Pub Date : 2005-11-01DOI: 10.2514/6.iac-04-iaa.3.6.2.08
C. Hempsell
No national programme has undertaken either the acquisition or operation of more than one personnel transportation system at one time. Only capsules can fulfil all the roles required for complete and sustained in-orbit operations so a capsule is the best approach. However when combined with an expendable launch system safety concerns limit the extent to which a capsule can be used to deliver crews to orbit. It follows that a capsule should be designed to maximise its multi-role capability with an emphasis on roles other than crew delivery (which should be undertaken by reusable systems). It is shown that with technology advances since the 1960s, capsules can be made with considerably greater potential. This is illustrated with a feasibility study design for a capsule of approximately 10 tonne fuelled weight and capable of carrying four people on a very wide range of missions. The conclusion reached is that a multi-purpose capsule can be a very high value investment, providing an effective way of doing many missions in both expendable and reusable launch system environments. However to achieve this potential the capsule has to be carefully specified, and employ the best of systems thinking in its implementation.
{"title":"MULTI-ROLE CAPSULES: FULFILLING THEIR POTENTIAL","authors":"C. Hempsell","doi":"10.2514/6.iac-04-iaa.3.6.2.08","DOIUrl":"https://doi.org/10.2514/6.iac-04-iaa.3.6.2.08","url":null,"abstract":"No national programme has undertaken either the acquisition or operation of more than one personnel transportation system at one time. Only capsules can fulfil all the roles required for complete and sustained in-orbit operations so a capsule is the best approach. However when combined with an expendable launch system safety concerns limit the extent to which a capsule can be used to deliver crews to orbit. It follows that a capsule should be designed to maximise its multi-role capability with an emphasis on roles other than crew delivery (which should be undertaken by reusable systems). It is shown that with technology advances since the 1960s, capsules can be made with considerably greater potential. This is illustrated with a feasibility study design for a capsule of approximately 10 tonne fuelled weight and capable of carrying four people on a very wide range of missions. The conclusion reached is that a multi-purpose capsule can be a very high value investment, providing an effective way of doing many missions in both expendable and reusable launch system environments. However to achieve this potential the capsule has to be carefully specified, and employ the best of systems thinking in its implementation.","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"57 1","pages":"347-356"},"PeriodicalIF":0.0,"publicationDate":"2005-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"75008566","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 : 2005-01-01DOI: 10.1016/B978-008044731-5/50043-3
A. Bolonkin
{"title":"Multi-reflex Propulsion Systems for Space and Air Vehicles and Energy Transfer for Long Distance","authors":"A. Bolonkin","doi":"10.1016/B978-008044731-5/50043-3","DOIUrl":"https://doi.org/10.1016/B978-008044731-5/50043-3","url":null,"abstract":"","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"38 1","pages":"223-244"},"PeriodicalIF":0.0,"publicationDate":"2005-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"84199336","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}
R. Walker, D. Izzo, C. Negueruela, L. Summerer, M. Ayre, M. Vasile
{"title":"Concepts for near-Earth asteroid deflection using spacecraft with advanced nuclear and solar electric propulsion systems","authors":"R. Walker, D. Izzo, C. Negueruela, L. Summerer, M. Ayre, M. Vasile","doi":"10.2514/6.iac-04-q.5.08","DOIUrl":"https://doi.org/10.2514/6.iac-04-q.5.08","url":null,"abstract":"","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"39 1","pages":"268-278"},"PeriodicalIF":0.0,"publicationDate":"2005-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"83168839","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 : 2004-10-01DOI: 10.2514/6.iac-04-q.2.a.10
C. Jack, R. Wall, C. Welch
A solar kite is a small rigid solar sail with an area of a few square metres, capable of carrying a payload of a few hundred grams. In contrast to more ambitious solar sails, a kite can be deployed from its canister by a simple spring-driven mechanism. Because of its very small moment of inertia, a kite can be steered by quasi-passive means. This paper summaries the findings of an ESA-funded research project examining the design, construction and deployment of solar kites, together with the missions they are capable of undertaking and the science data that could be obtained through their use. It focuses in particular on the high performance ‘Spacefarer’ kite capable of progressing from GTO to near-Earth targets including the Moon, Lagrange points and asteroids.
{"title":"Spacefarer Solar Kites for Solar System Exploration","authors":"C. Jack, R. Wall, C. Welch","doi":"10.2514/6.iac-04-q.2.a.10","DOIUrl":"https://doi.org/10.2514/6.iac-04-q.2.a.10","url":null,"abstract":"A solar kite is a small rigid solar sail with an area of a few square metres, capable of carrying a payload of a few hundred grams. In contrast to more ambitious solar sails, a kite can be deployed from its canister by a simple spring-driven mechanism. Because of its very small moment of inertia, a kite can be steered by quasi-passive means. This paper summaries the findings of an ESA-funded research project examining the design, construction and deployment of solar kites, together with the missions they are capable of undertaking and the science data that could be obtained through their use. It focuses in particular on the high performance ‘Spacefarer’ kite capable of progressing from GTO to near-Earth targets including the Moon, Lagrange points and asteroids.","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"9 1","pages":"155-166"},"PeriodicalIF":0.0,"publicationDate":"2004-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82102815","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 : 2002-01-01DOI: 10.1201/9781420084320-c37
R. Barclay, Randall Brooks
The loss of the Mir space station is shown to symbolize a new consciousness of the value of space artefacts. The reasons why such artefacts as Mir become historic objects worthy of preservation are examined. Preservation of space vehicles in situ is discussed, with particular reference to safety, monitoring and long term costs. An argument is made for a wider definition for World Heritage designations to include material beyond the surface of the Earth, and for international bodies to assess, monitor and oversee these projects. Such heritage sites are seen as an economic driver for the development of space tourism in the 21 st century.
{"title":"In situ Preservation of historic spacecraft","authors":"R. Barclay, Randall Brooks","doi":"10.1201/9781420084320-c37","DOIUrl":"https://doi.org/10.1201/9781420084320-c37","url":null,"abstract":"The loss of the Mir space station is shown to symbolize a new consciousness of the value of space artefacts. The reasons why such artefacts as Mir become historic objects worthy of preservation are examined. Preservation of space vehicles in situ is discussed, with particular reference to safety, monitoring and long term costs. An argument is made for a wider definition for World Heritage designations to include material beyond the surface of the Earth, and for international bodies to assess, monitor and oversee these projects. Such heritage sites are seen as an economic driver for the development of space tourism in the 21 st century.","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"6 1","pages":"173-181"},"PeriodicalIF":0.0,"publicationDate":"2002-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"74268576","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}
The first step in the human expansion into space consists of the construction of a human-tended base on the Moon. Establishment of a lunar base depends upon the development of a structure capable of accomodating human life and activities in a shirt sleeve environment. Design and construction of a structure on the Moon require addressing a host of issues and loads that are not encountered on Earth. A lunar structure is essentially a pressure vessel since the internal pressure is the dominating load. The external pressure is effectively an absolute vacuum and the dead loads from both the material mass and a protective regolith layer are quite small due to low lunar gravity. An inflatable structure made of a thin membrane integrated with an inflated supporting frame is highly efficient in resisting the internal pressure loading and the dead loads. Preliminary design computations for a generic lunar inflatable structure are presented.
{"title":"Inflatable structures for a lunar base","authors":"W. Sadeh, M. Criswell","doi":"10.2514/6.1993-4177","DOIUrl":"https://doi.org/10.2514/6.1993-4177","url":null,"abstract":"The first step in the human expansion into space consists of the construction of a human-tended base on the Moon. Establishment of a lunar base depends upon the development of a structure capable of accomodating human life and activities in a shirt sleeve environment. Design and construction of a structure on the Moon require addressing a host of issues and loads that are not encountered on Earth. A lunar structure is essentially a pressure vessel since the internal pressure is the dominating load. The external pressure is effectively an absolute vacuum and the dead loads from both the material mass and a protective regolith layer are quite small due to low lunar gravity. An inflatable structure made of a thin membrane integrated with an inflated supporting frame is highly efficient in resisting the internal pressure loading and the dead loads. Preliminary design computations for a generic lunar inflatable structure are presented.","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"889 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"1993-09-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77006751","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}
The planet Mars, while cold and arid today, once possessed a warm and wet climate, as evidenced by extensive fluvial features observable on its surface. It is believed that the warm climate of the primitive Mars was created by a strong greenhouse effect caused by a thick CO2 atmosphere. Mars lost its warm climate when most of the available volatile CO2 was fixed into the form of carbonate rock due to the action of cycling water. It is believed, however, that sufficient CO2 to form a 300 to 600 mb atmosphere may still exist in volatile form, either adsorbed into the regolith or frozen out at the south pole. This CO2 may be released by planetary warming, and as the CO2 atmosphere thickens, positive feedback is produced which can accelerate the warming trend. Thus it is conceivable, that by taking advantage of the positive feedback inherent in Mars' atmosphere/regolith CO2 system, that engineering efforts can produce drastic changes in climate and pressure on a planetary scale. In this paper we propose a mathematical model of the Martian CO2 system, and use it to produce analysis which clarifies the potential of positive feedback to accelerate planetary engineering efforts. It is shown that by taking advantage of the feedback, the requirements for planetary engineering can be reduced by about 2 orders of magnitude relative to previous estimates. We examine the potential of various schemes for producing the initial warming to drive the process, including the stationing of orbiting mirrors, the importation of natural volatiles with high greenhouse capacity from the outer solar system, and the production of artificial halocarbon greenhouse gases on the Martian surface through in-situ industry. If the orbital mirror scheme is adopted, mirrors with dimension on the order or 100 km radius are required to vaporize the CO2 in the south polar cap. If manufactured of solar sail like material, such mirrors would have a mass on the order of 200,000 tonnes. If manufactured in space out of asteroidal or Martian moon material, about 120 MWe-years of energy would be needed to produce the required aluminum. This amount of power can be provided by near-term multi
{"title":"Technological requirements for terraforming Mars","authors":"R. Zubrin, C. Mckay","doi":"10.2514/6.1993-2005","DOIUrl":"https://doi.org/10.2514/6.1993-2005","url":null,"abstract":"The planet Mars, while cold and arid today, once possessed a warm and wet climate, as evidenced by extensive fluvial features observable on its surface. It is believed that the warm climate of the primitive Mars was created by a strong greenhouse effect caused by a thick CO2 atmosphere. Mars lost its warm climate when most of the available volatile CO2 was fixed into the form of carbonate rock due to the action of cycling water. It is believed, however, that sufficient CO2 to form a 300 to 600 mb atmosphere may still exist in volatile form, either adsorbed into the regolith or frozen out at the south pole. This CO2 may be released by planetary warming, and as the CO2 atmosphere thickens, positive feedback is produced which can accelerate the warming trend. Thus it is conceivable, that by taking advantage of the positive feedback inherent in Mars' atmosphere/regolith CO2 system, that engineering efforts can produce drastic changes in climate and pressure on a planetary scale. In this paper we propose a mathematical model of the Martian CO2 system, and use it to produce analysis which clarifies the potential of positive feedback to accelerate planetary engineering efforts. It is shown that by taking advantage of the feedback, the requirements for planetary engineering can be reduced by about 2 orders of magnitude relative to previous estimates. We examine the potential of various schemes for producing the initial warming to drive the process, including the stationing of orbiting mirrors, the importation of natural volatiles with high greenhouse capacity from the outer solar system, and the production of artificial halocarbon greenhouse gases on the Martian surface through in-situ industry. If the orbital mirror scheme is adopted, mirrors with dimension on the order or 100 km radius are required to vaporize the CO2 in the south polar cap. If manufactured of solar sail like material, such mirrors would have a mass on the order of 200,000 tonnes. If manufactured in space out of asteroidal or Martian moon material, about 120 MWe-years of energy would be needed to produce the required aluminum. This amount of power can be provided by near-term multi","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"132 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"1993-06-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79650744","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 : 1993-01-01DOI: 10.1038/scientificamerican01111873-18a
D. A. Bryant
{"title":"A new theory of the aurora","authors":"D. A. Bryant","doi":"10.1038/scientificamerican01111873-18a","DOIUrl":"https://doi.org/10.1038/scientificamerican01111873-18a","url":null,"abstract":"","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"45 1","pages":"107-114"},"PeriodicalIF":0.0,"publicationDate":"1993-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77774161","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 : 1992-01-01DOI: 10.1007/3-540-54752-5_195
C. Matthews
{"title":"Hydrogen cyanide polymerization: a preferred cosmochemical pathway.","authors":"C. Matthews","doi":"10.1007/3-540-54752-5_195","DOIUrl":"https://doi.org/10.1007/3-540-54752-5_195","url":null,"abstract":"","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"177 1","pages":"43-8"},"PeriodicalIF":0.0,"publicationDate":"1992-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82678800","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
{"title":"The use of magnetic sails to escape from low earth orbit","authors":"R. Zubrin","doi":"10.2514/6.1991-3352","DOIUrl":"https://doi.org/10.2514/6.1991-3352","url":null,"abstract":"","PeriodicalId":54906,"journal":{"name":"Jbis-Journal of the British Interplanetary Society","volume":"18 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"1991-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"81816832","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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