排序方式: 共有9条查询结果,搜索用时 334 毫秒
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本文研究了硫酸钡在氨水溶液中与EDTA的反应条件,提出用EDTA滴定法测定三硝基间苯二酚中的硫酸。本法准确度较高,稳定性好,操作简单,与样品标准值对照,结果满意。 相似文献
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研究了NH3-NaSCN吸收式热泵系统的可能温度组合、有无回热器两种情况系统的热力参数和性能,如:吸收器和发生器中溶液浓度,循环倍率以及有无回热器时系统基于焓的性能系数等,分析了工作温度对系统性能的影响,结果表明,有无回热器时工作温度对系统性能的影响是不一致的。 相似文献
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Harry W. Jones Mark H. Kliss 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2010
As NASA implements the U.S. Space Exploration Policy, life support systems must be provided for an expanding sequence of exploration missions. NASA has implemented effective life support for Apollo, the Space Shuttle, and the International Space Station (ISS) and continues to develop advanced systems. This paper provides an overview of life support requirements, previously implemented systems, and new technologies being developed by the Exploration Life Support Project for the Orion Crew Exploration Vehicle (CEV) and Lunar Outpost and future Mars missions. The two contrasting practical approaches to providing space life support are (1) open loop direct supply of atmosphere, water, and food, and (2) physicochemical regeneration of air and water with direct supply of food. Open loop direct supply of air and water is cost effective for short missions, but recycling oxygen and water saves costly launch mass on longer missions. Because of the short CEV mission durations, the CEV life support system will be open loop as in Apollo and Space Shuttle. New life support technologies for CEV that address identified shortcomings of existing systems are discussed. Because both ISS and Lunar Outpost have a planned 10-year operational life, the Lunar Outpost life support system should be regenerative like that for ISS and it could utilize technologies similar to ISS. The Lunar Outpost life support system, however, should be extensively redesigned to reduce mass, power, and volume, to improve reliability and incorporate lessons learned, and to take advantage of technology advances over the last 20 years. The Lunar Outpost design could also take advantage of partial gravity and lunar resources. 相似文献
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运用Gaussian03W计算程序,在B3LYP/6—31G(d)方法水平上得到了氨质子化团簇(NH3)nH^+(n=1~8)的最稳定构型,并对其相应红外振动光谱进行了研究。通过对红外振动光谱中谱峰位置与振动模式之间的关系的分析,发现光谱中的最强峰均来自于NH4^+核中N—H键的反对称伸缩振动(n=2除外)。 相似文献
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《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2023,71(1):456-476
This paper presents a design of solar thermal propulsion (STP) system for microsatellite with liquid ammonia as propellant. The system was equipped with two concentrators, which were respectively placed in the tank and thrust chamber for propellant supply and heating. A platelet heat exchanger was adopted to heat the propellant in the chamber, and the fluid–solid coupling effect between the wall and the gas was considered. Meanwhile, the effects of satellite mass, initial orbit, nozzle size and target temperature on the performance of STP system were analyzed. The results show that for microsatellites with a total mass of 100 kg, the STP system can fully heat the propellant to more than 2050 K, generate an intermittent thrust of about 26 N, and enable the satellite to obtain a velocity increment of more than 1470 m/s within 19 days, consuming only 42 kg of propellant, which can directly meet the transfer mission from the geostationary transfer orbit (GTO) to the geostationary orbit (GEO). The maximum velocity increment could reach more than 1950 m/s when the propellant was completely consumed; Changing the mass and initial orbit of the satellite will not affect the thrust and specific impulse. Satellites with smaller mass will spend less time and propellant during orbit transfer. The lower is the perigee height of the initial orbit, the greater is the propellant consumption, while the shorter is the time of orbit transfer; The reduction of nozzle throat size and target temperature will lead to the increase of specific impulse and the decrease of orbital transfer time, but the reduction of thrust. 相似文献
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ADYNAMICMODELOFTHESOLAR-POWEREDSOLIDABSORPTIONREFRIGERATIONSYSTEMLinGuiping;MeiZhiguang(Faculty505,BeijingUniversityofAeronau... 相似文献
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某零组件渗氮时,其渗氮层易出现裂纹及剥落的问题。经研究发现,1Cr11Ni23Ti3MoB材料渗氮时,由于渗氮温度、氨分解率过低,导致零件表面氮势过高,极易在渗层内产生大量微裂纹,并会导致渗层表面出现剥落的现象。通过控制渗氮温度、渗氮时间、氨分解率,有效的解决该类质量问题。 相似文献
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