黑料不打烊

Bakalauro baigiamajame darbe pateiktas bepilo膷io orlaivio radiolokacinio atsakiklio projektavimas. Literat奴ros analiz臈s dalyje yra ap啪vegiami egzistuojan膷i懦 atsakikli懦 prototipai bei nagrin臈jama su prototip懦 elektrine sandara susijusi teorija. Projektin臈je dalyje yra formuojamos atsakiklio strukt奴rin臈s blokin臈s schemos, j懦 pagrindu yra parenkami konkret奴s komponentai bei sudaromos principin臈s elektrin臈s schemos. Darbe yra pateikti grafikai ir skai膷iavimai, 寞rodantys, kad projekto u啪davini懦 s膮lygos buvo 寞vykdytos. I拧vad懦 ir pasi奴lym懦 dalyje nurodomi darbo pasiekti rezultatai bei galimi tolimesnio sistemos tobulinimo galimyb臈s. Darb膮 sudaro 6 dalys: 寞vadas, literat奴ros ap啪valga ir prototip懦 analiz臈, schem懦 projektavimas ir parametr懦 skai膷iavimai, i拧vados ir pasi奴lymai, literat奴ros s膮ra拧as, priedai. Darbo apimtis 鈥� 90 p. teksto be pried懦, 46 iliustr., 7 lent., 36 bibliografiniai 拧altiniai. Atskirai pridedami darbo priedai.

In the final bachelor's thesis the design of a radar transponder for a drone. The literature analysis part of the thesis represents the prototypes of existing transponders and the theory related to the electrical structure of the prototypes. In the design part, the structural block diagrams of the transponder are developed, the specific components are selected on the basis of these diagrams, and the principle electrical schematics are drawn up. The work includes graphs and calculations demonstrating that the conditions of the project objectives have been met. The conclusions and suggestion section indicates the results achieved during the project and possible options for further improvement of the system. Structure: introduction, literature review and prototype analysis, circuit design and parameter calculations, conclusions and suggestions, references, annexes. Thesis consist of: 90 p. text without appendixes, 46 pictures, 7 tables, 36 bibliographical entries. Attachments are attached separately.

Darbe nagrin臈jami sluoksniuotieji pluo拧tu armuoti metaliniai (SPAM) kompozitai, tokie kaip GLARE, pasi啪ymintys didesniu atsparumu pa啪aidai ciklinio apkrovimo s膮lygomis. 艩ie kompozitai taikomi orlaivi懦 konstrukcijose, kur svarbus ilgalaiki拧kumas ir patikimumas. Tyrimo objektas 鈥� GLARE tipo kompozitai, sudaryti i拧 aliuminio lak拧t懦 ir stiklo pluo拧tu armuot懦 epoksidini懦 sluoksni懦, veikiami kvazistatini懦 ir ciklini懦 apkrov懦. Tyrime analizuojama pluo拧to s膮veikos 寞taka ply拧i懦 plitimui aliuminio sluoksniuose bei tarpsluoksn臈s s膮veikos praradimui. Siekiant 寞vertinti 拧i懦 rei拧kini懦 寞tak膮 kompozito ir膷iai, taikoma skaitinio modeliavimo metodika. Sukurtas modelis leid啪ia prognozuoti SPAM kompozit懦 varginam膮j膮 elgsen膮, 寞traukiant abu pagrindinius pa啪aid懦 mechanizmus ir pluo拧to s膮veikos mechanizm膮.

The study investigates fiber metal laminates (FMLs), such as GLARE, which exhibit enhanced damage resistance under cyclic loading conditions. These composites are used in aircraft structures where durability and reliability are critical. The research focuses on GLARE-type composites, composed of aluminum sheets and glass fiber-reinforced epoxy layers, subjected to quasi-static and cyclic loads. The study analyzes the effect of fiber bridging on crack propagation in the aluminum layers and the loss of interfacial bonding. To assess the impact of these phenomena on the composite's strength, a numerical modeling approach is applied. The developed model enables the prediction of the fatigue behavior of FML composites, incorporating both primary damage mechanisms and the fiber bridging effect.

Baigiamojo darbo u啪duotis yra atlikti bepilo膷io orlaivio skryd啪io trajektorijos optimizavim膮 taikant daugiakriterin寞 po啪i奴r寞. Darbe pateikiamos optimizacijos metodai, algoritmai mar拧rut懦 skai膷iavimui, j懦 rezultatai, mar拧rut懦 啪em臈lapiai ir ka拧t懦 funkcijos grafikai. Darb膮 sudaro 拧ios dalys: 寞vadas, literat奴ros analiz臈, metodologija, sukurto algoritmo derinimas, 啪mogaus ir algoritmo rezultat懦 palyginimas, bandymai, i拧vados, literat奴ros s膮ra拧as bei priedai. Taip pat pateikiamas ekonominis darbo 寞vertinimas bei darbo, aplinkos ir skryd啪i懦 saugos reikalavimai.

The objective of the final thesis is to perform the optimization of an unmanned aerial vehicle's flight trajectory using a multi-criteria approach. The thesis presents optimization methods, algorithms for route calculation, their results, route maps, and cost function graphs. The thesis consists of the following sections: introduction, literature review, methodology, tuning of the developed algorithm, comparison of human and algorithm results, experiments, conclusions, list of references, and appendices. Additionally, an economic evaluation of the work is provided, along with requirements for occupational, environmental, and flight safety.

Baigiamajame bakalauro darbe projektuojama kovinio bepilo膷io orlaivio pagrindin臈s 惫补啪颈耻辞办濒臈s atrama. Analizuojami egzistuojantys koviniai dronai, j懦 惫补啪颈耻辞办濒臈s i拧d臈stymas, mechanizmo i拧skleidimo kinematika. Pagal i拧analizuotus pana拧iausius dronus ir j懦 paskirtis sukurta pagrindin臈s bepilot臈s skraidykl臈s atramos kinematin臈 schema. Paskai膷iuoti dujinio-hidraulinio amortizatoriaus parametrai. Atlikti 惫补啪颈耻辞办濒臈s atramos ir jungiam懦j懦 mazg懦 stipruminiai, aerodinaminio pasiprie拧inimo skai膷iavimai. Remiantis skai膷iavimo rezultatais, parinkta 惫补啪颈耻辞办濒臈s i拧skleidimo pavara. Sukurti reikalingi agregat懦 br臈啪iniai. Pateiktos agregato med啪iagos. Apibendrinti sprendimai ir rezultatai, bei suformuluotos i拧vados. Darb膮 sudaro: 寞vadas, egzistuojan膷i懦 dron懦 analiz臈, kinematin臈s schemos k奴rimas, amortizatoriaus skai膷iavimai, pavaros parinkimas, stipruminiai skai膷iavimai, gamybos med啪iagos, i拧vados. Darbo apimtis 鈥� 53 p. teksto, 35 paveiksl懦, 15 lenteli懦, 13 bibliografiniai 拧altiniai. Atskirai pridedami darbo priedai.

The bachelor鈥檚 thesis focuses on the design of the main landing gear strut for a combat unmanned aerial vehicle (UAV). Existing combat drones are analyzed, including their landing gear layouts and the kinematics of deployment mechanisms. Based on the analysis of the most similar drones and their intended functions, a kinematic diagram of the UAV's main landing gear strut is developed. The parameters of a oleo-pneumatic shock absorber are calculated. Structural strength and aerodynamic drag calculations are performed for the landing gear strut and its connecting assemblies. Based on these results, a suitable landing gear deployment actuator is selected. The necessary component assembly drawings are created, and the materials used for the assembly are specified. The design solutions and results are summarized, and conclusions are presented. The thesis consists of the following sections: introduction, analysis of existing drones, development of the kinematic diagram, shock absorber calculations, actuator selection, strength calculations, materials used in production, and conclusions. The work comprises 53 pages of text, 35 figures, 15 tables, and 13 bibliographic sources. Appendices included.

艩iame moksliniame darbe nagrin臈jama orlaivi懦 Airbus A320 拧eimos keleivi懦 salon懦 modifikavimo galimyb臈, papildomai 寞rengiant daikt懦 laikymo vietas lub懦 konstrukcijoje. Atsi啪velgiant 寞 拧iuolaikinio oro transporto augan膷ius keleivi懦 ir baga啪o srautus, i拧ry拧k臈ja poreikis efektyviau i拧naudoti salono erdv臋, siekiant padidinti keleivi懦 komfort膮 ir salono funkcionalum膮. Darbe atliekama technin臈 analiz臈, 寞vertinant galimus konstrukcinius sprendimus, j懦 寞tak膮 orlaivio svoriui, saugai, aerodinamikai ir sertifikavimo reikalavimams. Taip pat pateikiami ergonomikos, med啪iag懦 parinkimo bei orlaivio svorio balanso aspektai. Tyrimo rezultatai gali b奴ti naudingi tiek orlaivi懦 gamintojams, tiek oro linij懦 bendrov臈ms, ie拧kan膷ioms inovatyvi懦 sprendim懦 keleivi懦 salono erdv臈s optimizavimui.

This scientific thesis investigates the possibility of modifying the passenger cabin of the Airbus A320 family aircraft by integrating additional overhead storage compartments into the ceiling structure. In response to the growing demand for air travel and increased baggage volume, the need to optimize cabin space to enhance passenger comfort and overall cabin functionality has become increasingly relevant. The study provides a technical analysis of potential structural solutions, evaluating their impact on aircraft weight, safety, aerodynamics, and certification requirements. Additionally, aspects of ergonomics, material selection, and aircraft weight balance are examined. The findings of this research may be valuable for both aircraft manufacturers and airlines seeking innovative approaches to optimize cabin space utilization.鈥�

Adityvios gamybos (AG) technologij懦 populiarumas did臈ja d臈l ekonomi拧kumo, gamybos grei膷io ir prieinamumo pradedantiesiems vartotojams, ypa膷 lyginant su tradiciniais dron懦 gamybos metodais. AG taip pat pa拧alina projektavimo apribojimus, leid啪ia naudoti kompiuterizuot膮 projektavim膮, pritaikyt膮 adityviai gamybai, kuris suteikia galimyb臋 kurti individualizuotas detales. Ta膷iau AG b奴du pagamint懦 detali懦 fizin臈s savyb臈s priklauso nuo toki懦 veiksni懦 kaip polimero med啪iaga, spausdinimo temperat奴ra ir greitis. Dron懦 gamyboje itin svarbu suma啪inti komponent懦 svor寞. Tai galima pasiekti optimizuojant vidin臋 strukt奴r膮 ir derinant med啪iagas, pasi啪ymin膷ias tinkamomis mechanin臈mis savyb臈mis, siekiant padidinti dalies stiprum膮. Be to, dron懦 dalys turi geb臈ti sugerti deformacijos energij膮, kad b奴t懦 i拧vengta trapi懦 l奴啪i懦. Svor寞 taip pat galima ma啪inti naudojant ma啪o tankio polimerus, kurie AG proceso metu sudaro elasting膮, por臈t膮 strukt奴r膮, i拧laikant konstrukcijos na拧um膮. 艩iuo metu rinkoje yra 寞vairi懦 med啪iag懦, tinkam懦 dron懦 gamybai. 艩iame tyrime eksperimenti拧kai vertinamas ma啪o tankio polimer懦鈥攌onkre膷iai PLA (polilaktido r奴g拧ties) ir LW-PLA (lengvos PLA)鈥攖inkamumas naudoti drono priek臈je dalyje - nosyje. D臈mesys skiriamas dalies tvirtumui, elastingumo moduliui ir deformacijos energijos sugerties savybi懦 analizei, naudojant lydymo si奴l懦 gamybos technologij膮. Supaprastintas atvejo tyrimas iliustruoja adityvios gamybos galimybes. Teoriniais skai膷iavimais nustatyta, kad staigaus drono susid奴rimo metu i拧siskiria 299,7 J deformacijos energijos. 艩i vert臈 naudojama kaip na拧umo vertinimo kriterijus. Kei膷iant dalies vidin臋 geometrij膮, tyrime nagrin臈jama, kaip AG metodai gali pad臈ti pasiekti tikslin寞 svor寞, pagerinti energijos sugert寞 ir mechanin寞 atsparum膮 esant tiek statin臈ms, tiek pasikartojan膷ioms spaudimo apkrovoms. Darbo strukt奴ra: 寞vadas, literat奴ros ap啪valga, projektavimas ir gamyba, rezultat懦 analiz臈, i拧vados, literat奴ros s膮ra拧as. Apimtis 鈥� 55 psl., 48 iliustracijos, 4 lentel臈s, 28 拧altiniai. Priedai pateikiami atskirai.

The rising popularity of additive manufacturing (AM) technologies is largely due to their cost-effectiveness, speed, and accessibility for entry-level users, especially compared to traditional methods of drone production. AM also removes design limitations, enabling the use of computer-aided design for additive manufacturing (DfAM), which allows for highly customized components. However, the physical properties of parts produced through AM are influenced by factors such as the polymer material, printing temperature, and speed. In drone manufacturing, minimizing weight is critical. This can be achieved by optimizing internal structures and combining materials with suitable mechanical properties to enhance structural strength. Additionally, drone components must be capable of absorbing strain energy to prevent brittle failure. Using low-density polymers that form elastic, porous structures during printing offers another route to reducing weight while maintaining performance. Various materials are now available for drone production. This study experimentally evaluates the potential of low-density polymers鈥攕pecifically PLA (polylactic acid) and LW-PLA (lightweight PLA)鈥攆or use in drone fuselage components. The focus is on analyzing their strength, elastic modulus, and strain energy absorption using fused filament fabrication (FFF) technology. A simplified case study demonstrates the potential of DfAM. Theoretical calculations estimate the deformation energy generated during a sudden drone impact, which is theoretically calculated to be 299.7J. These values are used as benchmarks for performance evaluation. By modifying the internal geometry of the components, the study explores how DfAM can help achieve target weight and enhance energy absorption and mechanical strength under both static and repeated compression loads. Structure of the thesis: introduction, literature review, design and manufacturing, analysis of results, conclusions, reference list. The thesis consists of: 55 p. of text, 48 illustrations, 4 tables, 28 references. Annexes included.

Baigiamajame bakalauro darbe nagrin臈jama ir projektuojama pradiniam mokymui skirto sklandytuvo 惫补啪颈耻辞办濒臈. Buvo atlikta prototip懦 analiz臈, palygintos kit懦 sklandytuv懦 va啪iuokli懦 konfig奴racijos, j懦 privalumai ir tr奴kumai. Atlikti 惫补啪颈耻辞办濒臈s aerodinamin臈s analiz臈s skai膷iavimai, priekin臋 ir galin臋 va啪iuokl臋 veikian膷i懦 apkrov懦 skai膷iavimai. Turint va啪iuokl臋 veikian膷ias apkrovas atlikti komponent懦 stipruminiai skai膷iavimai. Nubrai啪yti sklandytuvo 惫补啪颈耻辞办濒臈s, surinkimo, montavimo bei atskir懦 detali懦 br臈啪iniai. Darb膮 sudaro 8 dalys: 寞vadas, prototip懦 analiz臈, aerodinamin臈s charakteristikos skai膷iavimai, apkrov懦 apskai膷iavimas, stiprumin臈 komponent懦 analiz臈, gamybos med啪iag懦 parinkimas ir apra拧ymas, i拧vados, literat奴ros s膮ra拧as. Darbo apimtis 鈥� 79 p. teksto be pried懦, 51 iliustr., 18 lent., 16 bibliografiniai 拧altiniai. Atskirai pridedami darbo priedai.

The final bachelor's thesis analyzes and designs a glider chassis for initial training. Prototype analysis was performed, other glider chassis configurations were compared, their advantages and disadvantages were compared. Aerodynamic analysis calculations of the chassis were performed, calculations of the loads acting on the front and rear chassis were performed. With the loads acting on the chassis, strength calculations of the components were performed, and drawings of the assembly, and individual details of the glider chassis. The work consists of 8 parts: introduction, prototype analysis, aerodynamic characteristic calculations, load calculation, strength analysis of components, selection and description of manufacturing materials, conclusions, bibliography. The volume of the work is 79 p. of text without appendices, 51 illustrations, 18 tables, 16 bibliographical sources. Appendices are attached separately.

艩iame baigiamajame bakalauro darbe nagrin臈jamas C0 klas臈s fiksuoto sparno bepilo膷io FPV (pirmojo asmens vaizdo) orlaivio 蝉辫补谤苍耻辞迟臈s projektavimo procesas, pasitelkiant 3D spausdinimo technologijas. Darbe analizuojami bepilo膷i懦 orlaivi懦 konstrukcij懦 ypatumai, aerodinaminiai reikalavimai ir konstrukcini懦 med啪iag懦 pasirinkimas, siekiant u啪tikrinti lengv膮, tvirt膮 ir ekonomi拧kai efektyvi膮 konstrukcij膮. Pagrindinis d臈mesys skiriamas 蝉辫补谤苍耻辞迟臈s geometrijos, vidaus tvirtinimo element懦 ir servo mechanizm懦 integravimui. Naudojant CAD programin臋 寞rang膮 sukurti br臈啪iniai ir sukurtas 3D spausdinimui tinkamas modelis. Projektu siekiama pasi奴lyti sprendim膮, tinkant寞 m臈g臈j懦 aviacijai, edukacijai ar lengviems tyrim懦 tikslams.Darb膮 sudaro 8 dalys: 漠vadas, literat奴ros analiz臈; sparno j臈gin臈 schema, geometriniai parametrai, tvirtinimai, servo variklio montavimas ir kylis; aerodinamin臈 analiz臈, stipruminiai sparno skai膷iavimai; projektavimas ir gamyba; i拧vados ir literat奴ros s膮ra拧as Darbo apimtis 鈥� 51 p. teksto be pried懦, 37 iliustracija, 7 lentel臈s, 12 bibliografini懦 拧altini懦, 9 br臈啪iniai, 1 specifikacijos lapai.

This bachelor's thesis examines the design process of a C0 class fixed-wing FPV (First Person View) drone using 3D printing technologies. The study analyzes the structural characteristics of drones, aerodynamic requirements, and the selection of construction materials to ensure a lightweight, durable, and cost-effective structure. Special attention is given to the integration of wing geometry, internal reinforcement elements, and servo mechanisms. CAD software is used to create technical drawings and to develop a model suitable for 3D printing. The project aims to offer a solution suitable for recreational aviation, educational purposes, or lightweight research applications. The thesis consists of 8 sections: Introduction; Literature Review; Wing Load-Bearing Scheme, Geometric Parameters, Mounting, Servo Motor Installation, and Vertical Stabilizer; Aerodynamic Analysis; Structural Calculations of the Wing; Design and Manufacturing; Conclusions; and References. The thesis comprises 51 pages of text (excluding appendices), 12 illustrations, 7 tables, 9 technical drawings, and 1 specification sheet.

Baigiamajame bakalauro darbe yra projektuojama virpesi懦 slopinimo sistema, ,,3U CubeSat鈥樷�� palydovui. 艩ios sistemos tikslas yra nuslopinti palydove, misijos metu, kylan膷ias vibracijas. Palydove, kuriam projektuojama 拧i sistema, yra naudojamas ATLAS optin臈s komunikacijos modulis, kuris yra jautrus vibracijoms. Vibracij懦 拧altinis palydove yra reakcijos rat懦 mas臈s disbalansas. Projektuojamos virpesi懦 slopinimo sistema turi u啪tikrinti, kad ATLAS nepatirs poslink懦 vir拧ijan膷i懦 did啪iausius leistinus, u啪duotus gamintojo. Projektuodami 拧i膮 sistem膮, atsi啪velgiame 寞 palydovo keliamus geometrinius ir mas臈s reikalavimus. Atsi啪velgiame 寞 raketos ne拧臈jos keliam懦 perkrov懦 stiprumines s膮lygas ir kra拧tutines temperat奴ras, kurias palydovas gali patirti misijos metu.

In the final bachelor's thesis, a vibration damping system is designed for the "3U CubeSat" satellite. The purpose of this system is to suppress vibrations arising in the satellite during the mission. The satellite for which this system is designed uses the ATLAS optical communication module, which is sensitive to vibrations. The source of vibrations in the satellite is the mass imbalance of the reaction wheels. The designed vibration damping system must ensure that ATLAS will not experience displacements exceeding the maximum permissible ones set by the manufacturer. When designing this system, we take into account the geometric and mass requirements of the satellite. We take into account the strength conditions of the overloads imposed by the launch vehicle and the extreme temperatures that the satellite may experience during the mission.

Baigiamajame bakalauro darbe projektuojama bepilo膷io orlaivio katapultos ve啪im臈lio ir jo paleidimo mechanizmo sistema. 艩iame darbe i拧analizuoti skirting懦 konstrukcij懦 ve啪im臈li懦 prototipai, kurie kiekvienas turi savitus tr奴kumus ir privalumus. Pasirenkama projektui labiausiai tinkanti ir stabiliausia konstrukcija, kuri turi ir geriausias stiprumines savybes. Projektuojant bepilo膷io orlaivio katapultos ve啪im臈lio paleidimo mechanizm膮, atsi啪velgta ne tik 寞 tai, kad b奴t懦 tenkinami stipruminiai konstrukcijos reikalavimai, bet ir 寞 konstrukcijos kompakti拧kum膮 ir gamybos paprastum膮.

In the final bachelor's thesis, the design of a catapult trolley and its launch mechanism system for an unmanned aerial vehicle (UAV) is developed. This work analyzes various prototype designs, examining the different types of trolleys, each with their own advantages and disadvantages. The most suitable and stable design, offering the best strength characteristics, is selected for the project. When designing the UAV catapult trolley launch mechanism, attention was paid not only to meeting the structural strength requirements but also to ensuring the compactness of the construction and the simplicity of manufacturing.