共查询到16条相似文献,搜索用时 140 毫秒
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建立了氢氧爆震波点火器试验系统,并根据试验塞式喷管发动机工作状态要求设计了爆震波点火器。在高空条件下(0.005 ̄0.002MPa),爆震波点火器供气压力0.3MPa、混合比3左右,对爆震波点火器的点火性能进行了试验,成功实现了高空条件下爆震波点火火炬。在同样高空条件下对爆震波点火器点燃单元塞式喷管试验发动机成功进行了点火试验。试验结果表明,氢氧爆震波点火器能以较低的供气压力实现可靠点火。爆震波点火器在气氢气氧单元塞式喷管试验发动机点火的成功应用,为下一阶段应用于多管塞式喷管发动机的实际点火试验提供了技术基础。 相似文献
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富氧预燃室初步试验研究 总被引:2,自引:0,他引:2
为了研究全流量补燃循环发动机中富氧预燃室的点火以及燃烧特性,对点火方案和预燃室方案进行了分析。通过对多种预燃室结构形式和点火方式的比较,提出了适合于富氧预燃室初步试验要求的点火方案,研制了热表面谐振点火器并采用间接点火方式研制了氢氧火炬点火器。点火器的试验结果表明氢氧火炬点火器能够多次可靠地点火并生成稳定的点火火炬。由于不受谐振产生条件的限制,氢气和氧气的流量和混合比可以在较大的范围内选择,生成点火火炬的温度范围也很宽。对确定的富氧预燃室方案进行了设计加工,经过三个阶段的热试车,富氧预燃室的关键参数均达到了设计要求,结构无烧蚀,工作可靠,完全可以满足全流量补燃循环发动机系统对富氧预燃室的要求。 相似文献
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本文介绍了新型低温上面级发动机Vinci点火系统的研制状况,它的工作原理与当前使用的上面级点火系统不同,该点火系统由火花火炬点火器、点火器高压供应系统和激励器构成.首次介绍了点火器组件的构成,讨论了点火器及激励器试验结果. 相似文献
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采用主动冷却方式对超燃冲压发动机进行热防护是解决其长时间工作的有效措施。针对超燃冲压发动机燃烧室恶劣的热环境,设计了一种基于碳化硅陶瓷基复合材料的主动冷却结构,建立了发动机主动冷却结构设计的数学模型。引入发动机冷却液流量系数,从飞行器整体热防护角度出发,以发动机燃烧室主动冷却结构中冷却液的出口温度为依据来评价超燃冲压发动机可以达到的最大工作马赫数,以及分析发动机冷却液流量系数、飞行高度和燃烧室化学反应当量比对最大工作马赫数的影响。结果表明,增加冷却液流量系数、适当降低飞行高度、一定范围内提高化学反应当量比,可降低冷却液出口温度,从而提高发动机的最大工作马赫数。 相似文献
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采用数值计算方法对氧化亚氮/丙烷火炬式点火器的燃烧室和火炬流场特性进行了数值仿真研究,获得了点火器在定混合比工况下工质流量对火炬性能的影响以及定流量工况下余氧系数对火炬性能的影响:在定余氧系数0.350工况下点火器燃烧室压强、火炬功率和点火有效长度与点火器的流量基本呈线性关系,有效火炬长度与实验中所观察到的基本一致;在定流量9 g/s工况下点火器燃烧室压强、喷管出口温度、火炬功率和点火有效长度随余氧系数的不断增加均先迅速增加到最高值后开始逐渐减小,燃烧室压强、喷管出口温度、火炬功率和点火有效长度的计算最高值分别为1.73 MPa,2 823 K,33.14 kW和86.5 mm. 相似文献
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液氧/甲烷燃气发生器点火方案研究 总被引:1,自引:0,他引:1
在对比化学点火、火药点火及电火花点火优缺点的基础上,选取了技术成熟、点火可靠的火药点火用于液氧/甲烷燃气发生器热试。用黑火药点燃固体推进剂的点火药量计算公式估算了火药点火药量,给出了液氧/甲烷燃气发生器火药点火器的其它参数。根据液氧/甲烷推进剂特点,确定了火药燃气-液氧-甲烷依次进入燃气发生器的点火时序。成功进行了4次液氧/甲烷燃气发生器热试,结果表明:液氧/甲烷燃气发生器点火起动过程平稳,点火品质较好,点火方案合理,适于较宽工作条件下的液氧/甲烷点火。 相似文献
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Sanders D. Rosenberg 《Acta Astronautica》1983,10(1):19-30
When the oxygen/hydrogen bipropellant combination was selected for use in the Space Shuttle Main Engine, it became apparent that many advantages may result if the Auxiliary Propulsion System Engines were to use the same propellants. A new ignition system, possessing a dramatically new level of reliability, durability and response, is required because the oxygen/hydrogen combination is not hypergolic and the projected missions will require a very large number of fast-response engine starts.The objective of this program was to obtain basic data for spark torch ignition methods at operating conditions typical of a Space Shuttle Orbiter Auxiliary Propulsion System. The research included ignition analysis and igniter design, fabrication and hot-fire test.Extensive testing of spark torch igniters was performed (chamber pressure, 206.8 N/cm2, 300 psia, nominal) in the Igniter-Only and Igniter-Complete Thruster (thrust, 6672 N, 1500 lbF, nominal) operational modes. Reliable, repeatable ignitions were obtained with spark energies of 1–10 mJ. Hot-fire test results showed there is no effect of back pressure (1.013 × 105 to 1.333 × 10?2 N/m2, 7.60 × 102 to 1 × 10?4 mm Hg) or low temperature (O2, 170 K, 306 R; H2, 107 K, 193 R) on the response of the igniter or the ignition delay of the thruster over the ranges tested. Igniter durability and pulse capability were demonstrated with 150 sec of continuous operation and 1000 consecutive pulses, respectively. Durability was further demonstrated with a series of 2500 Igniter-Complete Thruster ignitions at nominal chamber pressure. No limiting variables were encountered. The hot-fire test results showed the spark torch igniter is capable of meeting fully the typical Space Shuttle Orbiter Auxiliary Propulsion System mission requirements. 相似文献
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固体火箭发动机点火器流量的预示 总被引:1,自引:0,他引:1
本文讨论了三种典型点火器的流量预估技术,提出了点火器流量预示的物理和数学模型,给出了计算结果。为了验证计算结果,建立了实验装置,并进行了验证性实验。计算和实验结果吻合良好。本文提供的预示方法已成功应用于“织女一号”气象火箭和“织女三号”探空火箭研制任务中。 相似文献
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The dynamics of a two dimensional plane jet injected at the base of a step, parallel to the wall, in backward facing step flow geometry is numerically studied. The objective of this work is to gain insight into the dynamics of the igniter flow field in solid fuel ramjet motors. Solid fuel ramjets operate by ingestion of air and subsequent combustion with a solid fuel grain such as polyethylene. The system of governing equations is solved with a finite volume approach using a structured grid in which the AUSM+ scheme is used to calculate the convective fluxes. The Spalart and Allmaras turbulence model is used in these simulations. Experimental data have been used to validate the flow solver and turbulence model simulation results. The comparison of the numerical results and experimental data has validated the use of the adopted turbulence model for the study of this type of problem. A special attention is paid to the igniter jet exit location. It is shown that the wall jet igniter, issuing from the base of the step, drastically changes the structure of recirculating region of backward facing step flow and produces large and damaging shear stress on the fuel surface. Moving the igniter jet exit location to the top of the backward facing step changes the flow field favorably, by reducing the fuel surface shear stress by an order of magnitude and maintaining the recirculating region behind the step, which can provide proper residence time for the fuel–air mixture chemical reactions. 相似文献
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爆震波点火器用于工程,其设计存在一个最佳结合点,使得在合适的管路中,爆震波传播速度、转捩距离、爆震波能量等能够符合点火器目标需求。为了研制适用于工程的爆震波点火器,在氢氧爆震波点火器基本特性试验的基础上,对初始混合气体的混合比等与爆震波特性的关系进行了研究。对实验结果进行分析认为。混合比对爆燃爆震转捩(DDT)距离影响较大,混合比大于3时,其转捩距离小于500mm。混合比增加时,爆震波传播速度会减小,但稳定的爆震波相对于波的混气的马赫数并小减小,维持在4.8左右。在初始混气压力不变情况下,质量流量可以提高爆震波能量,增强爆震波的点火能力。研究结论时爆震波点火器在工程中实际应用及以后的研究方向具有指导性作出。 相似文献