DESIGN OF THE AIRLIFTED NANO-LAUNCHER PERSEUS

机译：气化纳米发射器的设计

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PERSEUS is a two stages rocket which is launched from an Unmanned Aerial Vehicle (UAV) at 16,000m. The launcher is designed to deploy nano-satellites of 10kg into a polar orbit at an altitude of 250km. The vehicle is based on hybrid engines for both stages using hydrogen peroxide and paraffin. Analysis on structure, aerodynamics, and systems finished with the design of a complete launcher. Finally, an in house code for the trajectory validates the performance of the 4.2t nano-launcher on the polar orbit. The choice of a simple design and the low cost paraffin and hydrogen peroxide couple, makes the nano-launcher PERSEUS an affordable and adequate solution to access the actual nano-satellite market.

机译：PERSEUS是两级火箭，从16,000m的无人飞行器（UAV）发射。该发射器旨在将10kg的纳米卫星部署到250km的极地轨道上。该车辆基于混合动力发动机，两个阶段均使用过氧化氢和石蜡。结构，空气动力学和系统分析完成了完整的发射器的设计。最后，该轨迹的内部代码验证了4.2t纳米发射器在极地轨道上的性能。选择简单的设计以及低成本的石蜡和过氧化氢对，使纳米发射器PERSEUS成为进入实际的纳米卫星市场的负担得起的适当解决方案。

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《International Astronautical Congress(IAC2006); 20061002-06; Valencia(ES)》|2006年|P.92959305|共2页
会议地点 Valencia(ES)
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正文语种 eng
中图分类航天（宇宙航行）;
关键词
a, b: regression rate coefficient; ΔV: launcher increment speed; C_(x,p): drag coefficient induced by pressure; Θ_(rel): trim angle; δ: thrust deflexion angle; f: ratio of the fairing length and diameter; i: incidence angle; Isp: delivered specific im;

机译：a，b：回归速率系数;ΔV：发射器增量速度; C_（x，p）：压力引起的阻力系数;Θ_（rel）：纵倾角;δ：推力偏转角; f：整流罩长度与直径之比; i：入射角; Isp：传递的特定im;

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DESIGN OF THE AIRLIFTED NANO-LAUNCHER PERSEUS

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