Автоматизація розрахунку енерго-балістичної траєкторії польоту літального апарата
| dc.contributor.author | Хомин, Т. В. | |
| dc.contributor.author | Кривохатько, І. С. | |
| dc.date.accessioned | 2023-04-27T07:22:20Z | |
| dc.date.available | 2023-04-27T07:22:20Z | |
| dc.date.issued | 2019 | |
| dc.description.abstractother | The use of modern digital computing technology allows you to calculate a large amount of information quickly and with the required accuracy. Therefore, in today practice of ballistic calculations, numerical simulation of aircraft motion, which reflects real flight with certain tolerances, is actively used. The mathematical dependencies that describe the motion of the aircraft are nonlinear systems of differential equations. As it is known, in general case it is impossible to find solutions to such equations in simple functions. Therefore, to solve this problem numerical integration of differential equations by the Runge - Kutta method was used. The advantage of the method in C # implementing is the wide ability to change the initial conditions, aircraft parameters, flight conditions, clear display of calculations results, speed of calculations, which is very important for design problems solving. Two solid fuel adjustable missiles which are identical in design and differ only in the presence of a block of pulsed engines were designed for the research. The article presents simplifications accepted for this calculation, differential equations system, aerodynamic and mass - dimensional characteristics of both missiles, the flight paths of the products in the main window of the implemented program, additional trajectory characteristics in the form of graphs and comparison of the flight ranges of both missiles. Thus, by calculating the flight trajectory we obtained the following increase in range from a block of pulsed engines: for the initial start angles 35 – 22.4%, 40 – 18.2%, 45 – 14.3%, 52 – 8.2%. | uk |
| dc.format.pagerange | С. 30-41 | uk |
| dc.identifier.citation | Хомин, Т. В. Автоматизація розрахунку енерго-балістичної траєкторії польоту літального апарата / Т. В. Хомин, І. С. Кривохатько // Механіка гіроскопічних систем : науково-технічний збірник. – 2019. – Вип. 38. – С. 30-41. – Бібліогр.: 3 назв. | uk |
| dc.identifier.doi | http://dx.doi.org/10.20535/0203-3771382019202953 | |
| dc.identifier.uri | https://ela.kpi.ua/handle/123456789/54998 | |
| dc.language.iso | uk | uk |
| dc.publisher | КПІ ім. Ігоря Сікорського | uk |
| dc.publisher.place | Київ | uk |
| dc.relation.ispartof | Механіка гіроскопічних систем: науково-технічний збірник, Вип. 38 | uk |
| dc.subject.udc | 519.688 | uk |
| dc.title | Автоматизація розрахунку енерго-балістичної траєкторії польоту літального апарата | uk |
| dc.type | Article | uk |
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