rocket ramjet

基本解釋

The combustion flow field in secondary combustion chamber for static and spinning extended solid rocket ramjet were studied experimentally and numerically in detail.
本文從實驗和數(shù)值模擬兩方面，對靜止和旋轉(zhuǎn)增程固體火箭發(fā)動機補燃室燃燒流場進行了研究。
The numerical simulation of turbulent combustion in the afterburner of solid rocket ramjet was performed by applying the probability density function non -premixed mode.
應用概率密度函數(shù)非預混模型，對固體火箭沖壓發(fā)動機補燃室內(nèi)的湍流燃燒進行了數(shù)值模擬。
The paper presents the composition, functions, technical performance and research of the solid rocket ramjet engine ground test equipment and measurement control system in detail.
介紹了固體火箭沖壓發(fā)動機地面實驗裝置及測控系統(tǒng)組成、功能、技術指標和可以開展的研究工作。