Acta Astronautica最新文献_第10页

EDT demonstration for keeping low altitude orbit using carbon nanotube tether 利用碳纳米管系绳保持低空轨道的 EDT 演示

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-10-01 DOI: 10.1016/j.actaastro.2024.09.066

Masahiro Nohmi , Koki Matsuo , Satomi Kawamoto , Yasushi Ohkawa

{"title":"EDT demonstration for keeping low altitude orbit using carbon nanotube tether","authors":"Masahiro Nohmi , Koki Matsuo , Satomi Kawamoto , Yasushi Ohkawa","doi":"10.1016/j.actaastro.2024.09.066","DOIUrl":"10.1016/j.actaastro.2024.09.066","url":null,"abstract":"<div><div>This paper describes an electrodynamic tether system (EDT). Conductive tethers are used to overcome atmospheric resistance in low orbit and extend orbit life using EDT propulsion. First, based on the conceptual design, the feasibility of the EDT system has been evaluated through simulation. Especially, the induced electromotive force of the conductive tether has been clarified, the amount of current required to keep the orbital altitude, and the requirements for each device. Then, feasibilities of the key mission devices have been evaluated experimentally. Those are the conductive tether, the electron emission device, and the tether extension control mechanism. The conductive tether is planned to be made of carbon nanotubes, which are attracting attention as a new material, and its properties are evaluated. The electron-emitting device has been evaluated as a device that can be mounted on a micro/nano satellite. Tether extension mechanism was developed in our past project, then it should be evaluated with the purpose of adapting to conductive tether systems. Based on the evaluation, the orbital demonstration mission plan using a micro/nano satellite has been introduced. The mission is as follows. The conductive tether is extended and stabilized by the gravity gradient. By emitting electrons from an electron emitter mounted on a high-altitude satellite and collecting electrons on bare tether at low-altitude end, a current is generated from the high-altitude side to the low-altitude side. According to Fleming's law, the Lorentz force is generated in the direction of the orbiting accelerated, so it can be propelled in the upward direction of the orbit.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 881-890"},"PeriodicalIF":3.1,"publicationDate":"2024-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426086","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Modular design and structural optimization of CubeSat separation mechanism 立方体卫星分离机构的模块化设计和结构优化

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-09-30 DOI: 10.1016/j.actaastro.2024.09.067

Jiaolong Zhang , Jingao Su , Chao Wang , Yiqian Sun

{"title":"Modular design and structural optimization of CubeSat separation mechanism","authors":"Jiaolong Zhang , Jingao Su , Chao Wang , Yiqian Sun","doi":"10.1016/j.actaastro.2024.09.067","DOIUrl":"10.1016/j.actaastro.2024.09.067","url":null,"abstract":"<div><div>In order to achieve the design requirements of light weight and high stiffness of the CubeSat modular separation mechanism, a BPNN-GA-PSO size optimization method is proposed to optimize the design of the separation mechanism. Firstly, the separation mechanism of modularization and standardization is analyzed to select the optimization objects. Then, a hierarchical optimization strategy of topology optimization followed by size optimization is adopted to find the global optimum using a hybrid GA-PSO optimization algorithm. Meanwhile, the BPNN surrogate model is introduced to improve the optimization efficiency. The results show that the mass proportion of the optimized separation mechanism is reduced to 18 %, and the maximum deformation of the separation mechanism is 0.123 mm, which meets the design requirements of light weight and high stiffness of the separation mechanism. It proves the applicability of the optimization method to the optimal design of the separation mechanism. The CubeSat modular separation mechanism designed in this paper has been verified by ground verification with overload, vibration, and shock mechanical tests, and successfully deployed the BY-03 satellite in-orbit, which can provide reference for the design and development of subsequent CubeSat modular separation mechanisms.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 758-767"},"PeriodicalIF":3.1,"publicationDate":"2024-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426078","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Drag reduction mechanism based on the aerospike-jet composite approach under different incoming dynamic pressures 不同传入动压下基于气钉喷气复合方法的减阻机制

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-09-30 DOI: 10.1016/j.actaastro.2024.09.068

Zan Xie, Chao-yang Liu, Yu-shan Meng, Wei Huang, Ya-jie Liang, Zhen-tao Zhao

{"title":"Drag reduction mechanism based on the aerospike-jet composite approach under different incoming dynamic pressures","authors":"Zan Xie, Chao-yang Liu, Yu-shan Meng, Wei Huang, Ya-jie Liang, Zhen-tao Zhao","doi":"10.1016/j.actaastro.2024.09.068","DOIUrl":"10.1016/j.actaastro.2024.09.068","url":null,"abstract":"<div><div>The drag experienced by the nose of an aircraft varies significantly under different incoming flow conditions. In order to reduce the aerodynamic force on the nose of the (hypersonic) supersonic vehicle, the numerical simulation approach has been used to analyze the drag reduction laws and mechanisms of a blunt-body vehicle with the aerospike-counterflowing jet composite approach under different incoming flow dynamic pressures. The effects of two environments with <em>H</em> = 0.1 km and <em>H</em> = 30 km, as well as the influence of different incoming Mach numbers on the drag reduction at <em>H</em> = 0.1 km were investigated. The research has shown that there exists a minimum overall drag value for the vehicle under different dynamic pressures, while the variation in the wall pressure is related to the actual operating conditions. The recirculation zones at the aerospike and in front of the blunt body are important flow structures that affect the drag reduction. When the jet total pressure ratio increases, the position of the recirculation zone at the head of the drag reduction rod moves away from the central axis of the model. When the incoming flow dynamic pressure is higher, the separation point of the recirculation zone in front of the blunt body is located further downstream, and the reattachment point is related to the incoming flow and jet conditions, aligning with the trend of variation of the position of the maximum pressure on the blunt body wall. As it can effectively push away the shock wave, the enhanced drag reduction effect of the jet is significant when the incoming flow dynamic pressure is higher. However, the high jet pressure resulting from high dynamic pressure needs to be considered in the actual design. Furthermore, the complex turbulent flow field formed by the high dynamic pressure incoming flow and the jet is worthy of further study by means of the large eddy simulation.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 741-757"},"PeriodicalIF":3.1,"publicationDate":"2024-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426077","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Combustion flow field and thermal protection performance of a liquid oxygen/kerosene engine with pintle injectors 采用针形喷射器的液氧/煤油发动机的燃烧流场和热保护性能

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-09-30 DOI: 10.1016/j.actaastro.2024.09.065

Bowei Jiao , Nanjia Yu , Chuang Zhou , Yaming Zhao , Jiaqi Li

{"title":"Combustion flow field and thermal protection performance of a liquid oxygen/kerosene engine with pintle injectors","authors":"Bowei Jiao , Nanjia Yu , Chuang Zhou , Yaming Zhao , Jiaqi Li","doi":"10.1016/j.actaastro.2024.09.065","DOIUrl":"10.1016/j.actaastro.2024.09.065","url":null,"abstract":"<div><div>A pintle injector is a convenient method for adjusting propellant combustion and has received extensive attention in recent years. However, few studies have examined the effects of the injection direction and momentum ratio (ratio of liquid oxygen momentum to kerosene momentum) on the flow field, temperature field, and dual-belt liquid film cooling effect in the combustion chamber. This study verified a new computational fluid dynamics (CFD) engine combustion model based on a pintle injector through a hot-test experiment. A simulation was conducted using this model. With different injection directions, when the momentum ratio was increased, the trends in the combustion efficiency and chamber pressure growth were entirely opposite. For the axial kerosene and radial liquid oxygen injection direction of liquid film cooling, when the momentum ratio was 0.73–0.9, the proportion of the first ring belt liquid film flow was selected as 5–10 %, and the second ring belt liquid film flow proportion was selected as 5–7%. When the momentum ratio was less than 0.73, the liquid film flow proportions for both the first and second ring belts were selected as 5 %. When the total liquid film flow proportion was 10 %, the chamber pressure decreased by 0.2–0.3 MPa, and the combustion efficiency decreased by 8–10 %. This numerical study provides guidance for studying the combustion characteristics and cooling performance of pintle-type rocket combustion chambers.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 928-941"},"PeriodicalIF":3.1,"publicationDate":"2024-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426091","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Semi-analytic approximate time-optimal asteroid landing with dimensionality reduction shooting 半解析近似时间最优小行星着陆降维射击

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-09-28 DOI: 10.1016/j.actaastro.2024.09.032

Zibin Sun , Lin Cheng , Shengping Gong

{"title":"Semi-analytic approximate time-optimal asteroid landing with dimensionality reduction shooting","authors":"Zibin Sun , Lin Cheng , Shengping Gong","doi":"10.1016/j.actaastro.2024.09.032","DOIUrl":"10.1016/j.actaastro.2024.09.032","url":null,"abstract":"<div><div>Pinpoint landing on asteroid is very challenging due to the uncertainties of the gravitational field, which highlights the urgent need for autonomous landing algorithms under such uncertainties. Some well-known guidance algorithms, such as APDG and real-time convex programming, either ignore thrust boundary constraints or are severely time consuming. In addition, these algorithms have the same difficulty in analyzing landing errors due to model uncertainty propagation, making the reliability of the algorithms in actual landings questionable. To address these challenges, we propose a landing framework that combines model identification, trajectory analytical solution and closed-loop corrections to achieve near-optimal real-time landing control. Firstly, we simplified the landing scenario, focusing on reducing the dimension of shooting variables to enable rapid trajectory calculation. Secondly, we derived error propagation equations and established criteria for trajectory replanning based on landing error prediction. Finally, we validated our approach with practical examples of the Shoemaker probe landing on Eros 433. Through real-time landing error estimation, our proposed framework enables spacecraft to achieve near time-optimal land within a given error threshold.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 729-740"},"PeriodicalIF":3.1,"publicationDate":"2024-09-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142425581","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Learning-based control for deployment and retrieval of a spinning tethered satellite formation system 基于学习的控制，用于部署和回收旋转系留卫星编队系统

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-09-28 DOI: 10.1016/j.actaastro.2024.09.061

Caoqun Luo, Ti Chen, Hao Wen, Dongping Jin

{"title":"Learning-based control for deployment and retrieval of a spinning tethered satellite formation system","authors":"Caoqun Luo, Ti Chen, Hao Wen, Dongping Jin","doi":"10.1016/j.actaastro.2024.09.061","DOIUrl":"10.1016/j.actaastro.2024.09.061","url":null,"abstract":"<div><div>This paper investigates the nonlinear dynamics and control of the deployment and retrieval for a spinning tethered satellite formation system via artificial intelligent method. A dynamic model of the spinning tethered formation system is developed to describe the attitude motions of the system, involving the relative rotations of the tethers to the central main satellite. Considering the system with symmetric and asymmetric configurations, a learning-based control strategy with low time cost is proposed to achieve the stable deployment and retrieval of tethers. In the strategy, a nonlinear model predictive control law accounting for the control constraints and nonlinear dynamics is developed to achieve the control goal. Based on a deep learning method, a dataset including control input and state output obtained offline is trained to form deep neural networks. An online feedback control of the system can be achieved by conducting real-time mapping from the system state to the control input using the neural networks. Finally, numerical simulations for deployment and retrieval of the system with different configurations are presented to demonstrate the computational efficiency and to validate the effectiveness of the control strategy.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 788-800"},"PeriodicalIF":3.1,"publicationDate":"2024-09-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426080","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Accelerated biological evolution in outer space: Insights from numerical analysis 加速外太空生物进化：数值分析的启示

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-09-28 DOI: 10.1016/j.actaastro.2024.09.044

Satoshi Sano

引用次数: 0

Effect of semifluoroalkyl substituents in the POSS on atomic oxygen exposure POSS 中的半氟烷基取代基对原子氧暴露的影响

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-09-28 DOI: 10.1016/j.actaastro.2024.09.060

Kazuki Yukumatsu , Soichi Yokoyama , Aki Goto , Yugo Kimoto , Yutaka Ie

{"title":"Effect of semifluoroalkyl substituents in the POSS on atomic oxygen exposure","authors":"Kazuki Yukumatsu , Soichi Yokoyama , Aki Goto , Yugo Kimoto , Yutaka Ie","doi":"10.1016/j.actaastro.2024.09.060","DOIUrl":"10.1016/j.actaastro.2024.09.060","url":null,"abstract":"<div><div>Due to the many recent Earth observation missions, very low Earth orbit (VLEO) have become a pressing topic for satellite research. Since the density of atomic oxygen (AO) in VLEO is higher than in low Earth orbit (LEO), the need for AO-resistant materials based on polyhedral oligomeric silsesquioxane (POSS) is strong. However, the effects of the side-chain groups in the POSS on AO exposure are unclear. In this study, we focused on POSS molecules modified with semifluoroalkyl groups as side chains because fluorocarbon groups, such as fluorinated ethylene propylene (FEP), are known to have high AO resistance. Semifluoroalkyl- and alkyl-substituted POSS films were fabricated and exposed to a laser-detonation AO source. Microbalance measurements showed that the mass losses of the semifluoroalkyl-substituted POSS films were larger than those of alkyl-substituted POSS films. X-ray photoelectron spectroscopy measurements showed that the silica layers formed on the semifluoroalkyl-substituted POSS were thicker than on alkyl-substituted POSS films. Surface observation using a field emission scanning electron microscope revealed microscale cracks on the surface of the semifluoroalkyl-substituted POSS. These findings indicate that POSS molecules with fluorine substituents warrant careful consideration of the AO-barrier performance of the silica layer formed during AO exposure.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 812-820"},"PeriodicalIF":3.1,"publicationDate":"2024-09-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426082","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Service spacecraft for space debris removal 清除空间碎片的服务航天器

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-09-27 DOI: 10.1016/j.actaastro.2024.09.055

V.V. Svotina , A.V. Melnikov , A.I. Pokryshkin , A.I. Mogulkin , I.A. Nikolichev , G.A. Popov , V.A. Kirillov , YuV. Tsaytler

{"title":"Service spacecraft for space debris removal","authors":"V.V. Svotina , A.V. Melnikov , A.I. Pokryshkin , A.I. Mogulkin , I.A. Nikolichev , G.A. Popov , V.A. Kirillov , YuV. Tsaytler","doi":"10.1016/j.actaastro.2024.09.055","DOIUrl":"10.1016/j.actaastro.2024.09.055","url":null,"abstract":"<div><div>The problem of space debris removal from the near-Earth space is being studied in almost every country taking part in space exploration. This is due to the global threat of critical increase in the number of space debris objects predicted for the near future, in particular as a result of significant growth in demand for multi-satellite constellations for various purposes. To date, researchers have proposed a large number of different methods for space debris removal. The work presented is the development of one of the promising contactless methods of space debris removal by an ion beam. The results of modeling and optimization of physical processes in the ion source to be mounted on board a service spacecraft that is necessary for implementing the considered method of space debris removal are presented. Besides, the results of thermal modeling and thermal mapping of the ion source during its operation are presented also, and the calculation results of its output parameters are compared to experimental data, which verified the small divergence angles of the generated ion beam. To assess the prospects of using a system for contactless space debris transportation by an ion beam using the obtained data on the operating parameters of the ion source, the trajectory design and mission analysis were carried out, which revealed the feasibility of removing seven space debris objects out of the protected region in geostationary orbit by a single service spacecraft. Besides, the preliminary service spacecraft design is presented.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 821-832"},"PeriodicalIF":3.1,"publicationDate":"2024-09-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426093","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Study to integrate Delay-Tolerant Network protocols in IoT LEO constellations for flood prevention 研究在物联网低地轨道星座中整合容时网络协议，用于防洪

IF 3.1 2区物理与天体物理

Acta Astronautica Pub Date : 2024-09-27 DOI: 10.1016/j.actaastro.2024.09.004

Marcel Marin-de-Yzaguirre, Oriol Fuste, Joan A. Ruiz-de-Azua

{"title":"Study to integrate Delay-Tolerant Network protocols in IoT LEO constellations for flood prevention","authors":"Marcel Marin-de-Yzaguirre, Oriol Fuste, Joan A. Ruiz-de-Azua","doi":"10.1016/j.actaastro.2024.09.004","DOIUrl":"10.1016/j.actaastro.2024.09.004","url":null,"abstract":"<div><div>In the era of the Internet of Things (IoT) the development of Direct-to-Satellite IoT (DtS-IoT) applications are becoming increasingly relevant. These applications are based on enabling IoT devices to communicate directly with satellites. In this scenario, LEO satellites can provide global IoT service coverage, becoming essential to connect devices in remote areas. As an example, the deployment of NarrowBand-IoT (NB-IoT) service is being actively investigated with the apparition of Non-Terrestrial Network (NTN) and DtS-IoT concepts. Although some initiatives propose seamless and ubiquitous service, these features may not be required for IoT applications. This relaxes the requirements in the satellite constellation architecture, enabling it to be more sparse. The connection between sensors, satellites and ground segment becomes intermittent and discontinuous in these non-dense architectures. Delay/Disruptive-tolerant protocols are essential to coexist with this network characteristics. Unfortunately, traditional IoT protocols have not been designed with this delay-tolerant feature. This work tackles this challenge by integrating Delay-Tolerant Network protocols with NB-IoT architecture. Specifically, the integration is based on interconnecting the Bundle Protocol and IP traffic through a novel interface. This development has been divided in three phases: (1) The definition of an architecture and protocol stack to tackle NTN IoT scenarios with discontinuities, (2) the analysis from simulated data of the resulting protocol stack in a realistic scenario based on flooding prevention, and (3) the implementation and validation of it in a laboratory testbed. The proposed case study uses a Direct-to-Satellite IoT architecture to create an early warning flooding detection system. The simulation results provide insights of the achieved performance with these architectures when servicing hundreds of sensing nodes.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 968-977"},"PeriodicalIF":3.1,"publicationDate":"2024-09-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426036","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0