Pub Date : 2024-10-09DOI: 10.1016/j.actaastro.2024.10.004
Holger Krag , Mike Lindsay , Mark A. Skinner , Yukihito Kitazawa , Paolo Marzioli
Technology solutions and operational implications need a evaluation for their crucial role in tracking and identification methodologies. The growth of objects in Earth orbit have made it more important that every space system can be accounted for to be able manage the collision risk between all space objects. Tracking and identification are intimately related as enhanced tracking capabilities minimizes the need for special identification techniques. For both features, the difference between active and passive systems are discussed. Tracking is primarily optical or radar; which of these that is being used drives the most operationally-relevant identification solutions. For example, radar tags can be made to be respond to the radio frequency (RF) energy from the radar and laser reflectors can be completely passive. Whereas identification aids for use by optical tracking are active light sources (of some selected frequency) requiring a power source.
{"title":"Innovative methods for trackability and identification improvement of small objects for space traffic management","authors":"Holger Krag , Mike Lindsay , Mark A. Skinner , Yukihito Kitazawa , Paolo Marzioli","doi":"10.1016/j.actaastro.2024.10.004","DOIUrl":"10.1016/j.actaastro.2024.10.004","url":null,"abstract":"<div><div>Technology solutions and operational implications need a evaluation for their crucial role in tracking and identification methodologies. The growth of objects in Earth orbit have made it more important that every space system can be accounted for to be able manage the collision risk between all space objects. Tracking and identification are intimately related as enhanced tracking capabilities minimizes the need for special identification techniques. For both features, the difference between active and passive systems are discussed. Tracking is primarily optical or radar; which of these that is being used drives the most operationally-relevant identification solutions. For example, radar tags can be made to be respond to the radio frequency (RF) energy from the radar and laser reflectors can be completely passive. Whereas identification aids for use by optical tracking are active light sources (of some selected frequency) requiring a power source.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 1012-1018"},"PeriodicalIF":3.1,"publicationDate":"2024-10-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142433392","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}
Pub Date : 2024-10-09DOI: 10.1016/j.actaastro.2024.10.013
Hao Zhu , Jincheng Wang , Yuanjun Zhang , Xintong Li , Jiangning Wang , Hui Tian , Guobiao Cai
Currently, there is considerable emphasis on the electric pump-fed cycle for liquid engine, primarily due to its design simplicity. However, its development is hindered by the underdeveloped state of power battery technology. Drawing inspiration from hybrid power technology used in electric vehicles and turbochargers, a hybrid pump feed system for throttleable engines is originally proposed as a promising solution. This system integrates the electric motor into the gas generator cycle, with several topologies evaluated. The parallel configuration featuring a mid-motor is selected for its compact structure, efficient power-splitting and energy recovery. Additionally, customized energy management strategies and optimization models are developed to effectively allocate power throughout the operational processes of liquid engines. A comparative analysis of four engine cycles is conducted under the typically variable-thrust mission. The results indicate that attributed to the conservation of turbo-gas and battery energy, the optimized hybrid pump achieves a reduction of 2.39 % compared to the turbopump and 7.15 % to the electric pump in total mass. Adaptability assessment further indicates that the mass advantage of the hybrid pump system is more significant during prolonged engine burning and deep throttling. Specific working conditions are found in which the system prefers electric-motor driving or regenerating turbine energy. Although energy-recovery results in the system efficiency decrease, it serves to lower energy demand of battery pack, thus easing the burden on cell thermal management and structural design. This study provides a practical design framework for hybrid pump-fed rocket engines in future variable-thrust missions.
{"title":"Scheme design and assessment of hybrid pump feed system with energy management for throttleable liquid rocket engine","authors":"Hao Zhu , Jincheng Wang , Yuanjun Zhang , Xintong Li , Jiangning Wang , Hui Tian , Guobiao Cai","doi":"10.1016/j.actaastro.2024.10.013","DOIUrl":"10.1016/j.actaastro.2024.10.013","url":null,"abstract":"<div><div>Currently, there is considerable emphasis on the electric pump-fed cycle for liquid engine, primarily due to its design simplicity. However, its development is hindered by the underdeveloped state of power battery technology. Drawing inspiration from hybrid power technology used in electric vehicles and turbochargers, a hybrid pump feed system for throttleable engines is originally proposed as a promising solution. This system integrates the electric motor into the gas generator cycle, with several topologies evaluated. The parallel configuration featuring a mid-motor is selected for its compact structure, efficient power-splitting and energy recovery. Additionally, customized energy management strategies and optimization models are developed to effectively allocate power throughout the operational processes of liquid engines. A comparative analysis of four engine cycles is conducted under the typically variable-thrust mission. The results indicate that attributed to the conservation of turbo-gas and battery energy, the optimized hybrid pump achieves a reduction of 2.39 % compared to the turbopump and 7.15 % to the electric pump in total mass. Adaptability assessment further indicates that the mass advantage of the hybrid pump system is more significant during prolonged engine burning and deep throttling. Specific working conditions are found in which the system prefers electric-motor driving or regenerating turbine energy. Although energy-recovery results in the system efficiency decrease, it serves to lower energy demand of battery pack, thus easing the burden on cell thermal management and structural design. This study provides a practical design framework for hybrid pump-fed rocket engines in future variable-thrust missions.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 112-124"},"PeriodicalIF":3.1,"publicationDate":"2024-10-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142534891","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}
Pub Date : 2024-10-09DOI: 10.1016/j.actaastro.2024.09.069
Bo Tang , Qiquan Quan , Dong Pan , Chu Wang , Haoyu Zheng , Kaiyi Wang , Dewei Tang , Zongquan Deng
Due to the Mars rotorcraft can conduct extensive surface exploration of Mars and carry sampler for collecting samples on the Martian surface, it is gradually becoming the mainstream exploration devices for Mars missions. In response to the thin atmosphere on Mars, with the flight duration and sample-carrying capacity of the quadcopter as constraints, we design the propulsion system parameters for the Mars quadcopter with the function of sampling on the Martian surface. A method for evaluating rotor performance indicators, including mass and Mach number at the tip of the blade, is proposed. Based on the evaluation index and the steady RANS method for predicting the lift and drag characteristics of the rotor, an appropriate rotor diameter for the Mars quadrotor is selected. The method combining NSGA-II and two-dimensional steady RANS is employed to optimize the airfoil of the Mars quadcopter blade under the condition of a chord length of 40 mm, a Mach number of 0.43, an angle of attack of 20°, and a Reynolds number based on chord of 6080. Experimental verification for the lift-to-drag characteristics of the single rotor is conducted in an environment simulating the atmospheric density on the Martian surface. The results show that the blade after optimization can generate a thrust of 5.95 N and consume power of 164.9 W, at the rotational speed of 3650 r/min. Based on the test bench with the function of sliding up and down for testing aerodynamic performance of quadcopter, the temperature of the motor and battery discharge characteristics of the Mars quadcopter are conducted. The results of the test show that the quadrotor can provide a thrust-to-weight ratio of 1.66 for the Mars quadcopter while meeting the design requirement of 3 min.
{"title":"Design and experimental verification of propulsion system for a Mars quadcopter","authors":"Bo Tang , Qiquan Quan , Dong Pan , Chu Wang , Haoyu Zheng , Kaiyi Wang , Dewei Tang , Zongquan Deng","doi":"10.1016/j.actaastro.2024.09.069","DOIUrl":"10.1016/j.actaastro.2024.09.069","url":null,"abstract":"<div><div>Due to the Mars rotorcraft can conduct extensive surface exploration of Mars and carry sampler for collecting samples on the Martian surface, it is gradually becoming the mainstream exploration devices for Mars missions. In response to the thin atmosphere on Mars, with the flight duration and sample-carrying capacity of the quadcopter as constraints, we design the propulsion system parameters for the Mars quadcopter with the function of sampling on the Martian surface. A method for evaluating rotor performance indicators, including mass and Mach number at the tip of the blade, is proposed. Based on the evaluation index and the steady RANS method for predicting the lift and drag characteristics of the rotor, an appropriate rotor diameter for the Mars quadrotor is selected. The method combining NSGA-II and two-dimensional steady RANS is employed to optimize the airfoil of the Mars quadcopter blade under the condition of a chord length of 40 mm, a Mach number of 0.43, an angle of attack of 20°, and a Reynolds number based on chord of 6080. Experimental verification for the lift-to-drag characteristics of the single rotor is conducted in an environment simulating the atmospheric density on the Martian surface. The results show that the blade after optimization can generate a thrust of 5.95 N and consume power of 164.9 W, at the rotational speed of 3650 r/min. Based on the test bench with the function of sliding up and down for testing aerodynamic performance of quadcopter, the temperature of the motor and battery discharge characteristics of the Mars quadcopter are conducted. The results of the test show that the quadrotor can provide a thrust-to-weight ratio of 1.66 for the Mars quadcopter while meeting the design requirement of 3 min.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 992-1000"},"PeriodicalIF":3.1,"publicationDate":"2024-10-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426038","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}
Pub Date : 2024-10-09DOI: 10.1016/j.actaastro.2024.10.014
Shengbing Zhou , Rui Wang , Feng Liu , Huiming Ning , Yuan Ma , Taifeng Zhang , Ning Hu
Diesel fuel plays an indispensable role in the energy power sector. Detonation is a self-pressurizing combustion mode that can improve the utilization efficiency of diesel fuel. Through experiments, this paper explored the propagation characteristics of diesel/air RDWs within three different air-inlet slot width structures. A total of 24 high-pressure atomizing nozzles were evenly distributed circumferentially to inject diesel fuel into the combustor. The air, preheated by a heater, was injected into the combustor through the air-inlet slot. The results demonstrate the successful achievement of diesel/air rotating detonation under three different air-inlet slot width structures. As the width increases, the range of operating conditions for achieving detonation becomes more limited. As the air temperature rises, so does the detonation wave's propagation velocity, reaching up to 79 % of the theoretical CJ value. Both single-wave and two-wave collision modes were obtained in the experiments, with a constantly shifting collision point of the two-wave mode, forming the drift phenomenon. The establishment time for the detonation wave is comparatively short, ranging from 2.0 to 5.5 ms, and is minimally affected by the air-inject slot width and the total air temperature. The two-wave collision mode evolved from the single-wave form.
{"title":"Experimental investigation on propagation characteristics of rotating detonation wave fueled by diesel","authors":"Shengbing Zhou , Rui Wang , Feng Liu , Huiming Ning , Yuan Ma , Taifeng Zhang , Ning Hu","doi":"10.1016/j.actaastro.2024.10.014","DOIUrl":"10.1016/j.actaastro.2024.10.014","url":null,"abstract":"<div><div>Diesel fuel plays an indispensable role in the energy power sector. Detonation is a self-pressurizing combustion mode that can improve the utilization efficiency of diesel fuel. Through experiments, this paper explored the propagation characteristics of diesel/air RDWs within three different air-inlet slot width structures. A total of 24 high-pressure atomizing nozzles were evenly distributed circumferentially to inject diesel fuel into the combustor. The air, preheated by a heater, was injected into the combustor through the air-inlet slot. The results demonstrate the successful achievement of diesel/air rotating detonation under three different air-inlet slot width structures. As the width increases, the range of operating conditions for achieving detonation becomes more limited. As the air temperature rises, so does the detonation wave's propagation velocity, reaching up to 79 % of the theoretical CJ value. Both single-wave and two-wave collision modes were obtained in the experiments, with a constantly shifting collision point of the two-wave mode, forming the drift phenomenon. The establishment time for the detonation wave is comparatively short, ranging from 2.0 to 5.5 ms, and is minimally affected by the air-inject slot width and the total air temperature. The two-wave collision mode evolved from the single-wave form.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 949-959"},"PeriodicalIF":3.1,"publicationDate":"2024-10-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426034","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}
Pub Date : 2024-10-09DOI: 10.1016/j.actaastro.2024.10.006
Runxiang Huang , Xiaodong Liu , Di Wu
Tianqin is a project scheduled for detecting gravitational waves in space. The project requires high levels of constellation stability. This paper optimizes the Tianqin trajectory over 5 years using low-thrust maneuvers and a ‘3 months on +3 months off’ observation window scheme to improve constellation stability and reduce spacecraft fuel consumption. The result is a series of stable orbit configurations. The problem of fuel optimization is solved efficiently by combining a normalization strategy, a homotopic approach, and switching detection. Additionally, the optimization strategy quantitatively evaluates the fuel consumption required to maintain the stability of the Tianqin orbits. This evaluation provides a valuable reference for the performance design of the low-thrust propulsion system in the spacecraft.
{"title":"Optimization of low-thrust periodic reconfiguration in Tianqin orbit","authors":"Runxiang Huang , Xiaodong Liu , Di Wu","doi":"10.1016/j.actaastro.2024.10.006","DOIUrl":"10.1016/j.actaastro.2024.10.006","url":null,"abstract":"<div><div>Tianqin is a project scheduled for detecting gravitational waves in space. The project requires high levels of constellation stability. This paper optimizes the Tianqin trajectory over 5 years using low-thrust maneuvers and a ‘3 months on +3 months off’ observation window scheme to improve constellation stability and reduce spacecraft fuel consumption. The result is a series of stable orbit configurations. The problem of fuel optimization is solved efficiently by combining a normalization strategy, a homotopic approach, and switching detection. Additionally, the optimization strategy quantitatively evaluates the fuel consumption required to maintain the stability of the Tianqin orbits. This evaluation provides a valuable reference for the performance design of the low-thrust propulsion system in the spacecraft.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 1049-1060"},"PeriodicalIF":3.1,"publicationDate":"2024-10-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142444998","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}
Pub Date : 2024-10-09DOI: 10.1016/j.actaastro.2024.10.017
Yang Wang , Wei Guan , Jinchang Hu
A high-fidelity dynamical model that can depict the touchdown of a probe on a small body is fundamental for precise control and is critical to the success of a landing mission. However, such models are lacking in the literature, and existing models fail to adequately account for soil properties on the small body or flexible parts (solar panels) on the probe. In this study, we develop a dynamical model with dynamics, contact, and control modules to simulate a legged probe with solar panels landing on a small body with weak gravity, unknown soil properties, and rugged terrain. The dynamical equations for the probe landing are derived by considering the solar panel deformation. A valid method for calculating the penetration depth is proposed to address the contact between the probe and soft soil based on Polygonal Contact Model (PCM). Theories of terra-mechanics and Coulomb friction are introduced to characterize the physical properties of the soil. Numerical examples illustrate the natural/controlled landing sequence and demonstrate the validity of the dynamical model. Compared to the rigid-body dynamical model, flexible solar panels increase energy dissipation and thus make the controlled-landing probe less prone to bounce repeatedly on a small body. In the natural landing mode, the solar panels cause the probe to fluctuate continuously. For the physical properties of the soil, both larger friction moduli and smaller internal friction angles are detrimental to the stable landing of the probe on a small body.
{"title":"High-fidelity landing modeling of small-body probes: Considering solar panel deformation and soil properties","authors":"Yang Wang , Wei Guan , Jinchang Hu","doi":"10.1016/j.actaastro.2024.10.017","DOIUrl":"10.1016/j.actaastro.2024.10.017","url":null,"abstract":"<div><div>A high-fidelity dynamical model that can depict the touchdown of a probe on a small body is fundamental for precise control and is critical to the success of a landing mission. However, such models are lacking in the literature, and existing models fail to adequately account for soil properties on the small body or flexible parts (solar panels) on the probe. In this study, we develop a dynamical model with dynamics, contact, and control modules to simulate a legged probe with solar panels landing on a small body with weak gravity, unknown soil properties, and rugged terrain. The dynamical equations for the probe landing are derived by considering the solar panel deformation. A valid method for calculating the penetration depth is proposed to address the contact between the probe and soft soil based on Polygonal Contact Model (PCM). Theories of terra-mechanics and Coulomb friction are introduced to characterize the physical properties of the soil. Numerical examples illustrate the natural/controlled landing sequence and demonstrate the validity of the dynamical model. Compared to the rigid-body dynamical model, flexible solar panels increase energy dissipation and thus make the controlled-landing probe less prone to bounce repeatedly on a small body. In the natural landing mode, the solar panels cause the probe to fluctuate continuously. For the physical properties of the soil, both larger friction moduli and smaller internal friction angles are detrimental to the stable landing of the probe on a small body.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"226 ","pages":"Pages 125-136"},"PeriodicalIF":3.1,"publicationDate":"2024-10-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142534892","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}
Pub Date : 2024-10-06DOI: 10.1016/j.actaastro.2024.09.071
Alexander N. Cohen , Philip Lubin , Darrel Robertson , Mark Boslough , Sasha Egan , Angela M. Stickle , Elizabeth A. Silber , Peter Meinhold , Brin Bailey , Dharv Patel
Planetary defense from asteroids via deflective means alone does not offer viable solutions in terminal scenarios where there is little warning time before impact. The PI method of planetary defense enables operation in terminal interdiction modes where there is little warning time prior to impact, but can also operate in the same extended time scale interdiction modes as made possible by traditional deflection techniques, which results in a versatile, multi-modal planetary defense capability. The method is also practical and cost-effective since it relies solely on launch vehicles and penetrator materials already available today, and thus presents itself as a logical and competitive option for planetary defense. As per the PI method, we investigate the effectiveness of rubble pile asteroid disruption and deflection via hypervelocity impacts with 10:1 aspect ratio cylindrical tungsten penetrators. We present the results of an ongoing simulation campaign dedicated to investigating the PI method, using the Lawrence Livermore National Laboratory (LLNL) arbitrary Lagrangian–Eulerian (ALE) hydrodynamics code ALE3D run with the High-End Computing Capability (HECC) at NASA Ames Research Center. We model heterogeneous rubble pile asteroids with a distribution of spherical boulders of varying initial yield strengths set within a weak binder material. We find that rubble pile asteroids of this type in the 20–100 meter-class can be effectively mitigated via 20 km/s impacts with 100–1000 kg penetrators via the coupling of the penetrator kinetic energy into the bulk material of the asteroid.
在撞击前几乎没有预警时间的末端情况下，仅通过偏转手段来防御小行星并不能提供可行的解决方案。PI 行星防御方法可以在撞击前预警时间较短的末端拦截模式下运行，也可以在传统偏转技术所能实现的扩展时间尺度拦截模式下运行，从而形成一种多用途、多模式的行星防御能力。由于该方法完全依赖于目前已有的运载火箭和穿甲弹材料，因此实用性和成本效益也很高，是行星防御的一种合理而有竞争力的选择。根据 PI 方法，我们研究了用长宽比为 10:1 的圆柱形钨穿甲弹通过超高速撞击碎石堆小行星来破坏和偏转的有效性。我们利用劳伦斯利弗莫尔国家实验室（LLNL）的任意拉格朗日-欧勒（ALE）流体力学代码 ALE3D 和美国国家航空航天局艾姆斯研究中心的高端计算能力（HECC）运行，展示了正在进行的专门研究 PI 方法的模拟活动的结果。我们对异质碎石堆小行星进行建模，在弱粘合剂材料中分布着不同初始屈服强度的球形巨石。我们发现，这种类型的 20-100 米级碎石堆小行星可以通过 100-1000 千克穿透器以 20 千米/秒的速度撞击小行星，通过穿透器动能与小行星主体材料的耦合，有效地减缓撞击。
{"title":"Asteroid disruption and deflection simulations for multi-modal planetary defense","authors":"Alexander N. Cohen , Philip Lubin , Darrel Robertson , Mark Boslough , Sasha Egan , Angela M. Stickle , Elizabeth A. Silber , Peter Meinhold , Brin Bailey , Dharv Patel","doi":"10.1016/j.actaastro.2024.09.071","DOIUrl":"10.1016/j.actaastro.2024.09.071","url":null,"abstract":"<div><div>Planetary defense from asteroids via deflective means alone does not offer viable solutions in terminal scenarios where there is little warning time before impact. The PI method of planetary defense enables operation in terminal interdiction modes where there is little warning time prior to impact, but can also operate in the same extended time scale interdiction modes as made possible by traditional deflection techniques, which results in a versatile, multi-modal planetary defense capability. The method is also practical and cost-effective since it relies solely on launch vehicles and penetrator materials already available today, and thus presents itself as a logical and competitive option for planetary defense. As per the PI method, we investigate the effectiveness of rubble pile asteroid disruption and deflection via hypervelocity impacts with 10:1 aspect ratio cylindrical tungsten penetrators. We present the results of an ongoing simulation campaign dedicated to investigating the PI method, using the Lawrence Livermore National Laboratory (LLNL) arbitrary Lagrangian–Eulerian (ALE) hydrodynamics code ALE3D run with the High-End Computing Capability (HECC) at NASA Ames Research Center. We model heterogeneous rubble pile asteroids with a distribution of spherical boulders of varying initial yield strengths set within a weak binder material. We find that rubble pile asteroids of this type in the 20–100 meter-class can be effectively mitigated via 20 km/s impacts with 100–1000 kg penetrators via the coupling of the penetrator kinetic energy into the bulk material of the asteroid.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 960-967"},"PeriodicalIF":3.1,"publicationDate":"2024-10-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426035","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}
Pub Date : 2024-10-05DOI: 10.1016/j.actaastro.2024.09.072
Jason T. Wright , Macy Huston , Aidan Groenendaal , Lennon Nichol , Nick Tusay
In this third installment of SETI in 20xx, we very briefly and subjectively review developments in SETI in 2022. Our primary focus is 80 papers and books published or made public in 2022, which we sort into six broad categories: results from actual searches, new search methods and instrumentation, target and frequency selection, the development of technosignatures, theory of ETIs, and social aspects of SETI.
{"title":"SETI in 2022","authors":"Jason T. Wright , Macy Huston , Aidan Groenendaal , Lennon Nichol , Nick Tusay","doi":"10.1016/j.actaastro.2024.09.072","DOIUrl":"10.1016/j.actaastro.2024.09.072","url":null,"abstract":"<div><div>In this third installment of SETI in 20xx, we very briefly and subjectively review developments in SETI in 2022. Our primary focus is 80 papers and books published or made public in 2022, which we sort into six broad categories: results from actual searches, new search methods and instrumentation, target and frequency selection, the development of technosignatures, theory of ETIs, and social aspects of SETI.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 1-8"},"PeriodicalIF":3.1,"publicationDate":"2024-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426039","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}
The increasing launch rate of spacecraft, particularly due to the deployment of large constellations and miniaturized satellites in Low Earth Orbit (LEO), has led to a significant rise in space traffic and debris. This paper examines emerging technologies and strategies for future Space Traffic Management (STM) to ensure sustainable operations in space. Key focus areas include the use of artificial intelligence (AI) for enhanced Collision Avoidance (CA) systems, the development of advanced Space Surveillance and Tracking (SST) capabilities, and Active Debris Removal (ADR) techniques to mitigate the growing risks associated with space debris. Additionally, the paper explores the potential of in-orbit servicing, re-entry services, and the exploitation of Very Low Earth Orbits (VLEO) and cislunar space. The integration of these technologies and practices is essential to manage the anticipated growth in space activities while minimizing collision risks and ensuring the long-term sustainability of the space environment.
{"title":"Future activities in the near-earth space in the face of ever-increasing space traffic","authors":"Alessandro Rossi , Noelia Sánchez-Ortiz , Emmanuelle David , Roberto Opromolla , Dmitriy Grishko","doi":"10.1016/j.actaastro.2024.09.063","DOIUrl":"10.1016/j.actaastro.2024.09.063","url":null,"abstract":"<div><div>The increasing launch rate of spacecraft, particularly due to the deployment of large constellations and miniaturized satellites in Low Earth Orbit (LEO), has led to a significant rise in space traffic and debris. This paper examines emerging technologies and strategies for future Space Traffic Management (STM) to ensure sustainable operations in space. Key focus areas include the use of artificial intelligence (AI) for enhanced Collision Avoidance (CA) systems, the development of advanced Space Surveillance and Tracking (SST) capabilities, and Active Debris Removal (ADR) techniques to mitigate the growing risks associated with space debris. Additionally, the paper explores the potential of in-orbit servicing, re-entry services, and the exploitation of Very Low Earth Orbits (VLEO) and cislunar space. The integration of these technologies and practices is essential to manage the anticipated growth in space activities while minimizing collision risks and ensuring the long-term sustainability of the space environment.</div></div>","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"225 ","pages":"Pages 891-897"},"PeriodicalIF":3.1,"publicationDate":"2024-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142426087","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}
Pub Date : 2024-10-05DOI: 10.1016/j.actaastro.2024.10.009
M.H. Sabour , S. Nematiyan , P. Mazhari
Unmanned Aerial Systems (UAS) have garnered significant interest in recent years. These systems, commonly consisting of one or more Unmanned Aerial Vehicles (UAV) and satellite systems, have been extensively used to enhance the effectiveness of various SOSs, such as disaster management and relief efforts. In addition, the inaugural Mars unmanned helicopter, Ingenuity (Ginny), successfully took flight in April 2021, marking the beginning of the utilization of these systems on Mars. This research aims to build an integrated approach for developing Interlaced Unmanned Spatial Systems, considering the high level of precision required for space systems. This study aims to set up and optimize all parts of the proposed architecture for the design of IUSS, using Model-Based Systems Engineering theories and Dependency Structural Matrix foundations. This research introduces a comprehensive coherence architecture that considers all design domains, including the design process, design office, products, and requirements. Additionally, a design workflow model is provided.
近年来，无人机系统（UAS）引起了人们的极大兴趣。这些系统通常由一个或多个无人驾驶飞行器（UAV）和卫星系统组成，已被广泛用于提高灾害管理和救援等各种 SOS 的效率。此外，2021 年 4 月，首架火星无人直升机 Ingenuity（Ginny）成功飞行，标志着这些系统在火星上的应用已经开始。考虑到空间系统的高精度要求，本研究旨在建立一种开发交错无人空间系统的综合方法。本研究旨在利用基于模型的系统工程理论和依赖性结构矩阵基础，建立和优化用于设计交错式无人空间系统的拟议架构的所有部分。这项研究引入了一个全面的一致性架构，考虑了所有设计领域，包括设计流程、设计办公室、产品和需求。此外，还提供了一个设计工作流程模型。
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