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出 处:《固体火箭技术》2013年第4期491-495,共5页Journal of Solid Rocket Technology
摘 要:涡轮增压固冲发动机(TSPR)将ATR的燃气涡轮增压部件和固冲发动机高能推进剂有机组合,实现了高比冲宽包线的性能要求。建立了TSPR非设计点性能模型,提出了TSPR2种调节方案,即等余气系数和等富燃流量。通过热力循环相似的ATR试验结果,校核了本性能分析模型的准确性。研究TSPR2种调节方案的推力调节特性。2种调节方案的假想TSPR不同转速比冲均高于与设计推力比推力与其相等的ATR,等富燃流量调节方案的TSPR调节简单,推力调节范围大,性能更接近ATR。物理转速不变的假想TSPR可工作的速度、高度范围分别为Ma=0—2.4、0~16km,发动机高空高速比冲最高。等富燃流量调节方案TSPR的性能略低于等余气系数,但相比等余气系数,其控制规律简单,实现方便,是更实用的控制方案。In order to obtain propulsion systems with a high specific impulse and wide operating envelope, the turbocharged sol- id propellant ramjet (TSPR) propulsion system was proposed by integrating the turbocharged system of solid propellant air turbo rocket (ATR) and fuel rich gas generator of solid propellant ramjet (SPR). The off-design code was established for TSPR. Two control plans were proposed: constant air residual fraction of combustor, constant mass flow rate of fuel rich gas. The off-design code was validated by the test results of ATR which is similar to TSPR. Regulation characteristics of TSPR with these two control plans were studied. The specific impulse of designed TSPR for the two kinds the control plans are higher than ATR which has same design thrust and specific thrust of designed TSPR. TSPR with constant fuel-rich gas flow rate has larger thrust adjustment range than with constant air residual fraction, and the regulation characteristics is closer to ATR. Designed TSPR can operate within 0 2.4 Ma, 0 - 16 km with constant physical engine speed. TSPR has maximum thrust in low altitude and has the maximum specific impulse in high altitude. The performance of TSPR with constant fuel rich gas flow rate is slightly lower than constant air residual fraction plan, but regulation is simple and easy to achieve, so constant fuel rich gas flow rate plan is more practical for TSPR.
关 键 词:燃气涡轮增压 非设计点 性能分析模型 燃气涡轮增压固冲发动机
分 类 号:V435[航空宇航科学与技术—航空宇航推进理论与工程]
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