空射航天系统参数的技术经济论证

Pub Date : 2023-04-28 DOI:10.15407/knit2023.02.003
D. Kalynychenko, T. Mańko, V. Pavlenko, T. Pavlenko
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引用次数: 0

摘要

给出了由可重复使用的无人机和综合运载火箭组成的空射航天系统的技术经济参数论证。无人驾驶飞行器的推进系统采用涡扇发动机和冲压发动机的组合。所考虑的运载工具能够在不使用太空港的情况下将有效载荷送入低地球轨道。研究了空射航天系统参数的技术经济论证方法。通过寻找目标函数的最小值得到结果,建立了航天系统技术经济参数之间的关系。对于目标函数解,确定了集成运载火箭和无人机的设计参数,以及航天系统的总加速度速度限制。所使用的方法使我们能够确定由涡轮风扇发动机、冲压发动机和集成运载火箭级的三个固体推进剂发动机运行提供的速度约束,以及无人机表面的最大动压力和最大允许温度。确定了利用空中发射航天系统发射航天器进入地球轨道的成本估算方案。验证的结果是确定了综合运载火箭、无人机和整个航天系统的技术经济参数。分析了无人机表面最高温度和冲压发动机比冲对航天系统参数的影响。这是建立乌克兰航空航天空中发射系统的第一步。
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TECHNICAL AND ECONOMIC SUBSTANTIATION OF THE AIR LAUNCH AEROSPACE SYSTEM PARAMETERS
The substantiation of the technical and economic parameters of the air launch aerospace system, which consists of a reusable unmanned aerial vehicle and integrated launch vehicle, is given. A combination of a turbofan engine and a ramjet engine is used as the unmanned aerial vehicle propulsion system. The considered vehicle is capable of delivering a payload into low-Earth orbits without the use of a spaceport. We have developed the methodology of the technical and economic substantiation of the parameters of the air launch aerospace system. The results were obtained by searching for the minimum of the objective function, which established the relationship between the technical and economic parameters of the aerospace system. For the objective function solution, the design parameters of the integrated launch vehicle and unmanned aerial vehicle were determined, as well as the limitation of the total acceleration velocity of the aerospace system. The methods used allowed us to determine the velocity constraints provided by the operation of the turbofan engine, ramjet engine, and the three solid propellant motors of integrated launch vehicle stages, as well as maximum dynamic pressure and maximum permissible temperature on the unmanned aerial vehicle surface. We determined the scheme for estimating the cost of launching the spacecraft into Earth orbit by the air launch aerospace system. The result of the substantiation is the determination of the technical and economic parameters of the integrated launch vehicle, unmanned aerial vehicle, and the aerospace system as a whole. The influence of the maximum temperature on the surface of the unmanned aerial vehicle and the specific impulse of the ramjet engine on the parameters of the aerospace system was also evaluated. The substantiation is the first step towards the creation of the Ukrainian aerospace air launch system.
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