rocket pressure 中文意思是什麼
rocket pressure
解釋
火箭燃燒室壓力-
Gas generator rocket can pressurize a high-pressure feed system.
燃氣發生器能使高壓輸送系統增壓。 -
It can be used not only to change the fire precision of the base bleed projectile, but also to improve the effect of reduction drag and expansion range. the calculating model of the secondary expansive pressure of the burning gas is constructed by means of analysis of the experimental resuits, it has been confirmed that the new base bleed unit can be designed, with the secondary expansive principle of the burning gas pressure. the engineering project of a hybrid base - bleed - rocket high - level efficient extended - range projectile is designed, with the secondary expansive principle of the burning gas pressure, the feasibility and the true worth of its engineering applications is validated in theory
本文提出了底排燃氣壓力不隨外部壓力變化，既可改善底部彈射擊精度又可提高減阻效果的二次擴張原理，建立了底排燃氣二次擴張壓力的計算模型，並通過採用二次擴張原理的新型底排裝置與傳統底排裝置的對比試驗，驗證了新型底排裝置結構實現的可行性；完成了基於底排燃氣二次擴張高效增程原理的底排?火箭復合高效增程彈方案設計及其有關計算，從理論上驗證了其工程應用的可行性和實際價值。 -
Design optimization of chamber pressure and nozzle area expansion ratio of solid rocket motors
固體火箭發動機燃燒室壓強及噴管擴張比優化設計 -
The effect of area ratio, mach number, total pressure of primary rocket and geometry structure of primary rocket on ejectorjet performance was studied
通過數值計算研究了引射火箭堵塞比、來流馬赫數、一次火箭燃燒室總壓、一次火箭構型對引射火箭性能的影響。 -
The burning surface of the powder then increases, the pressure rises and the rocket may be blown up.
此時，無煙藥燃燒表面增加，壓力上升，火箭可能爆炸。 -
In the wave trough of the pressure curve, the pressure may be then if the rocket is accelerating or if it has assembling defects, the early explosion of the grenade on the ballistic may be caused
該模型的微分方程計算結果表明微小彈簧在彈道上的振動過程會使導電桿的受壓產生周期性變化，尤其是在一些波谷處，導電桿幾乎不受壓力，此時如果有火箭加速和其它裝配缺陷等因素的影響，就會引起彈丸在彈道上的早炸。 -
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。 -
It has a large region of application in solid rocket motor grain design and has made new improvements compared with other available codes. user can easily and rapidly build his initial grain shapes and then obtain geometric information of his design. according to the theory describeds in the paper, the regressions of the burning surface area and the pressure are obtainded
該系統擴展了固體火箭發動機裝藥的設計能力，用戶可利用它簡捷地構造出三維藥柱的初始形狀，並獲得設計所需的各個幾何參數，進而依據本論文提出的復雜三維藥柱內腔燃燒推移和燃面計算的方法，計算出燃面變化和壓強變化，得到推力隨時間變化的曲線，再依據這些計算結果進行再設計，直至達到滿意的結果為止。 -
Study on strap - on pressure propellant loading process for solid rocket motor
固體發動機捆綁式加壓成型裝藥工藝研究 -
In this way, supersonic fluid amplifier especially bistable valve with negative pressure switch is used in the rocket projectile thanks to its advantages of switching rapidly, the ability of low temperature air to control the high temperature gas and no moving parts in high temperature gas
超音速射流雙穩閥，特別是採用負壓切換的超音速射流雙穩閥因其具有切換快速、可用低溫氣流控制高溫燃氣和在高溫燃氣中無活動部件的優點而適用於火箭彈的姿態控制系統中。 -
The scraping coat technique for the thin layer propellant loading processing in mini inside radius solid rocket motor, precuring - bonding technique and secondary vacuum - pressure casting are developed and used to load the big slenderness ration ( 12. 5 / 1 ) solid rocket motor with thin web, internal insertion radial concentric dual - layer propellant
探索出小口徑薄層藥刮塗成型工藝、預固化粘結技術，二次真空加壓澆注，實施了大長細比（ 12 5 1 ）發動機薄肉厚內嵌式徑向同心雙層裝藥。 -
The results showed that the environmental pressure and catalysts have various actions on the thermal decomposition characteristics of the propellant and its ingredients. the burning rates of the gap / tmo fuel - rich propellants were measured by use of the pipe - connected unchoked ducted rocket testing facility
實驗結果表明，在不同壓強下，貧氧推進劑各組分的熱分解特徵有所不同；在同一壓強下， tmo催化劑對貧氧推進劑中不同組分的催化作用不盡相同；同一催化劑，在不同壓強下對同一組分的催化能力也不同。 -
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 -
A high - pressure vessel, made of filament - wound composite, has been used in many demanding applications such as rocket generator cases, and oxygen and hydrogen tanks etc. in the aeronautic and astronautic industry, because of having many advantages
纖維纏繞高壓復合容器具有許多優點而應用在航空和航天工程領域，例如：火箭發動機箱體，高壓氧氣或氫氣儲存器等。 -
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。 -
Moreover, the data processing method of accelerated life test is used to solve the problem of the reliability data conversion under different operating status to liquid rocket engine. and the counter power law model is introduced as the relation model between the characteristic life and the combustion chamber pressure, the accelerated life equation of the constant stress accelerated life test for the weibull distribution is obtained, through the accelerated life equation, the reliability estimate of different combustion chamber pressure is calculated
再次，採用加速壽命試驗的數據處理方法對液體火箭發動機不同工況下可靠性數據折算的問題進行了研究，引入逆冪律模型作為特徵壽命與燃燒室壓力之間的關系模型，得到了weibull分佈下恆定應力加速試驗的加速壽命方程，並通過加速壽命方程折算出不同室壓下的可靠度估計。 -
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。 -
Liquid rocket engine is a thermal kinetic system, it runs under extremely strict physical conditions, such as high temperature, high pressure, strong erosion, high density of energy release, strong components parameters coupling. it is very difficult to establish accurate dynamic mathematical model
液體火箭發動機是一種在極端的物理條件（如高溫、高壓、強腐蝕和高密度的能量釋放等）下運行的復雜的流體-熱動力系統，部件參數強烈耦合，很難建立精確的動態數學模型。 -
Firstly, the load - deformation relationship of the flanged connection system for rocket motors is analyzed by elastic theory, in which the flanged system is regarded as integer, in the same time, the effects of interior pressure and rotation of flange ring on load - deformation of flanged connection system are considered. compared with traditional methods that neglect the rotation of flange, the present approach is closer to the actual situation
將墊片螺栓法蘭作為一個整體，考慮到法蘭旋轉和內壓對法蘭連接系統受力與變形的影響，與不考慮法蘭旋轉的現有方法相比，能更好地反映法蘭系統的受載情況。
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