典型贫氧推进剂固体火箭冲压发动机性能

建立了基于热力计算的固体火箭冲压发动机性能计算模型,针对三类典型贫氧推进剂开展了固体火箭冲压发动机性能分析及变化规律研究。研究结果表明：相同高度和来流马赫数下,随着余气系数的增加,进气道裕度增加,推力系数减小,比冲先增加后减小。相同高度和余气系数下,随着来流马赫数的增加,进气道裕度增加,推力系数减小,比冲减小。相同来流马赫数和余气系数下,进气道裕度、推力系数、比冲随高度的变化不明显。空气总温对特征速度及发动机性能有较明显影响,是性能分析时不可忽略的因素。与碳氢贫氧推进剂、铝镁贫氧推进剂相比,含硼贫氧推进剂当量空燃比适中,比冲较高,推进剂密度大,在工程应用上更具优势。

Performance of ducted rocket with typical fuel rich propellant

Performance prediction model of ducted rocket was developed based on thermodynamic calculation. Research on performance characteristics of ducted rocket with three kinds of fuel rich propellants was conducted. The study shows that under the same height and Mach number, as excess air coefficient increases, inlet stability margin increases and thrust coefficient decreases, while specific impulse increases first and then decreases. Under the same height and excess air coefficient, as incoming Mach number increases, the inlet stability margin increases, while thrust coefficient and specific impulse decrease. Under the same incoming Mach number and excess air coefficient, the changes of inlet stability margin, thrust coefficient, and specific impulse caused by height variation are not obvious. The variations of characteristic velocity and ducted rocket performances are obvious with the increasing of air total temperature, which should not be neglected in performance analysis. Compared with hydrocarbon fuel rich propellant and aluminum magnesium fuel rich propellant, boron based fuel rich propellant has moderate equivalent air-fuel ratio, higher specific impulse, and higher density, which revealings advantages in engineering application.