中止燃燒方法模擬固體推進劑動態(tài)點火沖擊過程（英文）
發(fā)布時間：2024-05-28 20:09
為了研究火箭發(fā)動機點火過程中動態(tài)沖擊對固體推進劑的影響,設(shè)計了一個基于中止燃燒的模擬點火沖擊裝置。該裝置由點火螺栓、燃燒室和泄壓螺栓組成。金屬爆破片安裝在泄壓螺栓的剪切口處,在點火沖擊過程中準確控制泄壓壓力。模擬點火沖擊試驗的研究對象是圓環(huán)柱體形狀的poly(BAMO-THF)/AP/Al固體推進劑試樣。p-t曲線表明爆破片的泄壓壓力與測得的壓力一致,其誤差在±6%。根據(jù)p-t曲線計算增壓速率,10 MPa下增壓速率達到7000 MPa·s-1,15 MPa下增壓速率達到12000 MPa·s-1,這遠遠大于固體火箭實際點火過程中的增壓速率。在模擬點火沖擊試驗后,推進劑試樣端面(受損表面)鑲嵌的粒子受損,而內(nèi)側(cè)表面(未損表面)仍保持完整的狀態(tài)。點火沖擊試驗后,推進劑試樣的壓縮強度增加,而壓縮強度開始增加時的形變值降低。這說明在模擬點火沖擊試驗后,推進劑受損表面會進一步受損,力學(xué)性能也會發(fā)生改變。
【文章頁數(shù)】：9 頁
【文章目錄】：
1 Introduction
2 Experimental
2.1 Simulation Ignition Shock Principles
2.2 Experimental Setup
2.3 Propellant Samples
2.4 Mass of Ignition Material
2.5 Characteristic of Propellant Samples
3 Results and Discussion
3.1 Choice of the Ignition Mode
3.1.1 Weak Ignition
3.1.2 Strong Ignition
3.2 Repeatability Testing of Simulation Ignition Shock
3.3 p-t and dp/dt-t Curves at Different Ignition Pressure
3.4 p-t and dp/dt-t Curves at Different Propellant Temperatures
3.5 Effects on Propellant Micro Morphology by Ignition Shock Process
3.6 Effect of Ignition Pressure and Propellant Temperature on Compressive Strength
4 Conclusions
本文編號：3983667
【文章頁數(shù)】：9 頁
【文章目錄】：
1 Introduction
2 Experimental
2.1 Simulation Ignition Shock Principles
2.2 Experimental Setup
2.3 Propellant Samples
2.4 Mass of Ignition Material
2.5 Characteristic of Propellant Samples
3 Results and Discussion
3.1 Choice of the Ignition Mode
3.1.1 Weak Ignition
3.1.2 Strong Ignition
3.2 Repeatability Testing of Simulation Ignition Shock
3.3 p-t and dp/dt-t Curves at Different Ignition Pressure
3.4 p-t and dp/dt-t Curves at Different Propellant Temperatures
3.5 Effects on Propellant Micro Morphology by Ignition Shock Process
3.6 Effect of Ignition Pressure and Propellant Temperature on Compressive Strength
4 Conclusions
本文編號：3983667
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