Thematische Bibliographien / Reusable rocket booster

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Auswahl der wissenschaftlichen Literatur zum Thema „Reusable rocket booster“

Autor: Grafiati

Veröffentlicht am 28. Juni 2021

Zuletzt aktualisiert am 10. Februar 2022

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Zeitschriftenartikel zum Thema "Reusable rocket booster"

Benton, Mark G. „Reusable, flyback liquid rocket booster for the Space Shuttle“. Journal of Spacecraft and Rockets 26, Nr. 4 (Juli 1989): 252–58. http://dx.doi.org/10.2514/3.26063.

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Lamb, Thomas, Alex M. Loudon und Robert J. Van Slyke. „The Lockheed Space Shuttle Rocket Retrieval Ship“. Marine Technology and SNAME News 23, Nr. 02 (01.04.1986): 109–22. http://dx.doi.org/10.5957/mt1.1986.23.2.109.

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This paper describes the design and construction of a 200-ft rocket retrieval ship for West Coast space shuttle operations. The ship, MV Independence, is designed to retrieve the reusable solid rocket booster casings from each launch of the space shuttle. Construction design and technical management of the project are outlined and a typical rocket retrieval mission is described. Updated information on builder's trials and mission performance is appended.

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Buzuluk, V. I., und S. M. Mikhalyov. „A completely reusable aerospace system based on subsonic carrier with the return of the first stages to the starting point“. CEAS Aeronautical Journal 12, Nr. 3 (23.02.2021): 471–80. http://dx.doi.org/10.1007/s13272-020-00491-6.

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AbstractThe concept of aerospace system based on air launch from subsonic twin-fuselage aircraft and the rocket launch into orbit is investigated. The scheme of aerospace system trajectory providing a return to the starting point both of the carrier and the first rocket stage with liquid-fuel motors is proposed. It was shown that the use of subsonic carrier as a launching platform of the rocket system increases the payload mass by 1.2% of the rocket segment MTOW as compared to autonomous ground take-off. The comparative analysis of three versions of carrier aircraft and three fuel options at the first rocket stage was carried out. Analysis showed that compared to kerosene variant the hydrogen hypersonic booster makes it possible to significantly increase the payload mass while the launching costs stay the same.

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Hong, Z. C., C. C. Lee und C. J. Tseng. „A Concept of Vertical Takeoff Two-Stage-to-Orbit Reusable Launch Vehicle with an Integral-Rocket-Ramjet Booster“. Journal of Mechanics 21, Nr. 1 (März 2005): 51–56. http://dx.doi.org/10.1017/s172771910000054x.

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AbstractReusable launch vehicles (RLV) currently envisioned incorporate a wide variety of propulsion types. Various propulsion devices have been designed, or are being designed. The Integral-Rocket-Ramjet (IRR) propulsion mainly applies to a tactical missile boost system and few have mentioned this system in RLV design. According to the technological ability of Taiwan and a feasibility study, it shows that the present reusable launch system can exploit the potential benefit of IRR propulsion for the RLV system. A conceptual study of an unmanned two-stage-to-orbit (TSTO) launch vehicle is designed in this paper. The first stage of the vehicle is reusable with IRR engines. The second stage is expendable and rocket powered. The assumed mission is designed to insert a 100kg payload into a low earth circular orbit at various inclination angles. The calculations are made for the case where the TSTO system is used in Taiwan. The fundamentals of launch vehicle design are examined using simplified two-stage performance equations. Launch vehicle design is optimized when the performance and programmatic drivers are balanced. There is an acceptable set of launch and landing sites on islands off the coast of Taiwan.

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Zhang, Fan, Huiqiang Zhang und Bing Wang. „Conceptual study of a dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle“. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, Nr. 5 (01.05.2017): 944–57. http://dx.doi.org/10.1177/0954410017703148.

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The liquid oxygen/methane staged cycle liquid-rocket engine is one of the most potential rocket engines in the future for its higher performance, higher fuel density and reusable capacity. Two working states of this liquid-rocket engine named as full-load state and half-load state are defined in this paper. Based on this liquid-rocket engine, a dual-rocket-based-combined-cycle propulsion system with liquid oxygen /air/methane as propellants is therefore proposed. The dual-rocket-based-combined-cycle system has then five working modes: the hybrid mode, pure ejector mode, ramjet mode, scramjet mode and pure rocket mode. In hybrid mode, the booster and ejector rockets driven by the full-load liquid-rocket engine work together with the purpose of reducing thrust demand on ejector rocket. In scramjet mode, the fuel-rich burned hot gas generated by the half-load liquid-rocket engine is used as fuel, which is helpful to reduce the technical difficulty of scramjet in hypersonic speed. The five working modes of dual-rocket-based-combined-cycle are highly integrated based on the full- or half-load state of the liquid oxygen/methane staged cycle liquid-rocket engine, and the unified single type fuel of liquid methane is adopted for the whole modes. Then a preliminary design of a horizontal takeoff two-stage-to-orbit launch vehicle is conducted based on the dual-rocket-based-combined-cycle propulsion system. Under an averaged baseline thrust and specific impulse, the launch trajectory to reach a low Earth orbit at 100 km is optimized via the pseudo-spectral method subject to maximizing the payload mass. It is shown that the two-stage-to-orbit vehicle based on the dual-rocket-based-combined-cycle can achieve the payload mass fraction of 0.0469 and 0.0576 for polar mission and equatorial mission, respectively. Conclusively, insights gained in this paper can be usefully applied to a more detailed design of the dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle.

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Timushev, S. F., und A. A. Frolov. „Automatic Unloading Liquid Rocket Engine Fuel Feed System Booster Pump Radial Thrust Bearings from Axial Force“. Proceedings of Higher Educational Institutions. Маchine Building, Nr. 7 (736) (Juni 2021): 54–61. http://dx.doi.org/10.18698/0536-1044-2021-7-54-61.

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Increasing the suction capacity, efficiency and energy parameters of high-speed pumps is an important task in the development of power systems in the aerospace industry, as well as in their application in energy and oil production. With improved cavitation properties, the pumps can operate at a higher shaft speed, and at its given value - with lower cavitation reserves, i.e. at a reduced inlet pressure. When the shaft speed increases, the pump weight and overall dimensions decrease. To increase the anti-cavitation qualities of pumps in the power system, auxiliary (booster) pumping units are used, creating the pressure necessary for the cavitation-free operation of high-pressure and high-speed main pumps of the engine fuel supply system. In accordance with its purpose, the booster pump must provide the required supply pressure of the specified flow rate at the lowest possible liquid pressure at the inlet. At the same time, the efficiency of the booster pump unit should be maximum, and the overall dimensions and weight should be minimal. The last two characteristics predetermine the maximum possible number of revolutions of the pump shaft. Ensuring the operability of the ball-bearing supports of the fuel supply units is one of the most important and complex tasks in the development of modern and promising liquid rocket engines (LRE), especially reusable ones. This task has always been one of the priorities in the fine-tuning the fuel feed units of such engines. The article proposes a method for calculating and controlling the unloading liquid rocket engine booster pump radial thrust bearings from axial force. The method can be applied in the entire range of liquid rocket engine calculations. The further development of this work will be mathematical modeling of the operation of the booster pump automatic axial force unloading.

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Ashley, Steven. „Bringing Launch Costs Down to Earth“. Mechanical Engineering 120, Nr. 10 (01.10.1998): 62–68. http://dx.doi.org/10.1115/1.1998-oct-1.

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This article discusses the three federally funded projects that are underway to develop new rocket engines that can make it more affordable to send payloads into orbits. The new RS-68 propulsion system is Rocketdyne's entry in competition to power the US Air Force's new heavy-lift booster. The most ambitious of the new propulsion system designs is Rocketdyne's XRS-2200 linear aerospike engine, a seemingly nozzle-less oxygen/hydrogen powerplant that is designed to send the autonomously controlled NASA X-33 lifting body into orbit. The X-33 is being developed by Lockheed Martin Skunk Works, Palmdale, CA. The key for new launch vehicles, whether they're expendable or reusable, is to get the costs down. The article also highlights that the payload that can be lofted by a launch vehicle depends in large part on engine performance and the ratio of propellant to structural weight. Bell nozzles are designed to offer the best compromise of shape and length for a vehicle and flight path. Rocketdyne's R-68 engine is to be 17 feet tall and 8 feet wide at the base. The key to the R-68 engine design was the selection of hydrogen as the propellant rather than kerosene.

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Gyekenyesi, John P. „Potential Composite Structures for NASA Future Launch Vehicles and Crew Spacecraft“. Advanced Materials Research 410 (November 2011): 17. http://dx.doi.org/10.4028/www.scientific.net/amr.410.17.

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Because of their well known specific strength, stiffness and excellent durability properties, advanced composites are being considered for primary structures in launch vehicles, crew modules and various components for increased performance and cost reduction. Therefore, it is prudent and beneficial to review the engineering practices and lessons learned in connection with their use in related aeronautic and energy applications, where they are already replacing formerly used metallic materials. Examples of composite components will be shown for the reusable space shuttle orbiter where a number of different composite systems performed very satisfactorily. In addition, very large potential polymer composite designs for future launch vehicles will be discussed. Among them are payload shrouds, interstage structures and the typical intertank shell, wherein thrust booster rockets are often attached between the core stage propellant and oxidizer tanks. In addition, cryogenic propellant composite vessels of different sizes and shapes were fabricated with mostly excellent results, although some spectacular failures were also observed. High pressure composite overwrapped vessels, with and without metallic liners, will be described. Compared to widely used metallic materials, some special features of composites are listed. Relevant design allowables, depending on mission requirements, will be summarized and currently used design practice for aircraft and spacecraft in the US will be reviewed. The well-known “building - block” approach, which is often used to design military as well as civilian aircraft, will be summarized. Some of the most popular micromechanics and macromechanics computer programs used to analyze composite structures, especially with finite elements, will be listed. Although very high temperature composites like carbon/carbon, carbon/ceramic and ceramic/ceramic fiber/matrix systems are also selectively used, the focus in our discussion will be on advanced polymer matrix, carbon/glass fiber systems.

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Buzuluk, V. I., und S. M. Mikhalev. „Development of the method of forming the shape of a reusable aerospace system, optimization of its design parameters and motion paths“. Engineering Journal: Science and Innovation, Nr. 6 (90) (Juni 2019). http://dx.doi.org/10.18698/2308-6033-2019-6-1894.

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The paper investigates a concept of an aerospace system based on air launch from subsonic twin-fuselage aircraft and on the rocket launch into orbit. We propose a scheme of aerospace system trajectory providing return to the starting point both of the carrier and the first rocket stage with liquid-fuel motors. A method for multidisciplinary calculation and optimization of the design parameters of the aerospace system and approximately optimal control of the motion of the system steps with different power units in all flight segments, as well as a feasibility study, was developed On the basis of the developed techno-economic analysis methodology, a complex of computational programs in C ++ was compiled to determine the main design parameters and characteristics. The comparative analysis of three versions of carrier aircraft and three fuel options at the first rocket stage was carried out. The analysis showed that compared to kerosene variant the hydrogen hypersonic booster made it possible to significantly increase the payload mass while the launching costs stayed the same. We compared engineering-and-economic performance of the aerospace system with “Soyuz-2.1” expendable launch vehicle. The comparison showed that the unit cost of aerospace system injection can be reduced significantly compared to an expendable carrier due to system reusability.

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Dissertationen zum Thema "Reusable rocket booster"

Acker, Robert Lauren. „Determination of the nose cone shape for a large reusable liquid rocket booster“. Thesis, Massachusetts Institute of Technology, 1988. http://hdl.handle.net/1721.1/34027.

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Çelik, Ugurcan. „Robust Booster Landing Guidance/Control“. Thesis, KTH, Optimeringslära och systemteori, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-279684.

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The space industry and the technological developments regarding space exploration hasn’t been this popular since the first moon landing. The privatization of space exploration and the vertical landing rockets made rocket science mainstream again. While being able to reuse rockets is efficient both in terms of profitability and popularity, these developments are still in their early stages. Vertical landing has challenges that, if neglected, can cause disastrous consequences. The existing studies on the matter usually don’t account for aerodynamics forces and corresponding controls, which results in higher fuel consumption thus lessening the economical benefits of vertical landing. Similar problems have been tackled in studies not regarding booster landings but regarding planetary landings. And while multiple solutions have been proposed for these problems regarding planetary landings, the fact that the reinforcement learning concepts work well and provide robustness made them a valid candidate for applying to booster landings. In this study, we focus on developing a vertical booster descent guidance and control law that’s robust by applying reinforcement learning concept. Since reinforcement learning method that is chosen requires solving Optimal Control Problems (OCP), we also designed and developed an OCP solver software. The robustness of resulting hybrid guidance and control policy will be examined against various different uncertainties including but not limited to wind, delay and aerodynamic uncertainty.
Rymdindustrin och den tekniska utvecklingen av rymdutforskningen har inte varit så populär sedan den första månlandningen. Privatiseringen av utforskningen av rymden och de vertikala landningsraketerna medförde att raketvetenskapen återkom som en viktig huvudfråga igen. Även om det är effektivt att återanvända raketer i form av lönsamhet och popularitet, är denna utveckling fortfarande i sina tidiga stadier. Vertikal landning har utmaningar som, om de försummas, kan orsaka katastrofala konsekvenser. De befintliga studierna i frågan redovisar vanligtvis inte aerodynamikkrafter och motsvarande regulatorer, vilket resulterar i högre bränsleförbrukning som minskar de ekonomiska fördelarna med vertikal landning. Liknande problem har hanterats i studier som inte avsåg boosterlandningar utan om planetariska landningar. Även om flera lösningar har föreslagits för dessa problem beträffande planetariska landningar, det faktum att förstärkningsinlärningskonceptet fungerar bra och ger robusthet gjorde dem till en giltig kandidat för att ansöka om boosterlandningar. I den här studien fokuserar vi på att utveckla en lagstiftning för styrning av vertikala booster-nedstigningar som är robust genom att tillämpa koncepten inom förstärkningsinlärning. Ef- tersom förstärkt inlärningsmetod som väljs kräver lösning av optimala kontrollproblem (OCP), designade och utvecklade vi också en OCP-lösningsmjukvara. Robustheten för resulterande hybridstyrning och kontrollpolicy kommer att undersökas mot olika osäkerheter inklusive, men inte begränsat till vind, fördröjning och aerodynamisk osäkerhet.

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Király, Adrián. „Návrh navedení, navigace a řízení pro vertikální přistání opakovaně použitelného raketového urychlovače“. Master's thesis, Vysoké učení technické v Brně. Fakulta informačních technologií, 2021. http://www.nusl.cz/ntk/nusl-445539.

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Táto diplomová práca sa zaoberá vývojom systému pre navádzanie, navigáciu, a riadenie pre znovupoužiteľný raketový urýchľovač. Pre dosiahnutie tohto cieľu bol vytvorený simulačný model rakety v prostredí Simulink. Na základe dát získaných pomocou CFD softvéru bol pre túto simuláciu vytvorený tiež vlastný aerodynamický model. Pre účely demonštrácie dosiahnutých výsledkov bol ako súčasť práce tiež naprogramovaný interaktívny 3D vizualizačný nástroj.

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Bücher zum Thema "Reusable rocket booster"

Lyndon B. Johnson Space Center., Hrsg. STS-80 Space Shuttle Program Mission. Houston, Tex: Lyndon B. Johnson Space Center, 1997.

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Konferenzberichte zum Thema "Reusable rocket booster"

Moore, Dennis, Jack Phelps, Donna Freeland, Howard Kanner, Mark Vaccaro, David Wood und Derek Olson. „The Reusable Solid Rocket Booster (RSRB) - an Booster System“. In AIAA SPACE 2011 Conference & Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-7156.

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Bradford, John, und Brad St. Germain. „Rocket Back Trajectory Sensitivity Analyses for a Reusable Booster System“. In AIAA SPACE 2010 Conference & Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-8672.

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Rothschild, William, und Ernest Schuster. „Airbreathing Propulsion System design concepts for a Reusable First Stage rocket booster“. In 35th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-2380.

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