Modeling and Simulation of the Second-Generation Orion Crew Module Airbag Landing System

Timmers, Richard B.; Hardy, Robin C.; Willey, Cliff E.; Welch, Joseph V.

doi:10.2514/6.2009-6593

Cited by 6 publications

(3 citation statements)

References 2 publications

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“…Combined airbags are the most widely used. Both ILC Dover and Airborne Systems North America have designed the cushioning airbag system for the Crew Exploration Vehicle (CEV) [3,4] by using combined airbags. This system is composed of several combined airbags, all of which exhibit excellent cushioning performance to achieve functions such as deceleration, reducing impact Aerospace 2024, 11, 169 2 of 17 overload and avoiding the problems of tipping and sinking.…”

Section: Introductionmentioning

confidence: 99%

Multi-Objective Optimization Design of an Origami-Inspired Combined Cushion Airbag

Xu,

Yang,

Huang

et al. 2024

Aerospace

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To improve the cushioning performance of soft-landing systems, a novel origami-inspired combined cushion airbag is proposed. The geometry size, initial pressure, and exhaust vent area of the cushion airbags are designed preliminarily using a theoretical model. The finite element models, including the returnable spacecraft and cushion airbags, are established via the control volume method (CVM) to analyze the impact dynamic behavior and cushioning performance during the landing attenuation process. The cushioning performance of the cushion airbags in complex landing environments are studied to investigate the influence of horizontal velocity, lateral velocity and nonhorizontal landing surfaces. Four design parameters of the cushion airbags, including the initial pressure, venting threshold pressure, exhaust vent area and polygon edge number, are employed to study their influence on the cushioning performance. A multi-objective optimization model of the cushion airbags based on the neural network and multi-objective water cycle algorithm is established to realize the rapid optimization design. The Pareto front of the maximum overload and specific energy absorption is obtained. The analysis results show that the maximum overload of the proposed combined cushion airbags is 7.30 g. The system with the anti-rollover design can avoid rollover and achieve outstanding cushioning performance in complex landing environments. The maximum overload of the returning spacecraft is decreased by 16.4% from 7.30 g to 6.10 g after multi-objective optimizations. This study could provide the technical support for the soft-landing system design of returnable spacecrafts.

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Section: Introductionmentioning

confidence: 99%

Multi-Objective Optimization Design of an Origami-Inspired Combined Cushion Airbag

Xu,

Yang,

Huang

et al. 2024

Aerospace

View full text Add to dashboard Cite

show abstract

“…He et al [5] investigated an impact FE model for an airbag landing buffer system. Timmers et al [6] carried out simulation and experimental studies surrounding a second generation of the airbag design developed by ILC Dover, building off of relevant first-generation design, analysis, and testing efforts. Wang et al [7] analyzed the deployment and buffer process of the airbag system using FE based on a single-point Gaussian integral to improve the calculation efficiency.…”

Section: Introductionmentioning

confidence: 99%

Similarity Design Method of the Inflatable Buffer Landing System

Wang

2019

International Journal of Aerospace Engineering

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The inflatable buffer landing system, such as the airbag, has been widely used for deep space exploration as a low-cost entry. The impact performance of an airbag landing attenuation system on Mars had to be proven through cushion testing on Earth. In this paper, a design method for the airbag landing attenuation system on Earth is proposed based on similarity relation. With this method, the impact response of the spherical airbag landing attenuation system is derived based on assumptions, and the principal factors have great influence on the impact response of the landing system have been proved. Then, the similarity relation between the full-scale airbag landing attenuation system in the Martian atmosphere and its Earth prototype is obtained through theoretical derivation. Finally, the proposed similarity relationship has been tested on several ground prototypes by FEA. The results of the study show that the Earth prototype by the developed design method is capable of predicting the impact response with good accuracy.

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“…In view of its nonlinear characteristics, the most commonly used control is PID control, but there is still a problem of low control accuracy. With the continuous development of computer vision technology, visual feedback servo control technology is used by more and more experts and scholars to control nonlinear systems with its characteristics of fast response, stability, and robustness [5][6][7][8].…”

Section: Introductionmentioning

confidence: 99%

Dynamic Linear Predictive Optimization of Flexible Robot Profiling MFA Model

Lin

2019

Journal of Sensors

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As the airbag of a flexible robot is affected by external environmental factors during the profiling process, there are many uncertainties in the process of deformation of the airbag. For this reason, the general nonlinear control strategy cannot obtain an accurate data model. In this paper, a flexible robot profiling MFA (Model-Free Adaptive) model based on adaptive predictive dynamic linear optimization is proposed. Firstly, the real-time thickness of the airbag is obtained through edge detection by using the image processing algorithm. Secondly, the airbag aerodynamic model is constructed by visual servo control strategy. Then, a nonlinear control system based on model-free adaptive control is established. Thirdly, the weighting factor is used to limit the variation range of the input quantity, and the deviation of the actual value and the expected value is corrected by the adaptive prediction mechanism. Finally, the servo control the airbag is completed. The experimental results show that the improved model proposed in this paper solves the overshoot phenomenon of the standard control model with less control error and higher robustness.

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Modeling and Simulation of the Second-Generation Orion Crew Module Airbag Landing System

Cited by 6 publications

References 2 publications

Multi-Objective Optimization Design of an Origami-Inspired Combined Cushion Airbag

Multi-Objective Optimization Design of an Origami-Inspired Combined Cushion Airbag

Similarity Design Method of the Inflatable Buffer Landing System

Dynamic Linear Predictive Optimization of Flexible Robot Profiling MFA Model

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