黑料不打烊

Baigiamajame darbe nagrin臈jama elektrin臈s j臈gain臈s sistema eVTOL tipo orlaiviui. Darbe remiamasi analogi拧k懦 orlaivi懦 analize, apibr臈啪tais projektiniais reikalavimais, numatyta skryd啪io misija ir EASA dokumentais, susijusiais su VTOL orlaivi懦 sauga ir vertiport懦 infrastrukt奴ros reikalavimais. Pagrindinis darbo tikslas 鈥� parinkti ir pagr寞sti j臈gain臈s architekt奴r膮, kuri u啪tikrint懦 pakankam膮 trauk膮, energijos atsarg膮 ir valdom膮 skryd寞 kritinio gedimo atveju. Projektuojamam orlaiviui pasirinkta paskirstytos elektrin臈s varos architekt奴ra su 12 elektrini懦 varom懦j懦 mazg懦: 6 priekiniais pasukamais kintamojo 啪ingsnio propeleriais ir 6 galiniais stacionariais fiksuoto 啪ingsnio propeleriais. Sistemoje numatyti 拧e拧i baterij懦 paketai, 600 V nuolatin臈s srov臈s magistral臈, EMRAX 228 HV CC varikliai, inverteriai, reduktoriai ir au拧inimo sistema. Propeleri懦 parametrai apskai膷iuoti taikant ment臈s element懦 teorij膮, o j臈gain臈s tinkamumas 寞vertintas kab臈jimo, kreiserinio skryd啪io ir gedimo re啪imais. Gauti rezultatai parod臈, kad pasirinkta varomosios sistemos konfig奴racija atitinka nustatytus projektinius reikalavimus. Apskai膷iuota j臈gain臈s galia, baterij懦 energija ir propeleri懦 aerodinamin臈s charakteristikos leid啪ia pasiekti numatyt膮 180 km skryd啪io nuotol寞, i拧laikant reikiam膮 saugos atsarg膮. Kry啪minio baterij懦 ir varom懦j懦 mazg懦 suporavimo schema suma啪ina traukos asimetrij膮 gedimo atveju ir sudaro galimybes t奴pimui artimiausioje tinkamoje aik拧tel臈je.

The final thesis examines the electric propulsion system of an eVTOL aircraft. The work is based on an analysis of comparable aircraft, defined design requirements, the planned flight mission, and EASA documents related to VTOL aircraft safety and vertiport infrastructure requirements. The main aim of the thesis is to select and justify a propulsion architecture that ensures sufficient thrust, energy reserve, and controlled flight in the event of a critical failure. A distributed electric propulsion architecture with 12 electric propulsion units is selected for the designed aircraft: 6 front tilting variable-pitch and variable-RPM propellers and 6 rear stationary fixed-pitch propellers. The system includes six battery packs, a 600 V DC bus, EMRAX 228 HV CC motors, inverters, gearboxes, and a cooling system. The propeller parameters are calculated using blade element theory, while the suitability of the propulsion system is evaluated in hover, cruise, and failure conditions. The results show that the selected propulsion system configuration meets the defined design requirements. The calculated propulsion power, battery energy, and propeller aerodynamic characteristics allow the intended 180 km flight range to be achieved while maintaining the required safety margin. The cross-coupling scheme between the battery packs and propulsion units reduces thrust asymmetry in the event of a failure and provides a basis for a controlled landing at the nearest suitable landing site.

Baigiamajame bakalauro darbe projektuojamas ir gaminamas FPV drono valdymo sistemos da啪nio keitiklio maketas. Darbe nagrin臈jama standartinio 2,4 GHz valdymo signalo perk臈limo 寞 kit膮 da啪ni懦 ruo啪膮 galimyb臈, siekiant suma啪inti priklausomyb臋 nuo 寞prast懦 valdymo da啪ni懦. Literat奴ros analiz臈je aptariami FPV dron懦 ry拧io ypatumai, superheterodinin臈 architekt奴ra, mai拧ikliai, filtrai, generatoriai, stiprintuvai ir ELRS sistemos komponentai. Projektin臈je dalyje sudarytas da啪ni懦 planas, suprojektuotos si懦stuvo ir imtuvo da啪nio keitiklio blokin臈s schemos, parinkti komponentai ir pagamintas maketas. Atlikti laboratoriniai matavimai bei lauko bandymai parod臈, kad sistema gali perduoti FPV drono valdymo signal膮, ta膷iau jos veikim膮 riboja RF grandin臈s nuostoliai, anten懦 suderinimas ir i拧臈jimo galios lygis. Darbo apimtis 鈥� 82 p. teksto be pried懦, 70 iliustr., 14 lent., 36 bibliografiniai 拧altiniai. Atskiri priedai darbui nepridedami.

This bachelor thesis presents the design and production of a frequency converter for an FPV drone control system. The work analyses the possibility of converting a standard 2.4 GHz control signal to another frequency range in order to reduce dependence on common control frequencies. The literature review discusses FPV drone communication, superheterodyne architecture, mixers, filters, signal generators, amplifiers and ELRS system components. In the design part, a frequency plan is prepared, transmitter and receiver frequency converter block diagrams are created, components are selected and a frequency converter is produced. Laboratory measurements and field tests showed that the system can transmit an FPV drone control signal, but its performance is limited by RF chain losses, antenna matching and output power level. The thesis consists of 82 pages of text without appendices, 70 figures, 14 tables, and 36 bibliographic sources. Separate appendices are not included.

Baigiamajame magistro darbe nagrin臈jami bepilo膷i懦 orlaivi懦 automatinio valdymo algoritmai, vertinamos problemos, algoritm懦 b奴tinumas ir tikslai oro tar拧os 拧altiniams nustatyti realiuoju laiku. I拧nagrin臈ti pagrindiniai principai, kuriais remiantis dronas turi jud臈ti. Suprojektuota jutikli懦 sistema su elektronine nosimi ir 寞 dron膮 integruoti anglies monoksido jutikliai. Darbe sukurti trys paie拧kos algoritmai: zigzago, pseudogradiento bei aptikimo ir paie拧kos, remiantis Gauso sklaidos modeliu. Apra拧yta algoritm懦 metodika ir veikimo principai. Atliktos skaitmenin臈s simuliacijos oro tar拧os 拧altiniui aptikti. I拧nagrin臈jus teorinius ir simuliacij懦 aspektus, pateiktos i拧vados apie pasi奴lyt懦 algoritm懦 analiz臋 ir j懦 tarpusavio palyginim膮. Darb膮 sudaro 5 dalys: 寞vadas, literat奴ros analiz臈, metodologija, rezultatai ir literat奴ros s膮ra拧as. Darbo apimtis 鈥� 109 p. teksto be pried懦, 61 iliustracijos, 7 lentel臈s, 58 bibliografiniai 拧altiniai. Atskirai pridedami darbo priedai.

The master's thesis examines automatic control algorithms for unmanned aerial vehicles, evaluating the underlying problems, the necessity of these algorithms, and the objectives for real-time localization of air pollution sources. The fundamental principles guiding drone movement are analyzed. A sensor system featuring an electronic nose was designed, and carbon monoxide sensors were integrated into the drone. Three search algorithms were developed in the thesis: zigzag, pseudo-gradient, and a detection and search algorithm based on the Gaussian dispersion plume model. The methodology and operating principles of these algorithms are described. Numerical simulations were conducted to detect the air pollution source. Based on the analysis of theoretical and simulation aspects, conclusions regarding the performance and comparison of the proposed algorithms are presented. The thesis consists of 5 parts: introduction, literature review, methodology, results, and references. The scope of the thesis is 109 pages of text excluding appendices, 61 illustrations, 7 tables, and 58 bibliographic sources. The appendices of the thesis are attached separately.

Baigiamajame bakalauro darbe orlaiviui 鈥濩essna 310鈥� yra atliekama projektas - modifikacija 寞rengiant oro kondicionieri懦 . Analitin臈je dalyje yra atliekama prototip懦 analiz臈. Pagal atlikt膮 prototip懦 analiz臋 buvo pasirinkta oro kondicionieriaus sistema. 漠rengiant oro kondicionieri懦 buvo atsi啪velgta 寞 l臈ktuvo konstrukcijos pakeitimus, turi b奴ti kuo ma啪esni ir nepaliesti svarbiausi懦 j臈gini懦 liemens, sparno ar uodegos konstrukcijos elementai. Paskai膷iuota orlaivio 鈥濩essna 310鈥� mas臈 ir atlikti centruot臈s skai膷iavimai. Darbe buvo atlikti aerodinaminiai skai膷iavimai. Taip pat atlikti stipruminiai skai膷iavimai oro kondicionieriaus tvirtinimui. Atlikus visus skai膷iavimus buvo parengti br臈啪iniai Darb膮 sudaro 9 dalys: 寞vadas, prototip懦 analiz臈, masi懦 skai膷iavimas, oro kondicionieriaus montavimas, skryd啪io duomen懦 skai膷iavimai, stipruminiai skai膷iavimai, i拧vados, literat奴ros s膮ra拧as. Darbo apimtis 鈥� 79 p. teksto be pried懦, 47 iliustr., 15 lent., 16 bibliografiniai 拧altiniai. Atskirai pridedami darbo priedai.

In the final bachelor's thesis, the Cessna 310 aircraft project of modifications by installing an air conditioner. In the analytical part, the analysis of prototypes is performed. Based on the analysis of the prototypes, the air conditioner system was selected. When installing the air conditioner, the aircraft structures were considered, the elements of the fuselage, wing or tail structure must be as small as possible and the most important forces should not be affected. Calculated mass of Cessna 310 aircraft and performed center calculations. Aerodynamic calculations were performed in the work. Also perform strength calculations for air conditioner mounting. After all the calculations were done, the drawings were prepared The work consists of 9 parts: introduction, prototype analysis, mass calculation, air conditioner installation, flight data calculations, strength calculations, conclusions, bibliography. Thesis consist of: 79 p. text without appendixes, 46 pictures, 15 tables, 16 bibliographical entries. Appendixes included.

Baigiamajame bakalauro darbe suprojektuota aviacin臈 radijo stotis, skirta darbui 118-137 MHz da啪ni懦 ruo啪e, naudojant amplitudin臋 moduliacij膮. Darbo metu i拧analizuoti radijo si懦stuv懦, imtuv懦, da啪nio sintez臈s, FPGA ir aviacini懦 radijo sto膷i懦 sprendimai. Suprojektuota radijo stoties strukt奴rin臈 schema ir elektrin臈s principin臈s schemos. Darbe pateikti skai膷iavimai pagrind啪ia, kad darbo u啪daviniai yra 寞vykdyti: u啪tikrinamas keturi懦 imtuvo kanal懦 veikimas, 50 惟 imtuvo 寞臈jimo impedansas, ne ma啪esnis kaip 3 碌V imtuvo jautris, 25 kHz ir 8,33 kHz kanal懦 啪ingsnio palaikymas, didesn臈 kaip 10 W si懦stuvo i拧臈jimo galia 寞 50 惟 apkrov膮, FPGA architekt奴ra pagr寞stas skaitmeninis signal懦 apdorojimas ir maitinimas i拧 12 V arba 28 V nuolatin臈s 寞tampos 拧altinio. Darb膮 sudaro 5 dalys: 寞vadas, literat奴ros analiz臈, elektrini懦 schem懦 projektavimas, i拧vados, literat奴ros s膮ra拧as. Darbo apimtis - 83 p. teksto be pried懦, 36 iliustr., 4 lent., 62 bibliografiniai 拧altiniai. Atskirai pridedami darbo priedai.

The bachelor thesis presents the design of an aviation radio station operating in the 118-137 MHz frequency range using amplitude modulation. The work includes a literature review of radio transmitters, receivers, frequency synthesis, FPGA-based architectures, and existing aviation radio station solutions. A structural block diagram and electrical schematic diagrams of the radio station have been developed. Calculations are provided to verify that the design objectives are met: four-channel receiver operation, 50 惟 receiver input impedance, receiver sensitivity of at least 3 碌V, support for 25 kHz and 8.33 kHz channel spacing, transmitter output power exceeding 10 W into a 50 惟 load, FPGA-based digital signal processing, and power supply from a 12 V or 28 V DC source. The thesis is structured into five parts: introduction, literature review, electrical schematic design, conclusions, and list of references. The thesis is composed of 83 pages of text (excluding appendices), includes 36 illustrations, 4 tables, and cites 62 bibliographical references. The appendices to the work are attached separately.

Baigiamajame bakalauro darbe projektuojamas ir gaminamas bepilotis skraidan膷io sparno tipo orlaivis. darbe analizuojami analogai, nustatomos aerodinamin臈s charakteristikos, tokios kaip sparno aerodinaminis profilis, sparno plotas , orlaivio smukos greitis, did啪iausias greitis, bei reikalavimai varikliui ir kiti. Taip pat atliekami variklio tvirtinimo element懦 stipruminiai skai膷iavimai. Darb膮 sudaro: analog懦 analiz臈, aerodinaminiai skai膷iavimai, stipruminiai skai膷iavimai, komponent懦 gamyba, i拧vados, literat奴ros s膮ra拧as ir komponent懦 surinkimo bei darbo br臈啪iniai. Darbo apimtis - 52 p. 12 lent., 34 iliustr.

This bachelor's thesis focuses on the design and manufacturing of a flying-wing type unmanned aerial vehicle (UAV). The work includes an analysis of existing analogues and the determination and calculation of key aerodynamic characteristics, such as the aerodynamic profile, wing area, stall speed and engine requirements. Furthermore, a stress analysis of engine mounting components. The thesis consists of an analysis of analogues, aerodynamic calculations, stress analysis, component manufacturing, conclusions, a list of references, assembly and technical drawings. Scope of the thesis: 52 pages, 12 tables, 34 iliustartions.

Baigiamajame bakalauro darbe projektuojama saul臈s energija varomo didelio auk拧膷io ilgai ore i拧liekan膷io bepilo膷io orlaivio j臈gain臈s sistema. Darbe analizuojami pana拧ios paskirties saul臈s energija varom懦 bepilo膷i懦 orlaivi懦 prototipai, j懦 j臈gaini懦, propeleri懦 ir konstrukciniai sprendiniai. Remiantis atlikta analize, parenkami pagrindiniai j臈gain臈s sistemos komponentai ir projektuojama j臈gain臈s gondola su kintamo 啪ingsnio propelerio mechanizmu. Projektavimo metu kompiuterine programa 鈥濻olidWorks鈥� sudaromas j臈gain臈s gondolos 3D modelis, numatomas komponent懦 i拧d臈stymas, variklio tvirtinimo sprendimas ir propelerio men膷i懦 kampo keitimo mechanizmas. Skai膷iuojamojoje dalyje 寞vertinamas j臈gain臈s galios poreikis, gondolos aerodinaminis pasiprie拧inimas, propelerio men膷i懦 kampo poky膷io 寞taka skirtinguose skryd啪io auk拧膷iuose ir tvirtinimo mazgo stiprumas. Darb膮 sudaro 9 dalys: 寞vadas, misija, pagrindiniai teoriniai aspektai, prototip懦 analiz臈, j臈gain臈s sistemos ir kit懦 komponent懦 parinkimas, konstrukcinio sprendinio pagrindimas, skai膷iuojamoji dalis, i拧vados ir literat奴ros s膮ra拧as. Darbo apimtis 鈥� 80 p. teksto be pried懦, 50 paveiksl懦, 20 lenteli懦, 9 bibliografiniai 拧altiniai.

This bachelor鈥檚 thesis presents the design of the propulsion system for a solar-powered high-altitude long-endurance unmanned aerial vehicle. The thesis analyses prototypes of similar solar-powered unmanned aerial vehicles, including their propulsion, propeller, and structural solutions. Based on the analysis, the main propulsion system components are selected, and a powerplant nacelle with a variable-pitch propeller mechanism is designed. During the design process, a 3D model of the powerplant nacelle is created using the SolidWorks computer-aided design software, including the arrangement of components, the motor mounting solution, and the propeller blade pitch adjustment mechanism. In the calculation section, the required power for the propulsion system, the aerodynamic drag of the nacelle, the influence of propeller blade-pitch variation across different flight altitudes, and the strength of the mounting joint are evaluated. The thesis consists of 9 parts: introduction, mission, main theoretical aspects, prototype analysis, selection of the propulsion system and other components, justification of the structural solution, calculation section, conclusions, and references. The thesis consists of 80 pages of text without appendices, 50 figures, 20 tables, and 9 bibliographical sources.

Baigiamajame magistro darbe atliekama 3D spausdint懦 orlaivio pavir拧i懦 aerodinamin臈 analiz臈, daugiausia d臈mesio skiriant FDM technologijai b奴ding懦 pavir拧iaus defekt懦 寞takai oro srauto aptek臈jimui. Ma啪懦 matmen懦 bepilo膷iai orlaiviai da啪nai veikia ma啪懦 Reinoldso skai膷i懦 srityje, tod臈l j懦 aerodinamin臈s charakteristikos yra jautrios pavir拧iaus 拧iurk拧tumui, lokaliems defektams, pasienio sluoksnio virsmui ir srauto atsiskyrimui. Darbe atlikta literat奴ros analiz臈, skaitiniai CFD tyrimai ir empiriniai matavimai v臈jo tunelyje. Tyrimo metu vertinta skersini懦 pavir拧iaus 寞pjov懦, imituojan膷i懦 3D spausdinimo defektus, pad臈ties ir pavir拧iaus 拧iurk拧tumo 寞taka keliamosios j臈gos koeficientui, pasiprie拧inimo koeficientui ir aerodinaminei kokybei. Rezultatai parod臈, kad nagrin臈ti defektai nedaug kei膷ia keliamosios j臈gos koeficient膮, ta膷iau ai拧kiau veikia pasiprie拧inim膮 ir aerodinamin臋 kokyb臋. Did啪iausia 寞taka nustatyta vir拧utinio profilio pavir拧iaus defektams, ypa膷 esantiems priekin臈je profilio dalyje. 漠vertinus pavir拧iaus 拧iurk拧tum膮, lokali懦 寞pjov懦 poveikis suma啪臈jo, nes bendras 拧颈耻谤办拧迟耻尘补蝉 pats veikia kaip paskirstytas pasienio sluoksnio trikdis. Darb膮 sudaro 5 dalys: 寞vadas, literat奴ros analiz臈, metodologija, empirinis ir CFD tyrimai, i拧vados, literat奴ros s膮ra拧as. Darbo apimtis 鈥� 82 p. teksto be pried懦, 66 iliustracijos, 4 lentel臈s, 49 bibliografiniai 拧altiniai. Atskirai pridedami darbo priedai.

This master鈥檚 thesis presents an aerodynamic analysis of 3D-printed aircraft surfaces, focusing on the influence of surface defects characteristic of FDM technology on airflow behaviour. Small unmanned aircraft often operate at low Reynolds numbers; therefore, their aerodynamic characteristics are sensitive to surface roughness, local defects, boundary-layer transition and flow separation. The study includes a literature review, CFD simulations and experimental wind tunnel measurements. Transverse surface grooves, representing typical 3D-printing-related defects, were analysed by evaluating the influence of their position and surface roughness on the lift coefficient, drag coefficient and lift-to-drag ratio. The results showed that the investigated defects had only a limited effect on the lift coefficient, but a more noticeable influence on drag and aerodynamic efficiency. The strongest effect was observed for defects located on the upper surface of the airfoil, especially near the leading-edge region. When surface roughness was included, the influence of local grooves decreased because the overall roughness acted as a distributed boundary-layer disturbance. The thesis consists of 5 parts: introduction, literature review, methodology, experimental and CFD studies, conclusions, and references. The thesis comprises 82 pages of text excluding appendices, 66 figures, 4 tables and 49 references. Appendices are provided separately.

Baigiamajame bakalauro darbe projektuojamas stratosferinio daugiafunkcinio bepilo膷io orlaivio modulinis naudingojo krovinio skyrius, pritaikytas skirting懦 tip懦 optini懦 jutikli懦 integracijai. Literat奴ros analiz臈je nagrin臈jami saul臈s energija varom懦 HAPS tipo bepilo膷i懦 orlaivi懦 konstrukciniai sprendimai, naudingojo krovinio integravimo principai bei esami analogi拧ki prototipai. Atlikta prototip懦 analiz臈 ir 寞vertinti da啪niausiai naudojami naudingojo krovinio skyriai bei j懦 konstrukciniai ypatumai. Darbe atliktas RGB, infraraudon懦j懦 spinduli懦, multispektrini懦, 寞stri啪inio objektyvo ir gimbal kamer懦 parinkimas pagal j懦 mas臋, energijos s膮naudas, integravimo galimybes ir tinkamum膮 stratosferiniam bepilo膷iam orlaiviui. Remiantis atlikta analize, suprojektuotas modulinis naudingojo krovinio skyrius su kei膷iamais kamer懦 moduliais bei i拧skleid啪iamu mechanizmu 鈥濻IYI A8 Mini鈥� gimbal kamerai. 漠vertinta skirting懦 kamer懦 寞taka orlaivio skryd啪io trukmei, energijos s膮naudoms ir aerodinaminiam pasiprie拧inimui. Atlikti naudingojo krovinio skyriaus tvirtinimo element懦 bei kameros laikikli懦 stipruminiai skai膷iavimai. Baigiamojo darbo pabaigoje pateikti suprojektuoto naudingojo krovinio skyriaus konstrukciniai sprendimai, br臈啪iniai, atlikt懦 skai膷iavim懦 rezultatai ir suformuluotos i拧vados. Darb膮 sudaro 寞vadas, analog懦 analiz臈, kamer懦 parinkimas, konstrukcinio sprendinio pagrindimas, skai膷iavimai, i拧vados, literat奴ros s膮ra拧as ir priedai. Darbo apimtis 鈥� 63 puslapiai, 44 paveikslai, 8 lentel臈s ir 33 literat奴ros 拧altiniai.

The final bachelor thesis presents the design of a modular payload bay for a stratospheric multifunctional unmanned aerial vehicle, adapted for the integration of various optical sensors. The literature review analyzes the structural solutions of solar-powered HAPS-type unmanned aerial vehicles, payload integration principles, and existing analogous prototypes. A prototype analysis was carried out, and the most commonly used payload bay solutions and their structural characteristics were evaluated. The thesis includes the selection of RGB, infrared, multispectral, oblique, and gimbal cameras according to their mass, power consumption, integration capabilities, and suitability for a stratospheric unmanned aerial vehicle. Based on the performed analysis, a modular payload bay with interchangeable camera modules and a deployable mechanism for the 鈥淪IYI A8 Mini鈥� gimbal camera was designed. The influence of different cameras on flight endurance, energy consumption, and aerodynamic drag was evaluated. Strength calculations of the payload bay mounting elements and camera brackets were also performed. At the end of the thesis, the structural solutions of the designed payload bay, engineering drawings, calculation results, and final conclusions are presented. The thesis consists of an introduction, analysis of analogous systems, camera selection, justification of the structural solution, calculations, conclusions, references, and appendices. The thesis contains 63 pages, 44 figures, 8 tables, and 33 references.

Baigiamajame bakalauro darbe projektuojamas modulin臈s bepilot臈s platformos, skirtos 寞vairi懦 tip懦 dron懦 per臈mimui, naudingojo krovinio skyrius. Darbe atliekama prototip懦 ir analog懦 analiz臈, parenkami skyriaus matmenys, med啪iagos, tvirtinimo sprendiniai. Sprend啪iami krovinio talpinimo, fiksavimo, i拧metimo, dureli懦 valdymo mechanizacijos ir skyriaus sandarumo u啪daviniai. Atliekami stipruminiai skai膷iavimai, patikrinant potencialiai kritinius konstrukcijos elementus ir apkrovas, apskai膷iuojamos stiprumo atsargos, lyginant su leistinaisiais 寞tempiais pagal NATO AEP-83 standart膮. 聽Suprojektuotas modulin臈s bepilot臈s platformos naudingojo krovinio skyrius, galintis talpinti iki 20 kg krovin寞 30 litr懦 t奴rio ribose, su galimybe gabenti dronus per臈m臈jus ir juos i拧leisti skryd啪io metu. Krovinys patalpinamas per apatines dureles i拧 apa膷ios, i拧metamas atidarius tas pa膷ias dureles. Servo mechanizm懦 ir lankst懦 duomenys yra tinkami saugiam ir patikimam krovinio skyriaus dureli懦 veikimui. Darb膮 sudaro 5 dalys: prototip懦 ir analog懦 analiz臈, konstrukcinio sprendinio pagrindimas, skai膷iuojamoji dalis, i拧vados ir si奴lymai, literat奴ros s膮ra拧as. Darbo apimtis 鈥� 47 p. teksto be pried懦, 30 iliustr., 8 lent., 28 bibliografini懦 拧altini懦. Atskirai pridedami darbo priedai.

This bachelor's thesis presents the design of a payload compartment for a modular unmanned aerial platform intended for the interception of various types of drones. The work includes an analysis of prototypes and analogues, selection of compartment dimensions, materials, and fastening solutions. The tasks of payload accommodation, fixation, release, door actuation mechanism design, and compartment sealing are addressed. Structural strength calculations are performed to verify potentially critical structural elements and loads, with safety margins calculated and compared against allowable stresses in accordance with the NATO AEP-83 standard. A payload compartment for a modular unmanned aerial platform has been designed, capable of carrying up to 20 kg of payload within a 30-litre volume, with the ability to transport interceptor drones and release them during flight. The payload is loaded through the bottom doors and released by opening the same doors in flight. The servo actuator and hinge mechanism parameters are suitable for safe and reliable operation of the payload compartment doors. The thesis consists of 5 parts: analysis of prototypes and analogues, justification of the structural solution, structural calculations, conclusions and recommendations, and a list of references. The volume of the thesis is 47 pages of text excluding appendices, 30 illustrations, 8 tables, 28 bibliographic sources. Appendices are attached separately.