the deployment length changes slightly.

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“…There are two approaches to gain the aerodynamic coefficients of a parachute, one is the numerical computation [5][6][7][8][9][10][11][12][13][14][15][16] and the other is the wind tunnel test [17,18]. Among the parachute's descent process of deployment, inflation and terminal, the aerodynamic performances are so complex that the numerical computation method is usually not correct.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigations on Aerodynamic Characteristics of Parachutes in Mars Probe Decelerator System

Dong¹,

Yang²,

Yu³

et al. 2018

dtcse

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An experimental study is conducted to characterize the aerodynamic performances of two parachutes in the Mars probe decelerator system and the experiments are carried out in the 2.4 m×2.4 m transonic wind tunnel. The lift, drag and pitch moment coefficients versus the angle of attack from 0 to 25 degrees at Mach 0.4 and 0.8 are accurately measured and carefully analyzed. A novel mathematical model is proposed to express the aerodynamic characteristics of the parachutes. The obtained results show that the drag coefficient of the parachutes varies in a small range of 0.525~0.575 at Mach 0.4 and 0.8 as the angle of attack increases from 0 to 25 degrees. The simulated results of the propose model have a well agreement with the wind tunnel experimental data. The investigations in the present paper have a good significant to the engineering development of the parachutes in Mars probe decelerator system.

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A 6DOF mathematical model of parachute in Mars EDL

Cited by 10 publications

References 17 publications

Flight Trajectory Simulation and Aerodynamic Parameter Identification of Large-Scale Parachute

Flight Trajectory Simulation and Aerodynamic Parameter Identification of Large-Scale Parachute

Dynamic Simulation and Parameter Analysis of Weaved Composite Material for Unmanned Aerial Vehicle Parachute Recovery in Deployment Phase

Experimental Investigations on Aerodynamic Characteristics of Parachutes in Mars Probe Decelerator System

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