APPT FOR LEO APPLICATIONS

机译：LEO应用程序的APPT

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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：论文介绍了用于LEO应用的烧蚀脉冲等离子推进器（APPT）模型的估计。在RIAME中开发的模型在过去十年中覆盖了20- 150 J库的能量范围。它们具有高效率，并且由于其简单，质量轻，功率水平合适，Isp高和成本低等优点而成为小型航天器（SSC）的机载EP选件。介绍了俄罗斯开发的现代高推力效率APPT的主要特征，其能量范围为20-150J。测试了SSC及其功能仪表受到污染的威胁。可以观察到，在APPT使用寿命期间，光学设备在光谱的可见区域内的整体透明度的降低不会超过空间因素的影响的2.5％。感应电磁干扰也没有危险价值。可以考虑500至900 km的SSO轨道和100-350 kg质量的SSC。对于LEO应用而言，PPT技术在为SSC轨道控制（平移操纵，轨道维护和定位）而开发的其他小型推进系统之间显示出很高的竞争力。提出了许多任务的总冲量，推进系统质量和推进剂消耗量的说明，这些冲量，寿命为7至10年的SSC产生各种类型的轨道操纵。评估了质量为2500公斤的重型航天器在航天器控制系统中使用APPT的情况。用于重载航天器姿态控制的基于PPT的推进系统可大幅节省总的推进和推进系统质量。

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来源
《4th International spacecraft propulsion conference》|2004年|p.1-6|共6页
会议地点 Sardinia(IT)
作者
Nikolay N. Antropov; Garry A. Popov; Michael N. Kazeev; Vladimir P. Khodnenko;
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作者单位

Research Institute of Applied Mechanics and Electrodynamics,4, Volokolamskoye shosse, Moscow, 125810,Russia, E-mail:riame@sokol.ru;

Research Institute of Applied Mechanics and Electrodynamics,4, Volokolamskoye shosse, Moscow, 125810,Russia, E-mail:riame@sokol.ru;

Russian Research Centre Kurchatov Institute, 1, Kurchatov sq., Moscow, 123182, Russia;

E-mail: kazeev@nfi.kiae.ru;

All-Russian Research Institute of Electromechanics,101000, P.O. Box 496, Moscow, Russia;

E-mail: vniiem@orc.ru;

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原文格式 PDF
正文语种 eng
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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