摘要
根据SP-ATR目前存在的燃气难以兼顾清洁和富燃的问题,文章提出将原本由1股燃气单独承担驱动涡轮和补燃功能的工作模式分解为由2股燃气分别担负驱涡和补燃功能的工作模式。通过对比分析该工作模式的SP-ATR和固冲发动机、涡喷发动机工作特点,提出了适合该形式SP-ATR的性能计算模型,得到其飞行包线,发现该SP-ATR工作包线宽广,可完全包含涡喷和固冲发动机的工作包线。在此基础上,计算得到了SP-ATR在不同空域和速度条件下的飞行性能及变化规律:(1)随飞行高度和速度的增加,其比冲、比推力增加,但性能随外弹道变化幅度较小,整个工作范围性能稳定;(2)在近地面和低空SP-ATR均可实现低空亚音速盘旋和5 km高度以上的超音速飞行,且在比冲高于6 700 N.s/kg,同时保持比推力大于1 100 N.s/kg;(3)高空SP-ATR工作高度速度范围宽,比冲性能与冲压发动机相当,比推力为冲压发动机的2倍,相同飞行速度条件下飞行高度增加比冲增加、比推力增加,具有在更高高度巡航潜力,高空性能优势明显。
Based on the current problems on SP-ATR, a new SP-ATR was proposed, in which afterburner rich fuel gas was add- ed separately. A new model used for the new SP-ATR was presented through comparing the SP-ATR with the Ramjet and the Aero- jet. By the model,the flight envelope of the SP-ATR was calculated, and the Ramjet and Aerojet＇s envelope was completely con- tained by the SP-ATR~, which means taht the SP-ATR has a wide working range. Then SP-ATR~ performance were calculated in different heights and velocities. The results are as follows：firstly ,with the increase of height and velocity, the SP-ATR~ specific im- pulse and specific thrust increase, but its performance changs slightly with the changes in external ballistics, which means that the SP-ATR performance is stable. Secondly,in the height range of near-ground and low-level, SP-ATR could fulfill the request that its velocity could change from subsonic to supersonic and keep its specific impulse no less than 6 700 N · s/kg and specific thrust no less than 1 100 N ~ s/kg. Thirdly, in the high altitude, SP-ATR~ working range is wide. Compared with the Ramjet,its specific im- pulse is the same as the Ramjet＇s and its specific thrust is as twice as the RamjetS. Additionally,under the same flight velocity,its thrust increases with the increase of height,which means that SP-ATR has the ability to work in the higher altitude.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2013年第1期17-21,共5页
Journal of Solid Rocket Technology
作者简介
作者简介：刘诗昌（1983-），男，博士生，研究领域为航空宇航推进理论与工程。E-mail：liushichang1983212@163.com.
