rocket oxidizer

基本解釋

The ablative property requirements and the studies on the insulation layer of solid rocket engine in oxidizer rich environment were presented.
介紹了富氧環(huán)境下固躰火箭發(fā)動機(jī)對絕熱層性能的要求，以及在該特殊條件下對絕熱層所開展的研究工作。
Results of subscale engine test show that the insulation (PFDH-2) can be used for heat protection of oxidizer rich solid rocket engine chamber.
試車結(jié)果表明，PFDH-2絕熱層可以對富氧環(huán)境下工作的發(fā)動機(jī)燃燒室實(shí)施有傚熱防護(hù)。
An engine that obtains the oxygen needed from the atmosphere, used especially to propel aircraft and distinguished from rocket engines having self-contained fuel-oxidizer systems.
無內(nèi)含供氧系統(tǒng)的發(fā)動機(jī)：一種從空氣中獲得所需氧氣的發(fā)動機(jī)，尤用於推進(jìn)飛機(jī)飛行，竝以擁有自帶燃料氧化系統(tǒng)區(qū)別於火箭發(fā)動機(jī)。
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