Advances in Astronautics Science and Technology最新文献

{"title":"Correlation Between Light Curve Observations and Laboratory Experiments Using a Debris Scale Model in an Optical Simulator","authors":"Toshifumi Yanagisawa,&nbsp;Masato Hayashi,&nbsp;Hirohisa Kurosaki,&nbsp;Satomi Kawamoto","doi":"10.1007/s42423-021-00075-4","DOIUrl":"10.1007/s42423-021-00075-4","url":null,"abstract":"<div><p>Active debris removal (ADR) is promising methods for ensuring safe space activities, free from the danger of debris. To carry out an ADR mission, the attitude and motion of the target must be determined precisely. Developing methodology to extract these values using only the target’s light curve would be a great step forward. We started the light curve observations of the ADR candidates, H2A rocket bodies (R/Bs), 2nd stages of Japanese H2A rockets using the 60 cm telescope, and the CMOS (complementary metal-oxide semiconductor) sensor. We developed an optical simulator in the laboratory to mimic observed light curves. The simulator can reproduce the exact light curve using a scale model of the H2A R/B. It considers the attitude, motion, and lighting conditions of the H2A R/Bs. On March 19, 2019, two extremely strong peaks were observed in the light curve of one of H2A R/Bs (satellite number: 39771). Simulations showed that the observed light curve is explained by the attitude of the gravity gradient stabilization where the PAF (payload attach fitting) of the H2A R/B was directed toward the earth. We found a few degrees’ tilt of the target causes shifts of the timings of the peaks. This means that the attitude of the target can be ascertained using the peak timing in some cases. Although this is one case out of countless situations, simulating exactly the same light curve is the one step toward total understanding of ADR targets’ attitude and motion from light curve observations. We also developed a light curve simulation tool using the 3-D (three-dimensional) model of H2A R/B that can estimate the overall tendency of the light curve, which will dramatically reduce experimental times for simulating light curve using the optical simulator.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"4 1","pages":"47 - 54"},"PeriodicalIF":0.0,"publicationDate":"2021-05-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-021-00075-4","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50449638","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":"For the 71st IAC: Implementation and Validation of Murrell’s Version Kalman Filter for Attitude Estimation","authors":"Gaurav Sharma,&nbsp;Tushar Goyal,&nbsp;Aditya Bhardwaj,&nbsp;Nikita Saxena,&nbsp;Jeet Yadav","doi":"10.1007/s42423-021-00078-1","DOIUrl":"10.1007/s42423-021-00078-1","url":null,"abstract":"<div><p>Cubesats with imaging payloads face unique challenges in terms of stringent pointing accuracy and stability requirements. Team Anant is a student-run technical team working to build a 3U Cubesat. This paper discusses the implementation, validation and integration of an attitude estimation algorithm as part of the satellite’s Attitude Determination System (ADS). The ADS hardware usually comprises sensors such as an IMU, magnetometer, and sun sensors. Validation methodology and architecture design, which aims to satisfy the allocated pointing budget, are also discussed. The paper introduces the motivation to choose Murrell’s version Kalman Filter and a comparison with popular alternatives. This is followed by some prerequisites, after which, the paper describes the top level overview and testing framework developed for the Kalman Filter. This requires emulating the in-orbit environment and tracking the true state to establish the performance limit with a predefined performance metric. The verification procedure adopted by the team is discussed in detail. Apart from analysing the expected trend of the filter parameters over time, a quasi-Monte Carlo approach was also followed. Furthermore, the Cramer–Rao bound is used to establish a lower bound on the error covariance matrix. Lastly, an approach for fine sensor selection is provided based on emulating its integration with the ADS. The paper concludes by discussing the lessons learnt and the important stages in the development and testing of an attitude estimation algorithm.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"4 1","pages":"91 - 106"},"PeriodicalIF":0.0,"publicationDate":"2021-05-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-021-00078-1","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50446554","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":"Variations and Control of Thrust and Mixture Ratio in Hybrid Rocket Motors","authors":"Francesco Barato,&nbsp;Elena Toson,&nbsp;Daniele Pavarin","doi":"10.1007/s42423-021-00076-3","DOIUrl":"10.1007/s42423-021-00076-3","url":null,"abstract":"<div><p>Hybrid rocket motors have several attracting characteristics such as simplicity, low cost, safety, reliability, environmental friendliness. In particular, hybrid rockets can provide complex and flexible thrust profiles not possible with solid rockets in a simpler way than liquid rockets, controlling only a single fluid. Unfortunately, the drawback of this feature is that the mixture ratio cannot be directly controlled but depends on the specific regression rate law. Therefore, in the general case the mixture ratio changes with time and with throttling. Thrust could also change with time for a fixed oxidizer flow. Moreover, propellant residuals are generated by the mixture ratio shift if the throttling profile is not known in advance. The penalties incurred could be more or less significant depending on the mission profile and requirements. In this paper, some proposed ways to mitigate or eliminate these issues are recalled, quantitatively analysed and compared with the standard case. In particular, the addition of energetic additives to influence the regression rate law, the injection of oxidizer in the post-chamber and the altering-intensity swirling-oxidizer-flow injection are discussed. The first option exploits the pressure dependency of the fuel regression to mitigate the shift during throttling. The other two techniques can control both the mixture ratio and thrust, at least in a certain range, at the expense of an increase of the architecture complexity. Moreover, some other options like pulse width modulation or multi-chamber configuration are also presented. Finally, a review of the techniques to achieve high throttling ratios keeping motor stability and efficiency is also discussed.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"4 1","pages":"55 - 76"},"PeriodicalIF":0.0,"publicationDate":"2021-04-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-021-00076-3","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50036203","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":"Global Sensitivity Analysis of Parameters During Cure Process of SRM Composite Case","authors":"Qun Liang,&nbsp;Xi-ping Feng,&nbsp;Kun Zhang,&nbsp;Jian Li,&nbsp;Shu-hua Chen,&nbsp;Xiao Hou","doi":"10.1007/s42423-021-00072-7","DOIUrl":"10.1007/s42423-021-00072-7","url":null,"abstract":"<div><p>The case for modern solid rocket motor (SRM) is a complex compose structure with fiber reinforced resin matrix composite, insulation layer and metal connections, the case forming process is a multi-physical–chemical process which involving heat transfer, chemical reaction and structure deformation. During the cure process, temperature determines whether the case cure completely and the uniformity of temperature field is an important factor in causing residual thermal stress and shrinkage stress, so temperature field is the key to the mutual coupling effect of each physical and chemical process, and the basis to analyze the cure process of the case. During the cure process of case, fluctuation of cure temperature, cure time or heat transfer of hot air in the furnace may occur, which make the actual forming process of case deviate from the ideal cure process. In order to investigate the sensitive degree of thermal cycle, convective heat transfer coefficient and thermal properties to cure uniformity during cure process of composite case, the influence rule of the three factors on uniformity of temperature and cure degree fields were analyzed by numerical simulation. A thermal-chemical model was built for a simplified composite SRM case firstly, and the model was verified. Then, the influence degree of the three factors on cure uniformity of composite case was analyzed and quantized by the Morris global sensitivity analysis method. The results show that he sensitivity order of the uniformity of temperature field for the four parameters is: thermal diffusion coefficient &gt; heat transfer coefficient &gt; duration time &gt; cure temperature. Besides, he temperature and duration time of the fourth dwell stage have less effect on the cure uniformity of composite case than that of heat transfer coefficient. Therefore, it is a challenge to design a thermal cycle that can not only guarantee the vulcanization of EPDM insulation layer, but also improve the cure uniformity.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"4 1","pages":"19 - 26"},"PeriodicalIF":0.0,"publicationDate":"2021-04-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-021-00072-7","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50443850","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":"Design of a Gas Filled Bellow Pogo Suppression Device for Launch Vehicles","authors":"Sunny Mitra,&nbsp;Saxon Mathew,&nbsp;Aneesh Rajan,&nbsp;P. Sajeev","doi":"10.1007/s42423-021-00073-6","DOIUrl":"10.1007/s42423-021-00073-6","url":null,"abstract":"<div><p>One of the important challenges to be addressed during development of a new liquid rocket stage for a launch vehicle is the suppression of pogo. Pogo is a harmful dynamic phenomenon arising from the interaction of vehicle structural axial modes with propulsion fluid system modes. The vehicle structural axial mode frequency generally increases during the course of the stage operation. The likelihood of experiencing pogo phenomenon increases when the vehicle structural axial mode frequency crosses the propulsion system frequency during the flight time. To avoid this harmful effect generally a pogo suppression device (PSD) is installed in feedlines which helps to decouple these two frequencies by lowering the propulsion system frequency to a safe value which is called the targeted design frequency. The propulsion system frequency is lowered by providing the required compliance at the pump inlet. The present work describes the design of a gas filled bellow PSD for a semi-cryogenic stage of ISRO’s new launch vehicle. A gas filled bellow PSD utilizes the stiffness of the bellows and the pneumatic stiffness offered by the compressed gas in the bellows cavity to provide the required system compliance. In general, a PSD is positioned at the pump inlet. Bellows get compressed when the pump inlet pressure increases and undergoes expansion when the pump inlet pressure reduces. One of the challenges in designing a gas filled bellow PSD is achieving the system compliance maintaining bellow deflection within permissible limits and at the same time achieving the targeted design propulsion frequency. Since the stiffness of gas is a function of its pressure and volume at a particular instant, the system is a variable stiffness system which brings in further challenges in designing the pogo corrector. The system is to be designed considering the variation in pump inlet pressure, thermodynamic process the gas undergoes, the instantaneous volume and pressure of the gas and various bounds for each of these parameters. This paper illustrates how the inputs, system requirement and constraints are formulated mathematically so that the entire design is transformed into an optimization problem with envelope of the system as the minimization function. The choice of gas and initial gas pressure and volume to be maintained are also discussed. Finally, the performance of the pogo corrector under various thermal conditions is also looked into.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"4 1","pages":"27 - 37"},"PeriodicalIF":0.0,"publicationDate":"2021-03-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-021-00073-6","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50085447","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":"Sulphur-fuelled Surface Arc Thruster for Propelling Nanosatellites","authors":"Senior Shimhanda,&nbsp;Kotaro Hiraka,&nbsp;Taro Inoue,&nbsp;Kazuhiro Toyoda,&nbsp;Mengu Cho","doi":"10.1007/s42423-021-00074-5","DOIUrl":"10.1007/s42423-021-00074-5","url":null,"abstract":"<div><p>Pulsed electrothermal thrusters use kiloampere discharge currents for polytetrafluoroethylene (PTFE) ablation and sublimation. However, higher arc currents cause higher electromagnetic interference (EMI). A 10 J surface arc thruster (SAT), which adopts current regulating diodes (CRD), was developed that enables significant reduction in EMI. A CRD limits the discharge currents to 5 A in spite of the applied voltage. A low-melting-point sulphur propellant has been used that enables low-discharge currents to efficiently ablate it and accelerate it electrothermally. In this paper, the near-term potential for elemental sulphur propellant in SAT is investigated. The advantages of sulphur with respect to PTFE are presented. First, we measured the pulse width of the main discharge. Then sulphur propellant proved superior to PTFE propellant in discharge duration. The mean pulse widths of PTFE and sulphur are 3.38 and 22.1 ms, respectively. Second, we measured the pressure rise in the vacuum chamber after each discharge. The mean pressure rises of PTFE, sulphur powder and sulphur solid are 0.43, 0.94 and 1.9 mPa, respectively. Sulphur powder experienced the least intensity of discoloration in comparison with other propellants. The discharge initiator misfired frequently during PTFE ablation, but it ignited successively during sulphur ablation. Experimental results indicate sulphur is a suitable propellant for surface discharge propulsion, and for low arc currents is superior to PTFE.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"4 1","pages":"39 - 46"},"PeriodicalIF":0.0,"publicationDate":"2021-03-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-021-00074-5","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50492954","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":"Airbus Active Debris Removal Service","authors":"A. Hall,&nbsp;P. Steele,&nbsp;J. Moulin,&nbsp;E. Ferreira","doi":"10.1007/s42423-020-00064-z","DOIUrl":"10.1007/s42423-020-00064-z","url":null,"abstract":"<div><p>With the increasing number of both functional and defunct space assets being present in orbit, and having a better understanding of the space environment, it is clear that there is a need for active debris removal (ADR) today if not in the very near future. Previous demonstrators have been successful such as the RemoveDEBRIS mission which was co-funded by the European Commission and produced by a set of partners. Airbus have also worked extensively on other projects to develop the capability to rendezvous and capture objects in space (such as the ATV with 5 successful flights, e-Deorbit, DEOS, and Space Tug). Airbus have been working with agencies and industry to create a removal service with the aim of being both technically feasible and at an attractive price point to potential customers. The capture solutions have been outlined and an example mission profile is shown for providing the service for a mega-constellation operator. With this setup, a total of 20+ spacecraft could be deorbited with a single ADR vehicle which would provide an affordable price point.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"4 1","pages":"1 - 10"},"PeriodicalIF":0.0,"publicationDate":"2021-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-020-00064-z","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50018397","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 Technology for Improving Regenerative Cooling in Advanced Cryogenic Rocket Engines for Space Transportation","authors":"A. P. Baiju,&nbsp;N. Jayan,&nbsp;G. Nageswaran,&nbsp;M. S. Suresh,&nbsp;V. Narayanan","doi":"10.1007/s42423-020-00071-0","DOIUrl":"10.1007/s42423-020-00071-0","url":null,"abstract":"<div><p>Regenerative cooling of thrust chamber is the unique solution for the thermal management of high heat flux generated inside the combustion chamber of Cryogenic rocket engine. Heat is transferred from combustion hot gas to coolant through the channels provided on inner copper shell, thereby cools the inner wall of the nozzle. A novel technique of providing copper foam inside the channels will act as an infinite fin and also act as barrier for coolant stratification. This will improve the heat transfer to the coolant and reduce the nozzle wall temperature. Heat transfer improvement with copper foam inserts to the coolant channel is demonstrated through experiments with simulated fluids. Experiments are conducted with simulated hot gas chamber and coolant channels using water as the coolant. Copper foam with high porosity is selected to fill the channels. Hot tests are carried out with copper foam filled coolant channels and measured the coolant temperature rise and pressure drop across the channels. Tests are repeated with similar hot gas condition, but without inserting copper foam inside the channels. A substantial enhancement in heat transfer to the coolant is observed with copper foam inserts experiments, which will reduce the wall temperature. This gives a good handle on the life cycle improvement of multi-start cryogenic engines for future space transportation systems. This paper details the specification of copper foam, hardware design, experiments and measurements, and the application of the augmentation of heat transfer coefficient in operating cryogenic engines.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"4 1","pages":"11 - 18"},"PeriodicalIF":0.0,"publicationDate":"2021-01-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-020-00071-0","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50037368","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":"Radioluminescent Nuclear Battery Technology Development for Space Exploration","authors":"Zhiheng Xu,&nbsp;Yunpeng Liu,&nbsp;Xiaobin Tang","doi":"10.1007/s42423-020-00067-w","DOIUrl":"10.1007/s42423-020-00067-w","url":null,"abstract":"<div><p>Radioluminescent nuclear battery is an important representative type of indirect conversion in nuclear batteries. Design, fabrication, and performance optimization of such batteries have been studied in detail. The specific research contents including optimization of material parameters of fluorescent layers, fluorescent layer structure design, radioluminescent spectra regulation, and radioluminescence emission intensity enhancement. The electrical properties of nuclear batteries with different fluorescent layers were tested under beta particles and X-ray excitation. As the mass thickness of the fluorescent layer increases, the electrical performance parameters first increase and then decrease, and there is an optimal mass thickness. A series of ZnS:Cu phosphor layers with different structure geometric parameters were prepared by tape adhesion method. When the thickness of the phosphor layer is close to the radioactive particle range, a good output performance can be achieved. Moreover, the effect mechanism of nano-fluorescent materials has also been introduced to improve battery performance. CsPbBr₃ perovskite quantum dot thin film materials and their applications in the radioluminescent nuclear batteries have been studied. CsPbBr₃ can effectively enhance the spectral response coupling degree, and greatly improve the output power of the battery. Further, a novel type of radioluminescent material using CdSe/ZnS core–shell quantum dot coupled with Au nanoparticles was prepared. The results show that the nano-coupling system can indeed improve the luminescence emission intensity and battery output performance. This research work can provide a new direction for future space battery technology.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"3 2","pages":"125 - 131"},"PeriodicalIF":0.0,"publicationDate":"2021-01-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-020-00067-w","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50445071","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":"Chloride Salt Corrosion Mechanisms and Their Application in Spacecraft Structures","authors":"Long-kui Zhu","doi":"10.1007/s42423-020-00069-8","DOIUrl":"10.1007/s42423-020-00069-8","url":null,"abstract":"<div><p>Nowadays, numerous global spacecrafts are launched, transported, or served in marine environment, but corrosive chloride salts can attack their structures. It is considered in this paper that the chloride salt corrosion failure under low loads consists of pitting, pit-to-SCC transformation, SCC, and brittle–ductile fracture. During the pit-to-SCC transformation processes, the relationships among the normal stress on cleavage planes, the applied stress and the crystal orientations are expressed quantitatively on the basis of the crystallographic features. A typical brittle–ductile fracture mode is sequential or simultaneous occurrence of cleavage and shear. The stress intensity factor and the crack length are employed to evaluate the no-omen SCC and HE failure inside the structural solids. The corrosion area and depth, the weight change and the current density are often applied to characterization of general corrosion damage in multi-scale spacecraft structures. Further, the chloride salt corrosion should be protected systematically from three aspects of anti-corrosion materials, service environment, and concentrated stress. Meanwhile, the acidic cleaning processing must be forbidden to be used in the whole spacecraft life.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"3 2","pages":"99 - 104"},"PeriodicalIF":0.0,"publicationDate":"2021-01-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1007/s42423-020-00069-8","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50445072","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}