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首页> 外文会议>International astronautical congress >ADAPTIVE LOW RADIATION MULTIBODY GRAVITY ASSIST TOURS DESIGN IN JOVIAN SYSTEM FOR THE LANDING ON JOVIAN'S MOONS
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ADAPTIVE LOW RADIATION MULTIBODY GRAVITY ASSIST TOURS DESIGN IN JOVIAN SYSTEM FOR THE LANDING ON JOVIAN'S MOONS

机译：JOVIAN系统上的自适应低辐射多体重力辅助旅行设计

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Mission design of low-cost gravity assists tours in the Jupiter system for the landing on the Galilean moon is considered, taking radiation hazard into account. Limited dynamic opportunities of using flybys require multiple gravity assists. Relevance of regular creation of optimum scenarios -sequences of passing of celestial bodies with definition of conditions of their execution is obvious. This work is devoted to the description of criteria for creation of such chains. The problem is that the reduction of the asymptotic velocity Voo of the spacecraft with respect to the satellite for long close approaches is impossible. A valid reason consist in the invariance of Jacobi's integral and Tisserand's parameter in a circular restricted three-body model (CR3BP). Furthermore, the same-body flybys sequence on the Tisserand-Poincare graph falls according the V∞-isoline to the extra radiation zone. Heuristic formalization of overcoming the "endgame ballistic paradox" for providing long close approach with the satellite solved by the way of model's lifting up to the four-body configuration. Classes of "crossed" gravity assists from one small body of "first" sub-CR3BP ("Ganymede") to the second (with small body "not Ganymede"- mostly Callisto) and then - in the opposite direction are introduced. Regular formal overcoming the Tisserand's criterion becomes possible in new class of solutions. The region of exceeding of the total received radiation dose (TID) skirted along the "upper corridor" of Tisserand's graph. Withal low-cost reduction of the spacecraft asymptotic velocity required for approaching. The search for such scenarios become possible in the transition from the model of the CR3BP to terms of the four-and more-body problem. If the formalized algorithm to overcome the "paradox solo disturbances" during gravitational maneuvers in the Jovian system for approach to one of the satellites is found, we have answers to the questions "what" and "how". Answer is- cross maneuvers. But it is necessary to find the answer to the question "when" is the time for the generation of cross maneuvers? In our opinion new effective coordinates can be involved for such purposes to build "Multi-Tisserand's graphs". "Multi-Tisserand's" Ti-coordinates are introduced. It is shown that the gravity "cross"-maneuvers at the early stage of reduction of the orbital period are required. As a result, a reasonable increase in mission duration can be transformed on a significant decline radiation dose (less than 50 krad for 8 mm Al).
机译：考虑了辐射危害，考虑了木星系统中低成本重力辅助飞行器在加利利月球着陆时的任务设计。使用飞越的动态机会有限，需要多个重力辅助。定期创建最佳方案的相关性-天体通过的顺序及其执行条件的定义是显而易见的。这项工作致力于描述创建此类链的标准。问题在于，对于长时间近距离接近而言，减小航天器相对于卫星的渐近速度Voo是不可能的。一个有效的原因在于在循环约束三体模型（CR3BP）中Jacobi积分和Tisserand参数的不变性。此外，Tisserand-Poincare图上的同一物体飞越序列根据V∞等值线落入额外的辐射区。启发式形式化克服了“残骸弹道悖论”，从而为卫星提供了近距离接近方法，并通过模型提升至四体配置的方式得以解决。从“第一个”子CR3BP小实体（“ Ganymede”）到第二个（“小实体不是Ganymede”的主体-主要是Callisto）然后沿相反的方向引入“交叉”重力的类别。在新的解决方案类别中，定期正式克服Tisserand准则成为可能。超过总接收辐射剂量（TID）的区域沿Tisserand图的“上部走廊”倾斜。以低成本降低飞船接近所需的渐近速度。从CR3BP的模型到四人以上问题的转换中，寻找这种情况成为可能。如果找到一种形式化的算法来克服木星引力系统中引力操纵过程中的“悖论独奏干扰”，以接近其中一颗卫星，那么我们就对“什么”和“如何”问题有了答案。答案是-交叉演习。但是，有必要找到问题“何时”才是产生交叉机动的时间的答案？我们认为，可以为此目的使用新的有效坐标，以构建“ Multi-Tisserand图”。介绍了“多-蒂塞兰德”的Ti坐标。结果表明，在减小轨道周期的早期需要重力“交叉”操纵。结果，可以通过显着降低辐射剂量（8 mm Al小于50 krad）来转换任务持续时间的合理增加。

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