超声速进气道起动特性研究
本文关键词:超声速进气道起动特性研究 出处:《航天动力技术研究院》2016年硕士论文 论文类型:学位论文
更多相关文章: 超声速进气道 起动性能 进气道堵盖 出口反压 固体火箭冲压发动机
【摘要】:固体火箭冲压发动机具有比冲高、工作时间长、结构简单、机动性强等优点,是先进导弹动力系统的重要发展方向之一。超声速进气道作为冲压发动机的核心部件之一,其起动性能决定了发动机的工作包络。因此,确定超声速进气道的起动特性至关重要。地面仿真和飞行试验中多次证实,发动机转级装置——进气道堵盖对起动性能影响显著。某次飞行试验中,由于转级时进气道不起动,造成飞行失败。可见,确定进气道起动特性和堵盖影响机制已成为冲压发动机技术发展和工程应用中亟需解决的关键问题。本文基于工程实际需求,针对典型冲压发动机的双下侧二元混压式进气道起动特性,开展了数值仿真研究。本文首先建立了弹体/进气道一体化三维仿真模型,研究了双下侧二元进气道在转级工况下起动状态的流场特性。结果表明:随反压增加,结尾激波系逐渐向上游移动,到达喉道后,继续增大反压,在一定范围内,结尾激波系可以稳定在收缩通道内,即存在稳定的亚临界状态。然后,本文研究了Ma=2.5~3.5、α=-2o~8o、β=0o~6o工况下进气道的流场特性和抗反压性能,拟合了极限反压比预估公式。结果表明:进气道极限反压与来流总压、喉道总压恢复系数和流量系数相关;随来流马赫数增大,自由流总压和流量系数均提高,喉道总压恢复系数降低,综合影响下,进气道抗反压能力增强;随攻角增大,总压恢复系数和流量系数均提高,进气道极限反压升高;在侧滑情况下,背风侧进气道性能参数和抗反压能力均优于迎风侧进气道;随侧滑角增大,两侧性能参数变化趋势不同,背风侧进气道总压恢复系数、流量系数先升高后降低,迎风侧持续降低;当迎风侧不起动后,迎风侧脱体激波会干扰背风侧的外压缩波系,甚至可能使背风侧也不起动。其次,本文仿真分析了不同工况下进气道的不起动/再起动过程。分析结果表明:进气道入口前气流总压是决定进气道再起动反压的主要因素;来流马赫数越大,气流总压越高,再起动反压越高;攻角越大,弹体干扰越弱,入口前气流总压越高,再起动反压越高,α≥2o后弹体干扰极弱,再起动反压不再随攻角增大而变化;在侧滑情况下,两侧进气道再起动不同步;背风侧进气道受弹体干扰小,再起动反压基本不随侧滑角变化;对于迎风侧进气道,当侧滑角β≤2o时,弹体干扰较弱,再起动反压接近背风侧,当侧滑角β≥4o时,随侧滑角增大,弹体干扰增强,再起动反压降低,明显滞后于背风侧。最后,本文重点研究了固体火箭冲压发动机转级装置——进气道堵盖对进气道起动特性的影响。根据不同转级时序,分别对入口堵盖和出口堵盖开启过程进行非稳态流场仿真。结果表明:入口堵盖有利于进气道起动,可使进气道起动马赫数从Ma=2.31降到Ma=2.29;在入口开启,出口封堵时,进气道流场出现周期性振荡,频率与一阶声模态一致,进气道越下游位置压力峰值越高;出口堵盖开启时刻对进气道起动性能有较大影响,充填阶段开启更有利于进气道起动;在释放阶段开启,进气道会出现短时间的低频、大幅喘振。
[Abstract]:Solid rocket ramjet engine has high specific impulse, long working time, simple structure, flexibility, is one of the important development direction of advanced missile power system. As one of the core components of supersonic inlet of ramjet engine, its starting performance determines the working envelope of engine. Therefore, it is of great importance to determine the starting characteristics of supersonic inlet. Repeatedly confirmed ground simulation and flight test, engine level switching device, inlet blocking effect on the cover was starting performance. One of the flight tests, due to the unstart transfer, causing flight failure. Obviously, determine the inlet starting characteristics and cover influence mechanism has become a key issue in the urgent need for the development of ramjet technology and engineering the application in solution. In this paper, based on the demand of engineering, aiming at the typical double downside ramjet inlet two yuan starting characteristics And carry out numerical simulation. This paper established a three-dimensional simulation model of missile / engine integration, flow characteristics of the double side two yuan in transfer under the condition of inlet starting. The results show that with increasing back pressure at the end of the shock wave system gradually moves upstream to the throat, continue to increase the back pressure in the within a certain range, at the end of shock wave can stabilize the contraction in the channel, there is a stable subcritical state. Then, this paper studies the Ma=2.5~3.5, alpha =-2o~8o, beta =0o~6o under the condition of flow characteristics of the inlet and the anti pressure performance, fitting the limit back pressure ratio prediction formula. The results show that the inlet pressure and flow limit total pressure, total pressure recovery coefficient and flow coefficient of throat; with the Mach number increases, the free flow total pressure and flow coefficient were increased, the total pressure recovery coefficient decreased throat, under the combined effects of inlet of the anti pressure ability enhancement Strong; with the angle of attack increases, the total pressure recovery coefficient and flow coefficient were increased, the inlet pressure in the limit of anti sideslip; under the condition of the leeward side of the inlet performance parameters and anti pressure ability are better than the windward side inlet; with the increase of sideslip angle, different change trend on both sides of the performance parameters, the total pressure recovery coefficient of the inlet flow on the leeward side. The coefficient increased first and then decreased, the windward side continues to decrease; when the windward side does not start after the windward leeward side will interfere with the detached shock compression wave, even to the leeward side is not starting. Secondly, this paper analyzed the unstart / restart process under different conditions. The analysis results show that the inlet port in front of the entrance flow total pressure is decided to start the main factors of back pressure inlet; flow Maher number increases, the total air pressure is higher, then starting back pressure is high; the bigger the attack angle, body interference is weak in front of the entrance of air pressure The higher, then starting back pressure higher than 2O, alpha after body interference is very weak, and then starting back pressure is no longer with the angle of attack increases and changes in sideslip; under the condition of side inlet restarting is not synchronized; the leeward side inlet by projectile interference, then starting pressure almost does not change with the sideslip angle on the windward side; when the inlet, the sideslip angle beta = 2O, body interference is weak, then starting back pressure close to the leeward side, when the sideslip angle beta is greater than or equal to 4O, with the increase of the sideslip angle, body interference enhancement, then starting back pressure decreased, obvious lag in the leeward side. Finally, this paper focuses on the research of solid rocket ramjet transfer device inlet cover effect on inlet starting characteristics. According to different level timing of entrance closure and export cover opening process of unsteady flow simulation. The results show that the entrance cover for inlet starting, the inlet starting from the Maher number Ma=2.31 reduced to Ma=2.29; in the open entrance, exit plugging, inlet flow periodic oscillation frequency and first order acoustic mode, the inlet position downstream of the peak pressure is high; export cover opening time has great influence on the performance of inlet starting, the filling stage of opening more conducive to open the inlet starting in the release phase of low frequency; there will be a short period of time, the inlet surge sharply.
【学位授予单位】:航天动力技术研究院
【学位级别】:硕士
【学位授予年份】:2016
【分类号】:V211.48
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