There is a range of applied force over which the regression rate remains constant . 施加的力有一個范圍,在這個范圍內(nèi)遞減率保持不變。
The plateau domain is defined as a pressure regime in which the regression rate is insensitive of pressure . 平臺區(qū)是定義為這樣一個壓力區(qū),即其中壓力對速度沒有影響。
Model about regression rate of hybrid rocket motors was studied 研究了固液發(fā)動機固體燃料退移速率預(yù)示模型。
The reasons for higher oxidizer flow rate , lower fuel regression rate and lower motor performance in both hot firings are discussed . several necessary improvements for the test system are suggested . 6 通過對兩臺發(fā)動機試驗結(jié)果的分析,找出了試驗中氧化劑流量偏高、燃料退移速率和發(fā)動機性能偏低的原因,并提出了具體的改進措施。
The results of research indicate that the pressure , the thrust and the fuel regression rate of the motor decrease while the o / f ratio increasing with the burning time lasting . the special impulse reduces when throttling 研究結(jié)果表明:壓強、推力和燃料退移速率隨發(fā)動機工作時間增加而降低,氧化劑和燃料的配比升高;節(jié)流時,發(fā)動機比沖降低。
The result of analysis shows that the convective heat flux has main effect on fuel pyrolyzing and vaporizing , the liquid layer of pe fuel can increase the regression rate but also can cause unstable burning . 4 研究結(jié)果表明:對流熱流是引起燃料熱解氣化的主要因素, pe熔化產(chǎn)生的液體層提高了燃料熱解退移速率,但液體層厚度增加到一定程度時,對發(fā)動機工作穩(wěn)定性有負面影響。
Through malfunction of the tests of 810 research institute , the combustion performance of the hybrid motor and model about regression rate have been studied in the dissertation . the main aspects are as follows : the performance of the hno3 + n2o4 - htpb hybrid rocket motor were all discussed 本文結(jié)合航天科技集團公司810研究所正在研制的ak - 20l / htpb + al組合固液火箭發(fā)動機,開展了固液火箭發(fā)動機混合燃燒特性的數(shù)值模擬工作,在此基礎(chǔ)上給出固體燃料退移速率預(yù)示模型及預(yù)示結(jié)果。
Combining with the energy fluxes balance above fuel surface , the simulation and calculation of transient heat conduction of the pe fuel with liquid layer while melting and pyrolyzing are considered by use of the moving coordinates . the calculated regression rate of the pe fuel approximately tallies with the same kind of hybrid rocket motor test data from the abroad 建立了pe燃料的熔化、熱解、導(dǎo)熱模型,應(yīng)用動坐標系,結(jié)合燃料表面熱環(huán)境,對具有液體層的pe燃料的熔化、熱解和內(nèi)部瞬態(tài)導(dǎo)熱過程進行了模擬計算,計算的pe燃料退移速率與國外同類試驗的測量結(jié)果符合較好。