Advances in Astronautics Science and Technology最新文献

{"title":"Modular Design Concept of Microwave Power Transmitting Antenna Array and Its SCS Promotion","authors":"Shi-Wei Dong,&nbsp;Yazhou Dong,&nbsp;Chengguo Li,&nbsp;Ying Wang,&nbsp;Peng Lv,&nbsp;Xiaojun Li","doi":"10.1007/s42423-021-00087-0","DOIUrl":"10.1007/s42423-021-00087-0","url":null,"abstract":"<div><p>To design a gigantic microwave power transmitting array for space solar power station, modular design procedure is discussed. Besides microwave power channels, radiating array and thermal control, functions such as DC power source and beam steering should also be included in the design of the microwave power transmitting array. Smart composite structures integrate electronics, structures, thermal control and other functions into a module, providing an advanced design and integration paradigm. Modular smart composite structure antenna is an ideal candidate for its light weight and other performance.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"5 1","pages":"3 - 10"},"PeriodicalIF":0.0,"publicationDate":"2021-10-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42423-021-00087-0.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50049185","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Designing of Long Distance LWPT System for SPS","authors":"Dele Shi,&nbsp;Xinbin Hou,&nbsp;Xiujun Huang,&nbsp;Kaiming Wang,&nbsp;Jingjing Zhang,&nbsp;Hongyan Xu","doi":"10.1007/s42423-021-00086-1","DOIUrl":"10.1007/s42423-021-00086-1","url":null,"abstract":"<div><p>Laser wireless power transmission (LWPT) is one of the effective ways to provide long-distance convenient and perpetual energy supplies to electronics. Especially in space power satellite (SPS), LWPT can be used to transfer energy not only to ground, but also to other spacecrafts, which applied for satellite rescuing, spacecraft maintaining in orbit. In space application, LWPT system has characteristics of long distance, higher power, precisely aiming accuracy and better adaptability to space environment. In this paper, we propose a long distance LWPT system in SPS. Firstly the system diagram, composition and key technologies are described, which include the selection of laser, the collimated and expanded module of laser beam, the principle of the optical-to-electrical conversion efficiency of InGaAs photovoltaic cell for the high intensity laser with different laser wavelengths, the Acquisition Pointing and Tracking (APT) system and the Maximum Power Point Tracking (MPPT) technology. Then the LWPT system in SPS is designed, which composed of laser transmitting subsystem, laser receiving subsystem, APT platform and energy managing subsystem. Finally, we evaluate the power conversion performance of LWPT by simulation, which illustrates that the system can achieve better energy transmission effect under the condition of transmission distance of 400 km (space to ground) and beam pointing accuracy of 5 μrad.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"5 1","pages":"11 - 17"},"PeriodicalIF":0.0,"publicationDate":"2021-10-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50037837","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Challenges of the SAR-Enabled Microsatellite Concept INFANTE","authors":"José P. Ferreira,&nbsp;Nuno Andrada,&nbsp;Bruno Correia,&nbsp;Tiago Pinto,&nbsp;Rui Santos,&nbsp;Vitor Cristina,&nbsp;Sérgio Cunha","doi":"10.1007/s42423-021-00085-2","DOIUrl":"10.1007/s42423-021-00085-2","url":null,"abstract":"<div><p>The INFANTE project is a public–private initiative arising from the experience of Portuguese companies and R&amp;D institutes in developing critical subsystems for space missions over the last 20 years. Using such building blocks, TEKEVER leads a consortium of 20+ entities currently developing a technology demonstrator microsatellite for Earth Observation. This paper addresses a set of technical challenges faced in the conceptualization of a satellite-borne SAR, along with new project-level approaches within the framework of new space while managing a large consortium of partners.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"5 2","pages":"167 - 182"},"PeriodicalIF":0.0,"publicationDate":"2021-10-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42423-021-00085-2.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50457597","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Deployable SMA-Based Light Solar Sail Prototype","authors":"Sourav Karmakar,&nbsp;Anand Mishra","doi":"10.1007/s42423-021-00080-7","DOIUrl":"10.1007/s42423-021-00080-7","url":null,"abstract":"<div><p>The Solar Sail has been playing a major role in de-orbiting. It was introduced to deploy Sail which can open and close. The existing Solar Sail actuation is mostly based on the Origami model. This paper is about smart material implementation for robotic applications. The design and assembling of a mini version of the light Solar Sail have been developed here. The main task is to open and close the Solar Sail with basic control. The shape memory alloy (SMA) based linear actuator has been used for controlling the open and close operation of the Light Sail. The structural details of the light Solar Sail with SMA-based linear actuator have been demonstrated as well. The experimental study is about power requirements for the opening and closing operation of the light Solar Sail. It aims to obtain minimum power consumption for closing and opening the Solar Sail with SMA-based linear actuator. This kind of setup can be used further for real-time space exploration with a robust version.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"5 2","pages":"73 - 80"},"PeriodicalIF":0.0,"publicationDate":"2021-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42423-021-00080-7.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50055567","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Correction to: System Engineering a Solar Thermal Propulsion Mission Concept for Rapid Interstellar Medium Access","authors":"Jonathan Sauder,&nbsp;Michael Preudhomme,&nbsp;Juergen Mueller,&nbsp;Dean Cheikh,&nbsp;Eric Sunada,&nbsp;Reza R. Karimi,&nbsp;Abigail Couto,&nbsp;Nitin Arora,&nbsp;Jacqueline Rapinchuk,&nbsp;Leon Alkalai","doi":"10.1007/s42423-021-00084-3","DOIUrl":"10.1007/s42423-021-00084-3","url":null,"abstract":"","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"5 2","pages":"209 - 209"},"PeriodicalIF":0.0,"publicationDate":"2021-08-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-021-00084-3","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50516503","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"The Verification of Nanosatellites Solar Panels Automatic Deployment in Microgravity Conditions","authors":"Akram Abdellatif,&nbsp;Ali H. Ali,&nbsp;Mohamed E. El-sayed,&nbsp;Nermine M. Elhusseiny,&nbsp;Youmna Mabrouk,&nbsp;Youssef M. Fathy","doi":"10.1007/s42423-021-00083-4","DOIUrl":"10.1007/s42423-021-00083-4","url":null,"abstract":"<div><p>The solar panels installed on a CubeSat are considered the main energy source of a nanosatellites. The deployment mechanism of a solar panel must be analyzed and tested extensively. Any suggested solar panel design should present a low vibrating free spinning deployment mechanism. This paper examines various types of solar panels to reach a conclusion of the efficient design when deployed on a 1U or 2U unit. However, calculations, analysis, simulations do not always give an extensive picture of how the satellite shall behave during deployment. Thus, testing in a microgravity environment gives a more accurate answer of how the satellite shall behave. In our work, various solar panels mechanisms are developed and eventually tested in microgravity. The first accordion structure for a 1U structure is tested in a microgravity environment through a parabolic flight with the National Research Council Falcon 20 aircraft. The results are recorded and analyzed to optimize the next design. The second design is based on a drag-sail mechanism for a 2U structure. The design is improved upon the first experiment results for the next parabolic flight. The simulated amount of power generated in orbit is also a main factor in our evaluation.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"5 2","pages":"1 - 11"},"PeriodicalIF":0.0,"publicationDate":"2021-08-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-021-00083-4","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50473469","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"System Engineering a Solar Thermal Propulsion Mission Concept for Rapid Interstellar Medium Access","authors":"Jonathan Sauder,&nbsp;Michael Preudhomme,&nbsp;Juergen Mueller,&nbsp;Dean Cheikh,&nbsp;Eric Sunada,&nbsp;Reza R. Karimi,&nbsp;Abigail Couto,&nbsp;Nitin Arora,&nbsp;Jacqueline Rapinchuk,&nbsp;Leon Alkalai","doi":"10.1007/s42423-021-00077-2","DOIUrl":"10.1007/s42423-021-00077-2","url":null,"abstract":"<div><p>The interstellar medium (ISM) represents the next frontier in space exploration, with many new discoveries to be made. The challenge, being so far away from Earth, the ISM requires many decades to reach. To advance our knowledge of what exists beyond our solar system, new approaches for rapid access are required. One such approach is solar thermal propulsion (STP). The approach uses several Venus and Earth gravity assists to fly to Jupiter and use its gravity well to dive towards the Sun. Approaching within three solar radii a perihelion burn would be performed, maximising the spacecraft’s Δ<i>V</i> to achieve high solar system escape velocities. A unique aspect of the STP mission concept is that the Sun is used not only as a gravity well for an Oberth manoeuvre, but also to heat the fuel to ultra-high temperatures (&gt; 3000 K), enabling a monopropellant burn with high specific impulse (<i>I</i>_sp). Prior preliminary studies indicated escape velocities of over 20 astronomical unit (AU)/year would be possible. An in-depth modelling exercise was undertaken to determine how such a system would perform. The model in this paper showed the current STP design is capable of providing just under 9 ± 1 AU/year, but there are many technology developments that could increase escape velocity. The technologies vary from items that could be implemented in the near term, like turbo-pumps driven by the hydrogen, to items requiring more extensive development programs like thin coatings which do not erode in superheated hydrogen. After reviewing the STP approach, and comparing it to a solid rocket motor (SRM), it was found that with currently available technology, SRM outperforms STP with an escape velocity of approximately 10–12 AU/year. However, future advances in heat exchanger lining materials, turbo pumps, and advanced heat exchanger geometries may enable solar thermal propulsion to provide higher escape velocities, providing one of the fastest ways to exit the solar system. Ultimately, if all technology paths could be implemented with minimal side effects, the performance in a best-case scenario could reach up to 16 AU/year.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"4 1","pages":"77 - 90"},"PeriodicalIF":0.0,"publicationDate":"2021-07-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-021-00077-2","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50103276","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Starting Position-Based Database Pruning Strategy for Asteroid Missions Departing from a Main Belt Parking Orbit","authors":"Alena Probst","doi":"10.1007/s42423-021-00082-5","DOIUrl":"10.1007/s42423-021-00082-5","url":null,"abstract":"<div><p>One of the biggest open questions in the field of asteroid mining are the unknown characteristics and composition of more than 99% of the discovered objects. In order to minimize the risks of false investment, this uncertainty has to be diminished. One strategy to overcome this is to realize space missions that characterize the composition of asteroids in an efficient way. The above described issue is addressed in this paper. A target accessibility analysis is presented, that is tailored for asteroid characterization missions departing from a main belt parking orbit. To enable and facilitate a flexible, non predefined and autonomous object selection, adequate database constraints based on the orbital elements of the targets at departure are presented that enable the filtering of non-reachable objects without excluding potential targets. The constraints are applied to all asteroids currently listed in the JPL Small-Body Database Browser. With the derived constraints, the used database can be reduced to 1% of its original size.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"5 2","pages":"141 - 148"},"PeriodicalIF":0.0,"publicationDate":"2021-07-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-021-00082-5","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50496551","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Model Predictive and Inversive Control for State Transition of Dynamics Systems","authors":"Tianle Tan,&nbsp;Jie Chen","doi":"10.1007/s42423-021-00081-6","DOIUrl":"10.1007/s42423-021-00081-6","url":null,"abstract":"<div><p>In this paper, a new method of state stability, transition and tracking control for dynamics system based on model prediction and inversion is introduced. The estimation of system state bias in the future is obtained by model prediction. According to the dynamics evolution law of the controlled object, the control command to eliminate the future deviation is obtained by dynamics inversion. The compensation control is designed for the current and historical state deviations, and a state control method based on dynamics model of the controlled object is constructed. This method can be widely applied to various forms of control, and can better realize the state transition, tracking and stability control of dynamics system under the time constraint. The controller can be self-organized according to the model of the controlled object, and the parameters of the controller can be adjusted adaptively. It has good robustness to load/disturbance and deviations of model parameter, state measurement and control execution. The characteristics of this method are discussed, a simulation of rocket attitude control is given and the future research focus of this method is prospected.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"5 2","pages":"135 - 140"},"PeriodicalIF":0.0,"publicationDate":"2021-07-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-021-00081-6","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50465801","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"A Method for Calculating the Probability Distribution of Interference Involving Mega-Constellations","authors":"Ziqiao Lin,&nbsp;Jin Jin,&nbsp;Jian Yan,&nbsp;Linling Kuang","doi":"10.1007/s42423-021-00079-0","DOIUrl":"10.1007/s42423-021-00079-0","url":null,"abstract":"<div><p>In recent years, the mega-constellation programs represented by StarLink have been proposed successively. Mega-constellations compose of far more satellites than traditional constellations and possess more complex constellation configurations, which leads to a sharp increase in the calculation of probability distribution of interference. In this paper, we propose a new method to reduce the computational amount. For the satellite communication system whose operating mode and communication parameters have been determined, the interference value is only related to the position distribution of satellites in different constellations relative to the earth station. Hence, the probability distribution of inter-constellation interference value can be solved by deriving the probability of diverse constellations satellites’ position relative to the earth station. On basis of this, we calculate the occurrence probability of different constellation snapshots and the interference value between snapshots of different constellations in turn. Furthermore, we can use the joint probability of constellations’ satellite distribution to evaluate the probability distribution of interference between mega-constellations. Simulation results demonstrate that the proposed method achieves the same accuracy as the traditional method with higher computation efficiency, and the occurrence probability of maximum interference value can be obtained deterministically, which is suitable for the interference evaluation involving mega-constellations.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"4 1","pages":"107 - 117"},"PeriodicalIF":0.0,"publicationDate":"2021-05-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-021-00079-0","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50521767","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}