This diploma thesis deals with the calculation of composite wing loading and its stressanalysis. Furthermore work contains design of static strength test wing.

Modification of TST-14 MC glider, calculation of flight envelope, distribution of lift on the wing, calculation of loading cases of the wing, strength check of choosen construction nodes, design of the landing gear retraction mechanism, setting up loading of landing gear according to ULKM, strength check of landing gear

The object of diploma thesis is a loading determination for strength calculation of HPH 2 Twin Shark glider matching the requirements of Certification Specification for Sailplanes (CS-22). Loading of the wing, tail section, fuselage and undercarriage is determined in this work.

This diploma thesis deals with the calculation of stability and control of the L-13 SE Vivat Powered Glider. Furthermore comparing different methods of determining the aerodynamic derivatives.

The topic of the thesis is a design of an aicraft for towing of gliders. Based on the background research of the towing aircrafts currently used by the Czech aeroclubs and the analysis of the required characteristics of these aircrafts the design of the new airplane has been created. Moreover, the load of engine mount has been determined according to the CS-VLA directive (a certification guidelines for the Very-light aircrafts). Its construction design as well as strength calculation have been elaborated. The part of the thesis is a 3D model of the aircraft and the engine mount.

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.

With the help of sounding rockets, the Earth’sionosphere can be studied by ejecting cylindrical units thatmeasure various electromagnetic properties while falling. Theseunits are also known as Free Falling Units (FFUs). The goal of thisproject is to turn the FFUs into autonomous gliders by designingdeployable wings. A spring-loaded Scissor Structural Mechanism(SSM) was chosen as the main deploying mechanism. Furthermore,the conceptual wing design was simulated in Siemens NXand a structural analysis was performed in NASTRAN. Finally, aprototype was manufactured to confirm if the SSM would workas intended. Initial simulation results showed great promise withthe proper choice of materials. Due to resource limitations, theprototype could not be compared to the simulation. Based onthe prototype results, the design must be reinforced or alteredto become stronger and more rigid. / Med hjälp av sondraketer kan jordensjonosfär studeras genom att skicka ut cylindriska enhetersom mäter diverse elektromagnetiska egenskaper medan defaller. Dessa enheter är också kända som FFUs (Free FallingUnits). Målet med detta projekt var att förvandla dessa enhetertill autonoma glidare genom att designa utfällbara vingar.En fjäderbelastad saxmekanism valdes som den huvudsakligautfällningsmekanismen. Vidare simulerades den konceptuellavingdesignen i Siemens NX och strukturen analyserades i NASTRAN.Slutligen tillverkades en prototyp för att bekräfta omsaxmekanismen skulle fungera som avsedd. De första simuleringsresultatenvisade sig vara lovande med rätt materialval.På grund av begränsningar i resurser, kunde inte prototypenjämföras med simuleringen. Baserat på prototypresultaten måstedesignen förstärkas eller ändras för att bli starkare och mer styv. / Kandidatexjobb i elektroteknik 2021, KTH, Stockholm

Standartinės klasės sklandytuvo SZD – 48 – 3 “Jantar Standard 3” optimalios svorio centro padėties radimas. Pateikta skaičiavimai optimaliai svorio centro padėčiai surasti bei jos kitimas kintant greičiui. / The objective of this Master thesis is to investigate the glider gravity centre influence to the flight characteristics. Analyzing Frank Irving method, to find optimal centre of gravity. The subject of thesis is Standard class glider SZD – 48 – 3 “Jantar Standard 3”and calculation of optimal center of gravity position.

This master's thesis is focused on conceptual design of glider with electric propulsion system following the CS-22 regulation. Statistical analysis of the glider with an auxiliary electric engine has been carried out in order to determine basic design parameters for conceptual design. Based on analytical drag polar, the flight performance parameters are calculated, in particular flight range and influence of the solar panels on the flight range. This thesis also includes preliminary design solution of accumulator placement within the wing.

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.