| Abstract: | The problem of designing the optimal nozzle of a hypersonic ramjet engine for a given isoperimetric condition imposed on the moment and restricted overall dimensions is solved by the method of an indefinite control contour. The lift of the flight vehicle is treated as the optimized functional. It is shown that an increase in the moment due to the replacement of thrust optimization by lift optimization is efficiently compensated by taking the moment constraint into account. Moscow. Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No. 1, pp. 118–124, January–February, 1999. |
