• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>IEEE Aerospace Conference >System-level design considerations for asteroid despin via neutral beam emitting spacecraft
【24h】

System-level design considerations for asteroid despin via neutral beam emitting spacecraft

机译：通过中性束发射航天器进行小行星旋转的系统级设计考虑

获取原文
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

Asteroids have gained significant interest during the past several years in the areas of planetary defense, mining, and civil space. Hundreds of asteroids are discovered each year and that rate is increasing exponentially as technology improves. However, Chelyabinsk is a reminder that not every asteroid is observed and that the technology to prevent collision events has not been developed. Asteroids are not all likely to be monolithic boulders, but a large number are probably rubble piles held together by gravity and cohesion. To protect Earth, we must find ways to alter the trajectories of asteroids so that significant impact events never occur. Controlling smaller asteroids can be done through propulsive methods in proximity operation. However, as all asteroids spin, with some rotating on more than one axis, the thrust vector necessary to deflect an asteroid will likewise rotate. To thrust along the deflection vector for a long period of time, we must first despin the asteroid. This study investigates a novel concept for asteroid despin using spacecraft equipped with neutral beam emitters. While other methods for asteroid control employ vehicles that attach to the body, our proposed method only requires spacecraft to hover above the surface and induce a torque to stabilize the complex spinning behavior of asteroids. As the despin methods will cause considerable stresses inside the rubble pile, we present the maximum stress allowable before asteroid disaggregation due to Drukker-Prager failure calculated from gravitational and van der Waals (VDW) attraction. We provide relations for thrust and Isp as related to neutral beam application. The projected power required for a given beam energy is likewise presented to scale our system and concept. The time required to despin an example asteroid as dependent on force applied is also presented. In order to despin the asteroid to decrease the required power and time to despin, we then consider the possibility of multiple - pacecraft working together. While there are several concepts for Earth defense in the event of a probable asteroid impact, most require a precursor mission to determine the size and composition of the asteroid to design systems that latch on or bag the body. Launch opportunities to Near Earth Asteroids can vary anywhere from years to decades making such concepts difficult to implement if there is a limited time frame from discovery to orbital characterization to the likelihood of Earth impact. Our concept requires no such precursor mission as there is no need for direct contact with the asteroid. This work discusses the system-level trades and requirements of an asteroid despin mechanism that shows distinct operational advantages when compared to other designs.
机译：在行星防御，采矿和民用空间领域的过去几年中，小行星在过去几年中取得了重大兴趣。每年发现数百种小行星，并且随着技术的改善，该速率呈指数增长。然而，Chelyabinsk是一个提醒，并非没有观察到每个小行星，并且尚未开发防止碰撞事件的技术。小行星并不是很可能是单片巨石，但大量可能是通过重力和凝聚力一起保持在一起的瓦砾桩。为了保护地球，我们必须找到改变小行星轨迹的方法，以便从未发生过重大的影响事件。可以通过在接近操作中通过推进方法来完成控制较小的小行星。然而，随着所有小行星旋转，在多于一个轴上旋转，偏转小行星所需的推力矢量将同样旋转。沿着偏转向量推动很长一段时间，我们必须先守望小行星。本研究调查了小行星呵护的小说概念，呵护配备中性光束发射器的航天器。虽然小行星控制的其他方法采用连接到身体的车辆，但是我们所提出的方法仅需要航天器将悬停在表面上方并诱导扭矩以稳定小行星的复杂纺丝行为。由于宏观方法将在瓦砾桩内部引起相当大的应力，因此由于从引力和范德华（VDW）吸引力计算的DRUKKER-PRAGER失败，我们呈现了小行物分解前的最大应力。我们提供与中性光束应用相关的推力和ISP的关系。给定光束能量所需的投影电源同样呈现给我们的系统和概念。还提出了依赖于应用施加力的示例小行星所需的时间。为了避开小行星减少所需的力量和时间，我们将考虑多方 - PACRAFT一起工作的可能性。虽然在可能的小行星影响情况下存在几种地球防御概念，但大多数需要一种前体任务，以确定小行星的尺寸和组成，以确定闩锁或袋子的设计系统。从多年来可能会在几十年来的任何地方发射机会，可以在几十年来使这些概念难以实施，如果从发现到轨道表征到地球影响的可能性有限的时间框架。我们的概念不需要这样的前体使命，因为没有必要与小行星直接接触。这项工作讨论了与其他设计相比，展示了显示出明显的运营优势的小行星的系统级交易和要求。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号