Global ETD Search

1	Flight Testing Small UAVs for Aerodynamic Parameter Estimation Chase, Adam Thomas 01 June 2014 (has links) A flight data acquisition system was developed to aid unmanned vehicle designers in verifying the vehicle's design performance. The system is reconfigurable and allows the designer to choose the correct combination of complexity, risk, and cost for a given flight test. The designer can also reconfigure the system to meet packaging and integration requirements. System functionality, repeatbility, and accuracy was validated by collecting data during multiple flights of a radio-controlled aircraft. Future work includes sensor fusion, thrust prediction methods, stability and control derivative estimation, and growing Cal Poly's small-scale component aerodynamic database. UAV performance design testing drag polar system identification Aeronautical Vehicles
2	Analýza letových výkonů letounu VUT 081 KONDOR / Flight performance analysis of the airplane VUT 081 KONDOR Kerndl, Jindřich January 2013 (has links) The aim of this diploma thesis is to analyse flight performance of airplane VUT-081 Kondor. The first part focuses on determination and estimation of aerodynamic characteristics of the airplane. Based on this data flight performance was calculated and evaluated according to CS-ELSA. The last part is dedicated to comparison of flight performance of VUT-081 Kondor with other similar airplanes.
3	Flight Testing Small, Electric Powered Unmanned Aerial Vehicles Ostler, Jon N. 17 March 2006 (has links) (PDF) Flight testing methods are developed to find the drag polar for small UAVs powered by electric motors with fixed-pitch propellers. Wind tunnel testing was used to characterize the propeller-motor efficiency. The drag polar was constructed using data from flight tests. The proposed methods were implemented for a small UAV. A drag polar was found for this aircraft with CDo equal to 0.021, K1 equal to 0.229, and K2 equal to -0.056. This drag polar was then used to find the following performance parameters; maximum velocity, minimum velocity, velocity for maximum range, velocity for maximum endurance, maximum rate of climb, maximum climb angle, minimum turn radius, maximum turn rate, and maximum bank angle. Applications in UAV control and mission planning are also proposed. performance flight test flight testing drag polar UAV small electric powered electric unmanned uninhabited Mechanical Engineering
4	Návrh dvoumístného kovového letounu s ohledem na nízkou cenu a jednoduchost stavby / Design of the two seater ultralight aircraft with consideration the price and simplicity of the construction Machala, Martin January 2012 (has links) The object of the diploma thesis is a conceptual layout of two-seater metal ultralight aircraft which has simple construction and with respect to low price. The preamble of the work deals with concept, layout and technology of aircraft. As next part are solved an aerodynamic characteristics, a determinative of centre of gravity position and a performance. Last of all is strength of wing.
5	Aerodynamický návrh transsonického bezpilotního kluzáku / Aerodynamic design of transonic UAV glider Kóňa, Marián January 2015 (has links) This master thesis is focused on aerodynamic design of transonic glider, which is assigned for following an airliner at cruising regime of flight. Main goal of the thesis is to determine basic geometrical design of airplane with respect to Whitcomb aera rule, mass analysis and drag polar. Weight analysis includes determining center of gravity according to longitudinal static stability margin. The drag polar of the airplane is determine for cruising regime of flight, that means the regime of following an airliner.
6	Koncepční studie lehkého dvoumotorového proudového letounu / Conceptual study of very light twin jet aircraft Smýkal, Michal January 2015 (has links) Tématem diplomové práce je koncepční studie lehkého dvoumotorového letounu. Je provedeno srovnání současných letounů, jejich motorů, technický popis navrhovaného řešení, hmotový rozbor, výpočet aerostatických podkladů, výpočet obálky zatížení, nákladů na vývoj a základní konstrukce hlavních součástí.
7	Predicting Drag Polars For Micro Air Vehicles Luke, Mark Elden 03 November 2003 (has links) (PDF) Drag polars for three Micro Air Vehicles (MAVs) were measured at Reynolds numbers of 70,000, 50,000, 30,000, and 10,000 and compared to predictions generated using the classical approach. The MAVs tested had different configurations and aspect ratios varying from 1.2 to 1.6 and ratios of wetted surface area to planform area from 2.6 to 3.9. A force balance was used to measure the lift and drag on the MAVs at angles of attack ranging from -5 degrees (or -10 degrees) to 10 degrees. The force balance allowed the MAVs to rotate in the pitching axis. The MAV angle of attack was set using an elevator installed on the MAV and controlled using a standard radio control used by RC plane enthusiasts. Uncertainty analysis performed on the data showed the uncertainty for high Reynolds numbers was dominated by velocity uncertainty, and uncertainty for the lower Reynolds numbers was dominated by uncertainty in the force measurements. Agreement between measured and predicted drag polars was good with the measured drag never being more than two times the predicted drag. For the majority of the tests, the drag coefficients followed the expected Reynolds number trend: increasing with decreasing Reynolds number. Micro Air Vehicle MAV low Reynolds number drag polar predicted vs. measured wind tunnel force balance Cfe equivalent skin friction coefficient e0 oswald efficiency CL minD lift coefficient drag coefficient drag polar prediction angle of attack wetted surface area ratio wing loading aspect ratio parasite drag coefficient drag due to lift aerodynamics Mechanical Engineering
8	Návrh repliky letounu L-40 "Meta Sokol" - základní rozměry - technologie / Replica design of Aircraft "Meta Sokol" - Basic dimensions - technology Lipková, Alica January 2008 (has links) The object of the diploma thesis is a preparation of fundamentals for realization for replica of the aircraft L-40 „Meta Sokol“ matching the requirements of Certification Specification for Very Light Aeroplanes (CS-VLA). The preamble of the work deals with the changes made on the original aircraft necessary to satisfy the criterias of the above-mentioned specification. One of the main contents of the first part of the thesis is the definition of replica’s basic dimensions and preparation of aerostatic fundamentals, including longitudinal stability control. As next a suitable engine is chosen and calculation of corresponding performances is made. A detailed weight analysis and a determination of centre of gravity position (c.g. position), important for solving the stability of an airplane, is also presented. Finally, a brief description of the manufacturing process of individual components and also factors influencing the technology are discussed.
9	Konstrukční návrh letounu Avia BH534 v ultralehkém provedení / Avia BH534 airplane design as ultralight Kozelský, Martin January 2010 (has links) The object of the diploma thesis is a preparation of fundamental bases for realization aerofoils of the replica of the biplane aircraft BH534 Avia. The preambule of the work balances replica against the real historic aircraft. As next the basic aerodynamics characteristics, construction of aerofoils and strenght calculation of the aerofoils are described.
10	Návrh základní koncepce air - mobilu / Conceptual design of air- mobil Podhorský, Matěj January 2014 (has links) The topic of the thesis is a conceptual design of a roadable aircraft. The comparison of existing concepts is made, as well as description of proposed solution, aircraft mass analysis, basic aerostatic calculations, flight and gust envelope calculation and a design of truss construction of the fuselage. The CS-VLA, alternatively ELSA-K, has been used as a certification base. The compliance to this certification specification is one of the goals of this thesis.

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