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根据飞行任务要求,准确计算出飞行器所需的燃料消耗是推进系统设计的前提。该文针对火箭基组合循环动力(RBCC)推进方式,并以“地面起飞—巡航—滑翔着陆”的高超音速飞行器为研究对象,采用理论分析的方法建立了燃料消耗的计算模型,并提出一种以最小燃料消耗为目标的多参数优化方法。周期跳跃式巡航飞行器燃料消耗的研究结果表明:随着巡航初速度、爬升段航迹倾角、巡航轨迹角的增加,燃料消耗量增加;随着飞行动压的增加,燃料消耗量先减小后阶跃式增加。优化分析结果表明:对于起飞质量100t、2h全球到达的RBCC组合动力高超音速飞行器,在升阻比为4时巡航跳跃周期数为46,最小燃料消耗量约为32t。研究结果表明该燃料消耗分析方法合理、可行,为高超音速飞行器及组合循环动力推进系统的工程设计提供了依据。
According to the requirements of the mission, accurate calculation of the required fuel consumption of the aircraft is a prerequisite for advancing the system design. In this paper, based on the rocket-based combined cycle power (RBCC) propulsion method, and taking the “ground takeoff-cruise-glide landing” hypersonic vehicle as the research object, a theoretical model of fuel consumption calculation is established and put forward A Multi-Parameter Optimization Method with Minimum Fuel Consumption as Target. The results show that the fuel consumption increases with the initial cruise speed, the track inclination of the climbing section and the cruising track angle. With the increase of the dynamic pressure of the flight, the fuel consumption first decreases Step by step increase. The results of optimization analysis show that for a RBAC combined hypersonic vehicle reaching 100t and 2h globally, the number of cruise jumps is 46 and the minimum fuel consumption is about 32t at a lift-drag ratio of 4. The results show that the fuel consumption analysis method is reasonable and feasible, which provides the basis for the engineering design of hypersonic vehicle and combined cycle power propulsion system.