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1.
内装式空射运载火箭重力出舱机箭耦合动力学分析 总被引:1,自引:1,他引:0
研究了以运输机为平台的内装式运载火箭空射过程载机和火箭的耦合动力学建模。建模针对两个阶段:第一阶段,火箭固定于载机机舱内,两者构成一个整体,按照普通刚体的力学方法处理;第二阶段,火箭解锁后,沿着舱内的发射筒向外滑行,载机和火箭形成两刚体相互作用的耦合系统,基于牛顿-欧拉法建立系统动力学模型。载机在空射火箭过程中,油门和升降舵满偏,在加速前飞的同时拉大姿态俯仰角,火箭在自身重力分量和惯性力的作用下,沿着机舱内的发射筒加速向外滑行,直至与载机分离。数值仿真分析了空射过程载机的重要力学参数的变化过程,验证了载机操控策略的可行性和安全性,可为未来中国空射运载火箭技术设计提供数据参考。 相似文献
2.
《中国航空学报》2021,34(5):617-627
In this paper, a progressive approach to predict the multiple shot peening process parameters for complex integral panel is proposed. Firstly, the invariable parameters in the forming process including shot size, mass flow, peening distance and peening angle are determined according to the empirical and machine type. Then, the optimal value of air pressure for the whole shot peening is selected by the experimental data. Finally, the feeding speed for every shot peening path is predicted by regression equation. The integral panel part with thickness from 2 mm to 5 mm and curvature radius from 3200 mm to 16000 mm is taken as a research object, and four experiments are conducted. In order to design specimens for acquiring the forming data, one experiment is conducted to compare the curvature radius of the plate and stringer-structural specimens, which were peened along the middle of the two stringers. The most striking finding of this experiment is that the outer shape error range is below 3.9%, so the plate specimens can be used in predicting feeding speed of the integral panel. The second experiment is performed and results show that when the coverage reaches the limit of 80%, the minimum feeding speed is 50 mm/s. By this feeding speed, the forming curvature radius of the specimens with different thickness from the third experiment is measured and compared with the research object, and the optimal air pressure is 0.15 MPa. Then, the plate specimens with thickness from 2 mm to 5 mm are peened in the fourth experiment, and the measured curvature radius data are used to calculate the feeding speed of different shot peening path by regressive analysis method. The algorithm is validated by forming a test part and the average deviation is 0.496 mm. It is shown that the approach can realize the forming of the integral panel precisely. 相似文献
3.
航天应用的液体火箭发动机及燃烧型加热器燃烧室室压高、燃料流量大、温度低、有重复启动需求,实现安全可靠点火的难度较大。针对这些需求,研究了一种采用高背压设计的电弧等离子体点火器。实验研究了Ar,N2气体工质在高进气压力下的伏安特性,发现N2在宽压力范围内适用于点火。发射光谱分析表明,在高达数MPa的进气压力下,Ar,N2等离子体射流电子密度符合局部热力学平衡判据(LTE判据),点火能量集中。N2等离子体整体温度低于Ar,但阳极喷口附近温度高于Ar,N2等离子体射流火焰长,卷吸沿程空气造成射流平均温度偏低,但有助于低温液体推进剂的蒸发混合和强化点火。等离子体射流引起了臭氧和氮氧化物的形成,具有促进点火和化学反应的作用。背压提高引起电源输出电压升高,提高供气压力和电流,有助于点火器在高背压环境中稳定电压。燃烧型空气加热器燃烧室的点火实验发现,采用N2等离子体喷注面中心点火,可以在短时间内完成酒精-空气和酒精-液氧-空气的点火,最高燃烧室室压接近5MPa时,点火器仍能稳定工作,多次使用电极烧蚀不明显,在液体火箭发动机的重复可靠点火方面具有很好的应用前景。 相似文献
4.
A numerical procedure for the calculation of the transonic dip of airfoils in the time domain is presented. A viscous-inviscid aerodynamic interaction method is taken to calculate the unsteady aerodynamic loads. In the present case the integral boundary layer equations are coupled with the Transonic Small Disturbance (TSD) Potential Equation. The coupling between structural motion and aerodynamic loads is carried out using State Space equation. It is solved by State Transition Matrix technique. Results are presented for NACA 64A010 and NLR 7301 airfoils with structural data from Isogai and DLR, respectively. Comparisons show good agreement with other numerical results. Certain deviations of experimental data taken from literature need more insight in the detailed test conditions. 相似文献
5.
Steven D. Howe 《Space Policy》2001,17(4):275-283
The potential benefits to humankind of space exploration are tremendous. Space is not only the final frontier but is also the next marketplace. The orbital space above Earth offers tremendous opportunities for both strategic assets and commercial development. The critical obstacle retarding the use of the space around the Earth is the lack of low cost access to orbit. Further out, the next giant leap for mankind will be the human exploration of Mars. Almost certainly within the next 30 years, a human crew will brave the isolation, the radiation, and the lack of gravity to walk on and explore the Red planet. Both of these missions will change the outlook and perspective of every human being on the planet. However, these missions are expensive and extremely difficult. Chemical propulsion has demonstrated an inability to achieve orbit cheaply and is a very high-risk option to accomplish the Mars mission. An alternative solution is to develop a high performance propulsion system. Nuclear propulsion has the potential to be such a system. The question will be whether humanity is willing to take on the challenge. 相似文献
6.
介绍自行研制的VKM—5型立式捏合机的构造及工作原理,详述了该机采用液压传动和气动元件进行位置检测以及气、电、液安全联锁的特点,并说明与卧式捏合机对比试验情况。 相似文献
7.
根据工作实践研究了固体发动机切线照相无损检测中黑度分布、散射线防治、象质计使用、检测概率计算、脱粘临界值确定等技术问题. 相似文献
8.
球形铝粉的凝聚/燃烧特性 总被引:7,自引:0,他引:7
球形与非球形铝粉的表面分析表明,前者表面层比后者均匀;试验表明球形铝粉比非球形铝粉抗凝聚能力好,化学反应能力较差.因此球形铝粉在推进剂燃面形成的凝滴较小,凝滴燃烧速度较慢.这些特性对球形铝粉的合理使用具有指导意义. 相似文献
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