rocket flow 中文意思是什麼

rocket flow 解釋
火箭發動機噴流
  • rocket : n 火箭；火箭彈，火箭發動機；火箭式投射器；〈英俚〉斥責。 a carrier [freight] rocket 載運火箭。 an...
  • flow : vi 1 流，流動。2 （血液等）流通，循環。3 流過；川流不息；（時間）飛逝；（言語等）流暢。4 （衣服、...
  1. The 3 - d complex flowfield of rocket - missile with wings and empennages induced by the interaction between by base jet and the flow around the body has been numerically simulated. the main work is as follows : first, the gordon - mcbride program was developed to make it more friendly and efficient to the users

    本文對帶彈翼/尾翼彈箭的三維噴流繞流復雜流場進行了數值模擬，其主要研究內容有：首先，對gordon - mcbride火箭程序作了改進，使改進后的軟體具有了非常友好的人機交互界面。
  2. Fluent was used to simulate the flowfield of 3 - d complex flowfield of rocket - missile with wings and empennages induced by the interaction by base jet and the flow around the body. in order to study the complex flow problem above, numerical simulations were performed under the following kinds of flow conditions : ( l ) flow of rocket - missile with wings disturbed by supersonic upstream flow. ( 2 ) flow of rocket - missile with wings disturbed by supersonic upstream flow with attack angle

    為了研究以上復雜流場考慮了如下幾種情況： （ 1 ）帶彈翼彈箭超音速無攻角繞流； （ 2 ）帶彈翼彈箭超音速有攻角繞流； （ 3 ）帶彈翼彈箭亞音速有攻角繞流； （ 4 ）帶彈翼彈箭超音速有攻角繞流噴流干擾； （ 5 ）帶彈翼尾翼彈箭超音速有攻角繞流； （ 6 ）帶彈翼尾翼彈箭超音速有攻角繞流噴流干擾。
  3. Then, the navier - stokes equations for 2 - d axisymmetric compressible turbulent flow were constructed and phoenics was used to simulate the 2 - d axisymmetric compressible turbulent flowfield of rocket jet

    其次，建立了二維軸對稱可壓縮湍流流動的平均navier - stokes方程，並利用phoenics軟體對二維軸對稱火箭噴流進行了數值模擬。
  4. This paper described a cold gas simulation of solid rocket motor with submerged nozzle. a two - dimension model with rectangular channel was designed, which can simulate different flow conditions at three periods after ignition

    本文從冷流模擬的角度出發，設計了通道為矩形的含潛入噴管發動機冷流模型，可以模擬發動機工作過程中三個不同時刻的流動狀態。
  5. Contrast study on cold - flow mixing effect and combustion efficiency of afterburning chamber of solid rocket ramjet

    固沖發動機補燃室冷流摻混效果與燃燒效率對比研究
  6. For studying the performance of solid rocket ramjet under the influence of different flight conditions, it ' s significant to simulate the integrated flow field of inlet and combustor

    因此，開展超聲速進氣道/補燃室流場一體化數值模擬研究對于考查飛行狀態對於火箭沖壓發動機性能的直接影響具有重要的現實意義。
  7. 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。
  8. It is important to develop experiment techniques to simulate flow field in the study of solid rocket motor with high acceleration

    本文以高過載固體火箭發動機研製需求為背景，圍繞高過載發動機內流場的地面模擬試驗技術展開研究。
  9. In this paper, simple reacting flow model in solid - propellant ducted rocket combustor based on eddy break - up model is established. the model is used to simulate the three - dimensional combustion flowfields in an experimental motor. some factors how to affect the combustion efficiency are discussed in the paper, including air intake and gas generator nozzle

    本文基於簡單反應的旋渦分裂模型，建立了固體火箭沖壓發動機補燃室內的湍流燃燒模型，並在該模型下對某實驗發動機進行了三維數值模擬，研究了補燃室設計參數包括進氣道出口設計參數和燃氣發生器噴管設計參數對燃燒效率的影響。
  10. For the research requirement of the high g - load mobile missile srm, the work process of solid rocket motor under lateral overload is investigated by the use of theoretical analysis and numerical simulation methods involving the calculation of internal ballistics, the simulation of flow field and the analysis of structural integrity

    本文以高速機動防空導彈固體發動機研製需求為背景，採用理論分析和數值模擬方法，從內彈道計算、內流場模擬、結構完整性分析等幾個方面對橫向過載作用下固體火箭發動機工作過程進行了研究。
  11. In the theoretical aspect, performance analytical model of was proposed, in which allowances were made to allow for variable cross - sectional area, include the heat release of chemical reaction, and allow for mass addition. software was generated, and performance of rocket ejector was analyzed accounting for heat release location, flow parameters and structural configuration

    在理論方面，建立了引射火箭模態的性能分析模型，該模型考慮了化學反應放熱、加質和變幾何截面的影響；編寫了相應的軟體，並結合放熱位置、流動參數和發動機結構進行了引射火箭的概念設計。
  12. Submerged nozzles are commonly preferred in large solid rocket motors. the aft - end internal flows are very complex because of submergence. the flow process and mechanism are not very clear yet

    大型的固體火箭發動機通常採用潛入式噴管，其燃燒室尾部的流動非常復雜，流動過程及其機理尚不十分清楚。
  13. 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。
  14. In addition, the usaf continues to fund development work of the aerojet ( formerly atlantic research ) variable flow ducted rocket ramjet system as a future propulsion option for an extended range aam

    此外，美國空軍繼續投資于航空噴氣研究所（原來的大西洋研究所）的可變噴流管火箭發動機系統，將其作為增程空空導彈的未來推進選項。
  15. With zonal patched grid technology and second - order zonal solver method, the numerical simulation on inlet complex flow field of solid rocket ramjet assisted range projectiles with different struts shapes was made at different mach numbers

    摘要結合分區對接網格技術和二階精度區域分解演算法，對某沖壓增程彈丸進氣道在不同來流攻角和不同側向支柱形狀工況下的內外復雜流場進行了數值模擬。
  16. The main results are : supersonic region and subsonic region can co - exist in flow path simultaneously, subsonic flow is insignificance for engine performance ; total pressure of primary rocket should be decreased when mach number is increased. in the experimental aspect, some components of ejectorjet experimental system were improved, ejectorjet experiments using alcohol as secondary fuel were conducted

    由數值計算獲得的結論為：引射火箭內的一般流態為超音速區與亞音速區共存，亞音速區不具備做功能力；飛行馬赫數增大，引射火箭內更易於產生壅塞；為了獲得最佳的性能，隨著飛行馬赫數的提高，應當降低一次火箭的工作壓強。
  17. Gas flow control techniquc of rocket ramjct is discussed, and then some base idea and research achievements in the design of that are also expressed in the paper

    對固體火箭沖壓發動機燃氣流量調節技術進行了論述，闡述了固體火箭沖壓發動機燃氣流量調節技術在設計上的一些基本思想及研究成果。
  18. ( 3 ) on the background of the development of an ignition rocket, some application investigations have been carried out. some parameters related to water - resistant ignition mixture, the charge of ignition rocket, such as heat - flow, density of charges, structure of charges, coating and its process, area ratio of nozzle and high temperature corrosion of the nozzle, were calculated and studied, respectively. on the basis of the above studies, an ignition rocket was successfully developed

    （ 3 ）進行了應用研究，以某系列點火發動機的研製為背景，分別對耐水點火藥用作點火發動機裝藥所涉及的能量衡算、裝藥密度、裝藥結構、包覆及其工藝、喉面比及噴口燒蝕等問題進行了分析和實驗研究，在這些研究的基礎上成功地製作了一種點火發動機。
  19. 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。
  20. The influence of primary flow and secondary nozzle geometry on ejector effect and thrust was investigated, and the approach to increase thrust of rocket ejector was found gradually

    研究了一次流參數和二次噴管結構對引射效能和發動機推力的影響，找到了逐步提高推力的措施。
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