Turbojet engine is selected as propulsion system according to the practical situation . the work of this part ranges from design to characteristic analysis . the characteristic curves of engine in various situation are shown , which provides preparation for trajectory computation 并對渦噴發(fā)動機(jī)從設(shè)計到特性分析做了大量的工作,給出發(fā)動機(jī)在不同工作狀態(tài)下的特性曲線,為進(jìn)一步研究彈道設(shè)計提供了前期的準(zhǔn)備工作。
Design of two propulsion systems is studied - solid rocket ramjet and liquid ramjet . the performance analysis models and design methods are set up for these two kinds of engines . the different characteristics are analyzed and compared , which provide basis for farther trajectory computation and conceptual optimization design ( 4 )研究了兩種動力裝置? ?固體火箭沖壓發(fā)動機(jī)和液體燃料沖壓發(fā)動機(jī)的設(shè)計問題,建立了兩種發(fā)動機(jī)的性能分析模型和計算方法,對固體火箭沖壓發(fā)動機(jī)和液體燃料沖壓發(fā)動機(jī)的特性進(jìn)行計算分析及比較,為彈道計算及總體優(yōu)化設(shè)計提供依據(jù)。