先进火力支援系统/SPATR发动机一体化设计——约束分析与任务分析  

Integrated design of advanced fire support system and SPATR——constrain analysis and mission analysis

作　　者：陈湘[1] 蔡元虎[1] 黄兴鲁[1] 陈玉春[1] 屠秋野[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《固体火箭技术》2011年第3期269-272,289,共5页Journal of Solid Rocket Technology

摘　　要：通过导弹/发动机一体化设计的计算,验证了SPATR发动机在先进火力支援系统(AFSS—Advanced Fire SupportSystem)中的可用性。利用飞航导弹/涡扇发动机一体化设计思路,建立了AFSS/SPATR发动机一体化设计的约束分析和任务分析模型,并给出了算例和分析。简述了AFSS任务剖面和约束条件的给定、导弹的质量组成及SPATR发动机模型。对AFSS的约束分析和任务分析计算结果表明,建立的AFSS/SPATR发动机一体化约束分析与任务分析模型合理可行;采用SPATR的AFSS具有超音速飞行能力(H=3～5 km,Ma=1.8),比采用固体火箭发动机的导弹航程更远,并具有盘旋待机能力。By integrated design calculating of missile and engine,the usability of SPATR（Solid Propellant Air-Turbo-Rocket） in AFSS（Advanced Fire Support System） is validated.Referring to the integrated design method of cruise missile and turbofan engine,a model of AFSS and SPATR integrated constrain analysis and mission analysis was developed,and the competitive examples and analysis were given.The mission profile and constrain conditions given,weight distribution of the AFSS and the model of SPATR were presented.The constrain-analyzed results and the mission-analyzed results of AFSS indicate that the model of AFSS and SPATR integrated constrain analysis and mission analysis is feasible and available.The AFSS missiles with SPATR had supersonic flight capacity（H=3~5 km,Ma=1.8）,hovering capacity and a further missile flight range than the missiles with solid rocket engine.

关 键 词：先进火力支援系统(AFSS) 固体推进剂空气涡轮火箭发动机(SPATR) 一体化设计 约束分析 任务分析 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]