A Ticket pricing strategy for an oligopolistic space tourism market

It is important for any new launch system to develop a successful pricing strategy and to optimize launch system parameters to receive a high economic profit. A question arises, what will happen when an existing suborbital flight market (the first likely to be established in space) is interfered with by a new established orbital flight market for space tourism. There is a risk that the suborbital space tourism market could be almost instantly displaced when a product capable of reaching orbit was introduced. This is best discussed using the following three cases whose results are presented in this paper. Case A presents a ticket pricing strategy for a suborbital and orbital vehicle if the two vehicles do not compete in the same market. Case B shows the necessary ticket pricing strategy for a suborbital vehicle if there is competition from an orbital flight operator. However, the suborbital vehicle would not be able to keep up with a drop in ticket prices due to its obsolete characteristics. Thus, the suborbital vehicle would be forced to stop operation in the year when flight costs became higher than flight receipts as shown in case C.     

Exploration for the masses? Or joyrides for the ultra-rich? Prospects for space tourism

A space tourism industry appears to be about to take off. Businesses have announced plans to launch people into suborbital space for $200,000/person, with flights beginning as early as 2008. A brief review of the history of the idea of space tourism over the past four decades—and an awareness that many ventures have quietly shelved their grandiose plans—might aid thinking about the prospects for development of a safe and thriving space tourism industry. Today's space tourism model emphases the concept of luxury, and the lifestyle of hyper-consumption. It may be worth considering whether and how this conception of space tourism might affect the future of space exploration.     

Optimization of space orbits design for Earth orbiting missions

In Earth orbiting space missions, the orbit selection dictates the mission parameters like the ground resolution, the area coverage, and the frequency of coverage parameters. To achieve desired mission parameters, usually Earth regions of interest are identified and the spacecraft is maneuvered continuously to visit only these regions. This method is expensive, it requires a propulsion system onboard the spacecraft, working throughout the mission lifetime. It also requires a longer time to cover all the regions of interest, due to the very weak thrust forces compared to that of the Earth's gravitational field. This paper presents a methodology to design natural orbits, in which the regions of interest are visited without the use of propulsion systems, depending only on the gravitational forces. The problem is formulated as an optimization problem. A genetic algorithm along with a second order gradient method is implemented for optimization. The design process takes into consideration the gravitational second zonal harmonic, and hence allows for the design of repeated Sun-synchronous orbits. The field of view of the payload is also taken into consideration in the optimization process. Numerical results are presented that demonstrates the efficiency of the proposed method.     

Dreams and realities: the challenges facing development of space tourism

The era of public space travel is approaching faster than most people think, driven by the human desire for adventure, travel and fun, and by the economic motivation for creating a space industry. Before this will happen, advances in engineering, law and policy, and medicine must be made, as well as considering the issues involved in business and management. Public awareness of the possibility must be increased and world-wide excitement about space generated in order to make space tourism a reality. This is a slightly edited version of the executive summary of the design project produced by ISU students at their 2000 Summer Session Programme in Valparaiso, Chile.     

Deployment history and design considerations for space reactor power systems

The history of the deployment of nuclear reactors in Earth orbits is reviewed with emphases on lessons learned and the operation and safety experiences. The former Soviet Union's “BUK” power systems, with SiGe thermoelectric conversion and fast neutron energy spectrum reactors, powered a total of 31 Radar Ocean Reconnaissance Satellites (RORSATs) from 1970 to 1988 in 260 km orbit. Two of the former Soviet Union's TOPAZ reactors, with in-core thermionic conversion and epithermal neutron energy spectrum, powered two Cosmos missions launched in 1987 in ～800 km orbit. The US’ SNAP-10A system, with SiGe energy conversion and a thermal neutron energy spectrum reactor, was launched in 1965 in 1300 km orbit. The three reactor systems used liquid NaK-78 coolant, stainless steel structure and highly enriched uranium fuel (90–96 wt%) and operated at a reactor exit temperature of 833–973 K. The BUK reactors used U-Mo fuel rods, TOPAZ used UO₂ fuel rods and four ZrH moderator disks, and the SNAP-10A used moderated U-ZrH fuel rods. These low power space reactor systems were designed for short missions (～0.5 kW_e and ～1 year for SNAP-10A, <3.0 kW_e and <6 months for BUK, and ～5.5 kW_e and up to 1 year for TOPAZ). The deactivated BUK reactors at the end of mission, which varied in duration from a few hours to ～4.5 months, were boosted into ～800 km storage orbit with a decay life of more than 600 year. The ejection of the last 16 BUK reactor fuel cores caused significant contamination of Earth orbits with NaK droplets that varied in sizes from a few microns to 5 cm. Power systems to enhance or enable future interplanetary exploration, in-situ resources utilization on Mars and the Moon, and civilian missions in 1000–3000 km orbits would generate significantly more power of 10's to 100's kW_e for 5–10 years, or even longer. A number of design options to enhance the operation reliability and safety of these high power space reactor power systems are presented and discussed.     

Transformation: Structure/space studies in bionics and space design

This paper discusses the architectural design project “Transformation Structure Space”, which was carried out at the Department of Building Construction HB2 in 2004. The goal of the study was to find innovative solutions for space system design through the application of bionic (biomimetic) approaches. Using specific research both fields as the foundation, five different architectural projects based on a scientific-technological concept were developed. The introduction of natural role models into the design process and the development of the application in space and the respective setting proved to be a difficult task within the timeframe of a design program, nonetheless all of the projects show very innovative aspects.     

Cost Engineering – The new paradigm for space launch vehicle design

The paper describes the basic definition and application of 'Cost Engineering' which means to design a vehicle system for minimum development cost and/or for minimum operations cost. This is important now and for the future since space transportation has become primarily a commercial business in contrast to the past where it has been mainly a subject of military power and national prestige. Several examples are presented for minimum-cost space launch vehicle configurations, such as increasing vehicle size and/or the use of less efficient rocket engines in order to reduce development and operations cost. Further a cost comparison is presented on single-stage (SSTO)-vehicles vs. two-stage launchers which shows that SSTOs have lower development and operations cost although they are larger, respectively have a higher lift-off mass than two-stage vehicles with the same performance. The design of a space tourism-dedicated launch vehicle is an extreme challenge for a cost-engineered vehicle design in order to achieve cost per seat not higher than $50,000. Finally an outlook is presented on the different options for manned Earth-to-Moon transportation modes and vehicles – another most important application of 'cost engineering', taking into account the large cost of such a future venture.     

非柔性结构太空梯的构想

文章简略介绍太空梯的概念,概述了目前世界上太空梯系统的状况和研制遇到的普遍困难.由于现有的纳米技术和材料以及加工水平还不能满足缆绳式太空梯的要求,因此文章提出建造一种非柔性结构的太空梯的构想,这样的太空梯虽然运行效率不及缆绳式太空梯,但所要求的材料相对容易得到.     

关于提升航天产品设计质量的思考

分析当前航天产品面临的质量形势,从航天系统工程的角度,阐述航天产品的基本特性,结合工作实践,从产品方案设计的正确可行性、实现过程的简洁可靠性、系统协调匹配的兼容性、试验测试的覆盖充分性以及模拟任务的真实性等方面,提出提高设计水平和设计质量的实施途径与方法.     

空间压力容器可靠性定量设计方法研究

针对空间压力容器常规设计方法难以满足航天技术快速发展对轻质量、低成本、高可靠的需求,基于可靠性理论中应力-强度干涉模型,建立空间压力容器可靠性设计数学模型。结合某型号钛合金球形气瓶随机变量统计数据,开展了气瓶可靠性定量设计。计算结果表明,可靠性定量设计方法能够给出产品可靠度定量指标,并在一定程度上降低空间压力容器结构重量。     

As assessment of habitat pressure, oxygen fraction, and EVA suit design for space operations

At high cabin pressure [e.g. 1013 hPa (14.7 psi) 21% O2] there are serious issues relative to specification of suit pressure and the need for prebreathing. A high pressure suit will be costly but use of the existing, flexible suit requires up to 6 h of prebreathing. Or one could use a cabin pressure of 700 hPa (10.2 psi) prior to extravehicular activity (EVA) in order to use the existing suit with only 1 h of prebreathing. If these normal cabin pressures and O2 levels are utilized, existing physiological and medical databases apply, providing a known basis for evaluating effects of long duration space missions. If a 345 hPa (5 psi), 70-100% O2 atmosphere is adopted the existing suit can be used with no prebreathing required. However, there is no reference database on physiological effects under the conditions of lower pressure and higher O2 concentration. This paper considers the major issues involved in defining habitat pressure, O2 fraction, and EVA suit design for operations in space. A preliminary model for evaluating habitat/suit pressure and O2% strategies is presented.     

Funding for space - private finance for public space missions?

Private users of space capability are used to buying a service, not a spacecraft. The supplier builds, launches and operates the spacecraft and the users only pay for the service that they receive. Publicly funded users could benefit from the same approach. Transferring responsibility for the success of the mission to a true prime contractor who is best able to manage technical and programme risks can lead to significant reductions in costs and timescales, but demands changes in attitudes by governments, users, industry and space agencies.     

EVA Suit 2000: a joint European/Russian space suit design

A feasibility study in 1992 showed the benefits of a common European Russian space suit development, EVA Suit 2000, replacing the Russian space suit Orlan-DMA and the planned European Hermes EVA space suit at the turn of the century. This EVA Suit 2000 is a joint development initiated by the European Space Agency (ESA) and the Russian Space Agency (RKA). The main objectives of this development program are: first utilization aboard the Russian Space Station MIR-2; performance improvement with respect to current operational suits; development cost reduction. Russian experience gained with the present extravehicular activity (EVA) suit on the MIR Space Station and extensive application of European Technologies will be needed to achieve these ambitious goals. This paper presents the current status of the development activities, the space suit system design and concentrates in more detail on life support aspects. Specific subjects addressed will include the overall life support conceptual architecture, design features, crew comfort and operational considerations.     

Making space for history

This report summarizes the presentations given at the third annual British Rocketry Oral-History Project, held in Surrey, UK in April 2001. A wide range of papers was given (to an equally diverse audience), covering past and present developments in air and space, both military and civilian. Many of the scientists and engineers who had worked on specific projects were present and their personal reminiscences enlivened proceedings. The importance of history in understanding not only the past but also the future of space efforts was emphasized.     

International law-making for outer space

While the need for adequate space law may be as urgent as ever, the international community has discovered that today it is increasingly difficult to reach consensus on statutes to govern new space activities. In view of the noticeable slowdown in the law-making process, serious discussions about the most suitable and effective techniques of space legislation are required. The author discusses the political and legal problems of making laws to deal with space and space activities. A number of suggestions aimed at improving the present legislative process are formulated.     

Future for CIS space industry

The following is the executive summary of Volume 1 of Euroconsult's four volume study, Space Industries and Markets in Russia and Other Countries of the Former Soviet Union. The material reproduced covers space policy and industry in CIS countries, providing a transversal view of CIS space activities and organizations. Generic problems across all fields of applications are analysed; the final focus is on trade with foreign countries. The other volumes cover prospects for satellite communications in the CIS to 2000; prospects for Earth observation satellite systems in Russia and Ukraine to 2000; and prospects for space transportation systems in the CIS to 2000. Information on the whole — some 650 pages — may be obtained from Pauline Byrne at Euroconsult, 71 Boulevard Richard Lenoir, 75011 Paris, France.     

Prospects for Euro-Indian space cooperation

This is the executive summary of a report prepared for the European Commission by LD consultants on the status of India's space industry and the prospects for European firms to invest in it. India has impressive launch capabilities, telecommunications and disaster warning satellites but commercialization of its activities is occurring only slowly. There are many opportunities for joint ventures with Europe (which must not let the USA consolidate its superior position in the broadcasting field) but issues of technology transfer and India's unhappiness with the MTRC must first be resolved. As well as selling products and services, Europeans should also be prepared to buy those Indian components that are available more competitively.     

The case for small space missions

Three orders of arguments are outlined to illustrate the importance of small missions. First, the classical reasons (one has to begin small, educational aspects, introduction to the space field) are summarized; then some thoughts are introduced on the efficacy and the efficiency of the effort invested (how expensive is a national project, and how advantageous the inevitable multinational cooperation); finally, a synopsis of the considerations about the need for cultural changes in the space program (the challenge of the coming era, the resulting needs, the philosophy of “small missions” and its contributions) is given.     

Assessment of nanosystems for space applications

This paper first gives an overview of the applications of micro-electro-mechanical systems (MEMS) in space. Microsystems are advertised for their extremely low size and mass, along with their low power consumption and in some case their improved performances. Examples of actual flown MEMS and future missions relying on MEMS are given. Microsystems are now enjoying a dynamic and expanding interest in the space community. This paper intends to give an idea about the next step in miniaturization, since the microelectronic industry is already looking at nano-electro-mechanical systems (NEMS) driven by the more-than-Moore philosophy. We show that the impact of nanosystems should not be reduced at a homothecy in size, weight and power consumption. New forces appear at this scale (Casimir force…) which have to be considered in the system design. The example of a nano-mechanical memory is developed. We also show that performances of nanosystems are not systematically better than their microscopic counterparts through the study of the impact of dimension reduction on an accelerometer resolution and sensitivity. We conclude with the idea that nanosystems will find their greatest applications in distributed intelligent networks that will allow new mission concepts for space exploration.     

Modeling international cooperation for space exploration

Space exploration into the twenty-first century is contingent upon the ability of states to forge an appropriate vehicle for international cooperation. A theoretical framework that explains international cooperation in space exploration is proposed. This framework encompasses scientific, technological, political, and economic initial conditions, state and nonstate political actors, and models of cooperation that explain how initial conditions and actors interact to realize cooperative outcomes. It is hypothesized that the prevailing initial conditions favor certain political actors over others which, in turn, promote a specific model of cooperation. Cooperative policy outcomes are examined and assessed vis-à-vis case studies of cooperation in space exploration. On this basis, policy recommendations that engender effective cooperative outcomes in space exploration are suggested.