用于引力和太阳系物理学的带偏置抑制的静电加速度计
Electrostatic accelerometer with bias rejection for Gravitation and Solar System physics
摘要：
行星际探测器的无线电跟踪是导航目的以及测试物理定律或探索行星环境的重要工具。在航天器上增加一个加速计为轨道确定专家和物理学家提供了一个非常感兴趣的额外观测值：它测量作用在航天器上的非重力加速度的值，即探测器偏离测地运动的情况。这一技术现在经常用于地球轨道上带有静电加速度计的大地测量任务。本文提出了一种技术的演变，其中包括增加一个子系统，以消除静电加速度计的偏置。其目的是从基础物理学和太阳系物理学的角度加强太阳系行星际飞行任务的科学回报。该仪器的主要部分是一个名为MicroSTAR的静电加速度计，它继承了Onera在加速度测量领域经验基础上的成熟技术。该加速度计安装在旋转平台上，称为偏置抑制系统，其调节非重力加速度，从而允许从感兴趣的信号中去除仪器的偏置。本文介绍了这项研究的动机，描述了仪器，称为GAP，和测量原理，并讨论了仪器的性能以及集成的限制。在3.1 kg的质量和3 W的平均消耗内，对于用5小时的积分时间测量的加速度，可以达到1 pm s $^{-2}$的精度。因此，将这一观测数据与无线电跟踪数据相结合，就有可能将航天器的运动与理论预测进行比较，其精度比现有技术至少提高三个数量级。
英文摘要：
Radio tracking of interplanetary probes is an important tool for navigation purposes as well as for testing the laws of physics or exploring planetary environments. The addition of an accelerometer on board a spacecraft provides orbit determination specialists and physicists with an additional observable of great interest: it measures the value of the non-gravitational acceleration acting on the spacecraft, i.e. the departure of the probe from geodesic motion. This technology is now routinely used for geodesy missions in Earth orbits with electrostatic accelerometers. This article proposes a technological evolution which consists in adding a subsystem to remove the bias of an electrostatic accelerometer. It aims at enhancing the scientific return of interplanetary missions in the Solar System, from the point of view of fundamental physics as well as Solar System physics. The main part of the instrument is an electrostatic accelerometer called MicroSTAR, which inherits mature technologies based on Onera's experience in the field of accelerometry. This accelerometer is mounted on a rotating stage, called Bias Rejection System, which modulates the non-gravitational acceleration and thus permits to remove the bias of the instrument from the signal of interest. This article presents the motivations of this study, describes the instrument, called GAP, and the measurement principle, and discusses the performance of the instrument as well as integration constraints. Within a mass of 3.1 kg and an average consumption of 3 W, it is possible to reach a precision of 1 pm s$^{-2}$ for the acceleration measured with an integration time of five hours. Combining this observable with the radio tracking data, it is therefore possible to compare the motion of the spacecraft to theoretical predictions with a precision improved by at least three orders of magnitude with respect to existing techniques.
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