rocket thrust 中文意思是什麼
rocket thrust
解釋
火箭推力-
Abstract : solid propellant rocket motors are preferred for most ballistic missiles because they need simple maintenance and can be launched quickly. but the conventional thrust termination devices limit the depletion of every stage ' s grain and increase some extra - weight. an improved method for designing a multi - stage solid rocket based depleted shutdown was provided. in order to solve the problem of lack of thrust termination devices, a device to adjust the burnout angle will match the final burnout velocity and satisfy the desired range. the method can also limit the detection from anti - ballistic missile system
文摘:由於維護簡單和發射快速，彈道導彈多用固體火箭發動機，但繁雜的推力終止裝置使各級裝藥不能耗盡並讓結構增重.提出了一種對基於耗盡關機多級固體火箭概念設計的改進方法，此方法滿足導彈系統主要的戰技要求.為解決無推力終止裝置的末速不準問題，可在末級發動機採用姿態調整裝置，對射角進行調整，配合末速以滿足射程要求.本方法還可抑制敵方反導探測 -
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。 -
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。 -
It is determined now by calculation with mathematical relationship of the flight thrust to the physical quantities which can be measured directly. the optimization of the software development platform is also analyzed inspect of the solid rocket - ramjet developmental program
其次，為滿足固體火箭沖壓發動機試驗技術進一步研究需要，在深入分析labview圖形化編程軟體優化方法的基礎上，改進了現有的固體火箭沖壓發動機試驗測控程序，並應用於發動機試驗中。 -
Something, such as an explosive charge or a rocket fuel, that propels or provides thrust
發射藥，火箭燃料推進或提供爆炸的物體，比如爆炸炸藥或火箭燃料 -
Report back in the exhibit schedule : march 8, 2006 - 10 days am09 : march 10, 2006 - 12 days remove time : march 12, 2006 exhibitors range : car, car, motorcycle, light truck bearings, railway bearings, magnetic bearing spindle ; aviation aerospace marine bearings, rocket and satellite bearings ; industrial robot bearings, machining center and machine spindle bearings, textile machine bearings, motor bearings, and farm machinery bearings, paper machine bearings, bearings press, bearing mill, metallurgical mining, petrochemical machinery bearings, bearings sporting goods, marine rig bearing ; bearings, bearings gyroscope, high - precision bearings, high - speed bearings, linear motion bearings, needle roller bearings, thrust bearings, ultra - low - temperature bearings, special bearings, ceramic ball bearings, spherical with trophies bearing miniature bearings, quiet motor bearings, ball bearings, roller bearings, lubricating bearings corrosion resistant bearings, bearing joints ; bearing ring blank refinement, precision ball and roller crown, with nails cage
撤展時間： 2006年03月12日參展范圍：轎車汽車摩托車輕型車軸承鐵路軸承磁懸浮軸承電主軸航空航天航海軸承火箭及人造衛星軸承工業機器人軸承加工中心及機床主軸軸承紡織機軸承電機軸承農機軸承造紙機軸承印刷機軸承軋機軸承冶金礦山石油化工機械軸承體育用品軸承海洋鉆機軸承組合軸承陀螺儀軸承高精軸承高速軸承直線運動軸承滾針軸承推力軸承超低溫軸承特種專用軸承陶瓷球軸承帶座外球面軸承微型軸承靜音電機軸承球軸承滾子軸承潤滑軸承耐腐蝕軸承關節軸承軸承套圈精化毛坯精密鋼球凸度滾子帶釘保持架軸承滾動體等軸承部件。 -
After the first stage burns out, it falls back to earth along a parabolic path, while the engines of the second stage fire to thrust the rocket into an earth orbit
當第一級燒毀后，沿拋物線的軌道落到地球，而第二級的發動機點火把火箭發射到地球軌道。 -
Abstract : introduces a method to eliminate influence of power supply and air - feed system on exact measurement of micro - thrust of electric rocket in the gravity field, so micro - thrust can be measured accuratelg and automatically
文摘:介紹了在重力場中，消除電火箭自重及其供電供氣系統對微小推力測量影響的方法，從而實現電火箭微小推力自動準確的測量。 -
By comparison, the chemical power generated by a rocket equals one half the thrust times the exhaust velocity
相比之下，火箭的化學能功率是推進力的一半乘以排氣速度。 -
With grain design and the calculations of pressure - - - time and thrust ? time, the designers of rocket can improve their structure design
通過藥柱的設計和壓強? ?時間曲線和推力? ?時間曲線的計算，為固體火箭發動機設計、裝藥強度分析和裝藥完整性分析提供了有力的支持。 -
At liftoff, the three clustered boosters generate two million pounds of thrust. the rocket can place about 50, 000 pounds into earth orbit
這三個串聯的推進器總共產生2百萬磅推進力。因而該火箭將用來部署5萬磅重量的有效載荷到地球軌道中。 -
Based on widely assimilating the internal and overseas researches, the theory and methods of solid rocket motor ( srm ) thrust vector measurement and the automatic test technology are studied detailedly and comprehensively by means of theoretical analysis, engineering implement and experimental validation. the results attained are as follows
論文在廣泛吸收國內外研究成果的基礎上，藉助理論分析、工程實現和試驗驗證等手段，對火箭發動機地面試驗中的推力矢量測量理論與方法以及自動測試技術進行了系統深入的研究，取得了一系列研究成果。 -
The dynamic thrust measure technology for high - altitude simulation test of the attitude control liquid rocket engine was studied in the thesis
本文研究的是姿控發動機高空模擬試車中的動態推力測試技術問題。 -
According to the definition and expression of the thrust, as well as the condition derived from them, a method of solid rocket ramjet thrust determination and its program are provided on the basis of engine ground simulation test
本文以西北工業大學固體火箭沖壓發動機直連式試車臺為研究對象，探討固體火箭沖壓發動機地面試驗技術。首先，從推力的定義出發，建立了試驗中來流空氣流量、燃料流量與固體火箭沖壓發動機推力之關系。 -
The channel scale on transpiration cooling for the platelet thrust chamber of liquid propellant rocket engine is approaching micron dimension. it is very possible that micro - scale effects will occur in the flow and heat transfer of the channel. in the past, researchs on flow and heat transfer in the platelet micro - channel are mostly based on macro - scale theory
液體火箭發動機推力室壁面發汗冷卻通道的尺度已達微米量級，通道內的流動與換熱很可能存在微尺度效應，以前的相關研究都以宏觀尺度的理論為依據，其研究結果的合理性需要進行微尺度效應的分析。 -
The determination of solid rocket ramjet thrust and testing method are the important basis of the developing engine. an experimental program evaluating solid rocket - ramjet in nwpu connected - pipe facility is underway
我國發展中遠程、超音速導彈計劃已經啟動，其動力裝置首選固體火箭沖壓發動機，而地面試驗技術是發動機研究重要基礎。 -
Study on the influences of the pressure changes on rocket thrust misalignment
壓強變化對火箭推力偏心影響研究 -
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；存在一個最優的二次噴管出口面積，使發動機推力最大。 -
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。 -
Design method of multiperforated grain for single - chamber dual - thrust rocket motor
火箭發動機單室雙推力多孔裝藥設計方法
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