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首页> 外文期刊>Journal of Spacecraft and Rockets >Multibody Modeling and Simulation for Mars Phoenix Entry, Descent, and Landing
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Multibody Modeling and Simulation for Mars Phoenix Entry, Descent, and Landing

机译：火星凤凰号进入，下降和着陆的多体建模和仿真

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A multibody flight simulation for the Phoenix Mars Lander was developed that included high-fidelity six-degree-of-freedom rigid-body models for the parachute and lander system. The simulation predicted attitude and rate histories of all bodies throughout the flight. In so doing, a realistic behavior of the descending parachute/lander system dynamics was simulated that allowed assessment of the Phoenix descent performance and identification of sensitivities for landing. This simulation provided a complete end-to-end capability of modeling the entire entry, descent, and landing sequence for the mission. The simulation was used to predict the parachute and lander aerodynamic angles during entry and the response of the lander system to various wind models and windshears. Several different wind models were analyzed to determine which was most effective at exciting vehicle attitude dynamics. The simulation was used to drive a Monte Carlo analysis that provided a statistical evaluation of the performance capability of the Phoenix landing system.
机译：开发了凤凰火星着陆器的多体飞行模拟，其中包括用于降落伞和着陆器系统的高保真六自由度刚体模型。该模拟预测了整个飞行过程中所有物体的姿态和速率历史。在此过程中，模拟了降落伞/着陆器系统动力学下降的实际行为，从而可以评估Phoenix的下降性能并确定着陆的敏感性。该仿真提供了完整的端到端功能，可以为任务的整个进入，下降和着陆顺序建模。该模拟被用来预测进入期间的降落伞和着陆器空气动力学角度以及着陆器系统对各种风模型和风切变的响应。分析了几种不同的风模型，以确定哪种方法最有效地激发了车辆的姿态动态。该模拟用于驱动蒙特卡洛分析，该分析提供了Phoenix着陆系统性能的统计评估。

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