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A study of angle parametric optimization of the composite honeycomb on turbine blade tip 涡轮叶尖复合蜂窝角度参数优化研究
Qingguo Kong, Jiaxin Ning, Xiaopeng Sun, Xiande Pan, Shuang Sun, Lehan Lu, Haixu Si
To reduce the secondary flow loss of the high-pressure turbine caused by the tip leakage flow, the design of the composite honeycomb tip has been experimentally and numerically examined in this study. The arrangement angle of the composite honeycomb is defined and optimized using the radial basis function and genetic algorithm. The tip flow field of the high-pressure turbine blade with a 2.128 mm clearance is simulated by CFX 18.0, and the arrangement angle of the composite honeycomb is optimized to obtain a lower loss. Moreover, the flat tip, basic honeycomb tip, and optimized honeycomb tip are tested in a low-speed cascade test facility. The results show that the vortices and radial velocity induced by the honeycomb structure cavity increase the kinetic energy loss of the leakage flow and reduce the leakage flow rate. Compared with the basic honeycomb, the optimized honeycomb has a supplemental blocking effect on the tip leakage flow by reducing the crosswise pressure gradient in the blade tip. The optimized honeycomb also changes the outlet angle of the leakage flow in the tip clearance, reduces the leakage vortex, and the total pressure loss is further reduced by 2.5%.
为了减少高压涡轮机因叶尖漏流造成的二次流损失,本研究对复合蜂窝叶尖的设计进行了实验和数值检验。利用径向基函数和遗传算法定义并优化了复合蜂窝的排列角度。利用 CFX 18.0 模拟了间隙为 2.128 毫米的高压涡轮叶片的叶尖流场,并优化了复合蜂窝的排列角度,以获得更低的损耗。此外,还在低速级联试验设备中测试了扁平叶尖、基本蜂窝叶尖和优化蜂窝叶尖。结果表明,蜂窝结构空腔引起的涡流和径向速度增加了泄漏流的动能损失,降低了泄漏流速。与基本蜂窝相比,优化蜂窝通过降低叶尖横向压力梯度,对叶尖泄漏流具有补充阻挡作用。优化蜂窝还改变了叶尖间隙中泄漏流的出口角,减少了泄漏涡流,总压力损失进一步降低了 2.5%。
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引用次数: 0
Development and flight test of a manned electric propulsion lightweight airplane 载人电力推进轻型飞机的开发和飞行试验
Hyun-gi Kim, Sungchan Kim
Electrically powered airplanes can cope with global warming by reducing the use of fossil fuels and reduce airplane costs in the long run through the efficient use of energy. For this reason, advanced aviation countries such as the United States and several countries in the European Union are leading the development of innovative technologies to realize a fully electric airplane in the future. Currently, research and development efforts are underway domestically to convert existing two-seater airplanes into electric-powered airplanes. In this study, the KLA-100X, which was developed by converting the existing two-seat lightweight sport airplane KLA-100 into an electric propulsion airplane, was introduced. In this text, the main specifications, design characteristics, and performance of KLA-100X are examined. In addition, the performance of the major components of the propulsion system, in this case the propulsion motor, inverter, and battery developed for application to KLA-100X are assessed, and the control system, additionally altered according to electric propulsion modification, is explained. Finally, the applicability of the developed major components to an electric propulsion airplane is confirmed by conducting ground and flight tests on the KLA-100X and presenting the results. In the future, the expansion of research aimed at improving the performance of current electric propulsion airplanes can be reviewed through the development of a dedicated platform for an electric propulsion airplane.
从长远来看,电动飞机可以通过减少化石燃料的使用来应对全球变暖,并通过有效利用能源来降低飞机成本。因此,美国和欧盟一些国家等航空业发达国家正在引领创新技术的发展,以在未来实现全电动飞机。目前,国内正在努力研发将现有双座飞机改装成电动飞机。本研究介绍了将现有双座轻型运动飞机 KLA-100 改装为电力推进飞机而研制的 KLA-100X。本文对 KLA-100X 的主要规格、设计特点和性能进行了研究。此外,还评估了推进系统主要组件的性能,这里指的是为 KLA-100X 研发的推进电机、逆变器和电池。最后,通过在 KLA-100X 上进行地面和飞行测试,确认了所开发的主要组件在电力推进飞机上的适用性,并介绍了测试结果。今后,可通过开发电力推进飞机的专用平台来审查旨在提高当前电力推进飞机性能的研究扩展情况。
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引用次数: 0
Development and flight test of a manned electric propulsion lightweight airplane 载人电力推进轻型飞机的开发和飞行试验
Hyun-gi Kim, Sungchan Kim
Electrically powered airplanes can cope with global warming by reducing the use of fossil fuels and reduce airplane costs in the long run through the efficient use of energy. For this reason, advanced aviation countries such as the United States and several countries in the European Union are leading the development of innovative technologies to realize a fully electric airplane in the future. Currently, research and development efforts are underway domestically to convert existing two-seater airplanes into electric-powered airplanes. In this study, the KLA-100X, which was developed by converting the existing two-seat lightweight sport airplane KLA-100 into an electric propulsion airplane, was introduced. In this text, the main specifications, design characteristics, and performance of KLA-100X are examined. In addition, the performance of the major components of the propulsion system, in this case the propulsion motor, inverter, and battery developed for application to KLA-100X are assessed, and the control system, additionally altered according to electric propulsion modification, is explained. Finally, the applicability of the developed major components to an electric propulsion airplane is confirmed by conducting ground and flight tests on the KLA-100X and presenting the results. In the future, the expansion of research aimed at improving the performance of current electric propulsion airplanes can be reviewed through the development of a dedicated platform for an electric propulsion airplane.
从长远来看,电动飞机可以通过减少化石燃料的使用来应对全球变暖,并通过有效利用能源来降低飞机成本。因此,美国和欧盟一些国家等航空业发达国家正在引领创新技术的发展,以在未来实现全电动飞机。目前,国内正在努力研发将现有双座飞机改装成电动飞机。本研究介绍了将现有双座轻型运动飞机 KLA-100 改装为电力推进飞机而研制的 KLA-100X。本文对 KLA-100X 的主要规格、设计特点和性能进行了研究。此外,还评估了推进系统主要组件的性能,这里指的是为 KLA-100X 研发的推进电机、逆变器和电池。最后,通过在 KLA-100X 上进行地面和飞行测试,确认了所开发的主要组件在电力推进飞机上的适用性,并介绍了测试结果。今后,可通过开发电力推进飞机的专用平台来审查旨在提高当前电力推进飞机性能的研究扩展情况。
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引用次数: 0
Optimal sliding mode guidance law against maneuvering target with impact angle constraint 针对具有撞击角约束的机动目标的最佳滑模制导法
Mian Gong, Siteng Zhou, Di Zhou
In this paper, an optimal sliding mode guidance law with impact angle constraint is proposed against maneuvering targets. Firstly, the impact angle frame for a static target is extended to a maneuvering target. Then, in this impact angle frame, the optimal reaching law of sliding mode is proposed to design an optimal sliding mode guidance law which is robust to target maneuvers and satisfies an impact angle constraint. The optimal sliding mode guidance law with impact angle constraint is also extended to the three-dimensional case. Numerical simulations in different scenarios with a realistic missile model show that the guidance law can intercept a maneuvering target with a desired impact angle, and the control effort is close to the optimal value, which verifies that the proposed optimal sliding mode guidance law has both robustness and optimality.
本文针对机动目标提出了一种带有撞击角约束的最佳滑模制导法则。首先,将静态目标的撞击角框架扩展到机动目标。然后,在这一撞击角框架内,提出滑动模式的最优到达规律,设计出对目标机动具有鲁棒性且满足撞击角约束的最优滑动模式制导规律。带撞击角约束的最佳滑动模式制导法则也被扩展到三维情况。利用现实导弹模型在不同场景下进行的数值模拟表明,该制导法则能以所需的撞击角拦截机动目标,且控制努力接近最优值,这验证了所提出的最优滑模制导法则具有鲁棒性和最优性。
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引用次数: 0
Rapid trajectory generation for quadrotor with limited motor speed 为电机速度受限的四旋翼飞行器快速生成轨迹
Shikai Shao, Yi Guo, Yuanjie Zhao
Planning a safe and dynamic flyable trajectory for unmanned aerial vehicle (UAV) is the precondition for autonomous flight. Considering environmental complexity and flight safety under limited motor speed, we proposed a new time-segmented trajectory planning method, which can ensure motor speed within the allowable range and achieve safe flight. Firstly, the candidate trajectory for quadrotor UAV is expressed by high-order polynomials. Herein, polynomial is used as the expression of trajectory, and nonlinear programming (NLP) is used to calculate polynomial coefficient. Then, two strategies and an initial value calculation method are proposed to improve the efficiency of NLP. Furthermore, aiming at the problem that the initial trajectory of UAV motor cannot meet the current speed limit constraint after the motor speed drops, an adjustment strategy based on feasible trajectory is designed. The method presented in this paper not only enhances flexibility of the flight process, improves solving efficiency of the algorithm but also enables UAV to continue flying when the motor speed is limited. Finally, simulation analysis and comparison illustrate the effectiveness and superiority of the proposed method.
为无人飞行器(UAV)规划安全、动态的可飞轨迹是实现自主飞行的前提。考虑到环境的复杂性和有限电机转速下的飞行安全性,我们提出了一种新的分时轨迹规划方法,该方法可确保电机转速在允许范围内,实现安全飞行。首先,四旋翼无人机的候选轨迹由高阶多项式表示。在这里,多项式被用作轨迹的表达式,非线性编程(NLP)被用来计算多项式系数。然后,提出了两种策略和一种初始值计算方法,以提高 NLP 的效率。此外,针对电机转速下降后无人机电机初始轨迹无法满足当前限速约束的问题,设计了基于可行轨迹的调整策略。本文提出的方法不仅增强了飞行过程的灵活性,提高了算法的求解效率,还能使无人机在电机转速受限时继续飞行。最后,仿真分析和比较说明了所提方法的有效性和优越性。
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引用次数: 0
Optimal sliding mode guidance law against maneuvering target with impact angle constraint 针对具有撞击角约束的机动目标的最佳滑模制导法
Mian Gong, Siteng Zhou, Di Zhou
In this paper, an optimal sliding mode guidance law with impact angle constraint is proposed against maneuvering targets. Firstly, the impact angle frame for a static target is extended to a maneuvering target. Then, in this impact angle frame, the optimal reaching law of sliding mode is proposed to design an optimal sliding mode guidance law which is robust to target maneuvers and satisfies an impact angle constraint. The optimal sliding mode guidance law with impact angle constraint is also extended to the three-dimensional case. Numerical simulations in different scenarios with a realistic missile model show that the guidance law can intercept a maneuvering target with a desired impact angle, and the control effort is close to the optimal value, which verifies that the proposed optimal sliding mode guidance law has both robustness and optimality.
本文针对机动目标提出了一种带有撞击角约束的最佳滑模制导法则。首先,将静态目标的撞击角框架扩展到机动目标。然后,在这一撞击角框架内,提出滑动模式的最优到达规律,设计出对目标机动具有鲁棒性且满足撞击角约束的最优滑动模式制导规律。带撞击角约束的最佳滑动模式制导法则也被扩展到三维情况。利用现实导弹模型在不同场景下进行的数值模拟表明,该制导法则能以所需的撞击角拦截机动目标,且控制努力接近最优值,这验证了所提出的最优滑模制导法则具有鲁棒性和最优性。
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引用次数: 0
Rapid trajectory generation for quadrotor with limited motor speed 为电机速度受限的四旋翼飞行器快速生成轨迹
Shikai Shao, Yi Guo, Yuanjie Zhao
Planning a safe and dynamic flyable trajectory for unmanned aerial vehicle (UAV) is the precondition for autonomous flight. Considering environmental complexity and flight safety under limited motor speed, we proposed a new time-segmented trajectory planning method, which can ensure motor speed within the allowable range and achieve safe flight. Firstly, the candidate trajectory for quadrotor UAV is expressed by high-order polynomials. Herein, polynomial is used as the expression of trajectory, and nonlinear programming (NLP) is used to calculate polynomial coefficient. Then, two strategies and an initial value calculation method are proposed to improve the efficiency of NLP. Furthermore, aiming at the problem that the initial trajectory of UAV motor cannot meet the current speed limit constraint after the motor speed drops, an adjustment strategy based on feasible trajectory is designed. The method presented in this paper not only enhances flexibility of the flight process, improves solving efficiency of the algorithm but also enables UAV to continue flying when the motor speed is limited. Finally, simulation analysis and comparison illustrate the effectiveness and superiority of the proposed method.
为无人飞行器(UAV)规划安全、动态的可飞轨迹是实现自主飞行的前提。考虑到环境的复杂性和有限电机转速下的飞行安全性,我们提出了一种新的分时轨迹规划方法,该方法可确保电机转速在允许范围内,实现安全飞行。首先,四旋翼无人机的候选轨迹由高阶多项式表示。在这里,多项式被用作轨迹的表达式,非线性编程(NLP)被用来计算多项式系数。然后,提出了两种策略和一种初始值计算方法,以提高 NLP 的效率。此外,针对电机转速下降后无人机电机初始轨迹无法满足当前限速约束的问题,设计了基于可行轨迹的调整策略。本文提出的方法不仅增强了飞行过程的灵活性,提高了算法的求解效率,还能使无人机在电机转速受限时继续飞行。最后,仿真分析和比较说明了所提方法的有效性和优越性。
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引用次数: 0
Calculate the ignition height of the vertical landing phase online for the reusable rocket 在线计算可重复使用火箭垂直着陆阶段的点火高度
Guanghui Cheng, W. Jing, C. Gao
For the vertical landing phase of the reusable rocket, in order to improve the landing accuracy with consideration of multiple uncertainties, a novel strategy to calculate the ignition height online is proposed based on polynomial guidance law (PGL), particle swarm optimization (PSO), and deep reinforcement learning (DRL). Firstly, a deep neural network (DNN) is designed to describe the relationship between the state of the reusable rocket and the ignition height. To accomplish the guidance task of the vertical landing phase, PGL is modified by introducing the estimated aerodynamic acceleration. Through simulation, the output range of the DNN is estimated by the modified PSO. Then, the reward function is shaped and the parameters of the DNN are trained on a training set of simulation scenarios by the DRL algorithm. Finally, to demonstrate the effectiveness of the proposed strategy, the trained DNN is used to calculate the ignition height of 1500 unlearned simulation scenarios online. The numerical simulation results show that the proposed strategy has higher landing accuracy and lower fuel consumption than the offline strategy of fixed ignition height based on the modified PSO.
针对可重复使用火箭的垂直着陆阶段,为了在考虑多种不确定性的情况下提高着陆精度,提出了一种基于多项式制导法则(PGL)、粒子群优化(PSO)和深度强化学习(DRL)的在线计算点火高度的新策略。首先,设计了一个深度神经网络(DNN)来描述可重复使用火箭的状态与点火高度之间的关系。为了完成垂直着陆阶段的制导任务,通过引入估计的气动加速度对 PGL 进行了修改。通过仿真,修正后的 PSO 估算了 DNN 的输出范围。然后,通过 DRL 算法在模拟场景训练集上形成奖励函数并训练 DNN 的参数。最后,为了证明所提策略的有效性,利用训练好的 DNN 在线计算了 1500 个未学习模拟场景的点火高度。数值模拟结果表明,与基于改进 PSO 的离线固定点火高度策略相比,所提出的策略具有更高的着陆精度和更低的燃料消耗。
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引用次数: 0
Calculate the ignition height of the vertical landing phase online for the reusable rocket 在线计算可重复使用火箭垂直着陆阶段的点火高度
Guanghui Cheng, W. Jing, C. Gao
For the vertical landing phase of the reusable rocket, in order to improve the landing accuracy with consideration of multiple uncertainties, a novel strategy to calculate the ignition height online is proposed based on polynomial guidance law (PGL), particle swarm optimization (PSO), and deep reinforcement learning (DRL). Firstly, a deep neural network (DNN) is designed to describe the relationship between the state of the reusable rocket and the ignition height. To accomplish the guidance task of the vertical landing phase, PGL is modified by introducing the estimated aerodynamic acceleration. Through simulation, the output range of the DNN is estimated by the modified PSO. Then, the reward function is shaped and the parameters of the DNN are trained on a training set of simulation scenarios by the DRL algorithm. Finally, to demonstrate the effectiveness of the proposed strategy, the trained DNN is used to calculate the ignition height of 1500 unlearned simulation scenarios online. The numerical simulation results show that the proposed strategy has higher landing accuracy and lower fuel consumption than the offline strategy of fixed ignition height based on the modified PSO.
针对可重复使用火箭的垂直着陆阶段,为了在考虑多种不确定性的情况下提高着陆精度,提出了一种基于多项式制导法则(PGL)、粒子群优化(PSO)和深度强化学习(DRL)的在线计算点火高度的新策略。首先,设计了一个深度神经网络(DNN)来描述可重复使用火箭的状态与点火高度之间的关系。为了完成垂直着陆阶段的制导任务,通过引入估计的气动加速度对 PGL 进行了修改。通过仿真,修正后的 PSO 估算了 DNN 的输出范围。然后,通过 DRL 算法在模拟场景训练集上形成奖励函数并训练 DNN 的参数。最后,为了证明所提策略的有效性,利用训练好的 DNN 在线计算了 1500 个未学习模拟场景的点火高度。数值模拟结果表明,与基于改进 PSO 的离线固定点火高度策略相比,所提出的策略具有更高的着陆精度和更低的燃料消耗。
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引用次数: 0
Characterization modeling of wake vortex circulation decay under reasonable worst case conditions with cuckoo search algorithm 利用布谷鸟搜索算法建立合理最坏情况下的尾流涡旋环流衰减特性模型
Ridvan Oruc, T. Baklacioglu, Ozlem Sahin
Wake vortex (WV) produced by a large aircraft has the potential to cause serious damage to smaller aircraft following it. In this context, characterization of WV circulation decay under the reasonable worst case (RWC) conditions allows the separation minima to be found safely. In this study, modeling of dimensionless decay curves, which were developed using three experimental LIDAR (Light Detection and Ranging) datasets in the RECAT-EU project and is a useful tool to characterize the wake vortex circulation decay under RWC conditions, was carried out using cuckoo search algorithm (CSA). The decay curves used in the modeling are the median (P50), 10th (P10), and 90th (P90) percentile decay curves of the RWC tracks, which constitute the top 2% longest lasting wakes. The fact that the correlation coefficient (R) values are very close to 1 for all datasets as a result of the error analysis shows that the prediction success of the CSA model is quite high.
大型飞机产生的尾流涡旋(WV)有可能对尾随其后的小型飞机造成严重损害。在这种情况下,在合理的最坏情况(RWC)条件下对 WV 环流衰减进行表征,可以安全地找到分离最小值。在本研究中,使用布谷鸟搜索算法(CSA)对无量纲衰减曲线进行了建模。无量纲衰减曲线是利用 RECAT-EU 项目中的三个激光雷达(光探测和测距)实验数据集开发的,是描述 RWC 条件下尾涡环流衰减特征的有用工具。建模中使用的衰减曲线是 RWC 轨道的中位数(P50)、第 10 百分位数(P10)和第 90 百分位数(P90)衰减曲线,它们构成了持续时间最长的前 2% 纬流。误差分析结果表明,所有数据集的相关系数 (R) 值都非常接近 1,这表明 CSA 模型的预测成功率相当高。
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引用次数: 0
期刊
Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
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