该塞式喷管基本上体现了塞式喷管的优点。
This type of plug nozzle embodies the main advantages of plug nozzles.
结果表明，内喷管喉径是影响环簇式塞式喷管尺寸大小的最主要设计参数；
The results show that throat diameter of the inner nozzle is the most important design parameter influencing structure size of the annular clustered plug nozzle.
为了了解塞式喷管性能，采用固体推进剂对塞式喷管单元发动机进行了模拟实验。
To find out the performance characteristic of aerospike nozzle, the simulated tests were a aerospike engine unit using solid propellant.
从NS方程出发，采用二阶精度的NND格式对塞式喷管的流场进行了数值模拟。
The numerical simulations of the flow field around and aerospike nozzle cell were completed base on N S equations with Second order NND scheme.
基于实验数据和数值模拟结果，研究了外界反压和底部二次流对塞式喷管底部的影响。
Based on experimental data and numerical simulation results, effects of ambient pressure and base bleed on aerospike nozzle base behaviour are investigated.
重点介绍了塞式喷管单元发动机模拟实验的实验系统和高精度测量系统以及数据采集软件。
The experimental system and data acquisition system for simulated tests of an aerospike nozzle unit including the software of the data acquisition were presented in detail.
给出了典型的试验曲线，并分析了“瓦”状塞式喷管的高度特性和底部二次流对性能的影响情况。
The typical experimental curves are showed. The altitude characteristic and the effect of base bleed on aerospike nozzles are analyzed too.
采用气氧作氧化剂、气氢作燃料，对具有高度补偿特性的塞式喷管和双钟型喷管进行了点火热试。
By employing the gaseous oxygen as oxidizer and gaseous hydrogen as fuel, hot-firing tests were performed for aerospike nozzle and dual-bell nozzle test engines with altitude compensating features.
在单元数足够多时，环簇式塞式喷管可比相同面积比的钟形喷管的尺寸更小，重量更轻，推力效率更高；
When numbers of the inner nozzle are enough, plug nozzle has less size, less weight and higher thrust efficiency than the bell nozzle under same area ratio.
不同压强比下全锥塞式喷管的塞锥表面压强分布规律，可以作为研究截短型塞式喷管塞锥压强分布的基础。
The plug surface pressure profiles for the full-length plug nozzle at different NPR can provide valuable data for researching the truncated plug nozzle.
为了了解内喷管间隙宽度对线性塞式喷管性能的影响，提出了对应着同一个内喷管的三种不同间隙宽度的塞锥。
To understand the effects of gap width between nozzles on linear plug nozzles performance, three plugs with different wide gaps were brought forward, which were fixed on the same inner nozzle.
为了研究塞锥截短对塞式喷管性能的影响，对截短率为80%、40%、30%和20%的塞式喷管进行了冷流实验。
To discuss the performance effects of plug truncation ratios, cold-flow tests were performed for 80%, 40%, 30% and 20% truncated aerospike nozzles by employing cold air as propellant.
另外在计算过程中发现，内喷管的性能是整个线性塞式喷管性能的主要组成部分，占了整个塞式喷管性能的三分之二以上。
In addition, it was found that performance of inner nozzle is the largest part of that of linear plug nozzles, accounting for more than two thirds of whole engine's performance.
结果表明，在高的环境压强下工作时，由塞式喷管的高度补偿能力所获得的推力是引起效率高度特性曲线非单调变化的原因；
Results show that the thrust aroused from the altitude compensation capability is the cause of the non-monotone variation of nozzle efficiency with altitude at high ambient pressure;
结果表明，在高的环境压强下工作时，由塞式喷管的高度补偿能力所获得的推力是引起效率高度特性曲线非单调变化的原因；
Results show that the thrust aroused from the altitude compensation capability is the cause of the non-monotone variation of nozzle efficiency with altitude at high ambient pressure;
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