APPT FOR LEO APPLICATIONS

机译：适用于Leo应用程序

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Paper presents the estimate of Ablative Pulsed Plasma Thruster (APPT) models for LEO applications. The models developed in RIAME within last decade cover 20- 150 J bank energy range. These have high efficiency and are attractive onboard EP option for Small Spacecrafts (SSC) due to their simplicity, low mass, appropriate power level, high Isp and low cost. Main characteristics of modern high thrust efficiency APPT developed in Russia with the bank energy range 20- 150 J are presented. The threat of contamination of SSC and its functional instrumentation is tested. It is observed that decreasing of an integral transparency of optical devices in visible area of a spectrum during APPT service life will not exceed 2.5 % that much lower than effect of space factors. Inductive electromagnetic disturbances also have not dangerous value. SSO orbits from 500 to 900 km and SSC with mass 100-350 kg are considered. For LEO applications PPT technology shows the high competitiveness between other small propulsion systems developed for SSC orbit control (translational maneuvers, orbit maintenance and positioning). Accounts of total impulse, propulsion system mass and propellant consumption for producing all types of orbit maneuvers for SSCs, having 7 - 10 years service life, are presented for a number of missions. The use of APPT in the spacecraft control systems were assessed for a heavy spacecraft of 2 500 kg in mass. PPT based propulsion system for a heavy spacecraft attitude control allows substantial savings in the total impulse and propulsion system mass.

机译：纸张介绍了Leo应用的消融脉冲血浆推进器（APPT）模型的估计。在过去十年内覆盖了20-150 J银行能量范围内的Riame在Riame开发的模型。由于其简单性，低质量，适当的功率水平，高ISP和低成本，这些具有高效率，并且对于小型航天器（SSC）具有吸引力的SPACECRAFT（SSC）是有吸引力的。俄罗斯在俄罗斯开发的现代高推力效率的主要特点，提供了银行能量范围20-150 j。测试了SSC的污染威胁及其功能仪表。观察到，在APPT服务寿命期间，光谱的可见区域中光学器件的积分透明度的减小将不超过空间因素的效果远低于2.5％。电感电磁干扰也没有危险的价值。 SSO轨道从500到900公里和SSC的SSC考虑为100-350千克。对于Leo应用PPT技术显示出用于SSC轨道控制（平移演习，轨道维护和定位）的其他小型推进系统之间的高竞争力。为许多任务提出了一系列脉冲总脉冲，推进系统质量和推进剂消费，为SSCS提供了7至10年的SSCs的所有类型的轨道演习。将Appt在航天器控制系统中的使用被评估为200kg质量的厚重航天器。基于PPT的沉重航天器姿态控制的推进系统允许在总脉冲和推进系统质量中进行大量节省。

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《International spacecraft propulsion conference》|2004年||共6页
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Nikolay N. Antropov; Garry A. Popov; Michael N. Kazeev; Vladimir P. Khodnenko;
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中图分类推进系统（发动机、推进器）;
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APPT FOR LEO APPLICATIONS

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