某型靶标液体火箭动力参数优化
柳长安,李宏君,吴书山

(西安航天动力研究所,陕西 西安 710100)

靶标; 大机动; 工作包线; 优化

Parameter optimization of a liquid rocket propulsion system for a target drone
LIU Changan,LI Hongjun,WU Shushan

(Xi'an Aerospace Propultion Institute,Xi'an 710100,China)

target drone; high maneuvering; operating envelope; optimization

备注

随着高速大机动航空技术的发展,为武器鉴定及日常训练提供目标特性的靶标也应具备高速大机动能力。但是高速大机动能力就要求动力系统不仅在高速和大过载飞行工况下具有较大推力,而且应具有较大变推范围以适应靶标较宽的飞行包线。由于国内航发动力目前性能较低而无法满足该类型靶标需求,因此采用火箭动力就成为一种选择。已有采用火箭动力系统的飞行器大多采用推力室变推技术结合多推力室方案来实现大范围变推,但是这无疑就增加了设计参数和设计维度,导致设计分析工作会大大增加。针对这一要求,结合某型靶标的动力系统设计要求进行了动力系统设计参数分析,确定采用最小比冲及包线范围内主要工况点推力偏差的范数来进行设计方案的优劣对比,并借助粒子群优化算法进行了设计方案的优化选择,从而得到了较好的动力系统设计方案及参数。

With the development of the aero-weapon with high speed and high maneuvering,the target drones which were used for weapon authentication and daily training must also have the ability of high speed and high maneuvering.However, this requires the propulsion system should have not only big thrust at high speed and high maneuvering, but also large thrust variable range, in order to meet the requiement of wide flight envelope of the target drone.As now the domestic aeroengines are of low performance and can't satisfy what a target drone needs, so liquid rocket engine is an alternative choice.Most flight vehicles using rocket engines applied variable thruster combined with multi-thrusters to achieve large range thrust changing, which result in more designing parameters and more designing dimensions, thus leads to more design and analysis efforts.According to this question, design parameter analysis of a propulsion system was carried out here according to propulsion system designing demands from a target drone, in which the variables are optimized using the multi-objective particle swarm optimization method(MOPSO), and the design objectives are settled as the engine specific impulse and the thrust deviations.Through the optimization,some optimal design parameters are reached,which can help designers understand their design project and make decisions better.