迄今为止,导弹发动机的选择在大部分情况下遵循一种简单的考虑:短航程——固体燃料火箭发动机;远航程——涡轮喷气发动机。对于水平飞行的导弹,区别上述两种发动机的应用范围的航程边界,一般定为40公里。未来的导弹设计方案,针对性能最佳和价格的条件,要求更详尽的考虑。因为在不远的将来,会有大量不同类型的导弹发动机可供选用。本文以舰舰导弹为例,研究现有的以及未来的动力装置系统,对导弹的发射质量和要求推力的影响。在进行研究时,有效负载是给定的,而飞行马赫数和航程当作变量。借助于一些简单假设,有可能估定导弹、动力装置和助推火箭的价格。以这些结果为基础并兼顾到导弹维护、贮存和使用的费用,对所研究的发动机作出最后的评价。 To date, the choice of missile engine follows a simple consideration in most cases: short range - solid fuel rocket engine; long range - turbojet engine. For horizontal flight missiles, the range of the voyage, which distinguishes the application of the above two engines, is generally set at 40 km. Future missile design solutions, for the best performance and price conditions, require more detailed consideration. Because in the near future there will be a large number of different types of missile engines to choose from. Taking ship-to-ship missiles as an example, this paper studies existing and future power plant systems on the launch quality and required thrust of the missile. The payload is given while studying, and the flight Mach number and range are used as variables. With some simple assumptions, it is possible to estimate the prices of missiles, power units and booster rockets. Based on these results and taking into account the cost of missile maintenance, storage and use, the final assessment of the engine under study was made.