Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering最新文献_第4页

Effect of injector on flow characteristic and hydraulic performance in aero-fuel centrifugal pump 喷射器对航空燃料离心泵流量特性和液压性能的影响

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-06-22 DOI: 10.1177/09544100241263024

Jia Li, Bo Liu, Wen Zhou, Jian Xie, Xuan Chen

{"title":"Effect of injector on flow characteristic and hydraulic performance in aero-fuel centrifugal pump","authors":"Jia Li, Bo Liu, Wen Zhou, Jian Xie, Xuan Chen","doi":"10.1177/09544100241263024","DOIUrl":"https://doi.org/10.1177/09544100241263024","url":null,"abstract":"In the fuel system of an aircraft engine, aero-fuel centrifugal pumps are widely utilized as boost pumps. In this research, we propose the integration of an inlet injector with an aero-fuel centrifugal pump to optimize its flow characteristics and enhance performance. The key geometric parameters of the impeller, volute, and injector are meticulously designed. The effectiveness of our approach is validated through a combination of experimental and numerical analysis, which involves comparing simulation results with experimental data. The findings demonstrate that the presence of the injector significantly impacts the flow characteristics and hydraulic performance of the pump. Specifically, it effectively reduces flow losses in the specific channels of the impeller and volute. Furthermore, the injector enhances the regulation of the inlet flow fields by adjusting the inlet pressure and controlling the suction flow direction. Consequently, the pump’s efficiency is enhanced when equipped with the injector compared to its performance without it. Therefore, incorporating an injector in an aero-fuel centrifugal pump has a positive effect on regulating flow characteristics and improving hydraulic efficiency.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":"1 1","pages":""},"PeriodicalIF":1.1,"publicationDate":"2024-06-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141505850","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Control stability analysis of dynamic model with time delay for quadrotor UAV 带有时间延迟的四旋翼无人机动态模型的控制稳定性分析

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-06-21 DOI: 10.1177/09544100241262550

Xi Li, Guoyuan Qi, Limin Zhang

{"title":"Control stability analysis of dynamic model with time delay for quadrotor UAV","authors":"Xi Li, Guoyuan Qi, Limin Zhang","doi":"10.1177/09544100241262550","DOIUrl":"https://doi.org/10.1177/09544100241262550","url":null,"abstract":"For the first-order unstable object with time delay, the PD control parameter tuning method based on the traditional definition lacks consideration of the lower boundary of amplitude margin, resulting in a certain deviation between the result and the reality. In this paper, through analyzing the control loop of quadrotor UAV (QUAV), the integral link is moved from the controlled object to the controller, and the QUAV becomes a first-order unstable object, realizing the conversion of PD to PI in the hovering state. The system stability margin remains unchanged, and the position and attitude control objectives can be realized synchronously. By means of parameter setting method, the upper boundary of stability margin is obtained. Pade approximation is carried out for the time delay link, and then the lower margin of the amplitude margin is deduced according to Routh stability criterion, so as to obtain a more accurate reachable stability margin region. To avoid the high gain feedback of attitude angular velocity of QUAV, a numerical analytical setting formula for PD attitude control is derived to meet the requirements of gain and phase margin. The graph shows that the reachable region obtained by the strict definition of stability margin analysis decreases significantly. The proposed method can not only give the reachable region intuitively, but also give the tuning formula of the control parameters concisely, which has important engineering application value.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":"217 1","pages":""},"PeriodicalIF":1.1,"publicationDate":"2024-06-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141513869","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Desensitized optimal trajectory for hopping rovers on small bodies 小天体上跳跃漫游车的脱敏最佳轨迹

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-06-21 DOI: 10.1177/09544100241262559

Shengying Zhu, Chuncheng Zhao

{"title":"Desensitized optimal trajectory for hopping rovers on small bodies","authors":"Shengying Zhu, Chuncheng Zhao","doi":"10.1177/09544100241262559","DOIUrl":"https://doi.org/10.1177/09544100241262559","url":null,"abstract":"Future exploration tasks of small bodies will need to sample or visit multiple points on the target to obtain more scientific returns, requiring rovers to have the ability to hop on a small body surface. This paper proposes an approach to generate a desensitized optimal trajectory for hopping rovers, aiming at reducing the sensitivity of hopping trajectory in the presence of uncertainties. Firstly, considering parameter uncertainties and initial state errors, analytical expressions of optimal initial states are derived on a planar scene, based on ballistic dynamics. Then, similar methods are developed in both uphill and downhill cases of inclined scenes. Subsequently, the desensitization performance of long-distance hopping trajectory is analyzed under single-hop, identical, and non-identical N-hop strategies. To facilitate the application of the proposed analytical solution to the simulated surface environment of small bodies, a prediction-correction procedure is presented. Finally, Monte Carlo simulations are carried out to verify the effectiveness of the proposed methods. The results indicate that the sensitivity of the hopping trajectory to uncertainties can be effectively diminished by employing the desensitized optimal trajectory and multiple hopping strategy.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":"195 1","pages":""},"PeriodicalIF":1.1,"publicationDate":"2024-06-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141513870","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

An interval programming method of earth-moon trajectory for manned lunar exploration mission under interval uncertainty 区间不确定性下载人月球探测任务的地月轨迹区间编程方法

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-05-30 DOI: 10.1177/09544100241254156

Luyi Yang, Haiyang Li, Jin Zhang

{"title":"An interval programming method of earth-moon trajectory for manned lunar exploration mission under interval uncertainty","authors":"Luyi Yang, Haiyang Li, Jin Zhang","doi":"10.1177/09544100241254156","DOIUrl":"https://doi.org/10.1177/09544100241254156","url":null,"abstract":"There are always uncertainties in practical engineering, and the design of the optimal Earth-Moon trajectory under uncertainties significantly reduces flight risk for the manned lunar exploration mission (MLEM). This paper proposes an interval programming method to optimize the trans-lunar trajectory under interval uncertainties. Firstly, the influence of the trans-lunar injection uncertainties (TLI) is investigated, finding that the reached orbit at the perilune is very sensitive to the impulse errors at TLI. Then, the design methods of the Earth-Moon trajectory and the trajectory correction maneuver (TCM) are presented. Based on the mathematical tool of the interval possibility degree, the interval programming model is built to transform the uncertain optimization problem into a deterministic one, and then a multi-layer optimization scheme is proposed to solve it. The uncertain objectives and constraints’ interval bounds are calculated in the inner loop, and the design variables are searched and optimized in the outer loop. The proposed method is used to design the Earth-Moon trajectories of both manned and unmanned spacecraft. The designed trajectories are insensitive to the uncertainties and are validated by the Monte Carlo simulations.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":"39 1","pages":""},"PeriodicalIF":1.1,"publicationDate":"2024-05-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141197964","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Angular acceleration estimation and aerodynamic parameter identification based on angular velocity equivalent model 基于角速度等效模型的角加速度估算和气动参数识别

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-05-13 DOI: 10.1177/09544100241249350

Lixin Wang, Rong Zhao, Yi Zhang, Ting Yue

{"title":"Angular acceleration estimation and aerodynamic parameter identification based on angular velocity equivalent model","authors":"Lixin Wang, Rong Zhao, Yi Zhang, Ting Yue","doi":"10.1177/09544100241249350","DOIUrl":"https://doi.org/10.1177/09544100241249350","url":null,"abstract":"Conventional angular acceleration estimation methods generate non-negligible errors when the control surface rapidly deflects; hence, the estimated angular acceleration cannot be used for aerodynamic parameter identification directly. This paper proposes an angular acceleration estimation method based on angular velocity equivalent model. The angular acceleration of the angular velocity equivalent model, whose angular velocity response is consistent with the flight test data, is used as the estimated angular acceleration. Firstly, the equivalent angular velocity model is established by combining the generic aerodynamic model with the rotational dynamic equations of aircraft. Secondly, the angular velocity data and the control surface deflection data are synchronized. Finally, the angular velocity response of the equivalent model is used as the predictor, and the estimated angular acceleration is obtained by extended Kalman filter. The aerodynamic parameter identification and validation are carried out using the estimated angular acceleration of a large civil aircraft flight test data. The results show that the angular acceleration obtained through the proposed angular acceleration estimation method meets the accuracy requirement of aerodynamic parameter identification.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":"5 1","pages":""},"PeriodicalIF":1.1,"publicationDate":"2024-05-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140936246","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Drone path planning and dynamic arena-target allocation for crowd surveillance 用于人群监控的无人机路径规划和动态场馆目标分配

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-05-10 DOI: 10.1177/09544100241253646

Onkar Chopra, Samiksha Rajkumar Nagrare, Shuvrangshu Jana, Debasish Ghose

引用次数: 0

Aeroelastic analysis of a lightweight topology-optimized sandwich panel 轻质拓扑优化夹芯板的气动弹性分析

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-05-10 DOI: 10.1177/09544100241252041

Maliheh Najafi, António J. M. Ferreira, Flávio D. Marques

引用次数: 0

Optimal impact angle guidance law with barrier constraint 带障碍物约束的最佳撞击角引导法

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-05-09 DOI: 10.1177/09544100241252864

Cheol-Goo Jung, Pengyu Wang, Chang-Hun Lee

引用次数: 0

Deep reinforcement learning-based reactive trajectory planning method for UAVs 基于深度强化学习的无人飞行器反应式轨迹规划方法

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-05-07 DOI: 10.1177/09544100241252233

Lijia Cao, Lin Wang, Yang Liu, Weihong Xu, Chuang Geng

{"title":"Deep reinforcement learning-based reactive trajectory planning method for UAVs","authors":"Lijia Cao, Lin Wang, Yang Liu, Weihong Xu, Chuang Geng","doi":"10.1177/09544100241252233","DOIUrl":"https://doi.org/10.1177/09544100241252233","url":null,"abstract":"In order to improve the ability of avoiding dynamic threats during the flight of unmanned aerial vehicles (UAVs), a deep reinforcement learning-based reactive trajectory planning method is proposed in this paper. Firstly, a constrained Rapidly-exploring Random Tree-Connect algorithm (C-RRT-Connect) is proposed as the basic algorithm of reactive trajectory planning to globally plan for avoiding static obstacles in the environment. The C-RRT-Connect algorithm introduces the idea of target attraction to constrain the optimal growth point in the RRT-Connect algorithm. Then, based on the global trajectory, the local optimization is carried out according to the dynamic threats detected by the UAV during the flight. According to the real-time relative state between the UAV and the detected dynamic threat, the reaction sampling points and directional coefficients for avoiding the corresponding dynamic threat are generated online via the action network trained with the depth deterministic policy gradient algorithm (DDPG). And then the local trajectory is adjusted to modify the flight trajectory of the UAV to achieve reactive obstacle avoidance. The simulation experiment firstly compares the global trajectory planning performance of C-RRT-Connect and RRT-Connect in static environment, and secondly compares the local trajectory planning performance of DDPG algorithm and the artificial potential field method in dynamic environment. The experimental results show that in static environment, C-RRT-Connect algorithm has faster searching speed, less invalid samples and higher searching trajectory quality than RRT-Connect algorithm; In a dynamic environment, DDPG algorithm reduces the average running time by about 26% compared with the artificial potential field method, and has a stronger ability to evade dynamic threats in real time.","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":"43 1","pages":""},"PeriodicalIF":1.1,"publicationDate":"2024-05-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140936438","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Effects of rotational speed on transient cooling performance of nozzle spray with liquid nitrogen in a rotor-stator cavity 转速对转子-定子腔内液氮喷嘴喷雾瞬态冷却性能的影响

IF 1.1 4区工程技术

Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering Pub Date : 2024-05-07 DOI: 10.1177/09544100241251504

Xuesen Yang, Wei Zhao, Binglong Zhang, Sanqun Ren, Xiaorong Xiang, Qingjun Zhao

{"title":"Effects of rotational speed on transient cooling performance of nozzle spray with liquid nitrogen in a rotor-stator cavity","authors":"Xuesen Yang, Wei Zhao, Binglong Zhang, Sanqun Ren, Xiaorong Xiang, Qingjun Zhao","doi":"10.1177/09544100241251504","DOIUrl":"https://doi.org/10.1177/09544100241251504","url":null,"abstract":"This paper presents the results of an experimental investigation into the cooling performance of a rotor-stator cavity with liquid nitrogen spraying. The experiments were conducted under varying rotational Reynolds numbers ranging from 1.70 × 106 to 5.12 × 106. The effects of rotational speed on temperature drop rate are studied and compared in detail, as well as the heat transfer coefficient distribution. Sufficient data, such as heat flux, injection rate, and injection pressure, were collected to provide a basis for further study in explaining the spray and evaporation over the cavity. It was found that the cooling performance of the rotating disc is strongly affected by the rotational speed. The short-term period exhibits a peak cooling rate of 14°C/s, in contrast to the sustained cooling rate during the spray process at rotational speeds of 500r/min, which amounts to 0.9°C/s. The occurrence of cavitation and evaporation within the nozzle results in a reduction of flow coefficient and fluctuation of the injection differential pressure. The transient cooling performance is well-explained by the temperature changes and cooling-down time under different rotational speeds. The analysis of the heat transfer coefficient is further enhanced through an evaluation of the convective and conductive heat transfer rates using a one-dimensional theoretical approach. The average temperature of the disc is expected to decrease by 100°C within a time frame no longer than 120 s. Additionally, after a duration of 120 s, the average heat transfer rate on the cold side is anticipated to surpass 8000 W/(m·K).","PeriodicalId":54566,"journal":{"name":"Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering","volume":"24 1","pages":""},"PeriodicalIF":1.1,"publicationDate":"2024-05-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140936245","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0