Relevant bibliographies by topics / Glider (Sailplane)

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  1. Journal articles
  2. Dissertations / Theses
  3. Books

Academic literature on the topic 'Glider (Sailplane)'

Author: Grafiati
Published: 4 June 2021
Last updated: 12 February 2022

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Journal articles on the topic "Glider (Sailplane)"

1

Woods, Robert O. "Power to the Glider." Mechanical Engineering 130, no. 08 (August 1, 2008): 46–48. http://dx.doi.org/10.1115/1.2008-aug-6.

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This article discusses developments in powered sailplane. Jet propulsion clearly demonstrates the future direction of powered sailplanes. Powered glider applies to a new class of aircraft that takes off under their own power, and then, with the power plant stopped and streamlined, behave as true sailplanes. The advent of radio control has allowed model aviation to progress to an almost unbelievable degree. There are now small turbojet engines commercially available that weigh a little over 5 pounds and deliver 40 pounds force of thrust. Jet propulsion clearly demonstrates the future direction of powered sailplanes.
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Kozuba, Jarosław, Tomasz Wojnar, Magda Mrozik, and Bartosz Stołtny. "Use of Electric Motors in the Context of Glider Aviation." Journal of KONBiN 51, no. 2 (June 1, 2021): 103–15. http://dx.doi.org/10.2478/jok-2021-0025.

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Abstract In sailplane aviation, I attach great importance to the achieved aerodynamic parameters due to the main idea of sailplane flights, which is the flight of a sailplane without external energy supply for staying in the air and only in favourable weather conditions, e.g. increasing thermal movements of the air. Only during take-off, external devices, such as a winch or a towing plane, can be used. Therefore, the use of a propulsion installed in sailplanes and operating only during take-off is a very convenient solution. This is a step towards facilitating the access to flying for a wider group of people due to the reduction of costs related to the take-off processes, and also increases the level of safety of sailplane flights by enabling the use of propulsion at critical moments of the flight. The study presents the current trends in the development of gliding, in particular motor gliders. Additionally, as a result of research works, the energy storage system was shown, which is the weakest element of the system, and at the same time the one with the greatest development potential.
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Keskin, Göksel, Seyhun Durmus, Muharrem Karakaya, and Melih Cemal Kushan. "Designing and producing a bird-inspired unmanned sailplane." Aircraft Engineering and Aerospace Technology 93, no. 6 (July 16, 2021): 1052–59. http://dx.doi.org/10.1108/aeat-02-2021-0054.

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Purpose Increasing endurance was a very appropriate subject for the biomimetic approach. The study aims to design and manufacture a long-lasting mini unmanned aerial vehicle (UAV) using active gliding and soaring. Design/methodology/approach The endurance of mini UAVs is limited by battery or fuel capacity, and it is not always possible to increase these energy sources due to the fuselage size. Long endurance aircraft are required in various areas such as silent environment and traffic monitoring or search and rescue. Literature research on bird flight performance conducted to determine design parameters. These parameters are used in the theoretical design of the UAV for optimization. Computational fluid dynamics simulation and flight tests of the UAV performed to figure out the success of the design. Findings For a mini UAV to be produced in this class, it has been observed that it is more accurate to examine birds instead of gliders due to the size similarity. The UAV design reaches a 27.5 L/D (Glide ratio) ratio in the theoretical approach. However, flight results approved max L/D ratio is around 25 at the sea level. This flight performance is enough to outperform in glide ratio of Wandering albatrosses. Practical implications Sailplanes are known as sport aircraft. However, recent projects focus on glider designs due to fuel efficiency and silent tracking. Stemme S-14 that carries a high-resolution camera is one of the examples of these projects. The unmanned glider design can lead to these implications in the UAVs at least during the stand-by period in the air. Thanks to low weight, UAVs do not require strong thermals, which allows flying almost all over the world. Originality/value Researchers generally focus on increasing the battery capacity or the performance of the UAV. However, this study’s concentration is to increase the flight duration of the UAV by using geographical currents. For this purpose, taking advantage of bird morphology is quite a new topic. Also, glider type designs are rarely found in the field.
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Firmansyah, Hendrix Novianto, Buyung Junaidin, and M. Fatha Mauliadi. "PERANCANGAN AWAL SCALE MODEL GLIDER STTA-25-02_SAILPLANE." Angkasa: Jurnal Ilmiah Bidang Teknologi 8, no. 2 (August 25, 2017): 87. http://dx.doi.org/10.28989/angkasa.v8i2.122.

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The knowledge and experience in aircraft design, especially for glider or sailplane are very important to have. Today, process of designing glider developed so rapidly, especially in America and Europe, one of the significant achievement is the performance aspect of glider. For example, the German-built Eta has a wingspan 30.78 m, aspect ratio 51 and wing loading 50.97 kg/m2, with glide angle of 0.8 degree and 3 km altitude, the glider able to fly 213 km in horizontal direction. Therefore, as the first step to understand the preliminary design of glider, it is important to start with designing a scale model glider STTA-25-02_Sailplane. The goals of this design are to get geometry and configuration of the glider, to obtained stability of glider and to gain performance data that meet with design requirements and objectives data (DR&O). The conclusions from the preliminary design of scale model glider STTA-25-02_Sailplane are the geometry and configuration are good, for example the achivement in performance, the minimum sink rate 0.52 m/s, the glide ratio more than 20 at a cruising speed over 13 m/s, stall speed 11.45 m/s at angle of attack 0 degree. In addition glider STTA-25-02_Sailplane has static and dynamic stability, the static stability condition is indicated by the value of trim angle is positive 1 degree, curve of Cma and Clfi has negative slope, Cnfi curve has positive slope. The dynamic stability condition is indicated by the eigen value for each mode o f movement are negative except on phugoid and spiral mode, eigen value for short period -5.7681 ± 7.0010, phugoid 0.0403 ± 1.1136, rool damping -32.6243, dutch roll -1.0468 ± 3.4891 and spiral 0.1467. Positive eigen value on phugoid and spiral mode can be solved by adding a control parameter of the controlsurfaces.
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5

Kensche, Ch W. "Testing and Certification of Sailplane Structures." Proceedings of the Institution of Mechanical Engineers, Part D: Transport Engineering 200, no. 4 (October 1986): 287–94. http://dx.doi.org/10.1243/pime_proc_1986_200_193_02.

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Requirements for certification of composite materials used in sailplanes and powered sailplanes, as issued by the LBA (Luftfahrtbundesamt), the airworthiness authority of the Federal Republic of Germany, are reviewed. As an example of the certification procedure the fatigue life test of a CFRP Nimbus wing conducted at the DFVLR (German Aerospace Research Establishment) is outlined. Considering the fact that the certificated lifetime of 6000 hours for gliders is not long enough, a possible way is shown for getting more comprehensive general information about the fatigue behaviour of composites and for achieving higher design allowables in an acceptable time by means of structural tests.
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6

KALWARA, Maciej, Michał KUŹNIAR, and Marek ORKISZ. "A rotating piston engine with electric generator in serial hybrid propulsion system for use in light aircraft." Combustion Engines, September 1, 2021. http://dx.doi.org/10.19206/ce-141353.

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Analysis of the possibility of using a rotary engine based electric generator to propell a powered sailplane. The paper presents analysis of utilising Wankel type enine as a power input for an electric generator in the motor glider propulsion system. This generator would be a part of the propulsion system of a hybrid motor glider using the AOS 71 motor glider airframe. In the research, the rotational characteristics of the LCR 407ti wankel engine were determined experimentally. Driving torque run, power and fuel consumption were determined as a function of engine speed. The obtained results are presented in diagrams. The conceptual diagram of the hybrid drive is presented. The electric generator was selected and its effectiveness, as well as the effectiveness of entire propulsion system was assessed from the motor glider's performance point of view. Basing on the research conducted, conclusions were drawn and there were indicated the objectives and directions of further research on hybrid propulsion with specific aerodynamic and mass limitations of the aircraft
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Dissertations / Theses on the topic "Glider (Sailplane)"

1

Bilík, David. "Koncepční návrh konstrukce nového celokovového výcvikového kluzáku vycházejícího z kluzáku řady Blaník." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2015. http://www.nusl.cz/ntk/nusl-232027.

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The object of thesis is a new full metal wing design of L-23 Super Blanik glider for L-23 NG project. Thesis includes calculation of flight envelope according to CS 22, wing load, wing design and stress analysis of important part of construction. The final part of thesis include weight estimation and comparison with existing design.
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Malinowski, Matěj. "Aerodynamická analýza měnitelné geometrie wingletu pro aplikaci na výkonném kluzáku." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2017. http://www.nusl.cz/ntk/nusl-318705.

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Diplomová práce se zabývá aerodynamickou analýzou a optimalizací wingletu kluzáku. Winglet je uvažován s možností změny tvaru v průběhu letu a optimalizační proces je zaměřen na odhalení optimálních tvarů v odlišných letových režimech. První část práce popisuje současné snahy v oblasti návrhu a vývoje wingletů s měnitelnou geometrií. Druhá část je zaměřena na popis funkce wingletu, následována třetí částí, která popisuje optimalizační metody, které mohou být použity během optimalizace. Další částí práce je popis letadla vybaveného wingletem, který byl vybrán pro optimalizaci. Tato část je následována požadavky stavebního předpisu kategorie letadla, které bylo vybráno. Následuje model typického letu tohoto letadla. Zbytek práce je organizován dle procesu hledání optimálních tvarů wingletu. Popis tvorby CAD modelu je následován popisem tvorby CFD modelu a popisem přípravy CDF simulací. V předposlední kapitole jsou odhaleny detaily optimalizačního procesu. Závěrečná část práce obsahuje vyhodnocení výsledků optimalizačního procesu.
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3

Strauch, Gregory J. "Integrated multi-disciplinary design of a sailplane wing." Thesis, Virginia Tech, 1985. http://hdl.handle.net/10919/45660.

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The objective of this research is to investigate the techniques and payoffs of integrated aircraft design. Lifting line theory and beam theory are used for the analysis of the aerodynamics and the structures of a composite sailplane wing. The wing is described by 33 - 34 design variables which involve the planform geometry, the twist distribution, and thicknesses of the spar caps, spar webs, and the skin at various stations along the wing. The wing design must satisfy 30 â 31 aeroelastic, structural, aerodynamic, and performance constraints.

Two design procedures are investigated. The first, referred to as the iterative, sequential procedure, involves optimizing the aerodynamic design for maximum average cross-country speed at E1 constant structural weight, and then optimizing the the structural design of the resulting wing geometry for minimum weight. This value is then used in another aerodynamic optimization, and the process continues iteratively until the weight converges. The other procedure, the integrated one, simultaneously optimizes the aerodynamic and the structural design variables for either maximum average cross-country speed or minimum weight.

The integrated procedure was able to improve the value of the objective function obtained by the iterative procedure in all cases. This shows The objective of this research is to investigate the techniques and payoffs of integrated aircraft design. Lifting line theory and beam theory are used for the analysis of the aerodynamics and the structures of a composite sailplane wing. The wing is described by 33 - 34 design variables which involve the planform geometry, the twist distribution, and thicknesses of the spar caps, spar webs, and the skin at various stations along the wing. The wing design must satisfy 30 â 31 aeroelastic, structural, aerodynamic, and performance constraints. Two design procedures are investigated. The first, referred to as the iterative, sequential procedure, involves optimizing the aerodynamic design for maximum average cross-country speed at E1 constant structural weight, and then optimizing the the structural design of the resulting wing geometry for minimum weight. This value is then used in another aerodynamic optimization, and the process continues iteratively until the weight converges. The other procedure, the integrated one, simultaneously optimizes the aerodynamic and the structural design variables for either maximum average cross-country speed or minimum weight.

The integrated procedure was able to improve the value of the objective function obtained by the iterative procedure in all cases. This shows that definite benefits can be gained from taking advantage of aerodynamic/structural interactions during the design process.


Master of Science
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4

Randall, Brian H. "Flapping-wing propulsion as a means of drag reduction for light sailplanes." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02sep%5FRandall.pdf.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, September 2002.
Thesis advisor(s): Kevin D. Jones, Max F. Platzer. Includes bibliographical references (p. 93-94). Also available online.
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Books on the topic "Glider (Sailplane)"

1

Horvath, Les. Sailplane aerobatics. Tempe, AZ (3108 Fairway Dr., Tempe 85282): L. Horvath, 1985.

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2

Simons, Martin. Sailplanes. 2nd ed. Königswinter, Germany: EQIP, 2005.

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3

Fundamentals of sailplane design. 3rd ed. College Park, MD: College Park Press, 1999.

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4

Basics of radio control sailplanes. [Wilton, CT]: Air Age, 1989.

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5

Schweizer, Paul A. Sailplanes by Schweizer: A history. Shrewsbury: Airlife, 1998.

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6

Building and flying RC sailplanes and electric gliders. Waukesha, WI: Kalmbach Books, 1993.

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7

Sim, Alex G. Flight characteristics of a modified Schweizer SGS 1-36 sailplane at low and very high angles of attack. Edwards, Calif: Ames Research Center, 1990.

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8

Simons, Martin. Slingsby sailplanes: A comprehensive history of all designs. Shrewsbury: Airlife, 1996.

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9

Slingsby Sailplanes. Voyageur Press, 1996.

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Self-Launch: Retractable Engine Sailplanes. For the Birds, 1998.

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