thrust control 中文意思是什麼
thrust control
解釋
推力調節-
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。 -
The pneumatic - valve structure with simple, reliable operation, export thrust large maintenance convenient and inexpensive, such as fire blast merits pneumatic - valve widely used for chemical, oil, metallurgical, electrical, textile and other industrial production processes autopilot and remote control
由於氣動調節閥具有結構簡單，動作可靠，輸出推力大，維修方便，防火防爆和價廉等優點，氣動調節閥廣泛應用於化工、石油、冶金、電力、輕紡等工業生產過程的自動調節和遠程控制中。 -
Thrust vector control is one of objects being seeked by engineers in rocket propulsion area
流場控制以及基於此的發動機推力方向控制長期以來都是國內外火箭推進領域廣大工程技術人員追尋的目標之一。 -
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。 -
The application of thrust vectoring control technology makes the aircraft possess the ability to fly in post - stall domain, therefore the flight envelope is extended
推力矢量控制技術在戰斗機上的應用，使戰斗機有能力進入過失速飛行領域，使飛機的飛行包線得以擴展。 -
In order to determination the thrust, the thrust definition and many control parameters are analyzed discussed, which mass flow rate and flight altitude are involved. it is difficult to measure the flight thrust of solid rocket ramjet directly
通過討論高空飛行推力與地面可測試參數的關系，得到了固體火箭沖壓發動機高空飛行狀態下推力折算方法，並開發相應的計算程序。 -
Simultaneous lateral thrust and aerodynamic control of an agile missile
側向推力復合控制特性分析研究 -
A part or surface, such as a wing, propeller blade, or rudder, whose shape and orientation control stability, direction, lift, thrust, or propulsion
翼剖面；機翼；翼面一個部件或平面，如機翼、螺旋槳葉、方向舵等，其形狀或方位控制穩定性、方向、抬升、沖擊或驅動 -
It is the foundations to further analysis, such as thrust calculation, selection of exciting current and design of control method
為進一步進行推力計算、控制電流的選擇及控制方法的設計提供了理論基礎。 -
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。 -
B ) equivalent circuit method and finite element analysis ( fea ) to compute the static force are presented, the results obtained by each method are compared one with the other. c ) the results of dynamic simulation by means of the software, ansoft show the hlfm " s characteristics when the motor works in the special frequency and single stroke and the conditions used for position control. d ) the measured static thrust - displacement characteristics and the dynamic characteristics during starting show good correlation with the calculated results
在設計並製作了實驗樣機的基礎上所做的研究內容包括； （ 1 ）分別用能量法和麥克斯韋張量法推導電磁力的計算公式，並討論他們的不同應用范圍； （ 2 ）分別用等效磁路法和有限元法作直線力電機的靜特性分析，並比較分析它們的計算結果； （ 3 ）用有限元模擬軟體做直線力電機動態特性的模擬，分別分析直線力電機的頻率特性、動子開合閘特性和開環位置控制的工作特性； （ 4 ）做直線力電機的靜推力?位移特性實驗和動子開合閘的動態實驗，並將實驗結果與計算結果進行對比，實驗驗證了計算模型及計算方法的正確性。 -
Abstract : this paper briefly presents th e application of advanced brazing techniques for a larye number of assemblies of space vehicles, such as thrust chamber and turbine rotor of launch rock et engine, titanium tube of satellite, attitude control engine injector and wave guide component of satell ite, reflector, tube and honeycomb panel of manned spacecraft, main engine nozzl e and preburner of space shuttle as well as the pipeline systems of space statio n
文摘:簡略地介紹了先進釬焊技術在航天器部件，例如運載火箭發動機的推力室和渦輪轉子、人造衛星的鈦導管、姿控發動機噴注器和波導器件、載人飛船的反射器、導管和蜂窩壁板、航天飛機的主發動機噴管和預燃室以及空間站的管路系統等的廣泛應用情況。 -
A cascaded architecture is adopted, where desired propeller rate of revolution is generated by solving a static 2nd order equation with a parameter of desired thrust force, which is the input of the speed / position tracking control
在推進器動態模型的基礎上，採用滑模控制的方法，由速度位置誤差獲得期望推力，再通過求解包括來流速度的二次方程得到期望螺旋槳轉速。 -
With advantages of simple and reliable in structure, high isp and easy control over a wide range of thrust, pulsed plasma thruster （ ppt ） is very suitable for micro - satellite ' s orbit control and high precision attitude control
脈沖等離子體推力器（ ppt ）具有結構簡單可靠，比沖高，推力在較大范圍可控的特點，適合用於微、小衛星軌道控制和小衛星高精度姿態控制，其研究和應用得到了重視。 -
The thrust vectoring control technology and post - stall maneuverability enhance the aircraft ' s combat effectiveness greatly, and cause the worldwide interest
推力矢量控制技術和過失速機動使戰斗機的空戰效能大大增加，引起了世界各國的關注。 -
For researching the flight test techniques of thrust vector controlled aircraft, dynamic models of thrust vector controlled aircraft were established, four post stall maneuver control laws were designed with the dynamic inverse method, tested and investigated according to a standard evaluation maneuver set ( stems )
摘要為研究推力矢量飛機的試飛技術，建立了推力矢量飛機的動力學模型，用動態逆方法設計了4種過失速機動控制律，並在地面飛行模擬器上參考標準評估機動動作集（ stems ）進行了飛行模擬試驗研究。 -
I used nose attitude instead of modulating engine thrust to control airspeed during the climb to 15, 000 feet
在爬升至15 ， 000英尺高度的過程中我用機首的高度代替發動機節流閥來控制飛行速度。 -
The problem of control benchmark is solved by the use of hpop, and the problem of constant thrust control is solved by h control theory and pwpf modulator
本文利用衛星精密軌道預報的結果作為基準軌道，解決了控制基準的問題；利用h _控制理論和pwpf調制器解決了軌控小發動機常推力控制問題。 -
The other method is pontryagin maximum value principle dealing with low thrust control problem. however when the system is very complex, especially when the system contains uncertain factors, the method is not effective
但在多指標的要求下，這種方法難以求得最優解；另一種方法是應用pontryagin最大值原理解決有限推力最優控制問題，但對復雜的或者含有不確定因素的系統往往難以奏效。 -
Then the paper applies ea and spea to an orbital transformation problem. - time - energy optimization o the paper also solve low thrust control problem of relative motion using fuzzy logic
然後分別用一般的進化演算法和改進的spea方法解決軌道轉移的時間-能量優化問題，對于相對運動方程有限推力控制問題，本文用模糊控制的方法加以解決。
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