• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>AIAA guidance, navigation, and control conference;AIAA SciTech forum >Risk Assessment of Cassini Sun Sensor Integrity due to Hypervelocity Impact of Saturn Dust Particles
【24h】

Risk Assessment of Cassini Sun Sensor Integrity due to Hypervelocity Impact of Saturn Dust Particles

机译：土星尘埃颗粒超高速撞击对卡西尼太阳传感器完整性的风险评估

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

摘要

A sophisticated interplanetary spacecraft, Cassini is one of the heaviest and most sophisticated interplanetary spacecraft humans have ever built and launched. Since achieving orbit at Saturn in 2004, Cassini has collected science data throughout its four-year prime mission (2004-08), and has since been approved for first and second extended missions through September 2017. In late 2016, the Cassini spacecraft will begin a daring set of ballistic orbits that will hop the rings and dive between the upper atmosphere of Saturn and its innermost D-ring twenty-two times. The "dusty" environment of the inner D-ring region the spacecraft must fly through is hazardous because of the possible damage that dust particles, travelling at speeds as high as 31.4 km/s, can do to spacecraft hardware. During hazardous proximal ring-plane crossings, the Cassini mission operation team plans to point the high-gain antenna to the RAM vector in order to protect most of spacecraft instruments from the incoming energetic ring dust particles. However, this particular spacecraft attitude will expose two Sun sensors (that are mounted on the antenna dish) to the incoming dust particles. High-velocity impacts on the Sun sensor cover glass might penetrate the 2.54-mm glass cover of the Sun sensor. Even without penetration damage, craters created by these impacts on the surface of the cover glass will degrade the transmissibility of light through it. Apart from being directly impacted by the dust particles, the Sun sensors are also threatened by some fraction of ricochet ejecta that are produced by dust particle impacts on the large antenna dish (made of graphite fiber epoxy composite material). Finally, the spacecraft attitude control system must cope with disturbances due to both the translational and angular impulses imparted on the large antenna dish and the long magnetometer boom by the incoming high-velocity projectiles. Analyses performed to quantify the risks the Sun sensors must contend with during these hazardous ring-plane crossings are given in this paper.
机译：卡西尼号是一种复杂的行星际航天器，是人类有史以来建造和发射的最重，最复杂的行星际航天器之一。自2004年在土星进入轨道以来，卡西尼号已收集了其四年主要任务（2004-08年）的科学数据，并已获批准进行至2017年9月的第一次和第二次任务。2016年下半年，卡西尼号航天器将开始运行一系列大胆的弹道，它们会跳环并在土星的最高大气层与其最内层的D环之间潜入22次。航天器必须飞过的内部D形环区域的“尘土飞扬”环境具有危险性，因为可能以高达31.4 km / s的速度传播的尘埃颗粒可能对航天器硬件造成损害。在危险的近端环形飞机横越时，卡西尼号飞行任务小组计划将高增益天线指向RAM向量，以保护大多数航天器仪器免受高能环形灰尘进入的影响。但是，这种特殊的航天器姿态将使两个太阳传感器（安装在天线罩上）暴露于进入的尘埃颗粒中。高速撞击Sun传感器盖玻璃可能会穿透2.54毫米的Sun传感器玻璃盖。即使没有穿透损伤，由这些冲击在盖玻片表面上产生的凹坑也会降低光通过盖玻片的透射率。除了直接受到灰尘颗粒的影响外，Sun传感器还受到灰尘颗粒撞击大型天线碟（由石墨纤维环氧复合材料制成）所产生的一定比例的跳弹喷射的威胁。最后，航天器的姿态控制系统必须应对由于传入的高速射弹在大型天线碟形天线和长磁力计吊臂上施加的平移和角度脉冲而造成的干扰。本文给出了量化这些Sun传感器在这些危险的环形平面穿越过程中必须应对的风险的分析。

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