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Journal articles on the topic 'Launch vehicles (Astronautics) Space vehicles'

Author: Grafiati

Published: 4 June 2021

Last updated: 13 February 2022

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1

Tanaka, Yasuo. "Launch Vehicles of ISAS." International Astronomical Union Colloquium 123 (1990): 339–42. http://dx.doi.org/10.1017/s0252921100077253.

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AbstractThe Institute of Space and Astronautical Science (ISAS) has developed a series of launch vehicles for delivering modest scale scientific satellites into space. This capability is unique for an inter-university research institute. The present ISAS launch vehicle, M-3S II, carries a 770 kg payload into a low earth orbit (LEO). A new program for the development of a more capable vehicle, M-V, started recently, which will have a LEO capability three times that of M-3S II. The enhanced launch capability will further expand the scope of the ISAS missions to include planetary explorations.

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2

Sethi, Chitra. "The Return of Manned Missions." Mechanical Engineering 141, no. 07 (2019): 48–53. http://dx.doi.org/10.1115/1.2019-jul3.

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The United States space program has been without a launch vehicle for human spaceflight since 2011. That was when the space shuttle Atlantis returned on its final flight. Since then, NASA has relied on the Russian Soyuz spacecraft to take its astronauts to the International Space Station. However, if all goes to plan this could soon change, as two private companies are working with NASA to launch the first astronauts into orbit. The companies, SpaceX and Boeing, are building crew capsules and rockets, designing space suits, and training astronauts to fly these new vehicles into space.

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3

Pugachenko, S. E., and D. A. Kozedub. "Investigating Crew Maintenance Modes for a Lunar Orbital Spaceport Station." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 4 (127) (August 2019): 31–43. http://dx.doi.org/10.18698/0236-3941-2019-4-31-43.

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The investigation concerned a methodological approach to selecting crew maintenance modes for a lunar orbital spaceport station and sought to detect the most efficient mode. We assumed the orbital station characteristics to be close to those of the Lunar Orbital Platform-Gateway project that is currently scheduled in the USA. Using such a station as a base for assembling an interplanetary mission system is part of developing manned astronautics. We utilised systems analysis to conduct our investigation. We developed a mathematical model of the lunar space infrastructure, including the orbital

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4

Rugescu, Radu D., Dragos Ronald Rugescu, and Efim Micu. "Orbital Launcher NERVA as the First Proof of the Discontinuous Variational Solution for the Atmospheric Ascent." Applied Mechanics and Materials 555 (June 2014): 91–101. http://dx.doi.org/10.4028/www.scientific.net/amm.555.91.

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Since the earliest days of astronautics, more than a century ago, low cost space launchers persevered to be a long desire for the space flight thinkers. Once space flight became a daily business along the late `50-s, first by consuming large financial resources, the interest for cheap space launchers became even more laud. Today’s growing interest in small satellites have bolstered a large series of space technology companies including Virgin Galactic Corp., Garvey Spacecraft Corp., Quantum Research International, Ventions LLC, Sierra Nevada Corp., Generation Orbit Launch Services and even the

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5

Didkovskiy, Arkadiy, Ekaterina Mukhina, and Gleb Stanishevskiy. "Developing of transport airship for delivery oversized cargo to vostochny cosmodrome." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 63 (2020): 23–29. http://dx.doi.org/10.15593/2224-9982/2020.63.03.

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An overview of existing methods of delivering oversized cargo using water, rail, road, air and airship transport, an analysis of the world experience in creating lighter-than-air aircraft and identified the most urgent tasks for this type of vehicles in the field of rocket and space technology, in particular, transportation of oversized elements of super-heavy launch vehicles from manufacturers to the Vostochny cosmodrome, search and rescue of astronauts, evacuation of spent stages from fall fields to disposal points and transportation of oversized trusses. The goals and objectives of this wor

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6

Mccarthy, Dennis D. "Report on the World Space Congress." Symposium - International Astronomical Union 156 (1993): 435–37. http://dx.doi.org/10.1017/s0074180900173681.

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The World Space Congress comprised of the 43rd Congress of the International Astronautical Federation (IAF) and the 29th Plenary Meeting of the Committee of Space Research (COSPAR) was held in Washington, DC from 27 August to 4 September, 1992. Over 3000 people participated in the meetings where scientific papers were presented on such diverse topics as space travel, biological aspects of space travel, relativity, planetary atmospheres, space debris, space law, global change, launch vehicles, space station, space communication, navigation, Earth rotation, astrometry, satellite geodesy, use of

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7

Chudoba, B., G. Coleman, L. Gonzalez, E. Haney, A. Oza, and V. Ricketts. "Orbital transfer vehicle (OTV) system sizing study for manned GEO satellite servicing." Aeronautical Journal 120, no. 1226 (2016): 573–99. http://dx.doi.org/10.1017/aer.2016.3.

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ABSTRACTIn an effort to quantify the feasibility of candidate space architectures for astronauts servicing Geosynchronous Earth Orbit (GEO) satellites, a conceptual assessment of architecture-concept and operations-technology combinations has been performed. The focus has been the development of a system with the capability to transfer payload to and from geostationary orbit. Two primary concepts of operations have been selected: (a) Direct insertion/re-entry (Concept of Operations 1 – CONOP 1); (b) Launch to low-earth orbit at Kennedy Space Center inclination angle with an orbital transfer to

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8

Gupta, S. C. "India’s space launch vehicles." Journal of the Indian Society of Remote Sensing 23, no. 4 (1995): 163–74. http://dx.doi.org/10.1007/bf03024497.

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9

Ruppe, H. O. "Reusable launch vehicles." Space Policy 1, no. 3 (1985): 339–40. http://dx.doi.org/10.1016/0265-9646(85)90034-7.

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10

Jayawant, B. V., W. R. C. Dawson, L. S. Wickramaratne, J. D. Edwards, and T. C. Yang. "Electromagnetic launch assistance for space vehicles." IET Science, Measurement & Technology 2, no. 1 (2008): 42–52. http://dx.doi.org/10.1049/iet-smt:20060145.

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11

MacLaren, A. J., and H. D. Trudeau. "Solid rocket motor space launch vehicles." Acta Astronautica 30 (July 1993): 165–72. http://dx.doi.org/10.1016/0094-5765(93)90108-9.

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12

Galas', M. I., and A. A. Romanyuta. "Multipurpose nose fairing for space launch vehicles." Kosmìčna nauka ì tehnologìâ 5, no. 2-3 (1999): 60–65. http://dx.doi.org/10.15407/knit1999.02.060.

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13

Nagappa, Rajaram. "Development of Space Launch Vehicles in India." Astropolitics 14, no. 2-3 (2016): 158–76. http://dx.doi.org/10.1080/14777622.2016.1244877.

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14

Ghosh, Subir. "DESIGNING PROPULSION RELIABILITY OF SPACE LAUNCH VEHICLES." Quality Engineering 11, no. 3 (1999): 395–404. http://dx.doi.org/10.1080/08982119908919256.

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15

Xu, Yunjun, and Ming Xin. "Nonlinear Stochastic Control for Space Launch Vehicles." IEEE Transactions on Aerospace and Electronic Systems 47, no. 1 (2011): 98–108. http://dx.doi.org/10.1109/taes.2011.5705662.

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16

Boone, Tom R., and David P. Miller. "Capability and Cost-Effectiveness of Launch Vehicles." New Space 4, no. 3 (2016): 168–89. http://dx.doi.org/10.1089/space.2016.0011.

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17

Parkinson, R. C. "The future of launch vehicles." Space Policy 1, no. 2 (1985): 202–4. http://dx.doi.org/10.1016/0265-9646(85)90073-6.

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18

Krause, Robert B. "United States Launch Vehicle Systems." International Astronomical Union Colloquium 123 (1990): 325–32. http://dx.doi.org/10.1017/s025292110007723x.

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AbstractUnited States policy for national space launch capability provides for a balanced mix of launches, utilizing the Space Shuttle and Expendable Launch Vehicles (ELVs). It also directs government agencies to encourage and support the development of a domestic commercial expendable launch vehicle industry. This is to be accomplished by contracting for necessary ELV launch services directly from the private sector and by facilitating access by commercial launch firms to national launch and launch-related property and services they request to support these commercial operations.The current m

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19

Rising, John M., and Nancy G. Leveson. "Systems-Theoretic Process Analysis of space launch vehicles." Journal of Space Safety Engineering 5, no. 3-4 (2018): 153–83. http://dx.doi.org/10.1016/j.jsse.2018.06.004.

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20

Rao, B. N., D. Jeyakumar, K. K. Biswas, S. Swaminathan, and E. Janardhana. "Rigid body separation dynamics for space launch vehicles." Aeronautical Journal 110, no. 1107 (2006): 289–302. http://dx.doi.org/10.1017/s0001924000013166.

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Abstract This paper presents a systematic formulation for the simulation of rigid body dynamics, including the short period dynamics, inherent to stage separation and jettisoning parts of a satellite launcher. This also gives a review of various types of separations involved in a launch vehicle. The problem is sufficiently large and complex; the methodology involves iterations at successively lower levels of abstraction. The best choice to tackle such problems is to use state-of-the-art programming technique known as object oriented programming. The necessary classes have been identified to re

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21

Guikema, Seth D., and M. Elisabeth Paté-Cornell. "Probability of infancy problems for space launch vehicles." Reliability Engineering & System Safety 87, no. 3 (2005): 303–14. http://dx.doi.org/10.1016/j.ress.2004.06.001.

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22

Donahue, Thomas M. "Space Science Needs a Variety of Launch Vehicles." Physics Today 39, no. 7 (1986): 112. http://dx.doi.org/10.1063/1.2815109.

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23

Ruppe, Harry O. "Launch vehicles to low-Earth orbit." Space Policy 3, no. 3 (1987): 175–78. http://dx.doi.org/10.1016/0265-9646(87)90066-x.

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24

Nebylov, Alexander. "HTHL Space Vehicles: Concepts and Control Problems." Applied Mechanics and Materials 629 (October 2014): 382–87. http://dx.doi.org/10.4028/www.scientific.net/amm.629.382.

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Integrated launch systems that include aerospace plane (ASP) and another heavy winged vehicle (plane or better Wing-in-Ground effect vehicle) as a booster are reviewed. It is shown that WIG-vehicle with a mass of 1500 ton or more is capable to carry ASP with initial mass of 500 ton and landing mass of 60-70 ton. Ekranoplane can provide ASP with the primary speed of Mach 0.5-0.65 in the required direction that allows lowering the design requirements to ASP's wing area and engines. A number of other advantages from the offered transport system are linked to possible use of WIG-vehicle at ASP lan

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25

Nazarova, Yulia A., and Vladimir A. Tikhonov. "Comparative analysis of the economic feasibility of using ultra-small spacecrafts." RUDN Journal of Engineering Researches 22, no. 1 (2021): 43–53. http://dx.doi.org/10.22363/2312-8143-2021-22-1-43-53.

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The relevance of the issue under consideration is associated with the evolution of existing technologies, due to which the functionality increases and the mass of the payload decreases, as a result of which the question of the use of cost-effective launch vehicles is raised. The purpose of this work is to carry out a comparative analysis of the feasibility of using ultra-light launch vehicles to provide services for the delivery of small spacecraft to low-earth orbit. The article is written within the framework of socio-economic research methods. Retrospective analysis and comparative approach

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26

Boltz, Frederick W. "Miniature Launch Vehicles for Very Small Payloads." Journal of Spacecraft and Rockets 38, no. 1 (2001): 126–28. http://dx.doi.org/10.2514/2.3664.

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27

Donahue, Benjamin B. "Two-Stage Launch Vehicles for Heavy Payloads." Journal of Spacecraft and Rockets 39, no. 1 (2002): 125–30. http://dx.doi.org/10.2514/2.3790.

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28

Mistry, Dinshaw, and Bharath Gopalaswamy. "Ballistic Missiles and Space Launch Vehicles in Regional Powers." Astropolitics 10, no. 2 (2012): 126–51. http://dx.doi.org/10.1080/14777622.2012.696014.

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29

Wu, Kui, Xiaojun Wang, Lixiang Gu, and Xiu-Tian Yan. "A new system design method for space launch vehicles." Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 227, no. 1 (2012): 62–69. http://dx.doi.org/10.1177/0959651812456333.

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30

Hertzfeld, Henry R. "Launch vehicles and the commercial uses of outer space." Space Policy 1, no. 4 (1985): 379–89. http://dx.doi.org/10.1016/0265-9646(85)90005-0.

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31

Keyworth, G. A. "Launch Vehicles of the Future: Earth to Near-Earth Space." International Astronomical Union Colloquium 123 (1990): 347–54. http://dx.doi.org/10.1017/s0252921100077277.

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None of us thought, when this colloquium was scheduled, that the timing would enable it to become a celebration as well. The launch, after years of postponements, of the Hubble Space Telescope, has cast a galactic glow over the proceedings here this week. But at the same time, the frustrating delays caused by the collapse in 1986 and very slow regeneration of the U.S. space launch capabilities since then make this discussion of near-earth access very pointed.As we know, the sheer momentum of the U.S. Space Shuttle Program has dominated our perceptions of space launch for a decade and a half. I

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32

Azevedo, Joao Luiz F. "Aeroelastic analysis of launch vehicles in transonic flight." Journal of Spacecraft and Rockets 26, no. 1 (1989): 14–23. http://dx.doi.org/10.2514/3.26027.

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33

Dorrington, G. E. "Simple relations for analysis of airbreathing launch vehicles." Journal of Spacecraft and Rockets 26, no. 2 (1989): 124–26. http://dx.doi.org/10.2514/3.26042.

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34

Windhorst, Robert, Mark Ardema, and Jeffrey Bowles. "Minimum Heating Entry Trajectories for Reusable Launch Vehicles." Journal of Spacecraft and Rockets 35, no. 5 (1998): 672–82. http://dx.doi.org/10.2514/2.3384.

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35

Boltz, Frederick W. "Avionics Module Recovery System for Expendable Launch Vehicles." Journal of Spacecraft and Rockets 37, no. 3 (2000): 421–24. http://dx.doi.org/10.2514/2.3578.

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36

Fesmire, James E., Brekke E. Coffman, Jared P. Sass, Martha K. Williams, Trent M. Smith, and Barry J. Meneghelli. "Cryogenic Moisture Uptake in Foam Insulation for Space Launch Vehicles." Journal of Spacecraft and Rockets 49, no. 2 (2012): 220–30. http://dx.doi.org/10.2514/1.43776.

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37

Richardson, Matthew P., and Dominic W. F. Hardy. "Economic Benefits of Reusable Launch Vehicles for Space Debris Removal." New Space 6, no. 3 (2018): 227–37. http://dx.doi.org/10.1089/space.2018.0005.

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38

Ястремский, Виталий Леонидович, Дмитрий Андреевич Попов, Олег Яковлевич Комаченко, Александр Владимирович Аксененко, Дмитрий Сергеевич Калиниченко та Светлана Вадимовна Сенчакова. "ИССЛЕДОВАНИЕ ВОЗМОЖНОСТИ СОЗДАНИЯ АВИАЦИОННО-КОСМИЧЕСКОГО РАКЕТНОГО КОМПЛЕКСА НА БАЗЕ ПЕРСПЕКТИВНЫХ УКРАИНСКИХ ТРАНСПОРТНЫХ САМОЛЕТОВ". Aerospace technic and technology, № 5 (22 жовтня 2019): 38–50. http://dx.doi.org/10.32620/aktt.2019.5.05.

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The subject of study is the possibility of creating (generation) of the space launch systems based on perspective Ukrainian cargo aircrafts.The goal of the work is to consider the main aspects of an air launch and determine the keyword parameters of space launch systems. In the process, the following tasks were completed: an analysis of the Ukrainian air fleet cargo aircrafts; determine the transport aircraft which should be used as carrier-aircraft for launching of the integrated launch vehicles; analyzed the possibility of airdrop integrated launch vehicles from the cargo compartment of carr

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39

Дронь, Николай Михайлович, Кирилл Валерьевич Коростюк, Александр Вячеславович Голубек, Людмила Григорьевна Дубовик та Алексей Владимирович Кулик. "ОЦЕНКА ВОЗМОЖНОСТЕЙ ПРИМЕНЕНИЯ СУБОРБИТАЛЬНЫХ РАКЕТ-НОСИТЕЛЕЙ ДЛЯ ВЫВЕДЕНИЯ СРЕДСТВ УВОДА ОБЪЕКТОВ КОСМИЧЕСКОГО МУСОРА С НИЗКИХ ОКОЛОЗЕМНЫХ ОРБИТ". Aerospace technic and technology, № 4 (28 серпня 2020): 60–65. http://dx.doi.org/10.32620/aktt.2020.4.07.

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The article is devoted to an actual problem of clearing of low earth orbits from space objects of a technogenic origin. Existing versions of struggle against space debris, in particular, removal of technogenic objects with help of the special means for deorbiting delivered into a target orbit by launch vehicles that are especially actual for bulky space debris are considered. Recognizing that the ascent of such means for deorbiting by orbital launch vehicles demands large financial expenses, for an increase of efficiency of delivery the means for deorbiting on a low earth orbit widely known su

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40

Stanley, Douglas O., and Richard W. Powell. "Abort capabilities of rocket-powered single-stage launch vehicles." Journal of Spacecraft and Rockets 28, no. 2 (1991): 184–91. http://dx.doi.org/10.2514/3.26228.

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41

Sippel, Martin, Uta Atanassov, Josef Klevanski, and Volker Schmid. "First-Stage Design Variations of Partially Reusable Launch Vehicles." Journal of Spacecraft and Rockets 39, no. 4 (2002): 571–79. http://dx.doi.org/10.2514/2.3846.

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42

Griffin, Steven, Steven A. Lane, and Anthony Lazzaro. "Active Vibroacoustic Device for Noise Reduction in Launch Vehicles." Journal of Spacecraft and Rockets 45, no. 6 (2008): 1282–92. http://dx.doi.org/10.2514/1.36787.

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43

Kanda, Takeshi, Kouichiro Tani, and Kouichi Takasaki. "Extended Tsiolkovskii Equation and Its Application to Launch Vehicles." Journal of Spacecraft and Rockets 53, no. 5 (2016): 969–79. http://dx.doi.org/10.2514/1.a33554.

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44

Jozič, Zidanšek, and Repnik. "Fuel Conservation for Launch Vehicles: Falcon Heavy Case Study." Energies 13, no. 3 (2020): 660. http://dx.doi.org/10.3390/en13030660.

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Space exploration has recently been growing at an increasing pace and has caused a significant burden to the environment, in particular, during the launch of rockets, when a large amount of fuel is burned and the exhaust gases are released in the air. For this case study, we selected the SpaceX Falcon Heavy reusable heavy-lift launch vehicle, which is one of the most promising rockets for the low-cost lifting of heavy payloads into orbit and beyond. We evaluated several strategies for optimisation of fuel consumption and for minimisation of environmental impact during launch through the atmosp

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45

MIYAZAWA, Masafumi. "Japan's launch vehicles and technology transfer in the space applications area." Journal of the Japan Society for Aeronautical and Space Sciences 39, no. 445 (1991): 55–68. http://dx.doi.org/10.2322/jjsass1969.39.55.

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46

Song, Eun-Jung, Sangbum Cho, and Woong-Rae Roh. "A comparison of iterative explicit guidance algorithms for space launch vehicles." Advances in Space Research 55, no. 1 (2015): 463–76. http://dx.doi.org/10.1016/j.asr.2014.09.025.

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47

Friedrich, Linus, and Kai-Uwe Schröder. "Minimum stiffness criteria for ring frame stiffeners of space launch vehicles." CEAS Space Journal 8, no. 4 (2016): 269–90. http://dx.doi.org/10.1007/s12567-016-0126-4.

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48

Jeong, Seung-Min, Kui Soon Kim, Sejong Oh, and Jeong-Yeol Choi. "New Technologies of Space Launch Vehicles including Electric-Pump Cycle Engine." Journal of the Korean Society for Aeronautical & Space Sciences 44, no. 2 (2016): 139–55. http://dx.doi.org/10.5139/jksas.2016.44.2.139.

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49

Chou, H. C., M. D. Ardema, and J. V. Bowles. "Near-Optimal Entry Trajectories for Reusable Launch Vehicles." Journal of Guidance, Control, and Dynamics 21, no. 6 (1998): 983–90. http://dx.doi.org/10.2514/2.4335.

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50

Ardema, M. D., H. C. Chou, and J. V. Bowles. "Near-optimal operation of dual-fuel launch vehicles." Journal of Guidance, Control, and Dynamics 19, no. 5 (1996): 1180–82. http://dx.doi.org/10.2514/3.21771.

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