thrust performance 中文意思是什麼

thrust performance 解釋
推進特性
  • 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[...
  • performance : n. 1. 執行，實行，履行；完成；實現；償還。2. 行為，動作，行動；工作。3. 性能；特性。4. 功績；成績。5. 演奏；彈奏；演出；（馴獸等的）表演；把戲。6. 【物理學】演績。
  1. This paper simply introduces the device of on - line monitoring for the thrust of the rotating maching, then discu ed the finite dement analyses on the on - line monitoring elastic dement for measuring thrust in detail, in order to develop the performance of the se or and the device, we calculated the distribution of the stre 、 strain 、 axial di lacement in the elastic element using the finite element method when the axial forces f = 3 104n, the result is very satisfied

    簡單介紹大型旋轉機組軸向力在線監控裝置，然後詳細介紹軸向力測力彈性元件的有限元分析，為了提高所研製的測力傳感器的性能，採用有限元方法計算了彈性元件在軸向力f = 3 104n時的應變、應力、靈敏度及軸位移等的分佈情況，分析結果表明：所設計的測力傳感器完全符合廠方的要求及儀表性能指標。
  2. The main works and achievements are described : ( 1 ) the application of direct lateral force on the exoatmosphere kinetic - kill vehicle. at first, the collectivity project of the exoatmosphere kinetic - kill vehicle is specified, the motive model of the exoatmosphere kinetic - kill vehicle and target are constructed, and the thrust performance of trajectory - control engine and attitude - control engine are presented

    研究的內容及成果主要表現在以下幾個方面： （一）直接側向力在大氣層外動能攔截器中的應用首先確定了動能攔截器的總體方案，分別建立目標運動和動能攔截器運動的數學模型，以及軌控和姿控發動機的推力模型。
  3. By 1955 the sea hawk performance was already considered mediocre which led to the installation of the more powerful 5, 200 lb thrust nene 103 and the use of the sea hawk as a ground attack aircraft, cleared to carry external stores, a task at which the sea hawk excelled

    到1955年，因為「海鷹」的表現只能說是差強人意，所以換裝了推力為5 ， 200磅的「尼恩」 103發動機，同時， 「海鷹」的角色也轉變為一架對地攻擊機， 「海鷹」攜帶的外掛武器完全可以勝任。
  4. Our products are characterized by high precision, low noise ， long service life and stable performance, which mainly cover auto bearing, mute motor bearing, deep - groove ball bearing, needle roller bearing. thrust ball bearing ， tapered roller bearing and nonstandard bearing

    產品以精度高、噪音低、壽命長、性能穩定為優勢；主要生產高品質汽車軸承、靜音電機軸承、深溝球軸承、滾針軸承、推力球軸承、圓錐滾子軸承及其他非標軸承。
  5. Focusing on the performance evaluating and the design of tripropellant injector, adopting the cold test rig with background pressure supply, malvem particle analyzer, ccd photography system, tripropellant hot test - bed, numerical simulation software and auxiliary theoretical a nalysis, the d ischarge c haracteristic a s w ell a s a tomization p erformance o f the injector and the combustion performance as well as the mode - transition characteristic of thrust chamber are studied detailedly based on the 3 different structures of coaxial tripropellant injector, large numbers of important conclusions are gained

    本文圍繞三組元噴嘴的性能評定及設計方法。採用反壓冷試臺、馬爾文測粒儀、 ccd高速攝影系統、三組元發動機熱態試驗臺、數值模擬程序及輔助理論分析等多種技術手段和研究方法，對三種結構的同軸式三組元噴嘴深入進行了噴嘴流量特性和霧化特性、推力室燃燒性能和轉工況性能研究，得到了大量重要結果。
  6. According to the experimental parameters of mpt, the main performance parameters of different propellants have been given by engineering performance computation under designed and working states, which has great importance for the experimental research and the future work. 2. for helium and argon, the factors which influence on mpt ' s vacuum steady work have been discussed such as the material of microwave tie - in, the distance between the probe and inner - conductor, the position of the inner - conductor, the input power of microwave, the mass flowrate of propellant and the vacuum pressure of environment, and the influence has been discussed of the microwave power and the mass flowrate of propellant on the pressure of the resonance cavity, thrust, reflected power and the temperature of the resonance cavity

    論文的工作和新見解主要包括： 1在設計狀態和工作狀態下，根據mpt的實驗參數，對mpt使用不同工質時的性能進行了工程估算，這對mpt現階段的實驗研究和今後的研究有重要的指導意義； 2對于he 、 ar推進工質，討論微波的接頭材料、探針與內導體的間隙、內導體的位置、微波的輸入功率、工質的質量流量以及環境真空度對mpt真空啟動和穩定工作的影響，並探討微波的輸入功率、工質的質量流量對諧振腔壓強、推力、反射功率以及諧振腔溫度的影響； 3對于n _ 2 、 h _ 2 、 nh _ 3 、 h _ 2o推進工質，主要討論與he 、 ar工質不同的特性，並從長遠的眼光和工程應用的角度，認為其可行性不容置疑，潛在優勢不可忽略，是未來mpt應用的主流推進工質。
  7. The effects of such elements as primary flow total pressure, flow rate, degree of fuel rich, nozzle structure, flying speed and secondary combustion on ejecting mode performance were researched. it was found that thrust augmentation can be achieved on the condition that the flying mach number is above 0. 7. to deeply analyze thrust augmentation mechanism in low speed range, the research was further continued by changing secondary combustion organization and aft - body configuration

    研究了一次流總壓、流量、富燃程度、噴管結構、二次流來流速度、二次燃燒組織對引射模態性能的影響，發現實驗樣機構型在0 . 7ma以上的飛行條件下可以獲得推力增強，而在0 . 7ma以下無推力增強。
  8. 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。
  9. The simulation results show that the power factor and efficiency of lim are much lower than that of rotary induction motor due to end effect and big air gap of lim. end effect force has a great influence on the thrust of lim. the performance of lim can be improved with the proper secondary structure, small air gap, big goodness factor or heavy load

    結果表明:受邊端效應及大氣隙影響，直線感應電機功率因數及效率較低;運行狀態下的邊端效應力對電機推力有較大影響;設計電機時選用合適的次級材料、減小氣隙、增大品質因數、增加負載都可提升電機的輸出性能，通過設計有效的控制演算法可使電機在額定滑差下具有較高的運行效率。
  10. 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。
  11. Research on performance of rudder with additional thrust fin by panel method

    面元法計算槳后舵附推力鰭水動力性能
  12. The controllers have considered all sorts of imperceptible factors affecting the servo performances in a lpmsm servo system, which include the parametric uncertainties brought by the changes of the mobile mass, frictional coefficient, the thrust fluctuations aroused by the varieties of the magnetic density distributions and the time harmonic. the h state feedback controller restrains disturbances and uncertainties to keep the robust and stable performance. the ip controller, which has the ability of rapid response, is applied to satisfy the rapid performance

    在分析雙環控制問題時，針對直線永磁同步電動機，仔細考慮了能使伺服系統性能變壞的各種細微因素，如：永磁同步直線電機動子質量變化、摩擦系數變化等造成的模型參數不確定性，電機運行期間存在磁密分佈變化、時間諧波等產生的推力擾動等，採用了ip速度控制器和h _狀態反饋控制器相結合構成直線伺服的內環控制器，並輔助設計了外環的pi位置控制器。
  13. Thrust vectoring is the key technique for the modem fighter with agility and post - stall maneuver ability and good flight quality. and now it is the necessary technique for the fourth generation fighter and hot technique for the performance improvement for the third generation fighter

    推力矢量技術是現代戰機具有敏捷性、過失速機動能力、良好的飛行品質的關鍵技術，其已成為第四代戰斗機的必備技術和第三代戰斗機改型的熱門技術，得到了越來越多的重視。
  14. Research on lim thrust, efficiency and control scheme is made to conclude some measures of improving lim performance. and the electromagnetism resistance in maglev traffic is discussed in order to see the interaction mechanism of electromagnetism. firstly, the characters of lim are analyzed by simulation

    本文圍繞直線感應電機牽引系統的性能展開研究，其中涉及了直線牽引過程中的推力、效率、控制方法以及磁浮交通中的電磁阻力等問題，為提升直線牽引系統性能及明確電磁作用機理提供了參考。
  15. 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。
  16. The motion model and dynamics model of the rolling missile was constructed, and the thrust performance of attitude control system were presented

    建立了滾轉導彈運動學和動力學模型，以及姿控發動機的推力模型。
  17. The main work and achievements are described as follows : ( 1 ) the analysis of the extra - atmospheric kinetic - kill vehicle at first, the motion model and dynamics model of the kinetic - kill vehicle is constructed, and the thrust performance of trajectory - control system and attitude - control system are presented, then the algorithms of realizing the guidance law, the methods of trajectory and attitude control are studied

    研究內容及成果主要表現在以下幾個方面： （一）大氣層外動能攔截器分析首先建立了動能攔截器運動學和動力學模型，以及軌控發動機和姿控發動機的推力模型，提出了攔截導引律的實現方法及軌控和姿控發動機的控制規律。
  18. And then based on a surface - to - air missile that satisfies the requisition nearly, by means of reconstructing its geometry size, subsystems such as engine, the interceptor model used to continue the following studies is established. then the trajectory - control jet or attitude - control jet is added to the interceptor based on the analysis of the relationship between the missile performance and the thrust and configuration of the side jet

    然後以基本滿足方案要求的某型防空導彈為基礎，對其幾何尺寸、發動機等分系統進行改進，並通過分析導彈性能與側噴發動機參數之間的關系，增加了姿控或軌控側向裝置，這樣得到了本文的研究工作所需的導彈模型。
  19. 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。
  20. It is shown that when the exit area of secondary nozzle and the fuel / oxidizer ratio is fixed, the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow, and increase of total mass flow rate. the synthetical result of these two phenomenon cause the increase of thrust of rocket ejector, but the increasing magnitude is relatively small, indicating that these is no necessary to claim large bypass ratio in rocket ejector design. in the comparison between two configurations, the typical one has better performance, indicating the importance of pressure ratio

    結果表明：在固定二次噴管出口面積和氧燃比的條件下，二次流（引射空氣流）流量的增加引起混合氣體出口速度的下降和總流量的增加，二者綜合作用使發動機推力增加，但增幅不大，表明在設計發動機結構和工作參數時，不必過分追求大的引射系數；兩種結構的性能對比分析表明了增壓比對引射火箭性能的提高具有重要意義；對引射火箭的熱力循環分析同樣表明，增壓比對于提高發動機性能非常關鍵。
分享友人
分享到 Line

分享到臉書