Pub Date : 2022-04-01DOI: 10.5821/conference-9788419184405.008
David Hernando Diaz
OrbiSat is a high school educational project that was part of the CANSAT SPAIN 2020 student competition organized by ESERO. This project has ranked first in the Catalonia Championship and second at the National Championship, winning the prize for the best technical development. OrbiSat has successfully fulfilled the objective of creating a mini satellite with the size of a soda can that was later launched by a rocket of the COSMIC Research UPC Students Association to analyze physical aspects of the air such as pressure, temperature, humidity, or the amount of UV solar radiation of a territory. Thanks to the CanSat presented by this team, during the launch we were able to know the presence of up to 15 chemical elements in the air. Elements ranging from hydrogen and oxygen can indicate water in the atmosphere or other greenhouse gases such as CO2 or methane. The launched rocket reached an approximate height of 532.7 ± 1.5 meters, with the sensors we were able to determine the apogee of the rocket and the subsequent release of the minisatellite and deployment of the parachute. We were also able to interrelate the altitude data with parameters such as humidity, UV radiation, presence of hydrogen, among others. The CanSat presented by the OrbiSat team had a unique design never seen before in other CanSat competitions, solving problems such as high weight and overheating. This design made by AutoCAD was an open concept where the air can refrigerate the CPU and also the 3D printed concept saved 125 grams over a third of the maximum allowed. In addition, all the data collected was broadcast in real-time and received by a ground station every 0.25 seconds. Before the launch, a simulation was completed estimating a 61 seconds flight, finally, the real flight was 59 seconds. The vast majority of the project was done during the COVID-19 pandemic, the consequence was new methodologies to carry on the project with a minimum time for the workshop and test phase that were supplied with simulations having a better performance than expected
{"title":"CANSAT Competition 2020: Best technical development by OrbiSat team","authors":"David Hernando Diaz","doi":"10.5821/conference-9788419184405.008","DOIUrl":"https://doi.org/10.5821/conference-9788419184405.008","url":null,"abstract":"OrbiSat is a high school educational project that was part of the CANSAT SPAIN 2020 student competition organized by ESERO. This project has ranked first in the Catalonia Championship and second at the National Championship, winning the prize for the best technical development. OrbiSat has successfully fulfilled the objective of creating a mini satellite with the size of a soda can that was later launched by a rocket of the COSMIC Research UPC Students Association to analyze physical aspects of the air such as pressure, temperature, humidity, or the amount of UV solar radiation of a territory. Thanks to the CanSat presented by this team, during the launch we were able to know the presence of up to 15 chemical elements in the air. Elements ranging from hydrogen and oxygen can indicate water in the atmosphere or other greenhouse gases such as CO2 or methane. The launched rocket reached an approximate height of 532.7 ± 1.5 meters, with the sensors we were able to determine the apogee of the rocket and the subsequent release of the minisatellite and deployment of the parachute. We were also able to interrelate the altitude data with parameters such as humidity, UV radiation, presence of hydrogen, among others. The CanSat presented by the OrbiSat team had a unique design never seen before in other CanSat competitions, solving problems such as high weight and overheating. This design made by AutoCAD was an open concept where the air can refrigerate the CPU and also the 3D printed concept saved 125 grams over a third of the maximum allowed. In addition, all the data collected was broadcast in real-time and received by a ground station every 0.25 seconds. Before the launch, a simulation was completed estimating a 61 seconds flight, finally, the real flight was 59 seconds. The vast majority of the project was done during the COVID-19 pandemic, the consequence was new methodologies to carry on the project with a minimum time for the workshop and test phase that were supplied with simulations having a better performance than expected","PeriodicalId":340665,"journal":{"name":"4th Symposium on Space Educational Activities","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127455950","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}
Pub Date : 2022-04-01DOI: 10.5821/conference-9788419184405.071
Apoorva Joshi, C. Korn, Michail Magkos, Yassin Amara, Abhishek Anil, Souktik Bhattacherjee, Sisinio Dargent de Vicente, Patrick Haffmans, Nicolas Heinz, Andrea Hinkel, Merve Karakas, A. Kolchin, V. Mani, Ilja Skrypnyk, Anne Stadtmüller
Throughout the last decade a renewed interest for lunar space exploration has been expressed through the announcements of many ambitious missions such as Artemis. Annually the Space Station Design Workshop (SSDW) tasks students and young professionals to design a space station concept in a con-current engineering environment. In line with the elevated interest on the Moon this year's SSDW was centred around a self-sustainable lunar habitat. This paper presents the conceptual design of Team Blue at the SSDW 2021. Advanced Moon Operations and Resource Extraction (AMORE) is conceptu-alized as a public-private cooperation for the creation of a lunar platform that acts as an outpost for human exploration and robotic In-situ Resources Utilization (ISRU). AMORE’s proposed location is near the rim of Shackleton Crater at the Lunar South Pole. This location provides opportunities in science and ISRU and favourable sun coverage and thermal conditions. The terrain offers a natural shield for debris and storage advantages for ISRU. The mission architecture allows for incremental crew size increase through a modular dome structure, an initial prioritization of ISRU and a sustainable resource management strategy. Based on the identified system requirements, the initial configuration envisions one core module and two modular structures that would serve as greenhouses or living spaces. The phasing of the base assembly is designed to allow for adequate conditions of an increasing crew size capacity. The greenhouse modules are designed to provide all required oxygen and most required food supply. The modules are constructed using lightweight inflatable structures, while a regolith shell will provide radiation as well as thermal and micrometeorite protection. For reliable communication, a cus-tom relay network named Lunar Earth Telecommand Telemetry Relay (LETTER) is proposed. The mis-sion architecture analysis includes several methods to financially utilize the mission. These include a range of services on the lunar surface such as training facilities for deep space missions, leasing habitats to other Moon explorers, and performing scientific and technological demonstrations. A variety of rovers will be used throughout the mission that will assist in various aspects. In addition to this, a scalable hybrid power generation system that utilizes the abundant sunlight and nuclear energy assures a suffi-cient power supply throughout the entire mission lifetime. This research presents a holistic architecture for a Moon base, which provides an approach to initially utilize the Moon. Within this context, the mission concept is primarily based on already existing or currently in-development technologies. Hence, AMORE offers an approach for a financially and technologically feasible as well as a continuous and expandable human presence on the lunar surface
{"title":"AMORE - Mission concept overview for a progressively independent and self-sustainable lunar habitat","authors":"Apoorva Joshi, C. Korn, Michail Magkos, Yassin Amara, Abhishek Anil, Souktik Bhattacherjee, Sisinio Dargent de Vicente, Patrick Haffmans, Nicolas Heinz, Andrea Hinkel, Merve Karakas, A. Kolchin, V. Mani, Ilja Skrypnyk, Anne Stadtmüller","doi":"10.5821/conference-9788419184405.071","DOIUrl":"https://doi.org/10.5821/conference-9788419184405.071","url":null,"abstract":"Throughout the last decade a renewed interest for lunar space exploration has been expressed through the announcements of many ambitious missions such as Artemis. Annually the Space Station Design Workshop (SSDW) tasks students and young professionals to design a space station concept in a con-current engineering environment. In line with the elevated interest on the Moon this year's SSDW was centred around a self-sustainable lunar habitat. This paper presents the conceptual design of Team Blue at the SSDW 2021. Advanced Moon Operations and Resource Extraction (AMORE) is conceptu-alized as a public-private cooperation for the creation of a lunar platform that acts as an outpost for human exploration and robotic In-situ Resources Utilization (ISRU). AMORE’s proposed location is near the rim of Shackleton Crater at the Lunar South Pole. This location provides opportunities in science and ISRU and favourable sun coverage and thermal conditions. The terrain offers a natural shield for debris and storage advantages for ISRU. The mission architecture allows for incremental crew size increase through a modular dome structure, an initial prioritization of ISRU and a sustainable resource management strategy. Based on the identified system requirements, the initial configuration envisions one core module and two modular structures that would serve as greenhouses or living spaces. The phasing of the base assembly is designed to allow for adequate conditions of an increasing crew size capacity. The greenhouse modules are designed to provide all required oxygen and most required food supply. The modules are constructed using lightweight inflatable structures, while a regolith shell will provide radiation as well as thermal and micrometeorite protection. For reliable communication, a cus-tom relay network named Lunar Earth Telecommand Telemetry Relay (LETTER) is proposed. The mis-sion architecture analysis includes several methods to financially utilize the mission. These include a range of services on the lunar surface such as training facilities for deep space missions, leasing habitats to other Moon explorers, and performing scientific and technological demonstrations. A variety of rovers will be used throughout the mission that will assist in various aspects. In addition to this, a scalable hybrid power generation system that utilizes the abundant sunlight and nuclear energy assures a suffi-cient power supply throughout the entire mission lifetime. This research presents a holistic architecture for a Moon base, which provides an approach to initially utilize the Moon. Within this context, the mission concept is primarily based on already existing or currently in-development technologies. Hence, AMORE offers an approach for a financially and technologically feasible as well as a continuous and expandable human presence on the lunar surface","PeriodicalId":340665,"journal":{"name":"4th Symposium on Space Educational Activities","volume":"44 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115508775","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}
Pub Date : 2022-04-01DOI: 10.5821/conference-9788419184405.039
Johanna Mehringer, Lennart Werner, C. Riegler, Frederik Dunschen
Current developments in the aerospace industry point towards more frequent interplanetary travel in the future. However, the main focus of developments is on launcher technology, yet the descent of interplanetary probes is of high importance for the success of future missions. Additionally, to the present landing approaches using either a powered descent requiring fuel or a combination of different parachutes, a third method is investigated in this project. The chosen approach is called autorotation and is commonly used in helicopters. When a helicopter suffers a loss of power, it can still land and even choose its landing site without the utilization of an engine. Similar to parachutes, the presented technology can be applied to various atmospheric conditions by modification of rotor and control parameters. Moreover, a rotor in autorotation can provide directional control and thus the choice of a landing site, which is not feasible using a parachute. All these factors make autorotation an interesting option as an entry descent and landing (EDL) technology for interplanetary missions. Our project, Daedalus 2 implements the autorotation landing strategy as part of the REXUS student project campaign under DLR / ESA / SNSA supervision. Since 2018 we are developing the SpaceSeed Mk.2, a technology demonstrator that incorporates a rotor and all necessary technological means to perform an autorotation EDL maneuver from an apogee of 80 km. The mission concept is laid out within the presented paper. This includes the main challenges like miniaturization of the SpaceSeed v2 due to the size constraints of the REXUS rocket or the used sensors for height and position determination. The importance of a technology demonstrator tested on a sounding rocket to prove the feasibility of our presented system is laid out in our publication. Furthermore, the custom development of electrical, mechanical and software sub systems is discussed. Additionally, the planned mission profile will be explained, including flight phases and different activities conducted by the SpaceSeeds during flight. Moreover, the main differences and improvements to Daedalus 1 are being discussed
目前航空航天工业的发展表明，将来会有更频繁的星际旅行。然而，发展的主要焦点是发射技术，然而行星际探测器的降落对未来任务的成功至关重要。此外，除了目前使用需要燃料的动力下降或不同降落伞组合的着陆方法外，本项目还研究了第三种方法。所选择的方法被称为自旋，通常用于直升机。当直升机失去动力时，它仍然可以着陆，甚至可以在不使用发动机的情况下选择着陆点。与降落伞类似，该技术可以通过改变转子和控制参数来适应各种大气条件。此外，旋翼在自旋中可以提供方向控制，从而选择着陆点，这是不可行的使用降落伞。所有这些因素使自旋成为行星际任务的入口下降和着陆(EDL)技术的有趣选择。我们的项目代达罗斯2号实现了自动着陆策略，作为在DLR / ESA / SNSA监督下的REXUS学生项目活动的一部分。自2018年以来，我们正在开发SpaceSeed Mk.2，这是一种技术演示器，包含一个转子和所有必要的技术手段，可以从80公里的远地点执行自旋EDL机动。任务的概念在本文中阐述。这包括主要挑战，如由于REXUS火箭的尺寸限制或用于高度和位置确定的传感器而使SpaceSeed v2小型化。在我们的出版物中阐述了在探空火箭上进行技术演示以证明我们所提出的系统的可行性的重要性。此外，还讨论了电气、机械和软件子系统的定制开发。此外，还将解释计划的任务概况，包括飞行阶段和太空种子在飞行期间进行的不同活动。此外，代达罗斯1的主要区别和改进也在讨论中
{"title":"Suborbital autorotation landing demonstrator on REXUS 29","authors":"Johanna Mehringer, Lennart Werner, C. Riegler, Frederik Dunschen","doi":"10.5821/conference-9788419184405.039","DOIUrl":"https://doi.org/10.5821/conference-9788419184405.039","url":null,"abstract":"Current developments in the aerospace industry point towards more frequent interplanetary travel in the future. However, the main focus of developments is on launcher technology, yet the descent of interplanetary probes is of high importance for the success of future missions. Additionally, to the present landing approaches using either a powered descent requiring fuel or a combination of different parachutes, a third method is investigated in this project. The chosen approach is called autorotation and is commonly used in helicopters. When a helicopter suffers a loss of power, it can still land and even choose its landing site without the utilization of an engine. Similar to parachutes, the presented technology can be applied to various atmospheric conditions by modification of rotor and control parameters. Moreover, a rotor in autorotation can provide directional control and thus the choice of a landing site, which is not feasible using a parachute. All these factors make autorotation an interesting option as an entry descent and landing (EDL) technology for interplanetary missions. Our project, Daedalus 2 implements the autorotation landing strategy as part of the REXUS student project campaign under DLR / ESA / SNSA supervision. Since 2018 we are developing the SpaceSeed Mk.2, a technology demonstrator that incorporates a rotor and all necessary technological means to perform an autorotation EDL maneuver from an apogee of 80 km. The mission concept is laid out within the presented paper. This includes the main challenges like miniaturization of the SpaceSeed v2 due to the size constraints of the REXUS rocket or the used sensors for height and position determination. The importance of a technology demonstrator tested on a sounding rocket to prove the feasibility of our presented system is laid out in our publication. Furthermore, the custom development of electrical, mechanical and software sub systems is discussed. Additionally, the planned mission profile will be explained, including flight phases and different activities conducted by the SpaceSeeds during flight. Moreover, the main differences and improvements to Daedalus 1 are being discussed","PeriodicalId":340665,"journal":{"name":"4th Symposium on Space Educational Activities","volume":"45 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116050995","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}
Pub Date : 2022-04-01DOI: 10.5821/conference-9788419184405.124
André Teixeira, João Pedro Polito, Júlio Santos, Marcos Kakitani
There are several approaches to the diffusion of the space technologies, three of them are in this work: competition, research, and extension. Thus, the objective of this work is to focus on presenting the results of the Brazilian nanosatellite team called NoizOrbita, and also to qualify quantitatively the impact of using these approaches in popularizing the topic of small satellites for space educational purposes. The team was founded on September 29, 2020, by three people: an alumni of Telecommunications Engineering at Federal University of São João del- Rei (UFSJ), Alto Paraopeba Campus (CAP), currently pursuing his Ph.D. in CubeSat Antennas at UFSC; a student currently in the 6th period of the Telecommunications Engineering undergraduate course (class of 2019); and a professor in the Department of Telecommunications and Mechatronics Engineering (DETEM). This initiative is intended to be a gateway to the space/satellite technologies in the institution and is based on three main pillars: Competitions, Research, and Extension in Nanosatellites. The team aims to obtain and develop small satellite technologies involving CAP undergraduate and graduate students, which enables them to learn the concepts of Space Engineering with the methodology of "learning by doing", covering the entire lifecycle of a spacecraft, even in a less complex way, through Systems Engineering approach. It also encourages the students to carry out scientific studies, prepare and publish papers, participate in conferences, and through extension, spread all the knowledge acquired in the various layers of society in the Alto Paraopeba region. Team members are all undergraduate and graduate students. Considering that one of the main characteristics of the team is its multidisciplinary nature, it leads to the advantage that students from all courses offered at CAP can join the group. This is reflected a lot by the concept of satellite engineering, since professionals from various areas of knowledge are sought for working with satellites and small satellites. Thus, in this work the main numbers related to the team were gathered, collected and presented in order to assess the impact and/or reach of the activities in its first year of existence. Data were extracted from databases, histories, and records on the various knowledge and information dissemination platforms. Regarding the research approach, the team obtained a significant number of scientific productions; regarding extension, presentations with satellite subjects were performed; and a great achievement with the competition aspect was obtained, which shows the effectiveness of these three approaches.
{"title":"Competition, research and extension: the three approaches to the popularization of small satellites in the Alto Paraopeba region in Brazil","authors":"André Teixeira, João Pedro Polito, Júlio Santos, Marcos Kakitani","doi":"10.5821/conference-9788419184405.124","DOIUrl":"https://doi.org/10.5821/conference-9788419184405.124","url":null,"abstract":"There are several approaches to the diffusion of the space technologies, three of them are in this work: competition, research, and extension. Thus, the objective of this work is to focus on presenting the results of the Brazilian nanosatellite team called NoizOrbita, and also to qualify quantitatively the impact of using these approaches in popularizing the topic of small satellites for space educational purposes. The team was founded on September 29, 2020, by three people: an alumni of Telecommunications Engineering at Federal University of São João del- Rei (UFSJ), Alto Paraopeba Campus (CAP), currently pursuing his Ph.D. in CubeSat Antennas at UFSC; a student currently in the 6th period of the Telecommunications Engineering undergraduate course (class of 2019); and a professor in the Department of Telecommunications and Mechatronics Engineering (DETEM). This initiative is intended to be a gateway to the space/satellite technologies in the institution and is based on three main pillars: Competitions, Research, and Extension in Nanosatellites. The team aims to obtain and develop small satellite technologies involving CAP undergraduate and graduate students, which enables them to learn the concepts of Space Engineering with the methodology of \"learning by doing\", covering the entire lifecycle of a spacecraft, even in a less complex way, through Systems Engineering approach. It also encourages the students to carry out scientific studies, prepare and publish papers, participate in conferences, and through extension, spread all the knowledge acquired in the various layers of society in the Alto Paraopeba region. Team members are all undergraduate and graduate students. Considering that one of the main characteristics of the team is its multidisciplinary nature, it leads to the advantage that students from all courses offered at CAP can join the group. This is reflected a lot by the concept of satellite engineering, since professionals from various areas of knowledge are sought for working with satellites and small satellites. Thus, in this work the main numbers related to the team were gathered, collected and presented in order to assess the impact and/or reach of the activities in its first year of existence. Data were extracted from databases, histories, and records on the various knowledge and information dissemination platforms. Regarding the research approach, the team obtained a significant number of scientific productions; regarding extension, presentations with satellite subjects were performed; and a great achievement with the competition aspect was obtained, which shows the effectiveness of these three approaches.","PeriodicalId":340665,"journal":{"name":"4th Symposium on Space Educational Activities","volume":"27 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122587873","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}
Pub Date : 2022-04-01DOI: 10.5821/conference-9788419184405.077
Adrián Pérez Portero, Lara Pilar Fernandez Capon, Marc Badia Ballús, P. Fabregat, L. Rayón, Amadeu Gonga Siles, Ieremia Crisan, A. Garcia, Mar Munuera Vilalta, L. Contreras, Juan José Ramos Castro, A. H. Jallad, A.J. Camps Carmona
The Remote sensing and Interference detector with radiomeTry and vegetation Analysis (RITA) is one of the Remote Sensing payloads selected as winners of the 2nd GRSS Student Grand Challenge in 2019, to fly on board of the 3U AlainSat-1. This CubeSat is being developed by the National Space Science and Technology Center (NSSTC), United Arab Emirates University. RITA has been designed as an academic mission, which brings together students from different backgrounds in a joint effort to apply very distinct sensors in an Earth Observation mission, fusing their results to obtain higher-accuracy measurements. The main payload used in RITA is a Total Power Radiometer such as the one on board the FSSCat mission. With these radiometric measurements, soil moisture and ice thickness will be obtained. To better characterize the extensive Radio-Frequency Interferences received by EO satellites in protected bands, several RFI Detection and Classification algorithms will be included to generate a worldwide map of RFI. As a novel addition to the 3Cat family of satellites and payloads, a hyper-spectral camera with 25 bands ranging from 600 to 975 nm will be used to obtain several indexes related to vegetation. By linking these measurements with the soil moisture obtained from the MWR, pixel downscaling can be attempted. Finally, a custom- developed LoRa transceiver will be included to provide a multi-level approach to in-situ sensors: On-demand executions of the other payloads will be able to be triggered from ground sensors if necessary, as well as simple reception of other measurements that will complement the ones obtained on the satellite. The antennas for both the MWR and the LoRa experiments have been developed in-house, and will span the entirety of one of the 3U sides of the satellite. In this work, the latest development advances will be presented, together with an updated system overview and information about the operations that will be conducted. Results obtained from the test campaign are also presented in the conference.
{"title":"RITA: a 1U multi-sensor Earth observation payload for the AlainSat-1","authors":"Adrián Pérez Portero, Lara Pilar Fernandez Capon, Marc Badia Ballús, P. Fabregat, L. Rayón, Amadeu Gonga Siles, Ieremia Crisan, A. Garcia, Mar Munuera Vilalta, L. Contreras, Juan José Ramos Castro, A. H. Jallad, A.J. Camps Carmona","doi":"10.5821/conference-9788419184405.077","DOIUrl":"https://doi.org/10.5821/conference-9788419184405.077","url":null,"abstract":"The Remote sensing and Interference detector with radiomeTry and vegetation Analysis (RITA) is one of the Remote Sensing payloads selected as winners of the 2nd GRSS Student Grand Challenge in 2019, to fly on board of the 3U AlainSat-1. This CubeSat is being developed by the National Space Science and Technology Center (NSSTC), United Arab Emirates University. RITA has been designed as an academic mission, which brings together students from different backgrounds in a joint effort to apply very distinct sensors in an Earth Observation mission, fusing their results to obtain higher-accuracy measurements. The main payload used in RITA is a Total Power Radiometer such as the one on board the FSSCat mission. With these radiometric measurements, soil moisture and ice thickness will be obtained. To better characterize the extensive Radio-Frequency Interferences received by EO satellites in protected bands, several RFI Detection and Classification algorithms will be included to generate a worldwide map of RFI. As a novel addition to the 3Cat family of satellites and payloads, a hyper-spectral camera with 25 bands ranging from 600 to 975 nm will be used to obtain several indexes related to vegetation. By linking these measurements with the soil moisture obtained from the MWR, pixel downscaling can be attempted. Finally, a custom- developed LoRa transceiver will be included to provide a multi-level approach to in-situ sensors: On-demand executions of the other payloads will be able to be triggered from ground sensors if necessary, as well as simple reception of other measurements that will complement the ones obtained on the satellite. The antennas for both the MWR and the LoRa experiments have been developed in-house, and will span the entirety of one of the 3U sides of the satellite. In this work, the latest development advances will be presented, together with an updated system overview and information about the operations that will be conducted. Results obtained from the test campaign are also presented in the conference.","PeriodicalId":340665,"journal":{"name":"4th Symposium on Space Educational Activities","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124207199","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}
Pub Date : 2022-04-01DOI: 10.5821/conference-9788419184405.014
Jordi Grau Rifà
Amateur rocket structures are usually made of composite materials, wood or aluminium, their internal geometries and interfaces are usually restricted by the available manufacturing techniques. However, with the appearance of the additive manufacturing sector new possibilities arise for the design of the structures and its complexity. In this paper a PA-12 and glass fibre composite structure for the Phobos rocket is designed which the UPC Space Program aims to use to participate in the European Rocketry challenge. The Phobos rocket structure is designed and optimized to be fabricated using additive manufacturing by Hewlett-Packard. The structure is designed using a lattice approach to obtain a PA-12 skeleton which is then reinforced with a skin of glass fibre composite. Moreover, to obtain the desired structure an optimization methodology is set using a design loop in which the critical section of the rocket is parametrically optimized to reach the equivalent traditional structure performance. The structure is optimized in the size of the lattice geometry and in the thickness of the skin as parameters. To do so, the critical load during the flight of the rocket is identified and translated to the Nastran environment to run a parametric optimization of the structural model. The optimized geometry is then extended to the rest of the rocket to obtain the overall optimized structure. In addition, several analyses are conducted to validate the structure behaviour for the different load cases. Finally, both the optimized critical case and the overall optimized structure are compared to traditional design structures to obtain conclusive results about the use and limitations of the available additive technology and its materials
{"title":"Design and optimization of a rocket structure following the requirements for the European Rocketry Challenge (EUROC) to be fabricated using additive manufacturing","authors":"Jordi Grau Rifà","doi":"10.5821/conference-9788419184405.014","DOIUrl":"https://doi.org/10.5821/conference-9788419184405.014","url":null,"abstract":"Amateur rocket structures are usually made of composite materials, wood or aluminium, their internal geometries and interfaces are usually restricted by the available manufacturing techniques. However, with the appearance of the additive manufacturing sector new possibilities arise for the design of the structures and its complexity. In this paper a PA-12 and glass fibre composite structure for the Phobos rocket is designed which the UPC Space Program aims to use to participate in the European Rocketry challenge. The Phobos rocket structure is designed and optimized to be fabricated using additive manufacturing by Hewlett-Packard. The structure is designed using a lattice approach to obtain a PA-12 skeleton which is then reinforced with a skin of glass fibre composite. Moreover, to obtain the desired structure an optimization methodology is set using a design loop in which the critical section of the rocket is parametrically optimized to reach the equivalent traditional structure performance. The structure is optimized in the size of the lattice geometry and in the thickness of the skin as parameters. To do so, the critical load during the flight of the rocket is identified and translated to the Nastran environment to run a parametric optimization of the structural model. The optimized geometry is then extended to the rest of the rocket to obtain the overall optimized structure. In addition, several analyses are conducted to validate the structure behaviour for the different load cases. Finally, both the optimized critical case and the overall optimized structure are compared to traditional design structures to obtain conclusive results about the use and limitations of the available additive technology and its materials","PeriodicalId":340665,"journal":{"name":"4th Symposium on Space Educational Activities","volume":"94 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126290021","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}
Pub Date : 2022-04-01DOI: 10.5821/conference-9788419184405.022
W. Crofts, Mattias Langer, Alex Bolland, Tahrim Uddin, Chiara Biquet, Eduard Hopkins, Jai Bassi, Myles Ing, Julia Hunter Anderson
WUSAT-3 is a 3U CubeSat being designed to carry an experimental RF signal direction finding payload in Low Earth Orbit (LEO). Successful outcome of this experiment could lead to significant benefits for the field of wildlife monitoring from Space. Commercial adoption of this process would enable the development and use of much smaller, lighter RF tracking tags, which in turn would considerably increase the potential range of species that could be tracked by Satellites. The effect of the Covid-19 pandemic lockdowns has limited physical progress over the past 18 months, but the team continues to gain enormous experience and motivation from pursuing this exciting project with a very real-world mission. A recent return to near-normal working patterns has enabled the team to fully engage with the practicalities of progressing the previously produced WUSAT-3 Configuration Model, towards a testable Engineering Model. This paper outlines the development of both the initial chassis prototype (including mechanisms) and a subsystem FlatSat as a first stage towards building the complete Engineering Model. The chassis prototype was required to meet all the requirements of the FYS Design Specification [1], the NanoRacks CubeSat ICD [2], the CubeSat Design Specification [3] and those features identified by the outcomes of the WUSAT-3 Configuration Model. The FlatSat was required to include all subsystems capable of being constructed and tested without the availability of certain proprietary items that will be purchased later. The function and interface of these items, where it was necessary for the purpose of testing the assembled subsystem units that were available, was met by the design and inclusion of temporary substitute arrangements that provided similar performance. Systems Engineering methodologies were employed throughout as a means of ensuring that the design features of both chassis and FlatSat met all necessary requirements
{"title":"Developing a 3U CubeSat Engineering Model - FlatSat & Chassis Design","authors":"W. Crofts, Mattias Langer, Alex Bolland, Tahrim Uddin, Chiara Biquet, Eduard Hopkins, Jai Bassi, Myles Ing, Julia Hunter Anderson","doi":"10.5821/conference-9788419184405.022","DOIUrl":"https://doi.org/10.5821/conference-9788419184405.022","url":null,"abstract":"WUSAT-3 is a 3U CubeSat being designed to carry an experimental RF signal direction finding payload in Low Earth Orbit (LEO). Successful outcome of this experiment could lead to significant benefits for the field of wildlife monitoring from Space. Commercial adoption of this process would enable the development and use of much smaller, lighter RF tracking tags, which in turn would considerably increase the potential range of species that could be tracked by Satellites. The effect of the Covid-19 pandemic lockdowns has limited physical progress over the past 18 months, but the team continues to gain enormous experience and motivation from pursuing this exciting project with a very real-world mission. A recent return to near-normal working patterns has enabled the team to fully engage with the practicalities of progressing the previously produced WUSAT-3 Configuration Model, towards a testable Engineering Model. This paper outlines the development of both the initial chassis prototype (including mechanisms) and a subsystem FlatSat as a first stage towards building the complete Engineering Model. The chassis prototype was required to meet all the requirements of the FYS Design Specification [1], the NanoRacks CubeSat ICD [2], the CubeSat Design Specification [3] and those features identified by the outcomes of the WUSAT-3 Configuration Model. The FlatSat was required to include all subsystems capable of being constructed and tested without the availability of certain proprietary items that will be purchased later. The function and interface of these items, where it was necessary for the purpose of testing the assembled subsystem units that were available, was met by the design and inclusion of temporary substitute arrangements that provided similar performance. Systems Engineering methodologies were employed throughout as a means of ensuring that the design features of both chassis and FlatSat met all necessary requirements","PeriodicalId":340665,"journal":{"name":"4th Symposium on Space Educational Activities","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121908547","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}
Pub Date : 2022-04-01DOI: 10.5821/conference-9788419184405.049
Maximilian Von Arnim, S. Gaisser, S. Klinkner
Flying Laptop is a small satellite carrying an optical communications payload. It was launched in 2017. To improve the satellite’s attitude determination, which is used to point the payload, a new sensor fusion algorithm based on a low pass filter and a multiplicative extended Kalman filter (MEKF) was developed. As an operational satellite, improvements are only possible via software updates. The algorithm estimates the satellite's attitude from star tracker and fibre-optical gyroscope (FOG) measurements. It also estimates the gyroscope bias. The global attitude estimate uses a quaternion representation, while the Kalman filter uses Gibbs Parameters to calculate small attitude errors. Past Kalman filter predictions are saved for several time steps so that a delayed star tracker measurement can be used to update the prediction at the time of measurement. The estimate at the current time is then calculated by predicting the system attitude based on the updated past estimate. The prediction step relies on the low-pass-filtered gyroscope measurements corrected by the bias estimate. The new algorithm was developed as part of a master’s thesis at the University of Stuttgart, where Flying Laptop was developed and built. It was simulated in a MATLAB/Simulink environment using the European Space Agency’s GAFE framework. In addition, the new filter was applied to measurement data from the satellite. The results were used to compare the performance with the current filter implementation. The new Kalman filter can deal with delayed, missing, or irregular star tracker measurements. It features a lower computational complexity than the previous standard extended Kalman filter used on Flying Laptop. The mean error of the attitude estimate was reduced by up to 90%. The low pass filter improves the rotation rate estimate between star tracker measurements, especially for biased and noisy gyroscopes. However, this comes at the cost of potentially less accurate attitude estimates. Educational satellites benefit from the new algorithm given their typically limited processing power and cheap commercial-off-the-shelf (COTS) sensors. This paper presents the approach in detail and shows its benefits
{"title":"Improved sensor fusion for flying laptop based on a multiplicative EKF","authors":"Maximilian Von Arnim, S. Gaisser, S. Klinkner","doi":"10.5821/conference-9788419184405.049","DOIUrl":"https://doi.org/10.5821/conference-9788419184405.049","url":null,"abstract":"Flying Laptop is a small satellite carrying an optical communications payload. It was launched in 2017. To improve the satellite’s attitude determination, which is used to point the payload, a new sensor fusion algorithm based on a low pass filter and a multiplicative extended Kalman filter (MEKF) was developed. As an operational satellite, improvements are only possible via software updates. The algorithm estimates the satellite's attitude from star tracker and fibre-optical gyroscope (FOG) measurements. It also estimates the gyroscope bias. The global attitude estimate uses a quaternion representation, while the Kalman filter uses Gibbs Parameters to calculate small attitude errors. Past Kalman filter predictions are saved for several time steps so that a delayed star tracker measurement can be used to update the prediction at the time of measurement. The estimate at the current time is then calculated by predicting the system attitude based on the updated past estimate. The prediction step relies on the low-pass-filtered gyroscope measurements corrected by the bias estimate. The new algorithm was developed as part of a master’s thesis at the University of Stuttgart, where Flying Laptop was developed and built. It was simulated in a MATLAB/Simulink environment using the European Space Agency’s GAFE framework. In addition, the new filter was applied to measurement data from the satellite. The results were used to compare the performance with the current filter implementation. The new Kalman filter can deal with delayed, missing, or irregular star tracker measurements. It features a lower computational complexity than the previous standard extended Kalman filter used on Flying Laptop. The mean error of the attitude estimate was reduced by up to 90%. The low pass filter improves the rotation rate estimate between star tracker measurements, especially for biased and noisy gyroscopes. However, this comes at the cost of potentially less accurate attitude estimates. Educational satellites benefit from the new algorithm given their typically limited processing power and cheap commercial-off-the-shelf (COTS) sensors. This paper presents the approach in detail and shows its benefits","PeriodicalId":340665,"journal":{"name":"4th Symposium on Space Educational Activities","volume":"35 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115858950","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}
Pub Date : 2022-04-01DOI: 10.5821/conference-9788419184405.006
Iván Sermanoukian Molina, Lluís Montilla Rodríguez, David González Díez, Miquel Sureda Anfres, Jorge Mata Diaz, Juan José Alins Delgado
CubeSat reliability is still considered an obstacle due to the sizeable fail rates generally attributed to the dead-on-arrival cases and early subsystem malfunctions. Thus, as CubeSats' primary purpose moves from technological demonstrations and university projects to missions where a significant risk of failure is not acceptable, an inexpensive method to emulate low Earth orbit constellations is being researched. The results presented have been developed in the framework of the PLATHON research project, which intends to develop a hardware-in-the-loop emulation platform for nanosatellite constellations with optical inter-satellite communication and ground-to-satellite links. Consequently, a crucial aspect of this project is to have a sufficiently precise orbital propagator with real-time manoeuvring control and graphical representation. NASA's OpenSatKit, a multi-faceted open-source platform with an inbuilt propagator known as 42, has been chosen to analyse the programme's feasibility in order to create a constellation testing bench. As an initial development of a software-in-the-loop application, the pre- processing of files has been automated; enhanced Attitude Determination and Control System manoeuvres have been added and configured through bidirectional socket interfaces, and the results format has been modified to be easily post-processed with MATLAB and Simulink
{"title":"Mission analysis of nanosatellite constellations with OpenSatKit","authors":"Iván Sermanoukian Molina, Lluís Montilla Rodríguez, David González Díez, Miquel Sureda Anfres, Jorge Mata Diaz, Juan José Alins Delgado","doi":"10.5821/conference-9788419184405.006","DOIUrl":"https://doi.org/10.5821/conference-9788419184405.006","url":null,"abstract":"CubeSat reliability is still considered an obstacle due to the sizeable fail rates generally attributed to the dead-on-arrival cases and early subsystem malfunctions. Thus, as CubeSats' primary purpose moves from technological demonstrations and university projects to missions where a significant risk of failure is not acceptable, an inexpensive method to emulate low Earth orbit constellations is being researched. The results presented have been developed in the framework of the PLATHON research project, which intends to develop a hardware-in-the-loop emulation platform for nanosatellite constellations with optical inter-satellite communication and ground-to-satellite links. Consequently, a crucial aspect of this project is to have a sufficiently precise orbital propagator with real-time manoeuvring control and graphical representation. NASA's OpenSatKit, a multi-faceted open-source platform with an inbuilt propagator known as 42, has been chosen to analyse the programme's feasibility in order to create a constellation testing bench. As an initial development of a software-in-the-loop application, the pre- processing of files has been automated; enhanced Attitude Determination and Control System manoeuvres have been added and configured through bidirectional socket interfaces, and the results format has been modified to be easily post-processed with MATLAB and Simulink","PeriodicalId":340665,"journal":{"name":"4th Symposium on Space Educational Activities","volume":"24 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131928551","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}
Pub Date : 2022-04-01DOI: 10.5821/conference-9788419184405.081
Alessandro Bortotto, Giuliano degli Agli, Federico Favotto, Fabio Mattiazzi, Miroljub Mihailovic, N. Pozzato, Francesco Branz, L. Olivieri, Alex Caon, A. Francesconi
In the last decades, small satellites have played an important role in space missions. Due to their reduced dimension and costs, they became affordable to smaller companies and research laboratories to conduct scientific experiments and technological demonstrations in space. In addition, the number of these satellites has considerably increased due to their wide use in technological, scientific and commercial domains. In this scenario, autonomous architectures, as well as miniaturized mechanical subsystems for small satellites, are continuously investigated. Experimental Rendezvous in Microgravity Environment Study (ERMES) is a student project that focuses on the simulation of an autonomous docking manoeuvres between two CubeSats mock-ups equipped with miniaturized Guidance Navigation and Control systems and mechanical docking interfaces. ERMES aims to integrate different subsystems for autonomous docking, to increase the Technology Readiness Level and to study possible applications for in-orbit servicing. This paper deals with the design and development of the tests for autonomous docking manoeuvres between two CubeSats mock-ups to be performed in a reduced-gravity environment during a parabolic flight. A Target-Chaser configuration has been selected, where the Chaser is fully active and the Target is cooperative. The Chaser is equipped with a miniaturized cold gas propulsion system with eight thrusters to control its attitude and position; in contrast, the Target has a set of three reaction wheels to control only its attitude. The tested miniaturized mechanical docking interfaces employs a probe-drogue configuration. The most demanding aspect of the development phase will be the dedicated software for the proximity navigation. The reduced-gravity conditions will be achieved during a campaign of parabolic flights thanks to the participation to the European Space Agency “Fly Your Thesis!” programme 2022.
{"title":"ERMES: Design and preliminary simulations for an autonomous docking manoeuvre","authors":"Alessandro Bortotto, Giuliano degli Agli, Federico Favotto, Fabio Mattiazzi, Miroljub Mihailovic, N. Pozzato, Francesco Branz, L. Olivieri, Alex Caon, A. Francesconi","doi":"10.5821/conference-9788419184405.081","DOIUrl":"https://doi.org/10.5821/conference-9788419184405.081","url":null,"abstract":"In the last decades, small satellites have played an important role in space missions. Due to their reduced dimension and costs, they became affordable to smaller companies and research laboratories to conduct scientific experiments and technological demonstrations in space. In addition, the number of these satellites has considerably increased due to their wide use in technological, scientific and commercial domains. In this scenario, autonomous architectures, as well as miniaturized mechanical subsystems for small satellites, are continuously investigated. \u0000Experimental Rendezvous in Microgravity Environment Study (ERMES) is a student project that focuses on the simulation of an autonomous docking manoeuvres between two CubeSats mock-ups equipped with miniaturized Guidance Navigation and Control systems and mechanical docking interfaces. ERMES aims to integrate different subsystems for autonomous docking, to increase the Technology Readiness Level and to study possible applications for in-orbit servicing. This paper deals with the design and development of the tests for autonomous docking manoeuvres between two CubeSats mock-ups to be performed in a reduced-gravity environment during a parabolic flight. A Target-Chaser configuration has been selected, where the Chaser is fully active and the Target is cooperative. The Chaser is equipped with a miniaturized cold gas propulsion system with eight thrusters to control its attitude and position; in contrast, the Target has a set of three reaction wheels to control only its attitude. The tested miniaturized mechanical docking interfaces employs a probe-drogue configuration. The most demanding aspect of the development phase will be the dedicated software for the proximity navigation. The reduced-gravity conditions will be achieved during a campaign of parabolic flights thanks to the participation to the European Space Agency “Fly Your Thesis!” programme 2022.","PeriodicalId":340665,"journal":{"name":"4th Symposium on Space Educational Activities","volume":"83 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132211822","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}
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