Pub Date : 2023-06-14DOI: 10.59332/jbis-076-04-0134
A. Giordano
Interplanetary CubeSat missions are currently becoming more popular, with a significant number of recently planned missions. The context of this paper is a Mars mission, starting from a parking orbit around Earth: the adoption of a chemical propulsion system for the Earth-Mars transfer phase is investigated, considering the recent technological developments for CubeSats. A trade-off of propulsion system type and propellant results in the choice of a mono-propellant system adopting the HAN-based propellant AF-M315E (ASCENT). The main challenge for the propulsion system is to fit inside a CubeSat standardised volume, which can range up to 24 U, for which the implementation of a suitable COTS micro-pump is considered. Finally, the complete architecture and design of the propulsion system is presented. This work demonstrates the feasibility of adopting full chemical propulsion for an interplanetary CubeSat mission, with consequent advantages in terms of transfer time and required power, at the cost of relatively small mass and volume left for the other subsystems. Even better results can be expected for interplanetary missions requiring slightly lower ΔV budgets, such as Near Earth Objects exploration or asteroid fly-by missions. Keywords: CubeSat, Chemical Propulsion, Green Mono-propellant, Interplanetary Mission, Mars Exploration
{"title":"Enabling Interplanetary Exploration for CubeSats with a Fully Chemical Propulsion System","authors":"A. Giordano","doi":"10.59332/jbis-076-04-0134","DOIUrl":"https://doi.org/10.59332/jbis-076-04-0134","url":null,"abstract":"Interplanetary CubeSat missions are currently becoming more popular, with a significant number of recently planned missions. The context of this paper is a Mars mission, starting from a parking orbit around Earth: the adoption of a chemical propulsion system for the Earth-Mars transfer phase is investigated, considering the recent technological developments for CubeSats. A trade-off of propulsion system type and propellant results in the choice of a mono-propellant system adopting the HAN-based propellant AF-M315E (ASCENT). The main challenge for the propulsion system is to fit inside a CubeSat standardised volume, which can range up to 24 U, for which the implementation of a suitable COTS micro-pump is considered. Finally, the complete architecture and design of the propulsion system is presented. This work demonstrates the feasibility of adopting full chemical propulsion for an interplanetary CubeSat mission, with consequent advantages in terms of transfer time and required power, at the cost of relatively small mass and volume left for the other subsystems. Even better results can be expected for interplanetary missions requiring slightly lower ΔV budgets, such as Near Earth Objects exploration or asteroid fly-by missions. Keywords: CubeSat, Chemical Propulsion, Green Mono-propellant, Interplanetary Mission, Mars Exploration","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"22 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90094190","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 : 2023-06-14DOI: 10.59332/jbis-076-04-0145
Samantha Rawlins, L. Thomas
Today’s space nuclear technology programs are often confronted with two fundamental challenges early in the project life cycle: 1) development and testing will be more expensive than a non-nuclear alternative, and 2) the consequences of failure will be more severe. As a result, many space nuclear programs have been designed to minimize testing and maximize their probability of success: their reliability. The United States' Nuclear Engine for Rocket Vehicle Applications Program recognized these facts early on, and by 1961 the program’s primary objective set safety and reliability as the overriding considerations. This focus on reliability greatly influenced the engine's design towards minimizing the possible number of catastrophic failures modes. As such, the final configuration heavily relied on duplicate components for redundancy, including duplicate turbopumps. Despite these efforts, at program cancellation in 1972, the non-nuclear subsystem only achieved a mission predicted reliability of 33%. Some of the most significant contributions to rocket engine reliability in the last 50 years have been from advancements in the Health Monitoring System (HMS). Through rigorous instrumentation and control an engine's HMS has the potential to convert over 90% of a system's catastrophic failure modes to a safe shutdown situation. Due to this, many modern rocket engine designs no longer require redundant components and can prioritize performance-enhancing configurations over those that inherently minimize failure modes. Unfortunately, a standard liquid rocket engine HMS will likely not be compatible with a nuclear rocket engine (NRE). The HMS for a liquid rocket engine most often prevents catastrophic failure by shutting off flow to the combustion chamber. This would not work for a NRE, as removing propellant flow to the reactor could result in reactor overheating and meltdown. Maintaining flow to the reactor is often essential for safe NRE operation, such that reliance on an advanced HMS system alone may not be sufficient. This work investigates the feasibility of an NRE HMS by comparing the HMS designs for liquid rocket engines and terrestrial nuclear power plants and evaluates the necessity for redundant components to maximize overall system reliability. Keywords: Nuclear Thermal Propulsion, Nuclear Rocket Engine, Reliability, Fault Prevention, Fault Tolerance, Turbopump
{"title":"Reliability Assessment of Nuclear Thermal Engine Configuration and Health Monitoring System","authors":"Samantha Rawlins, L. Thomas","doi":"10.59332/jbis-076-04-0145","DOIUrl":"https://doi.org/10.59332/jbis-076-04-0145","url":null,"abstract":"Today’s space nuclear technology programs are often confronted with two fundamental challenges early in the project life cycle: 1) development and testing will be more expensive than a non-nuclear alternative, and 2) the consequences of failure will be more severe. As a result, many space nuclear programs have been designed to minimize testing and maximize their probability of success: their reliability. The United States' Nuclear Engine for Rocket Vehicle Applications Program recognized these facts early on, and by 1961 the program’s primary objective set safety and reliability as the overriding considerations. This focus on reliability greatly influenced the engine's design towards minimizing the possible number of catastrophic failures modes. As such, the final configuration heavily relied on duplicate components for redundancy, including duplicate turbopumps. Despite these efforts, at program cancellation in 1972, the non-nuclear subsystem only achieved a mission predicted reliability of 33%. Some of the most significant contributions to rocket engine reliability in the last 50 years have been from advancements in the Health Monitoring System (HMS). Through rigorous instrumentation and control an engine's HMS has the potential to convert over 90% of a system's catastrophic failure modes to a safe shutdown situation. Due to this, many modern rocket engine designs no longer require redundant components and can prioritize performance-enhancing configurations over those that inherently minimize failure modes. Unfortunately, a standard liquid rocket engine HMS will likely not be compatible with a nuclear rocket engine (NRE). The HMS for a liquid rocket engine most often prevents catastrophic failure by shutting off flow to the combustion chamber. This would not work for a NRE, as removing propellant flow to the reactor could result in reactor overheating and meltdown. Maintaining flow to the reactor is often essential for safe NRE operation, such that reliance on an advanced HMS system alone may not be sufficient. This work investigates the feasibility of an NRE HMS by comparing the HMS designs for liquid rocket engines and terrestrial nuclear power plants and evaluates the necessity for redundant components to maximize overall system reliability. Keywords: Nuclear Thermal Propulsion, Nuclear Rocket Engine, Reliability, Fault Prevention, Fault Tolerance, Turbopump","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"14 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82062814","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 : 2023-06-14DOI: 10.59332/jbis-076-04-0114
A. Genovese, Nadim Maraqten
Electric Propulsion (EP) comprises all types of space propulsion in which a certain amount of propellant is ionized and then accelerated by electric or magnetic fields, or both. This propulsion technology allows for much higher specific impulses (Isp > 2,000 s) than conventional chemical propulsion (Isp < 500 s), resulting in a major reduction of the propellant mass or a considerably higher final speed for a certain space mission. Hence, EP can enable very challenging space missions as DAWN has clearly shown. Furthermore, an EP system coupled with an advanced nuclear reactor could enable fast manned missions to Mars (one-way travel times less than 4 months). This propulsion technology can be scaled up to even higher specific impulses (Isp > 5,000s). However, the power needed for the same thrust is also increasing. An Oberth maneuver performed very close to the Sun could provide the additional power to a high-Isp Solar Electric Propulsion (SEP) system in order to reach the needed delta-v for challenging interstellar precursor missions. A breakthrough in power source specific mass is needed in order to enable missions with ultra-high specific impulses (> 10,000 s); this breakthrough could be realized having the power source not on board, as with Laser-powered Electric Propulsion (LEP), where the needed power is beamed to the spacecraft from an external laser source. In this case the on-board power source is limited to a light-weight photovoltaic receiver/converter. The development of ultra-high Isp ion thrusters powered by an external laser source could enable the most challenging interstellar precursor missions up to the Oort Cloud and beyond. This paper gives an update on the status of these advanced propulsion concepts, and provides some examples of interstellar precursor missions enabled by advanced EP systems which could be launched before 2040. Keywords: Interstellar, Electric Propulsion, Oberth, Laser
{"title":"Advanced Electric Propulsion Concepts for Fast Missions to the Outer Solar System and Beyond","authors":"A. Genovese, Nadim Maraqten","doi":"10.59332/jbis-076-04-0114","DOIUrl":"https://doi.org/10.59332/jbis-076-04-0114","url":null,"abstract":"Electric Propulsion (EP) comprises all types of space propulsion in which a certain amount of propellant is ionized and then accelerated by electric or magnetic fields, or both. This propulsion technology allows for much higher specific impulses (Isp > 2,000 s) than conventional chemical propulsion (Isp < 500 s), resulting in a major reduction of the propellant mass or a considerably higher final speed for a certain space mission. Hence, EP can enable very challenging space missions as DAWN has clearly shown. Furthermore, an EP system coupled with an advanced nuclear reactor could enable fast manned missions to Mars (one-way travel times less than 4 months). This propulsion technology can be scaled up to even higher specific impulses (Isp > 5,000s). However, the power needed for the same thrust is also increasing. An Oberth maneuver performed very close to the Sun could provide the additional power to a high-Isp Solar Electric Propulsion (SEP) system in order to reach the needed delta-v for challenging interstellar precursor missions. A breakthrough in power source specific mass is needed in order to enable missions with ultra-high specific impulses (> 10,000 s); this breakthrough could be realized having the power source not on board, as with Laser-powered Electric Propulsion (LEP), where the needed power is beamed to the spacecraft from an external laser source. In this case the on-board power source is limited to a light-weight photovoltaic receiver/converter. The development of ultra-high Isp ion thrusters powered by an external laser source could enable the most challenging interstellar precursor missions up to the Oort Cloud and beyond. This paper gives an update on the status of these advanced propulsion concepts, and provides some examples of interstellar precursor missions enabled by advanced EP systems which could be launched before 2040. Keywords: Interstellar, Electric Propulsion, Oberth, Laser","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"68 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"75368836","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 : 2023-06-14DOI: 10.59332/jbis-076-04-0122
G. Genta
Half a century ago the Apollo missions carried 12 people to spend a short time on the Moon. After all this time, the space agencies of some countries and a number of private companies committed themselves to restart human lunar exploration, this time with the aim to establish a long-term human presence on our satellite and to start a lunar economy. Most of the planned lunar missions are based on the use of chemical propulsion, which allows to perform the one-way Earth-Moon travel in 3 or 4 days. Recently NASA and DARPA joined forces to develop a nuclear thermal rocket for planetary and lunar missions. In spite of the relatively small distance of the Moon from the Earth, carrying the required payload to the Moon is costly and there is some interest in using more advanced propulsion systems, with the purposes of reducing both the travel time and the cost. In particular, advanced propulsion devices will be developed for travelling to more distant destinations and, when they will be available, they could be used with advantages also for the Moon. The aim of the present paper is to discuss the perspectives which will be opened in the future by the possibility of using nuclear (both thermal and electric) or solar electric propulsion and, in a more distant future, nuclear fusion propulsion to travel to the Moon. A number of examples of lunar missions performed with different types of advanced propulsion show what are the conditions at which these advances can be achieved and which are the constraints that will limit these efforts. Keywords: Lunar Missions, Human Lunar Exploration, Advanced Propulsion, Trajectory Optimization, Specific Impulse Optimization
{"title":"Advanced Propulsion for Fast Lunar Missions","authors":"G. Genta","doi":"10.59332/jbis-076-04-0122","DOIUrl":"https://doi.org/10.59332/jbis-076-04-0122","url":null,"abstract":"Half a century ago the Apollo missions carried 12 people to spend a short time on the Moon. After all this time, the space agencies of some countries and a number of private companies committed themselves to restart human lunar exploration, this time with the aim to establish a long-term human presence on our satellite and to start a lunar economy. Most of the planned lunar missions are based on the use of chemical propulsion, which allows to perform the one-way Earth-Moon travel in 3 or 4 days. Recently NASA and DARPA joined forces to develop a nuclear thermal rocket for planetary and lunar missions. In spite of the relatively small distance of the Moon from the Earth, carrying the required payload to the Moon is costly and there is some interest in using more advanced propulsion systems, with the purposes of reducing both the travel time and the cost. In particular, advanced propulsion devices will be developed for travelling to more distant destinations and, when they will be available, they could be used with advantages also for the Moon. The aim of the present paper is to discuss the perspectives which will be opened in the future by the possibility of using nuclear (both thermal and electric) or solar electric propulsion and, in a more distant future, nuclear fusion propulsion to travel to the Moon. A number of examples of lunar missions performed with different types of advanced propulsion show what are the conditions at which these advances can be achieved and which are the constraints that will limit these efforts. Keywords: Lunar Missions, Human Lunar Exploration, Advanced Propulsion, Trajectory Optimization, Specific Impulse Optimization","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"72 4","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-06-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"72422159","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 : 2023-05-15DOI: 10.59332/jbis-076-03-0078
Piotr Fil, Debdut Sengupta, Ivan Riesco, B. Tortosa, Bartosz Krawczyk, G. Ribeiro, Krzysztof Kwiatkowski, M.Ye. Boguslavskiy, Chang Liu, Junglin Sung
Project Svarog is a student-led initiative aiming to reach the heliopause using a solar sail. Orbital models have proven the feasibility of the mission given the mass-to-area ratio of about 9 grams per square meter of the sail for a satellite launched on a piggyback mission to Mars. Solar sailing increases the flexibility of missions to the outer Solar System, as unique planet alignment, which was crucial for gravity assists is no longer required. Long-term missions require a better understanding of thin membrane behaviour since buckling of sail material under solar radiation pressure might cause the spacecraft to tumble unpredictably. Reduced order model of membrane deflection is thus coupled with orbital simulation, resulting in the determination of the operation regime, for which the mission escapes the Solar System. Additionally, vacuum chamber experiments designed to investigate the effects of solar radiation pressure and heating on the transient and steady-state behaviour of the sail have been devised. The system is designed to be built as a 6U CubeSat, being one of the first missions to utilise small-scale platforms for deep space missions. Granted that the first mission is successful, the Svarog system could also serve as a low-cost testbed for new technologies and research opportunities in deep space. Keywords: Satellite, Deep Space, CubeSat, Solar Sail, Orbital Mechanics, Structural Design
{"title":"Mission Concept and Development of the First Interstellar CubeSat Powered by Solar Sailing Technology","authors":"Piotr Fil, Debdut Sengupta, Ivan Riesco, B. Tortosa, Bartosz Krawczyk, G. Ribeiro, Krzysztof Kwiatkowski, M.Ye. Boguslavskiy, Chang Liu, Junglin Sung","doi":"10.59332/jbis-076-03-0078","DOIUrl":"https://doi.org/10.59332/jbis-076-03-0078","url":null,"abstract":"Project Svarog is a student-led initiative aiming to reach the heliopause using a solar sail. Orbital models have proven the feasibility of the mission given the mass-to-area ratio of about 9 grams per square meter of the sail for a satellite launched on a piggyback mission to Mars. Solar sailing increases the flexibility of missions to the outer Solar System, as unique planet alignment, which was crucial for gravity assists is no longer required. Long-term missions require a better understanding of thin membrane behaviour since buckling of sail material under solar radiation pressure might cause the spacecraft to tumble unpredictably. Reduced order model of membrane deflection is thus coupled with orbital simulation, resulting in the determination of the operation regime, for which the mission escapes the Solar System. Additionally, vacuum chamber experiments designed to investigate the effects of solar radiation pressure and heating on the transient and steady-state behaviour of the sail have been devised. The system is designed to be built as a 6U CubeSat, being one of the first missions to utilise small-scale platforms for deep space missions. Granted that the first mission is successful, the Svarog system could also serve as a low-cost testbed for new technologies and research opportunities in deep space. Keywords: Satellite, Deep Space, CubeSat, Solar Sail, Orbital Mechanics, Structural Design","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"133 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-05-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"89659879","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 : 2023-05-15DOI: 10.59332/jbis-076-03-0094
K. Long
HeliosX is a system integrated programming design tool which has the purpose of calculating spacecraft mission profile and propulsion performance for inertial confinement fusion (ICF) driven designs. This code uses the vehicle configuration input and capsule assumptions and then calculates the likely mission profile for a given destination target. The key technology is the inclusion of the fusion propulsion system and an adequate modelling of its likely energy outputs. This paper discusses calculations for perturbed design concepts from a baseline model in both series and parallel thrust mode. These new concepts are collectively known as the advanced baseline models which are presented in preliminary form under the names Resolution, Endeavour and Pegasus. These are for missions to 4.3 ly in trip times of less than 100 years for flyby and rendezvous configurations carrying a 150 tons payload. The designs utilise an ICF capsule mass of 0.288 g filled with D-3He fuel detonated at a pulse frequency in the range 100-150 Hz. The calculations show that the propulsion systems are characterised by thrusts 0.3-2 MNkg-1, jet powers 1.2-9.2 TW and specific powers 2.9-5.1 MWkg-1 for interstellar missions at 0.045-0.049c. In addition to the preliminary mission performance calculations we also discuss the philosophy and methodology used in the design evolution. Keywords: Interstellar Studies, Fusion Propulsion, HeliosX, Project Icarus
{"title":"Application of the HeliosX ICF Advanced Propulsion Mission Analysis Code to Perturbed Interstellar Design Models","authors":"K. Long","doi":"10.59332/jbis-076-03-0094","DOIUrl":"https://doi.org/10.59332/jbis-076-03-0094","url":null,"abstract":"HeliosX is a system integrated programming design tool which has the purpose of calculating spacecraft mission profile and propulsion performance for inertial confinement fusion (ICF) driven designs. This code uses the vehicle configuration input and capsule assumptions and then calculates the likely mission profile for a given destination target. The key technology is the inclusion of the fusion propulsion system and an adequate modelling of its likely energy outputs. This paper discusses calculations for perturbed design concepts from a baseline model in both series and parallel thrust mode. These new concepts are collectively known as the advanced baseline models which are presented in preliminary form under the names Resolution, Endeavour and Pegasus. These are for missions to 4.3 ly in trip times of less than 100 years for flyby and rendezvous configurations carrying a 150 tons payload. The designs utilise an ICF capsule mass of 0.288 g filled with D-3He fuel detonated at a pulse frequency in the range 100-150 Hz. The calculations show that the propulsion systems are characterised by thrusts 0.3-2 MNkg-1, jet powers 1.2-9.2 TW and specific powers 2.9-5.1 MWkg-1 for interstellar missions at 0.045-0.049c. In addition to the preliminary mission performance calculations we also discuss the philosophy and methodology used in the design evolution. Keywords: Interstellar Studies, Fusion Propulsion, HeliosX, Project Icarus","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"1 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-05-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82096199","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 : 2023-05-15DOI: 10.59332/jbis-076-03-0087
Gary Steven Robertshaw
The Rare Earth Hypothesis contends that Earth’s unusual formation and distinct evolutionary pathways led to the unlikely emergence of Homo sapiens. This contention is developed further by combining the universal principles of the Newtonian n-body problem and Darwinism to argue that there is also an inherent randomness in the sequence, timing, duration and nature of evolutionary outcomes on alien worlds. This has two important implications. Firstly, where alien life might emerge, evolutionary pathways must differ considerably to those on Earth. Within this, intelligence is not the goal of evolution nor is it necessarily the best adaptation for a given niche; there is no systematic, inexorable progression towards higher intelligence and technology. Secondly, the chances of an advanced alien civilisation emerging from a separate, random evolutionary pathway with matching technology, and proximate signalling in deep time are vanishingly small. This re appraisal of the challenges associated with detecting alien signals has the advantage of using two key universal principles without relying explicitly on anthropocentric assumptions. Keywords: Fermi Paradox, Rare Earth Hypothesis, Alien Signals, SETI, Exoplanets
{"title":"A Re-appraisal of the Challenges Associated with Detecting Alien Signals and Technosigniatures","authors":"Gary Steven Robertshaw","doi":"10.59332/jbis-076-03-0087","DOIUrl":"https://doi.org/10.59332/jbis-076-03-0087","url":null,"abstract":"The Rare Earth Hypothesis contends that Earth’s unusual formation and distinct evolutionary pathways led to the unlikely emergence of Homo sapiens. This contention is developed further by combining the universal principles of the Newtonian n-body problem and Darwinism to argue that there is also an inherent randomness in the sequence, timing, duration and nature of evolutionary outcomes on alien worlds. This has two important implications. Firstly, where alien life might emerge, evolutionary pathways must differ considerably to those on Earth. Within this, intelligence is not the goal of evolution nor is it necessarily the best adaptation for a given niche; there is no systematic, inexorable progression towards higher intelligence and technology. Secondly, the chances of an advanced alien civilisation emerging from a separate, random evolutionary pathway with matching technology, and proximate signalling in deep time are vanishingly small. This re appraisal of the challenges associated with detecting alien signals has the advantage of using two key universal principles without relying explicitly on anthropocentric assumptions. Keywords: Fermi Paradox, Rare Earth Hypothesis, Alien Signals, SETI, Exoplanets","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"26 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-05-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"75382045","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 : 2023-05-02DOI: 10.59332/jbis-076-02-0056
Diana Nikitaeva, L. Thomas
The current goals of lunar exploration include the return of humans to the Moon for scientific activities and the ability to implement lunar in-situ resource utilization (ISRU) for propellant production and construction. Both goals will consume power and one option to meet these power requirements are small nuclear reactors (Kilopower or Pylon). Launching these might not be beneficial in the future as the lunar infrastructure develops and the power requirements grow. The possibility of lunar independence from Earth in terms of ISRU must be considered. This paper discusses the materials used in each nuclear reactor including the fuel, reflector, working fluid, etc. along with lunar abundancy of each element used in these materials. Since no lunar ore mining or material production concepts were found, a review of Earth-based mining and production methods for each material were described. As a result, furnaces, mills/crushers, and fluidized bed reactors can be utilized for various processes in material production. Other processes including leaching, flotation, etc. will need their own machines. In the future, designing multifunctional furnaces and ball mills or crushers can be considered since this will simplify the lunar infrastructure and can be advantageous in the long run decreasing Earth dependency and cost. Keywords: Lunar Resource Utilization, Fission Surface Power, Material Production
{"title":"Analysis of Small Modular Nuclear Reactor Construction on the Moon","authors":"Diana Nikitaeva, L. Thomas","doi":"10.59332/jbis-076-02-0056","DOIUrl":"https://doi.org/10.59332/jbis-076-02-0056","url":null,"abstract":"The current goals of lunar exploration include the return of humans to the Moon for scientific activities and the ability to implement lunar in-situ resource utilization (ISRU) for propellant production and construction. Both goals will consume power and one option to meet these power requirements are small nuclear reactors (Kilopower or Pylon). Launching these might not be beneficial in the future as the lunar infrastructure develops and the power requirements grow. The possibility of lunar independence from Earth in terms of ISRU must be considered. This paper discusses the materials used in each nuclear reactor including the fuel, reflector, working fluid, etc. along with lunar abundancy of each element used in these materials. Since no lunar ore mining or material production concepts were found, a review of Earth-based mining and production methods for each material were described. As a result, furnaces, mills/crushers, and fluidized bed reactors can be utilized for various processes in material production. Other processes including leaching, flotation, etc. will need their own machines. In the future, designing multifunctional furnaces and ball mills or crushers can be considered since this will simplify the lunar infrastructure and can be advantageous in the long run decreasing Earth dependency and cost. Keywords: Lunar Resource Utilization, Fission Surface Power, Material Production","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"24 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-05-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"86057290","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 : 2023-05-02DOI: 10.59332/jbis-076-02-0042
F. Arias
It is believed that the use of rockoons will revolutionize the space industry by giving priority service to microsatellite developers that now are secondary payloads for large rocket companies. However, stratospheric balloons, including rockoons, are typically filled with helium, the price of which has been rising sharply in the last decade, and if the tendency continues the use of helium in this technology could be seriously compromised. Here, we present a first assessment of the possibility for a helium closed buoyancy system in which helium is stored in a pressurized tank attached to the stratospheric balloon and pumped into the balloon and back by means of a centrifugal pump. Preliminary reckoning shows that by using a carbon-fiber-reinforced polymers (CFRP) composite as material for the storage vessel, a vessel diameter around 4.5 m will be necessary to transport a small rocket with a total mass of 150 kg. A helium closed buoyancy system will allow not just saving helium but also controlled buoyancy during lifting and the landing. Keywords: Rockoon, Helium Stratospheric Balloons, Helium Market
{"title":"A rockoon closed helium buoyancy system; a first assessment","authors":"F. Arias","doi":"10.59332/jbis-076-02-0042","DOIUrl":"https://doi.org/10.59332/jbis-076-02-0042","url":null,"abstract":"It is believed that the use of rockoons will revolutionize the space industry by giving priority service to microsatellite developers that now are secondary payloads for large rocket companies. However, stratospheric balloons, including rockoons, are typically filled with helium, the price of which has been rising sharply in the last decade, and if the tendency continues the use of helium in this technology could be seriously compromised. Here, we present a first assessment of the possibility for a helium closed buoyancy system in which helium is stored in a pressurized tank attached to the stratospheric balloon and pumped into the balloon and back by means of a centrifugal pump. Preliminary reckoning shows that by using a carbon-fiber-reinforced polymers (CFRP) composite as material for the storage vessel, a vessel diameter around 4.5 m will be necessary to transport a small rocket with a total mass of 150 kg. A helium closed buoyancy system will allow not just saving helium but also controlled buoyancy during lifting and the landing. Keywords: Rockoon, Helium Stratospheric Balloons, Helium Market","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"65 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-05-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"85020391","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 : 2023-05-02DOI: 10.59332/jbis-076-02-0046
M. Lipińska
The harmful cosmic and solar radiation is the major challenge in constructing surface habitats on the Moon. Common solutions for protecting astronauts are to cover the base with a thick layer of regolith or place the habitat underground, in lava tubes. However, these approaches sacrifice the psychological well-being of astronauts by completely cutting off their connection to the outside environment. Therefore, the study was motivated by the need to develop a system of protection against radiation for a surface lunar base that would allow for the introduction of sunlight into the habitat. The objective was to discover a technical solution that would allow greater flexibility in designing the base shell structure, provide a translucent membrane, and guarantee the safety of astronauts. This paper discusses an approach to constructing lunar habitable structures based on soil reinforcement principles and biotechnology. The nano-cellulose membranes, grown in situ, are proposed as passive radiation shielding. Nano-cellulose is a light solid substance with exceptional strength and radiation protection characteristics. After certain processes, it becomes translucent, which is a big asset when considering the introduction of natural light to the habitat. Combined with lunar regolith, cellulose membranes form a composite system enabling the construction of stable vertical surface structures while minimizing material use and habitat footprint. Keywords: Space Architecture, Lunar Base, Radiation Protection, Biotechnology, Nano-cellulose
{"title":"The Lunar Lighthouse: a Beacon of Safety and Psychological Comfort through Cellulose Application in Habitat Construction","authors":"M. Lipińska","doi":"10.59332/jbis-076-02-0046","DOIUrl":"https://doi.org/10.59332/jbis-076-02-0046","url":null,"abstract":"The harmful cosmic and solar radiation is the major challenge in constructing surface habitats on the Moon. Common solutions for protecting astronauts are to cover the base with a thick layer of regolith or place the habitat underground, in lava tubes. However, these approaches sacrifice the psychological well-being of astronauts by completely cutting off their connection to the outside environment. Therefore, the study was motivated by the need to develop a system of protection against radiation for a surface lunar base that would allow for the introduction of sunlight into the habitat. The objective was to discover a technical solution that would allow greater flexibility in designing the base shell structure, provide a translucent membrane, and guarantee the safety of astronauts. This paper discusses an approach to constructing lunar habitable structures based on soil reinforcement principles and biotechnology. The nano-cellulose membranes, grown in situ, are proposed as passive radiation shielding. Nano-cellulose is a light solid substance with exceptional strength and radiation protection characteristics. After certain processes, it becomes translucent, which is a big asset when considering the introduction of natural light to the habitat. Combined with lunar regolith, cellulose membranes form a composite system enabling the construction of stable vertical surface structures while minimizing material use and habitat footprint. Keywords: Space Architecture, Lunar Base, Radiation Protection, Biotechnology, Nano-cellulose","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"15 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-05-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82137210","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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