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IN-ORBIT COLLISION ANALYSIS FOR VEGA SECOND FLIGHT

机译：VEGA第二次飞行的在轨碰撞分析

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ELV, as prime contractor of the VEGA launcher, whichrnoperates in the protected LEO zone (up to 2000 kmrnaltitude), has to demonstrate that it abides by ESArndebris mitigation rules, as well as by those imposed byrnthe French Law on Space Operations (LOS).rnAfter the full success of VEGA qualification flight, thernsecond flight(VV02) will extend the qualificationrndomain of the launcher to multi-payload missions, withrnthe release of two satellites (Proba-V and VNRedSat-1)rnand one Cubesat (ESTCube-1) on different SSO orbitsrnThe multi-payload adapter, VESPA, also separates itsrnupper part before the second payload release. This paperrnwill present the results of the long-term analyses on inorbitrncollision between these different bodies.rnTypical duration of propagation requested by ELVrncustomer is around 50 orbits, requiring a state-of-the-artrnsimulator able to compute efficiently orbits disturbs,rnusually neglected in launcher trajectory optimizationrnitself. To address the issue of in-orbit collision, ELV hasrntherefore developed its own simulator, POLPO [1], arnFORTRAN code which performs the long-termrnpropagation of the released objects trajectories andrncomputes the mutual distance between them.rnThe first part of the paper shall introduce the simulatorrnitself, explaining the computation method chosen andrnbriefly discussing the perturbing effects and theirrnmodels taken into account in the tool, namely:rn1 gravity field modeling (zonal and tesseralrnharmonics)rn2 atmospheric modelrn3 solar pressurern4 third-body interactionrnA second part will describe the application of the inorbitrncollision analysis to the second flight mission.rnMain characteristics of the second flight will bernintroduced, as well as the dispersions considered for thernMonte-Carlo analysis performed. The results of thernlong-term collision analysis between all the separatedrnbodies will then be presented and discussed.
机译：ELV作为VEGA发射器的主要承包商，它在受保护的LEO区域（海拔高度高达2000公里）内沉没，必须证明它遵守ESArndebris缓解规则以及法国太空操作法（LOS）所施加的规则。在VEGA资格飞行完全成功之后，第二次飞行（VV02）将把发射器的资格范围扩展到多有效载荷任务，同时释放两颗卫星（Proba-V和VNRedSat-1）和一枚立方体卫星（ESTCube-1）。不同的SSO轨道多有效载荷适配器VESPA在第二个有效载荷释放之前也将其上部分开。本文将介绍对这些不同物体之间的轨道碰撞进行长期分析的结果。ELV客户的典型传播持续时间约为50轨道，需要一种能够有效计算轨道干扰的先进仿真器，在发射器中通常被忽略轨迹优化为了解决在轨碰撞的问题，ELV因此开发了自己的模拟器POLPO [1]，arnFORTRAN代码，该代码执行释放物体轨迹的长期传播并计算它们之间的相互距离。rn本文的第一部分将介绍模拟器本身，说明选择的计算方法，并简要讨论该工具中的扰动效应及其模型，即：rn重力场建模（区域和阶谐谐波）rn 2大气模型rn 3太阳压力rn 3第三体相互作用rn第二部分将描述将介绍第二次飞行任务的轨道碰撞分析。第二次飞行的主要特征以及进行蒙特卡洛分析时考虑到的弥散将被介绍。然后将介绍和讨论所有分离体之间的长期碰撞分析结果。

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  • 会议地点 Darmstadt(DE)
  • 作者

    M. Volpi; T.Fossati; F. Battie;

  • 作者单位

    ELV S.pA., C.so Garibaldi 22 Colleferro (RM) 00034 Italy, Email: matteo.volpi@elv.it;

    ELV S.pA., C.so Garibaldi 22 Colleferro (RM) 00034 Italy, Email: tommaso.fossati@elv.it;

    ELV S.pA., C.so Garibaldi 22 Colleferro (RM) 00034 Italy, Email: francois.battie@elv.it;

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