thrust ratio 中文意思是什麼

thrust ratio 解釋
推力比
  • thrust : vt （thrust）1 猛推，沖；猛撳，沖入，插入，推入（出），突出，伸出，塞，刺，戳，戳穿。2 逼迫，把[...
  • ratio : n. （pl. ratios）1. 比，比率，比值；比例；系數。2. 【經濟學】復本位制中金銀的法定比價。vt. 1. 用比例方式表達；求出…的比值；使…成比例。2. 將（相片）按比例放大或縮小。
  1. With the ground effect, they own higher lift / drag ratio than general aircraft, so need less thrust power and have the ability to carry more loads or fly longer

    在地效的作用下，它的升阻比比一般的飛機大，因而飛行時所消耗的推進功率小，具有更大的載重量或航程。
  2. Owing to complicated earth ' s surface condition such as the steep stratum outcropping of front - zone of mountain or the huge thick gravel stratum ' s overlay and earth ' s surface large undulation, complicated underground geology structure developed extremely such as thrust and overthrust nappe, and violent change of the lateral velocity, etc. in front - zone of mountain there are a series of problems such as serious secondary disturbance and low signal - to - noise ratio in seismic exploration gathering

    由於山前帶高陡巖層出露或巨厚礫石層的覆蓋、地表起伏大等復雜的地表條件、逆沖和逆掩推覆等復雜地下地質構造發育、速度橫向變化劇烈等原因，造成了山前帶地震勘探資料採集存在次生干擾嚴重和信噪比低等一系列問題。
  3. Ratio control of cvt is the key for engine running according to ideal curve, and controlling thrust of driving and driven pulley reasonably can improve efficiency and extend life - span of metal belt, and it is coupling relation between control of ratio and thrust

    無級變速傳動系統的速比控制是實現發動機按理想工作線運行的關鍵，合理控制主、從動帶輪的夾緊力能提高傳動效率和金屬帶的壽命，而夾緊力和速比控制存在耦合效應。
  4. By adjusting many variable geometry components of the engine, bypass ratio can be changed during large range ( the most 0. 25 of military fighter ). the high specific thrust characteristic of turbojet engine and the low specific fuel consumption characteristic of the turbofan engine can be realized during different flight phase by the usage of vce technology

    變幾何變循環發動機是應用於第四代多用途戰斗機的理想動力裝置，通過多個部件幾何的調節在較大范圍內改變涵道比，能夠使發動機在不同航段分別實現渦噴發動機的高單位推力性能和渦扇發動機的低油耗性能。
  5. The results showed that the thrust - weight ratio reached 1. 04 for the launch weight 5400kg in the condition of specific impulse near 600s

    結果表明:在發動機工作比沖接近600s的情況下，對于起飛質量為5400kg的飛行器而言，推重比為1 . 04左右。
  6. To optimize specific impulse to 700s or 800s, the thrust - weight ratio could be improved to 1. 23 or 1. 41, it is enough to achieve the launch requirement for this vehicle

    進一步將比沖優化至700s或800s ，可以將推重比提高至1 . 23或1 . 41 ，這樣就完全能夠保證發射任務的完成。
  7. With the development of multi - variable control technology and aero - propulsion technology, future excellent engine must have the character, which is high ratio in thrust and weight low fuel and long use life. therefore the control system of aero - engine has also been becoming more and more complicated. the precision of control system is also extra higher

    隨著高推重比、低油耗、長使用壽命、高機動性航空發動機的研製，現代航空發動機需要控制的變量越來越多、精度越來越高，因此，航空發動機控制系統變得越來越復雜，傳統的航空發動機控制系統是採用機械液壓控制。
  8. Compress disk is the very important rotational component in the areoengine. when the compress disk is working, the grads of temperature and stress between the rim and the center of the disk are great. in order to raise the thrust - weight ratio of the disk and reduce oil consumption. the best prospective way is the dual alloys disk used

    壓氣機盤是航空發動機上一個很重要的轉動部件，壓氣機盤工作時，輪緣和輪轂溫度梯度和應力梯度較大，為了提高飛機發動機推重比、減低耗油量，要求壓氣機盤的工作溫度、使用性能更高，雙合金盤製造是最有發展前景的技術。
  9. Weight to thrust ratio

    重量推力比
  10. Mass to thrust ratio

    質量推力比
  11. Much works has been distributed to the development of a vacuum system to simulate the outer space and a measurement system to test the arcjet performance. ignition experiments in various operational modes have been done with argon as propellant. macroscopical working parameters including thrust, mass flow rate, voltage, current, inlet pressure and vacuity are obtained by the test measurement system and actual performance parameters including specific impulse, thrust efficiency, ratio of thrust and power and ratio of power and mass flow are calculated

    以氬氣作為推進劑，在不同工況下進行點火實驗，測量獲得了其工作推力、電弧電壓和電流、推進劑流率和弧室壓力等宏觀參數，得到了不同實驗條件下其工作的實際比沖、推力效率、推力/功率比以及比功率等性能參數，分析了推進劑質量流率、電弧功率、電弧加熱發動機電弧室結構尺寸等因素對其性能的影響，為數值模擬研究和實際的低功率電弧加熱發動機優化設計及研製提供了實驗基礎。
  12. Finally, by practical test, experimental data obtained show that the dynamic thrust measuring system is dramatically available and successful. especially, it shows that when the impulse width is 20ms and the duty ratio is 1 : 3, the measured results are stable and reliable. hence, the system designed here can meat the test requirements of the actual applications, and the technology studied in the thesis also give a good foundation to future research work

    最後，系統建成以後，通過多次調試試車、考核試車和實際型號試車的考核，試車結果表明，該系統的設計是成功的，動態推力數據穩定、可靠，可滿足發動機以20ms脈寬工作，占空比為1 : 3的情況下，進行發動機的動態推力性能指標測試，滿足實際應用的需求，為進一步進行動態推力測試技術研究奠定了良好的基礎。
  13. Cfd is also used to get the data of performance parameters of the nozzle at different nozzle pressure ratio, different nozzle area ratio and different geometric defected angle. the theory of function approximation is used to establish the transient model of thrust vectoring with the data calculated

    本文通過cfd計算獲得矢量噴管的性能參數，如流量系數、推力系數以及有效推力矢量角等與矢量噴管壓比、面積比以及幾何偏轉角之間的關系數據，並利用函數逼近理論建立了矢量噴管的動態數學模型。
  14. The experimental results indicates that the secondary mass flow increases with increasing of primary mass flow rate, but the bypass decrease because the primary mass flow rate increase more rapidly than secondary mass flow. the expansion configuration shows low thrust property due to low pressure in flow path. the secondary nozzle changes the pressure distribution in ejector combustor, and decreases bypass ratio, but obtain more completely mixing

    結果表明：二次流流量隨著一次流流量的增加而增加，由於二次流流量的增加速度低於一次流，引射系數減小；在純擴張式結構實驗中，引射燃燒室壓強很低，難以實驗推力增強；二次噴管改變了引射燃燒室的壓強分佈，降低了引射系數，改善了混合狀況能；對于本文的實驗結構，存在一個最優的二次噴管出口面積，使引射火箭推力最大，同數值模擬結果相吻合。
  15. Thrust fluctuation ratio

    推力脈動率
  16. Thrust - weight ratio

    推力重量比
  17. More than 200 different condition 3d viscosity steady flow fields in the thrust vectoring nozzle at different nozzle pressure ratio and different nozzle area ratio and different geometric defected angle is calculated by the program developed. and the related performance parameters are acquired by numerical simulation

    利用該程序計算了某矢量噴管在不同的壓比、面積比和幾何偏轉角下的200多種三維有粘流場，獲得了矢量噴管的性能數據。
  18. At present, arcjet has been the highlight of investigation and application because of its high thrust density, high ratio of thrust and power, preferable specific impulse, better system successiveness and reliability

    電弧加熱發動機以較高的推力/功率比、推力密度、中高的比沖、良好的系統繼承性和可靠性等特點，已經成為當前國際研究和應用的熱點。
  19. Arcjet is one of the highlight of electric propulsion investigation and application because of its high thrust density, high ratio of thrust and power, preferable specific impulse, better system successiveness and reliability

    作為電推進的一種方式，電弧加熱發動機以較高的推力/功率比、推力密度、中高的比沖、良好的系統繼承性和可靠性等特點，成為當前國際研究和應用的熱點。
  20. Composite laminate shells have been applied more and more widely in aerospace structures. in order to increase thrust to weight ratio and improve the comprehensive performance of airplane, optimization design must be carried out. this thesis brings forward utilizing the method of aga - fem, which combines adaptive genetic algorithm ( aga ) and finite element method ( fem ), to optimize fibre - reinforced composite shells

    本文提出採用自適應遺傳演算法（ adaptivegeneticalgorithm ）和有限元方法（ finiteelementmethod ， fem ）結合即aga - fem方法進行纖維增強型復合材料層合殼結構的優化設計，並對某航空發動機復合材料機匣進行優化設計分析，取得了很好的效果。
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