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TranslationMobile

最大沖量
最大推力

"maximum" in Chinese : n. (pl. maximums, -ma ) 極點，最 ...
"thrust" in Chinese : vt. (thrust) 1.猛推，沖；猛撳，沖入，插入 ...
"maximum certified thrust" in Chinese : 最大驗證推力
"maximum climb thrust" in Chinese : 最大上升推力
"maximum continuous thrust" in Chinese : 最大連續(xù)推力
"maximum continuous thrust climb" in Chinese : 額定推力上升
"maximum cruise thrust" in Chinese : 最大巡航推力
"maximum standard rating thrust" in Chinese : 最大推力
"maximum thrust climb" in Chinese : 最大推力狀態(tài)上升
"maximum thrust combat ceiling" in Chinese : 最大推力狀態(tài)戰(zhàn)斗升限
"maximum-thrust arc" in Chinese : 最大推力飛行軌跡弧
"thrust at maximum reheat" in Chinese : 最大加力推力
"maximum continuous thrust cruise ceiling" in Chinese : 額定狀態(tài)巡航升限
"thrust" in Chinese : vt. (thrust) 1.猛推，沖；猛撳，沖入，插入，推入(出)，突出， ...
"thrust at" in Chinese : 刺向; 用刀劍等向……猛刺

Examples

10 maximum thrust force of top drive power head 30 kn
10動力頭最大給進力30 kn
10 maximum thrust force of top drive power head 15 kn
10動力頭最大給進力15 kn
Maximum thrust force of top drive power head 15 kn
9動力頭最大給進力kn 15
Stand by . we ' re going to maximum thrust
準(zhǔn)備，我們要加速了
Hardware - in - loop simulating system of ifpc is built to research the digital simulations , which are conducted with two optimization modes : maximum thrust mode and minimum fuel consumption mode
構(gòu)建了實物在回路的飛推綜合控制仿真試驗系統(tǒng)，進行了最大推力模式和最小油耗模式的優(yōu)化仿真試驗。
The conclusion that the optimal secondary nozzle exit area generating the maximum thrust agrees well with the numerical simulation , indicating that the exit area of secondary nozzle should be optimized according to structure and flow parameters during design
表明在引射火箭設(shè)計時，應(yīng)結(jié)合引射火箭的結(jié)構(gòu)和流動參數(shù)對二次噴管出口面積進行優(yōu)化設(shè)計，以達到最佳推力性能。
Simulation results presented here demonstrate that during accelerating flight at constant altitude thrust increases up to approximately 12 percent in the maximum thrust mode , and at subsonic cruise specific fuel consumption decreases up to 2 percent in the minimum fuel consumption mode
試驗結(jié)果表明兩種優(yōu)化模式下，飛推綜合控制的優(yōu)化算法可以顯著提高發(fā)動機性能，也驗證了該優(yōu)化計算機設(shè)計方案是可行的。
The results indicate that with decrease of exit area of secondary nozzle , the bypass ratio is decreasing , and the static pressure in integrated ejector combustor is increasing , and mixing condition becomes better . there exists an optimal exit area of secondary nozzle to get maximum thrust of rocket ejector
結(jié)果表明：引射能力隨著二次噴管出口面積的減小而減小；整體式引射燃燒室壓強隨著二次噴管出口面積的減小而上升，混合隨之更為充分；存在一個最優(yōu)的二次噴管出口面積，使發(fā)動機推力最大。