Thematische Bibliographien / Air-launched rocket

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Auswahl der wissenschaftlichen Literatur zum Thema „Air-launched rocket“

Autor: Grafiati

Veröffentlicht am 28. Juni 2021

Zuletzt aktualisiert am 3. Februar 2022

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Zeitschriftenartikel zum Thema "Air-launched rocket"

Eberhart, J. „Air-Launched Rocket Orbits Two Satellites“. Science News 137, Nr. 15 (14.04.1990): 229. http://dx.doi.org/10.2307/3974547.

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Zheng, Wu-ji, und Deng-cheng Zhang. „Dynamic model for internally carried air-launched rocket“. Journal of Central South University 25, Nr. 11 (28.11.2018): 2641–53. http://dx.doi.org/10.1007/s11771-018-3942-1.

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Parkinson, R. C., V. A. Skorodelov, I. I. Serdijk und V. Ya Neiland. „RADEM: An air launched, rocket demonstrator for future advanced launch systems“. Acta Astronautica 37 (Oktober 1995): 215–22. http://dx.doi.org/10.1016/0094-5765(95)00089-i.

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Zhang, Yan Hua, Hua Xing Li, Deng Cheng Zhang und Liang Qu. „The Effect of Nose Bluntness and Forebody Strakes on Aerodynamic Characteristics of Air-Launched Rocket Model“. Applied Mechanics and Materials 391 (September 2013): 143–49. http://dx.doi.org/10.4028/www.scientific.net/amm.391.143.

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In this paper, the aerodynamic characteristics of the rocket model that might be used in a cabin air-launched system have been studied through experiments in low speed wind tunnel. The angle of incidence range is 0-80°, and the speed is 17m/s or 25m/s, including typical flight conditions prior to engine ignition. Forces and moments were measured through six-component balance. It is found that vortex asymmetry appears under certain condition with zero side slip. Asymmetrical phenomenon leads to larger side force and yaw moment, which can affect the trajectory of the rocket and put the carrier aircraft at risk. In addition, changes in regulation of the pitching moment with angle of attack are important to longitudinal stability, so the model with convergent-expanded afterbody was designed to improve stability. The effects of nose bluntness and forebody strakes on side force and yaw moment were presented, and the differences of aerodynamic characteristics with pointed and blunt nose, with and without forebody strakes were described. Results show that nose bluntness delays the appearance of asymmetric vortex, and the maximum side force is reduced by at least 50%. The forebody strakes reduce side force and yaw moment by weakening the asymmetric vortical interactions. The results can provide some references for designing the cabin air-launched rocket.

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Anandhanarayanan, Karuppanasamy, Ankit Raj, Rajah Krishnamurthy und Debasis Chakraborty. „Engineering Method of Prediction of Plume Path of Air Launched Missile“. Defence Science Journal 70, Nr. 2 (09.03.2020): 201–6. http://dx.doi.org/10.14429/dsj.70.13853.

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Separation dynamics study of an air-launched missile is a paramount task for ensuring the safety of launch aircraft. The study should certify that there is absolute absence of any physical interference of missile with the aircraft at any circumstance. It is also important to ensure that the interference of rocket motor plume of hot-launched missile does not have any significant effect on the structure, on board electronic components and sensitive parts of the aircraft. The plume ingestion into the aircraft intake is a critical problem which endangers the safety of the aircraft. Therefore, the prediction of plume path of hot-launched missile is a significant part of separation dynamics study. An engineering approach based on a particle tracking method was followed in predicting the plume path in the present work. Further, the method is modified using reverse particle tracking method to make it more efficient. The method is applied in predicting plume path for an air-to air-missile and is found that this approach gives reasonably accurate plume path with minimum computational requirements.

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Zhang, G. Q., S. C. M. Yu, A. Chien und Y. Xu. „Unsteady Aerodynamic Investigation of the Propeller-Wing Interaction for a Rocket Launched Unmanned Air Vehicle“. Advances in Mechanical Engineering 5 (Januar 2013): 735168. http://dx.doi.org/10.1155/2013/735168.

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Huan-Ding, Zhou, Xie Wei-Qi und Cai Yuan-Wen. „The Analysis of Compound Control in the Pre-launch Attitude of Internally Carried Air-launched Rocket Based on Simulink“. IOP Conference Series: Materials Science and Engineering 449 (29.11.2018): 012007. http://dx.doi.org/10.1088/1757-899x/449/1/012007.

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Lübken, F. J., B. Strelnikov, M. Rapp, W. Singer, R. Latteck, A. Brattli, U. P. Hoppe und M. Friedrich. „The thermal and dynamical state of the atmosphere during polar mesosphere winter echoes“. Atmospheric Chemistry and Physics 6, Nr. 1 (02.01.2006): 13–24. http://dx.doi.org/10.5194/acp-6-13-2006.

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Abstract. In January 2005, a total of 18 rockets were launched from the Andøya Rocket Range in Northern Norway (69° N) into strong VHF radar echoes called "Polar Mesosphere Winter Echoes" (PMWE). The echoes were observed in the lower and middle mesosphere during large solar proton fluxes. In general, PMWE occur much more seldom compared to their summer counterparts PMSE (typical occurrence rates at 69° N are 1–3% vs. 80%, respectively). Our in-situ measurements by falling sphere, chaff, and instrumented payloads provide detailed information about the thermal and dynamical state of the atmosphere and therefore allow an unprecedented study of the background atmosphere during PMWE. There are a number of independent observations indicating that neutral air turbulence has caused PMWE. Ion density fluctuations show a turbulence spectrum within PMWE and no fluctuations outside. Temperature lapse rates close to the adiabatic gradient are observed in the vicinity of PMWE indicating persistent turbulent mixing. The spectral broadening of radar echoes is consistent with turbulent velocity fluctuations. Turbulence also explains the mean occurrence height of PMWE (~68–75 km): viscosity increases rapidly with altitude and destroys any small scale fluctuations in the upper mesosphere, whereas electron densities are usually too low in the lower mesosphere to cause significant backscatter. The seasonal variation of echoes in the lower mesosphere is in agreement with a turbulence climatology derived from earlier sounding rocket flights. We have performed model calculations to study the radar backscatter from plasma fluctuations caused by neutral air turbulence. We find that volume reflectivities observed during PMWE are in quantitative agreement with theory. Apart from turbulence the most crucial requirement for PMWE is a sufficiently large number of electrons, for example produced by solar proton events. We have studied the sensitivity of the radar echo strength on various parameters, most important electron number density and turbulence intensity. Our observational and theoretical considerations do not provide any evidence that charged aerosol particles are needed to explain PMWE, in contrast to the summer echoes which owe their existence to charged ice particles.

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Lübken, F. J., B. Strelnikov, M. Rapp, W. Singer, R. Latteck, A. Brattli, U. P. Hoppe und M. Friedrich. „The thermal and dynamical state of the atmosphere during polar mesosphere winter echoes“. Atmospheric Chemistry and Physics Discussions 5, Nr. 4 (29.08.2005): 7613–45. http://dx.doi.org/10.5194/acpd-5-7613-2005.

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Abstract. In January 2005, a total of 18 rockets were launched from the Andøya Rocket Range in Northern Norway (69° N) into strong VHF radar echoes called 'Polar Mesosphere Winter Echoes' (PMWE). The echoes were observed in the lower and middle mesosphere during large solar proton fluxes. In general, PMWE are much more seldom compared to their summer counterparts PMSE (typical occurrence rates at 69° N are 1–3% vs. 80%, respectively). Our in-situ measurements by falling sphere, chaff, and instrumented payloads provide detailed information about the thermal and dynamical state of the atmosphere and therefore allow an unprecedented study of the background atmosphere during PMWE. There are a number of independent observations indicating that neutral air turbulence has caused PMWE. Ion density fluctuations show a turbulence spectrum within PMWE and no fluctuations outside. Temperature lapse rates close to the adiabatic gradient are observed in the vicinity of PMWE indicating persistent turbulent mixing. The spectral broadening of radar echoes is consistent with turbulent velocity fluctuations. Turbulence also explains the mean occurrence height of PMWE (~68–75 km): Viscosity increases rapidly with altitude and destroys any small scale fluctuations in the upper mesosphere, whereas electron densities are usually too low in the lower mesosphere to cause significant backscatter. The seasonal variation of echoes in the lower mesosphere is in agreement with a turbulence climatology derived from earlier sounding rocket flights. We have performed model calculations to study the absolute magnitude of backscatter from plasma fluctuations caused by neutral air turbulence. We find that volume reflectivities observed during PMWE are in quantitative agreement with theory. Apart from turbulence the most crucial requirement for PMWE is a sufficiently large number of electrons, for example produced by solar protons. We have studied the sensitivity of the radar echo strength on various parameters, most important electron number density and turbulence intensity. Our observational and theoretical considerations do not provide any evidence that charged aerosol particles are needed to explain PMWE, in contrast to the summer echoes which owe their existence to charged ice particles.

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Bertaina, Mario, Toshikazu Ebisuzaki, Piero Galeotti und Fumiyoshi Kajino. „THE JEM-EUSO MISSION“. Acta Polytechnica 53, A (18.12.2013): 811–13. http://dx.doi.org/10.14311/ap.2013.53.0811.

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The JEM-EUSO mission explores the origin of the extreme energy cosmic rays (EECRs) above 50EeV and explores the limits of the fundamental physics, through the observations of their arrival directions and energies. It is designed to open a new particle astronomy channel. This superwide-field (60 degrees) telescope with a diameter of about 2.5m looks down from space onto the night sky to detect near UV photons (330 ÷ 400nm, both fluorescent and Cherenkov photons) emitted from the giant air showers produced by EECRs. The arrival direction map with more than five hundred events will tell us the origin of the EECRs and allow us to identify the nearest EECR sources with known astronomical objects. It will allow them to be examined in other astronomical channels. This is likely to lead to an nderstanding of the acceleration mechanisms perhaps producing discoveries in astrophysics and/or fundamental physics. The comparison of the energy spectra among the spatially resolved individual sources will help to clarify the acceleration/emission mechanism, and also finally confirm the Greisen–Zatsepin–Kuz’min process for the validation of Lorentz invariance up to γ ~ 10<sup>11</sup>. Neutral components (neutrinos and gamma rays) can also be detected as well, if their fluxes are high enough. The JEM-EUSO mission is planned to be launched by a H2B rocket about 2017 and transferred to ISS by H2 Transfer Vehicle (HTV). It will be attached to the Exposed Facility external experiment platform of “KIBO”.

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Mehr Quellen

Dissertationen zum Thema "Air-launched rocket"

Sigvant, John. „Conceptual Design of an Air- launched Multi-stage Launch Vehicle“. Thesis, KTH, Fysik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-284355.

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In the present thesis, the objective was to find the maximum amount of payload mass that can be put into a 500 km polar orbit by a 1400 kg air-launched multi-stage rocket launched from a fighter jet platform. To fulfill the objective an algorithm incorporating several modules was developed. The modules performed calculations based on theoretical models and literature values to arrive at optimal design variables. From the design the maximum payload mass was able to be derived and it was concluded that a three-stage launch vehicle was able to deliver a 22.0 kg payload to the desired orbit.
I den här avhandlingen var syftet att hitta den maximala mängden nyttolastmassa som kan transporteras av en 1400 kg flerstegsraket uppskjuten från luften till en 500 km polär bana. För att uppfylla målet utvecklades en algoritm med flera moduler. Modulerna utförde beräkningar baserade på teoretiska modeller och litteraturvärden för att komma fram till optimala designvariabler. Från konstruktionen kunde den maximala nyttolastmassan härledas och det konstaterades att en trestegsraket kunde leverera en nyttolast på 22.0 kg till den önskade omloppsbanan.

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Rasmussen, Måns. „Conceptual Design of an Air-Launched Three-Staged Orbital Launch Vehicle“. Thesis, KTH, Rymdteknik, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-302775.

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The objective of this study was to design a launch vehicle capable of deploying a nanosatellite into a Sun-synchronous orbit at 500 km orbital altitude from the JAS 39E/F Gripen fighter aircraft. This was achieved by first performing theoretical calculations for the required nozzles and solid propellant grain configurations for the first two solid stages, followed by the necessary liquid propellant configuration for the third stage. Lastly, two methods were investigated in solving the trajectory ascent problem for the launch vehicle design. First, by stating the trajectory problem as an initial value problem while guessing a Sigmoidal steering law. Secondly, by stating the trajectory problem as a boundary value problem. The latter was solved by transcribing the trajectory problem into a nonlinear program where a parametric steering law was derived using a Sequential quadratic programming algorithm.Ultimately, resulting in a launch vehicle design with a gross lift-off mass of 1,289 kg, capable of launching an 8.4 kg payload into the targeted orbit, with suggested modifications to increase the possible payload mass to 12.9 kg.
Målet med den här studien var att designa en luftlanserad trestegsraket kapabel till att transportera en nanosatellit upp till en solsynkron omloppsbana på 500 km altitud från ett JAS 39E/F Gripen jaktflygplan. Det gjordes genom att först beräkna de nödvändiga dysorna och krutladdningsformerna för de två första stegen tillsammans med en flytande bränsledesign för det tredje steget. Två metoder undersöktes för bananalysen. Först genom att anta en Sigmoidal styrningsfunktion för pitchen, sedan genom att transkribera problemet till ett icke-linjärt program där en parametrisk styrlag togs fram genom att använda en Sequential quadratic programming algoritm. Slutligen presenterades en raketdesign med en total vikt på 1 289 kg, kapabel till att skjuta upp en nyttolast på 8,4 kg till den önskade omloppsbanan tillsammans med förslag som kan öka den möjliga nyttolasten till 12,9 kg.

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Musil, Tomáš. „Létající atmosférický nosič pro vypouštění raket“. Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2021. http://www.nusl.cz/ntk/nusl-443187.

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The main objective of this thesis is to introduce the reader to the problematics of air-launch and to a custom design solution applying this concept. The specifics of this method of bringing a payload into orbit are described and explained. Overview of projects which use aircraft to launch spacecraft is included. Determination of primary parameters of a launch vehicle designed to carry a payload of a specified mass is conducted. The required flight performance has been estimated, a computational model has been developed in software MATLAB, and a multidisciplinary optimization of the design parameters has been performed using a genetic algorithm optimization method. Parameters of the designed air-launched rocket are compared with those of a ground-launched rocket. According to the specific criteria, the Airbus A310-300 aircraft was selected as the most suitable transport aircraft to be used for launching the designed launch vehicle. The last part of the thesis is devoted to the proposal of necessary modifications and estimation of the flight performance.

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Beerer, Ingrid Mary. „Modeling dispersions in initial conditions for air-launched rockets and their effect on vehicle performance“. Thesis, Massachusetts Institute of Technology, 2013. http://hdl.handle.net/1721.1/86865.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2013.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 157-159).
Growing interest in air-launched rockets as a method for lofting satellites into orbit motivates the need to investigate the unique challenges that air launch presents. This thesis explores how uncertainties in an air-launched rocket's state at ignition can affect system performance and investigates a reference trajectory strategy to mitigate performance loss. First, representative vehicle configurations for a generic air-launch system are presented. Mass properties, propulsion characteristics, and vehicle aerodynamics are estimated for the generic rocket configuration. A six-degree-of-freedom (6-DOF) simulation models the vehicle's behavior during the uncontrolled drop phase prior to rocket ignition. The results of 1000 Monte Carlo runs with various initial conditions produce a statistical representation of the expected dispersions in vehicle state at ignition. A 6-DOF Simulink simulation of the rocket's first stage bum is used to quantify the vehicle's performance. The simulation is run for a variety of ignition states, reference trajectories, and constraints on the rocket's control system. The results indicate that for a highly responsive thrust vector control (TVC) system, the rocket experiences negligible performance losses due to dispersions in ignition conditions. However, for a rocket with a less responsive TVC system, dispersions will result in significant performance loss by the end of first stage burn. Finally, the thesis illustrates how selection of a reference trajectory that is optimized for a given dispersed ignition state can significantly reduce the system's performance loss due to dispersions..
by Ingrid Mary Beerer.
S.M.

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Konferenzberichte zum Thema "Air-launched rocket"

Roychowdhury, Anjali, Thomas White, Andrew Lesh, Tim Vrakas, Michael Arcidiacono, Jackson Miller, Rayan Sud et al. „Air-Launched. Low-SWaP, Space-Capable Sounding Rocket“. In 2019 IEEE Aerospace Conference. IEEE, 2019. http://dx.doi.org/10.1109/aero.2019.8741861.

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Haglind, Fredrik, Henrik Edefur und Stefan Olsson. „Design of a Solid Propellant Air Turbo Rocket for a Tactical Air-Launched Missile“. In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27826.

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Traditionally, air-launched missiles are powered by a turbojet engine, rocket motor or a ramjet engine. A novel concept that may offer advantages over these concepts is the Air Turbo Rocket (ATR), which is a combined cycle engine, featuring a cycle where the turbine is isolated from the core engine flow entirely and powered by a separate gas generator. This paper is aimed at assessing the suitability of the solid propellant ATR as power source for a tactical air-launched missile. The ATR cycle is designed to achieve optimum performance, and a suitable solid propellant is selected. In addition, a turbojet and a solid rocket motor are designed for the same requirements, and the performances of these three engine concepts are compared. The ATR offers high thrust to weight and thrust to frontal area weight ratios, throttleability, and a wide speed-altitude operating envelope. The calculations suggest that, provided that the afterburning cooling issues can be solved, it would be reasonable to design the ATR such that a stoichiometric fuel/air mixture is obtained in the afterburner. For the Mach number range evaluated here, the ATR may offer advantages over the turbojet and the solid propellant rocket motor.

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Noh, Kyung-Ho, Young Moo Ji, Mee-Young Park, Jae-Woo Lee, Yung-Hwan Byun und Young Chang Choi. „Integrated Analysis of Air-launched Rocket Using Fluid-Structure Interaction“. In 45th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-728.

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Xu, Zhi, und Shuo Tang. „Air-launched rocket attitude control of separation stage based on RCS“. In 2010 3rd International Conference on Advanced Computer Theory and Engineering (ICACTE 2010). IEEE, 2010. http://dx.doi.org/10.1109/icacte.2010.5579561.

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Hendrick, P., und M. Saint-Mard. „Subsonic in-flight LOX collection for an all-rocket air-launched orbiter“. In 35th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-2351.

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Karabeyoglu, Arif, Todd Falconer, Brian Cantwell und Jose Stevens. „Design of an Orbital Hybrid Rocket Vehicle Launched from Canberra Air Platform“. In 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-4096.

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Logan, William, Roger Davis, Nesrin Sarigul-Klijn und Marti Sarigul-Klijn. „Engine Thrust Effects on Air-Launched Rocket Aerodynamic Characteristics at High Angle of Attack“. In 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-4963.

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Edefur, Henrik, Fredrik Haglind und Stefan Olsson. „Design of an Air-Launched Tactical Missile for Three Different Propulsion Systems: ATR, Rocket and Turbojet“. In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27844.

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The objective of this paper is to assess the feasibility of a solid propellant Air Turbo Rocket (ATR), in comparison with a conventional turbojet engine or a solid rocket motor, as power source for a medium range tactical air-launched missile from an overall system point of view. A sizing method for missiles is developed, which together with flight performance calculations and engine performance data determines the final size and weight of the missile and its engine. The results suggest that an ATR engine is more favourable than a jet engine when the ratio between maximum (manoeuvre) thrust and minimum (cruise) thrust is large; for example for a mission including a cruise segment and a high load factor manoeuvre made at constant speed. For the missile range investigated in this paper no breakpoint in distance has been found beyond which the ATR engine becomes impractical. The rocket motor can produce a huge amount of thrust, thus giving it a very large maximum to minimum thrust ratio. However, it has a disadvantage in its low fuel efficiency and high combustion temperature, making it impracticable for missions requiring any longer duration. Altogether the choice of propulsion system has a large impact on maximum take-off weight, size and performance of the missile.

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Geisler, Robert, Thomas Moore, Eric Rohrbaugh und Carl Pignoli. „Unlocking the Mystery of the D-21B Solid Rocket Boosted Air-Launched Mach-3 UAV“. In 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-5761.

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Ishkov, Sergey, Victor Balakin, Andrew Khramov und Nikolay Elisov. „Optimizing an Ascent Trajectory of a Small Spacecraft Launched by an Air-based Two-Stage Rocket“. In 2019 9th International Conference on Recent Advances in Space Technologies (RAST). IEEE, 2019. http://dx.doi.org/10.1109/rast.2019.8767875.

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