In this paper, employing rigorous variational calculus, equations of control surface at maximum thrust nozzle exit are derived.
本文用严格的变分法导出了最大推力喷管出口控制面方程。
The condition of the existence of solution of functional extreme value problem applied to maximum thrust nozzle is also presented.
同时，还导出了最大推力喷管这个泛函极值问题解存在的条件。
How can a rocket engine that generates 5,000 degree steam and 13,800 pounds of thrust form icicles at the rim of its nozzle?
一个能制造出5000度高温蒸汽和13800磅推力的火箭推进器，是怎样使喷口边缘结冰的呢？
The computing method of differential throttling and the analytical process of thrust vector of inner nozzle and plug were introduced. The generated moments of pitch were given.
介绍了差分流量调节的计算方法和内喷管与塞锥推力矢量变化的分析过程，计算产生的俯仰力矩。
Thrust vector control is often achieved by throttling individual thrusters or by injecting gas through the nozzle wall to cause a change in the local pressure distribution.
推力矢量控制，往往所取得的节流个别推力器或注入气体通过喷嘴壁造成的变化在当地的压力分布。
The deflecting nozzle thrust vector control is usually used in a large solid booster.
对大型运载火箭的固体助推器，通常采用摆动喷管推力向量控制。
There exists an optimal exit area of secondary nozzle to result in a maximum thrust of rocket ejector in the light of the investigated ejector chamber structure.
在文中所研究的引射燃烧室结构条件下，存在一个最佳二次喷管出口面积，它能使引射火箭的推力达到最大。
Based on a thermal model of monopropellant thrust chamber system including its components such as adiabatic frame, catalyst bed, nozzle etc.
建立了单组元发动机推力室系统（包括结构部件如隔热框、催化床、喷管等）的传热模型。
Under the same wall heat condition, with the increase of momentum correction coefficient, viscosity loss of the nozzle increases, but thrust and specific impulse decrease.
在同等壁面热条件下，随着动量调节系数的增加，喷管粘性损失增大，喷管的推力和比冲都将下降；
When numbers of the inner nozzle are enough, plug nozzle has less size, less weight and higher thrust efficiency than the bell nozzle under same area ratio.
在单元数足够多时，环簇式塞式喷管可比相同面积比的钟形喷管的尺寸更小，重量更轻，推力效率更高；
For the movable TVC, the thrust and lateral forces with respect to nozzle deflection angles and the depth of water were obtained.
对摆喷管推力矢量方式，获得了推力、侧向力、推力矢量角随发动机喷管偏角以及水深的变化规律。
Test results from an experimental investigation of the effect of nozzle on the thrust of a straight tube pulse detonation engine are presented.
在直管脉冲爆震发动机上安装不同类型的喷管，利用推力传感器测量了不同频率下发动机的瞬态推力和平均推力。
Experimental tests and applications on rockets show that the mini thrust misalignment nozzle exists and the new method of design is feasible.
试验和应用表明，微推偏喷管是存在的，新设计方法是可行的。
Lastly, the results of unsteady flow point out, counterflow thrust vectoring nozzle is a efficiency fluidic vectoring nozzle.
最后，非定常流的结果进一步表明，逆流喷管是一种较高效率的射流式矢量喷管。
The thrust characteristics of axis symmetry nozzle were mainly measured in test. For the nozzle having a vectoring angle, the deflection efficiency was measured too.
对于轴对称喷管模型主要进行了喷管的推力特性测量，对于实施矢量偏转后的喷管模型除了给出了喷管推力特性外，还给出了喷管的偏转效率。
Thrust misalignment in parabolic nozzle is investigated for the situation where the gas flow is misaligned with respect to the axis of the supersonic region of the nozzle.
研究了当气流偏离抛物型喷管超音速段对称轴时所引起的喷管推力偏心。
The scarfed nozzle is used in engines which can produce reversal thrust, or to produce revolving torque on turbine rocket engines at high speed.
斜切喷管+常用于产生反向推力，或产生旋转力矩使火箭高速旋转的涡轮式火箭发动机中。
Systematic researches on combined nozzle and its flow regulation, as well as thrust vector technologies are carried out in this dissertation.
围绕组合喷管及其流量分配调节和推力矢量技术，本文开展了系统性研究。
Results show that pintle could change the nozzle throat area and thus the motor pressure and thrust, which provided the capability for thrust control.
结果显示喉栓能够有效改变发动机燃烧室压力和推力，满足发动机推力控制要求。
The mathematical model of turbofan engine transient process with thrust vectoring nozzle was established.
建立带矢量喷管的涡扇发动机动态数学模型。
By measuring the thrust and lateral forces of solid rocket motor during firing conditions, the thrust vector control performances of jet TAB TVC and movable nozzle TVC were studied.
通过测量固体火箭发动机水下工作过程中的推力和侧向力，研究了扰流片和摆喷管两种推力矢量方式的水下推力矢量特性。
By allowing the influence of ambient pressure to be transmitted to the nozzle wall, the aerospike yields a net thrust advantage over conventional bell-type nozzles.
允许的影响，环境压力，以传送给喷嘴墙，气动收益率，净推力的优势，与传统的罩式喷嘴。
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.
研究了一次流参数和二次喷管结构对引射效能和发动机推力的影响，找到了逐步提高推力的措施。
The gases which form expand rapidly, and are exhausted through the rear of the combustion chambers and out through the nozzle (blow) providing the forward thrust.
这些气体的形式迅速扩大，并通过燃烧室，并通过喷嘴（打击）提供前进推力出后用尽。
Internal performance of unsteady flow of counterflow thrust vectoring nozzle has researched base on numerical simulation.
基于数值模拟方法，研究了逆流矢量喷管非定常内流性能。
The truncated nozzle is found to have a higher thrust.
截断的喷管具有较大的推力。
As thrust vectoring nozzle is the feature of advanced fighters, the difficulties in implementing thrust vectoring are summarized.
矢量喷管是先进战斗机的特征，本文讨论了实现推力矢量存在的技术难点。
Computational investigation of secondary flow thrust vector control technology used in a convergent-divergent nozzle;
采用六分力试验技术对某推力矢量发动机燃气舵的气动特性进行了试验研究。
Results show that the thrust aroused from the altitude compensation capability is the cause of the non-monotone variation of nozzle efficiency with altitude at high ambient pressure;
结果表明，在高的环境压强下工作时，由塞式喷管的高度补偿能力所获得的推力是引起效率高度特性曲线非单调变化的原因；
Results show that the thrust aroused from the altitude compensation capability is the cause of the non-monotone variation of nozzle efficiency with altitude at high ambient pressure;
结果表明，在高的环境压强下工作时，由塞式喷管的高度补偿能力所获得的推力是引起效率高度特性曲线非单调变化的原因；
应用推荐