Aerospace Science and Technology最新文献_第6页

A comprehensive investigation of the effect of hole diameter and number on film cooling performance of rotating blade leading edge 孔径和孔数对旋转叶片前缘薄膜冷却性能影响的综合研究

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-18 DOI: 10.1016/j.ast.2024.109659

Meng Gu , Hai-wang Li , Zhi-yu Zhou , Gang Xie , Song Liu , Yu-zhu Lou

The combined effect of film hole number and diameter on the film cooling were investigated on the rotating blade leading edge by using experimental and numerical methods. The film cooling performance was obtained by pressure sensitive paint technique under rotational condition. To better understand the experimental results, the flow fields obtained from numerical simulation were also analyzed. The effects of hole length-to-diameter ratio (L/d = 2.5/5/7.5), hole number (N = 7/9/10/11/13), hole diameter(d = 0.64∼1.26 mm), Hole to hole pitch, (P/d = 6.3∼9.2) and hole exit area (A_hole/A_LE=4 %-14 %) on the film cooling performance are investigated. Five blowing ratios are also employed (M = 0.5 to 2.0). The results indicate that the hole length-to-diameter ratios (L/d = 2.5∼7.5) have a negligible influence on the film cooling effectiveness. Both the film hole number (N = 10/13) and the hole diameter (d = 0.64/0.75 mm) monotonically affect the film cooling performance under each blowing ratios. However, a comprehensive study indicates that there is a significant quadratic correlation between the area-averaged cooling effectiveness and the total film hole exit area for different combinations of hole number and diameter. Meanwhile, there is an optimal film hole exit area on the leading edge and it increases as the blowing ratio or mass flow rate increases.

通过实验和数值方法研究了薄膜孔数和直径对旋转叶片前缘薄膜冷却的综合影响。通过压敏涂料技术获得了旋转条件下的薄膜冷却性能。为了更好地理解实验结果，还对数值模拟得到的流场进行了分析。研究了孔长径比 (L/d = 2.5/5/7.5)、孔数 (N = 7/9/10/11/13)、孔直径 (d = 0.64∼1.26 mm)、孔间距 (P/d = 6.3∼9.2) 和孔出口面积 (Ahole/ALE=4 %-14 %) 对薄膜冷却性能的影响。同时还采用了五种吹气比（M = 0.5 至 2.0）。结果表明，孔的长径比（L/d = 2.5∼7.5）对薄膜冷却效果的影响微乎其微。薄膜孔数（N = 10/13）和孔径（d = 0.64/0.75 mm）对各吹气比下的薄膜冷却性能均有单调影响。然而，综合研究表明，在不同的孔数和孔径组合下，区域平均冷却效果与薄膜孔出口总面积之间存在显著的二次相关性。同时，前缘存在一个最佳薄膜孔出口面积，它随着吹气比或质量流量的增加而增大。

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引用次数: 0

Real-time adaptive model of mainstream parameters for aircraft engines based on OSELM-EKF 基于 OSELM-EKF 的飞机发动机主流参数实时自适应模型

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-18 DOI: 10.1016/j.ast.2024.109662

Yingchen Guo , Jiazhu Teng , Xin Zhou , Zelong Zou , Jinquan Huang , Feng Lu

Gas path parameters play a crucial role in the health management of aeroengines, which are usually generated from the nonlinear component-level model. However, risks of stability and substantial time consumption confine online applications of conventional models. This paper proposes a mainstream parameter model that exclusively involves rotating components using fewer gas path parameters, including an adaptive strategy based on an online sequential extreme learning machine and an extended Kalman filter. The mainstream parameter model is designed in a linear parameter-varying form with a non-iterative smooth state-switching mechanism and enables real-time operation by simplifying the component complexity. Besides, some sensor measurements are employed to update rotor speeds, thus eliminating the need for derivative computations. Neural networks are introduced in compressor component calculations. Additionally, the extended Kalman filter is developed to estimate health parameters to tune the system equation residuals, and the learning machine is applied to compensate for rotating components’ pressure ratios under different degradation magnitudes. Finally, systematic tests are carried out to evaluate the computation accuracy and fast capabilities of the mainstream parameter adaptive model in various scenarios. Simulations demonstrate the proposed methodology's superiority over traditional adaptive correction schemes.

气路参数在航空发动机的健康管理中起着至关重要的作用，这些参数通常由非线性组件级模型生成。然而，稳定性风险和大量时间消耗限制了传统模型的在线应用。本文提出了一种主流参数模型，只涉及旋转部件，使用较少的气体路径参数，包括基于在线顺序极限学习机和扩展卡尔曼滤波器的自适应策略。主流参数模型以线性参数变化形式设计，采用非迭代平滑状态切换机制，通过简化组件复杂性实现实时运行。此外，一些传感器测量值可用于更新转子速度，因此无需进行导数计算。在压缩机组件计算中引入了神经网络。此外，还开发了扩展卡尔曼滤波器来估计健康参数，以调整系统方程残差，并应用学习机来补偿不同退化幅度下的旋转部件压力比。最后，还进行了系统测试，以评估主流参数自适应模型在各种情况下的计算精度和快速能力。仿真证明了所提出的方法优于传统的自适应修正方案。

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引用次数: 0

Distributed two-channel dynamic event-triggered adaptive finite-time fault-tolerant containment control for multi-leader UAV formations 多领航无人机编队的分布式双通道动态事件触发自适应有限时间容错遏制控制

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-18 DOI: 10.1016/j.ast.2024.109678

Lihao Wang , Aijun Li , Fuqiang Di , Hongshi Lu , Changqing Wang

This paper addresses the distributed adaptive finite-time containment control problem in multi-leader UAV formations with actuator failures, limited communication, and external disturbances. A two-channel dynamic event-triggered strategy based on adaptive and sliding mode control is proposed as a containment control scheme, which solves the contradiction between the need to include containment error in the continuous term of the sliding mode surface in the adaptive law and the discontinuity of the communication between neighboring subsystems (follower UAVs) by constructing intermediate variables. Unlike the traditional event triggering condition that can only be applied to asymptotically convergent systems, the dynamic triggering condition designed in this paper, based on auxiliary variables, hyperbolic tangent function, and adaptive techniques, realizes finite-time convergence during the adjustment of the system and sets a more reasonable lower limit for the triggering thresholds, thus further reducing the communication frequency and ensuring the finite-time convergence of the system. The stability of the closed-loop system can be proved by the Lyapunov theorem. Zeno behavior can be avoided. The simulation results verify the effectiveness of the developed control algorithm.

本文探讨了多领航无人机编队中的分布式自适应有限时间遏制控制问题，该编队具有致动器故障、通信受限和外部干扰等问题。本文提出了一种基于自适应控制和滑模控制的双通道动态事件触发策略作为遏制控制方案，通过构建中间变量，解决了自适应法则中滑模面连续项包含遏制误差的必要性与相邻子系统（跟随者无人机）之间通信不连续性之间的矛盾。与传统的事件触发条件只能适用于渐近收敛系统不同，本文设计的动态触发条件基于辅助变量、双曲正切函数和自适应技术，在系统调整过程中实现了有限时间收敛，并为触发阈值设定了更合理的下限，从而进一步降低了通信频率，保证了系统的有限时间收敛性。闭环系统的稳定性可由李雅普诺夫定理证明。可以避免 Zeno 行为。仿真结果验证了所开发控制算法的有效性。

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引用次数: 0

Multifidelity approach to the numerical aeroelastic simulation of flexible membrane wings 采用多保真度方法对柔性膜翼进行气动弹性数值模拟

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-18 DOI: 10.1016/j.ast.2024.109673

A.J. Torregrosa, A. Gil, P. Quintero, A. Cremades

Due to their lightness, the capacity to adapt to the flow conditions, and the safety when operating near humans, the use of membrane-resistant structures has increased in fields as micro aerial vehicles and yachts sails. This work focuses on the computational methodology required for simulating the aeroelastic coupling of the structure with the incident wind flow. A semi-monocoque structure (composed of a main spar, a set of ribs, and an external membrane) inside a wind tunnel is simulated using two different methodologies. Firstly, a complete fluid-structure interaction is calculated by combining the finite element methodology for the solid and the unsteady Reynolds average Navier-Stokes computational fluid dynamics for the air, including nonlinear effects and prestress. Then, a low-fidelity model is applied, obtaining the linear aeroelastic eigenvalues and the temporal response of the wing. Both methodologies results are in agreement with estimating the transient mean deformation and flutter velocity. However, the modal analysis tends to overestimate the aeroelastic effects, as it calculates potential aerodynamics, predicting an instability velocity lower than that provided by the transient simulations.

由于抗膜结构重量轻、适应流动条件的能力强，而且在靠近人体的情况下运行安全，因此在微型飞行器和游艇风帆等领域的应用越来越多。这项工作的重点是模拟结构与入射风流的气动弹性耦合所需的计算方法。采用两种不同的方法对风洞内的半单体结构（由主梁、一组肋骨和外部薄膜组成）进行了模拟。首先，结合固体的有限元方法和空气的非稳态雷诺平均纳维-斯托克斯流体力学计算方法（包括非线性效应和预应力），计算出完整的流固相互作用。然后，应用低保真模型，获得机翼的线性气动弹性特征值和时间响应。这两种方法的结果与估计瞬态平均变形和扑翼速度的结果一致。然而，模态分析往往会高估气动弹性效应，因为它计算的是潜在的空气动力学，预测的失稳速度低于瞬态模拟提供的速度。

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引用次数: 0

The decoupled effect of oxidizer mass flux and combustion pressure on turbulent combustion characteristics of finite-length solid fuel 氧化剂质量通量和燃烧压力对有限长度固体燃料湍流燃烧特性的解耦效应

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-18 DOI: 10.1016/j.ast.2024.109661

Hanqing Xia, Ningfei Wang, Jiantao Pang, Yiming Zhang, Ran Wang, Yi Wu

Combustion pressure and oxidizer mass flux are key factors influencing the performance of hybrid rocket motors. In the present work, the decoupled effects of oxidizer mass flux and combustion pressure on turbulent combustion characteristics were investigated. First, a finite-length combustion theory of fuel grains was developed to identify the main sensitive parameters, including flame structure and the recirculation zone, which affect the combustion of solid fuel. Then, a two-dimensional transient numerical model, based on the coupling characteristics of the heat transfer process in solid fuel grains and dynamic combustion flow, was developed and validated through fire experiments under a wide range of inflow conditions. A quantitative analysis was conducted to assess the impact of flame structure and the recirculation zone on the dynamic combustion characteristics of finite-length solid fuel. The results showed that the fuel characteristic temperatures of the front and central parts are negatively correlated with flame height, while the characteristic temperature of the rear part is positively correlated with the recirculation zone temperature. Both the mass flow rate and combustion pressure are negatively correlated with flame height and positively correlated with the temperature of the recirculation zone. Compared to combustion pressure, the influence of mass flow rate is more significant. The transient processes of the solid fuel regression rate under different inflow conditions exhibit a consistent tendency: an increase in mass flow flux and combustion pressure results in faster attainment of peak regression rate and stabilization.

燃烧压力和氧化剂质量通量是影响混合火箭发动机性能的关键因素。在本研究中，研究了氧化剂质量通量和燃烧压力对湍流燃烧特性的解耦影响。首先，建立了燃料颗粒的有限长度燃烧理论，确定了影响固体燃料燃烧的主要敏感参数，包括火焰结构和再循环区。然后，根据固体燃料颗粒传热过程和动态燃烧流的耦合特性，建立了二维瞬态数值模型，并通过多种流入条件下的火灾实验进行了验证。定量分析评估了火焰结构和再循环区对有限长度固体燃料动态燃烧特性的影响。结果表明，前部和中部的燃料特征温度与火焰高度呈负相关，而后部的特征温度与再循环区温度呈正相关。质量流量和燃烧压力与火焰高度呈负相关，而与再循环区温度呈正相关。与燃烧压力相比，质量流量的影响更为显著。不同流入条件下固体燃料回归率的瞬态过程表现出一致的趋势：质量流量和燃烧压力的增加导致回归率更快达到峰值并趋于稳定。

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引用次数: 0

Research status and development trend of air-breathing high-speed vehicle/engine integration 喷气式高速飞行器/发动机集成的研究现状和发展趋势

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-18 DOI: 10.1016/j.ast.2024.109675

Shibin Luo , Yuhang Sun , Jun Liu , Xun Xie , Jiaqi Tian , Jiawen Song

Air-breathing vehicles, a crucial field of the aerospace industry in recent years, are required to have exceptional flight performance in a wide range. As a practical and essential way to realize efficient flight, the integration design emerges as a prominent characteristic of air-breathing vehicles. This article reviews and analyzes the design connotation, critical progress, and technical attributes of high-speed air-breathing integration vehicles, including supersonic aerodynamics/propulsion integration, hypersonic cruise-type airframe/engine integration, and wide-range aircraft/engine integration. In the supersonic aerodynamics/propulsion integrated design phase, creating a vehicle with excellent maneuverability and stealth performance has become the design focus. While in the hypersonic cruise-type airframe/engine integrated design phase, designers proposed various rotational symmetrical slender body and lifting-body configurations to match the scramjet engines. This provided strong support for breaking through thrust-drag matching in hypersonic cruise. For wide-range aircraft/engine integration vehicles, a more complex service environment imposes higher requirements on their levels of integration. The progression from supersonic aerodynamics/propulsion integration to hypersonic cruise-type airframe/engine integration, and further to wide-range aircraft/engine integration, signifies the exploration of air-breathing aircraft towards wider speed range and broader airspace. Finally, a detailed analysis of the distinctions among these three types of integrated vehicles is presented, and the development proposals and trends of wide-range aircraft/engine integration vehicles are discussed.

空气呼吸飞行器是近年来航空航天工业的一个重要领域，要求其在大范围内具有优异的飞行性能。作为实现高效飞行的重要实用途径，一体化设计成为喷气飞行器的突出特点。本文从超音速气动/推进一体化、高超声速巡航型机体/发动机一体化、大航程飞行器/发动机一体化等方面，对高速喷气式一体化飞行器的设计内涵、关键进展和技术特性进行了回顾和分析。在超音速气动/推进一体化设计阶段，设计的重点是创造一种具有优异机动性和隐身性能的飞行器。而在高超声速巡航型机体/发动机集成设计阶段，设计人员提出了各种旋转对称的细长机体和升力机体构型，以匹配涡喷发动机。这为在高超音速巡航中突破推力-阻力匹配提供了有力支持。对于大范围的飞机/发动机集成飞行器来说，更复杂的服役环境对其集成水平提出了更高的要求。从超音速气动/推进集成到高超声速巡航型机体/发动机集成，再到大航程飞行器/发动机集成，标志着喷气式飞行器正朝着更宽的速度范围和更广阔的空域探索。最后，详细分析了这三类集成飞行器的区别，并讨论了大航程飞机/发动机集成飞行器的发展建议和趋势。

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引用次数: 0

Gust load alleviation of a flexible flying wing with linear parameter-varying modeling and model predictive control 利用线性参数变化建模和模型预测控制减轻柔性飞翼的阵风负荷

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-17 DOI: 10.1016/j.ast.2024.109671

Wei Gao, Yishu Liu, Qifu Li, Bei Lu

This paper presents a practical model predictive control (MPC) framework for gust load alleviation of a flexible flying wing. Both the controller solving and state estimation are based on a reduced-order model, which features a linear parameter-varying (LPV) form, avoiding online linearization and reducing the scale of the corresponding quadratic programming problem. An improved modeling and model reduction process is used to enhance modeling efficiency and ensure that the reduced-order model can accurately capture the rigid-flexible coupled characteristics of the flexible flying wing under arbitrary gusts. By reconstructing the output of the control-oriented model to include both rigid-body motion and flexible vibrations, the rigid-flexible coupled multi-objective control is established as an MPC problem for reference tracking. The online optimization is formulated in a sparse fashion and combined with an iterative algorithm based on predicted trajectories, describing the variation of model dynamics within the prediction horizon more accurately. With a time-varying Kalman estimator for state updating, the closed-loop simulations are performed for gust alleviation performance validation. Additionally, the real-time potential of the proposed MPC framework is demonstrated through Monte Carlo simulations.

本文提出了一种用于减轻柔性飞翼阵风负荷的实用模型预测控制（MPC）框架。控制器求解和状态估计都基于一个减阶模型，该模型采用线性参数变化（LPV）形式，避免了在线线性化，并缩小了相应二次方程编程问题的规模。改进的建模和模型缩减过程提高了建模效率，并确保缩减阶模型能准确捕捉柔性飞翼在任意阵风下的刚柔耦合特性。通过重构控制导向模型的输出，使其包括刚体运动和柔性振动，将刚柔耦合多目标控制建立为参考跟踪的 MPC 问题。在线优化以稀疏方式制定，并与基于预测轨迹的迭代算法相结合，从而更准确地描述预测范围内的模型动态变化。利用时变卡尔曼估计器进行状态更新，并进行闭环模拟以验证阵风缓解性能。此外，还通过蒙特卡罗模拟展示了所提出的 MPC 框架的实时潜力。

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引用次数: 0

Variational resolution probability maps for multi-UAV search tasks with changeable searching behaviors 具有可变搜索行为的多无人机搜索任务的变分辨率概率图

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-16 DOI: 10.1016/j.ast.2024.109669

Daifeng Zhang , Haibin Duan

Cooperative search is a fundamental task in the autonomous control of multiple unmanned aerial vehicles (UAV) and much effort has been spent on finding an effective way to improve the global search performances. Two behavioral aspects are essentially considered during the multi-UAV cooperative search. One is the coverage (exploration) and the other is the retrospect to hotspot regions (exploitation). Most existing studies focus on the solutions to the former issue, by using the cognitive maps with fixed grid layouts, while ignoring the coexistence of both sides, which potentially induces the failures of finding hidden and indetectable targets. This paper presents a novel search method based on the cognitive maps with alternative grid settings, namely the variational resolution probability map (VRPM), to support the global searches with changeable phases and behaviors. To realize the transformations between different resolution maps in a given budget, the incremental learning is used to update the VRPM under limited number of samples. Potential games with different objectives are used to model the multi-UAV searching behaviors during explorations and exploitations. Lyapunov vector field (LVF) is then used to steer the UAVs toward their target grids in a given time horizon, so that the control period can be properly coincided with the temporal sequences of decision makings. Simulation results demonstrate the phase transitions from the explorations to the exploitations by the proposed method. Search accuracy and the retrospects to hotspot areas are also improved by comparison with the existing search strategies.

合作搜索是多无人飞行器（UAV）自主控制中的一项基本任务，人们花费了大量精力来寻找提高全局搜索性能的有效方法。在多无人飞行器合作搜索过程中，主要考虑两个行为方面。一个是覆盖范围（探索），另一个是对热点区域的回溯（开发）。现有研究大多侧重于前一个问题的解决方案，即使用固定网格布局的认知地图，而忽略了双方共存的问题，这有可能导致无法找到隐藏和无法探测的目标。本文提出了一种基于认知图的新型搜索方法，即变异分辨率概率图（VRPM），以支持具有可变阶段和行为的全局搜索。为了在给定预算内实现不同分辨率地图之间的转换，我们采用了增量学习方法，在有限的样本数量下更新 VRPM。不同目标的潜在博弈被用来模拟探索和开发过程中的多无人机搜索行为。然后，利用 Lyapunov 向量场（LVF）引导无人飞行器在给定的时间范围内飞往目标网格，从而使控制期与决策的时间序列适当吻合。仿真结果表明了拟议方法从探索到利用的阶段转换。与现有搜索策略相比，搜索精度和对热点区域的回溯也得到了提高。

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引用次数: 0

A novel constrained skew-Gaussian filter and its application to maneuverable reentry vehicle tracking 新型约束偏高斯滤波器及其在机动再入飞行器跟踪中的应用

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-16 DOI: 10.1016/j.ast.2024.109666

Wang Ruipeng, Wang Xiaogang

The state of the system generally satisfies specific constraints imposed by material properties or physical laws, so the application of these constraints can improve the accuracy of state estimation. In this paper, a novel recursive filter referred as constrained high-degree cubature skew-Gaussian filter (CHCSGF) is proposed, which achieves soft-constrained state estimation by compressing the probability density of unconstrained states with constraint information. First, the probability density of the state under inequality soft constraints is modeled as a skew-Gaussian (SG) distribution, rather than truncated or single Gaussian distributions. Then, a recursive constrained SG filter is developed to handle inequality soft constraints in linear systems. Addressing nonlinear challenges, a 5th-degree spherical-radial cubature approximation method is presented to numerically calculate SG-weighted integrals for the nonlinear transformation of SG distribution. Finally, the CHCSGF algorithm is proposed using this method to tackle nonlinear filtering problems. The CHCSGF is applied to reentry trajectory tracking to improve estimation accuracy by dealing with heat flow, dynamic pressure and overload constraints during reentry flight. Simulation results demonstrate that the CHCSGF achieves higher estimation accuracy than unconstrained methods under nonlinear inequality soft constraints, and is robust to the constraints with a prior error. Compared to particle filter and moving horizon estimation, the computational complexity of CHCSGF is significantly reduced.

系统的状态通常满足材料特性或物理规律施加的特定约束，因此应用这些约束可以提高状态估计的精度。本文提出了一种新型递归滤波器，即约束高阶立方体偏高斯滤波器（CHCSGF），它通过利用约束信息压缩无约束状态的概率密度来实现软约束状态估计。首先，不等式软约束下的状态概率密度被建模为偏高斯（SG）分布，而不是截断分布或单一高斯分布。然后，开发了一种递归约束 SG 滤波器，用于处理线性系统中的不平等软约束。针对非线性挑战，提出了一种 5 度球面-径向立方近似方法，用于数值计算 SG 分布非线性变换的 SG 加权积分。最后，利用该方法提出了 CHCSGF 算法，以解决非线性滤波问题。CHCSGF 被应用于再入轨道跟踪，通过处理再入飞行过程中的热流、动态压力和过载约束来提高估计精度。仿真结果表明，在非线性不等式软约束条件下，CHCSGF 比无约束方法获得了更高的估计精度，并且对具有先验误差的约束条件具有鲁棒性。与粒子滤波和移动地平线估计相比，CHCSGF 的计算复杂度大大降低。

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引用次数: 0

Modelling and dynamic analysis of a synchropter 同步器的建模和动态分析

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-16 DOI: 10.1016/j.ast.2024.109664

Giulia Bertolani , Emanuele L. de Angelis , Fabrizio Giulietti , Marilena D. Pavel

This paper addresses the flight dynamics modelling, trim, and dynamic analysis of an intermeshing-rotor helicopter, indicated as synchropter. This configuration has gained a great interest for its suitability within heavy load lifting and transportation in extreme high temperature and altitude, and other harsh environments. The paper presents some relevant features related to synchropter's flight dynamics modelling of the interference between its two tilted main rotors. Trim results show the advantage of the synchropter in forward flight where the yawing moment is naturally balanced at almost all speeds and no lateral-directional compensation is needed. The synchropter's dynamic stability shows similarity to a conventional helicopter in the longitudinal phugoid. However, in the lateral phugoid, the synchropter is unstable at all flying speeds and therefore its vertical fin needs to be carefully designed.

本文论述了同步旋翼直升机的飞行动力学建模、修整和动态分析。这种构型因其适用于在极端高温、高海拔和其他恶劣环境下的重型负载吊装和运输而备受关注。本文介绍了同步螺旋桨飞行器两个倾斜主旋翼之间干扰的飞行动力学建模的一些相关特点。试验结果表明，同步飞行器在向前飞行时具有优势，几乎在所有速度下都能自然平衡偏航力矩，无需进行横向补偿。同步飞行器的动态稳定性在纵向凤尾形上与传统直升机相似。但是，在横向飞行时，同步飞行器在所有飞行速度下都不稳定，因此需要对其垂直鳍进行精心设计。

引用次数: 0