Modelling of the MICROSCOPE Mission

The French space mission MICROSCOPE aims at testing the Equivalence Principle (EP) up to an accuracy of 10^?15. The experiment will be carried out on a satellite which is developed and produced within the CNES Myriade series. The measuring accuracy will be achieved by means of two high-precision capacitive differential accelerometers that are built by the French institute ONERA, see Touboul and Rodrigues (Class. Quantum Gravity 18:2487–2498, 2001). At ZARM, which is a member of the science team, the data evaluation process is prepared. Therefore, a comprehensive simulation of the real system including the science signal and all error sources is built for the development and testing of data reduction and data analysis algorithms to extract the EP violation signal. Currently, the ZARM Drag-Free simulator, a tool to support mission modelling, is adapted for the MICROSCOPE mission in order to simulate test mass and satellite dynamics. Models of environmental disturbances like solar radiation pressure are considered, also. Additionally, detailed modelling of the on-board capacitive sensors is done. The actual status of the mission modelling will be presented. Particularly, the modelling of disturbances forces will be discussed in detail.     

Microscope Instrument Development,Lessons for GOCE

Two space missions are presently under development with payload based on ultra-sensitive electrostatic accelerometers. The GOCE mission takes advantage of a three axis gradiometer accommodated in a very stable thermal case on board a drag-free satellite orbiting at a very low altitude of 250 km. This ESA mission will perform the very highly accurate mapping of the Earth gravity field with a geographical resolution of 100 km. The MICROSCOPE mission is devoted to the test of the “Universality of free fall” in view of the verification of the Einstein Equivalence Principle (EP) and of the search of a new interaction. The MICROSCOPE instrument is composed of two pairs of differential electrostatic accelerometers and the accelerometer proof-masses are the bodies of the EP test. The satellite is also a drag-free satellite exhibiting a fine attitude control and in a certain way, each differential accelerometer is a one axis gradiometer with an arm of quite null length. The development of this instrument much interests the definition and the evaluation of the sensor cores of the gradiometer. The in flight calibration process of both instruments is also very similar. Lessons form these parallel developments are presented. This revised version was published online in August 2006 with corrections to the Cover Date.     

Determination of the Equivalence Principle Violation Signal for the MICROSCOPE Space Mission: Optimization of the Signal Processing

The MICROSCOPE space mission aims at testing the Equivalence Principle (EP) with an accuracy of 10^?15. The test is based on the precise measurement delivered by a differential electrostatic accelerometer on-board a drag-free microsatellite which includes two cylindrical test masses submitted to the same gravitational field and made of different materials. The experiment consists in testing the equality of the electrostatic acceleration applied to the masses to maintain them relatively motionless at a well-known frequency. This high precision experiment is compatible with only very little perturbations. However, aliasing arises from the finite time span of the measurement, and is amplified by measurement losses. These effects perturb the measurement analysis. Numerical simulations have been run to estimate the contribution of a perturbation at any frequency on the EP violation frequency and to test its compatibility with the mission specifications. Moreover, different data analysis procedures have been considered to select the one minimizing these effects taking into account the uncertainty about the frequencies of the implicated signals.     

Modeling of Thermal Perturbations Using Raytracing Method with Preliminary Results for a Test Case Model of the Pioneer 10/11 Radioisotopic Thermal Generators

Electromagnetic radiation emitted from a source carries momentum. Thus, the dissipation of waste thermal energy can produce disturbance forces on spacecraft surfaces if the energy is not dissipated in a symmetric pattern. This force can be computed for a plate element as the quotient of the radiated power in normal direction and the speed of light. Depending on mission and spacecraft design the resulting surface forces have to be included into the disturbance budget. At ZARM an elaborated method for the exact modeling of the disturbances caused by heat radiation was developed which can be used for any satellite mission with high requirements on perturbation knowledge (e.g. LISA, LISA pathfinder, MICROSCOPE). The method which will be presented in this paper is based on raytracing and finite element (FE) thermal analysis. As a demonstration of the potential of the method, preliminary results acquired with a test case model of the Pioneer 10/11 Radioisotopic Thermal Generators (RTGs) will be shown.     

微重力条件下卫星贮箱中的推进剂管理问题

微重力条件下贮箱中液体管理的主要问题是控制液体推进剂在箱中的位置,保证向发动机输送不含气泡的推进剂.对用于自旋稳定卫星的梨形贮箱,在透明的有机玻璃缩比模型中用去离子水作试验介质进行落塔试验.在弹星分离以后,卫星自旋以前通过落塔试验确定气液界面的形状,排出液体时夹气现象和发生夹气时剩余液体的体积,试验为贮箱设计提供可靠的依据.在长寿命的卫星上将采用一种大型表面张力贮箱,在微重力条件下将要进行相关的液体流动特性试验,如气液界面的平衡位置,挤出效率,液体流动的阻力损失,流体的晃动等,验证设计的合理性.     

The Equivalence Principle and the Constants of Nature

We briefly review the various contexts within which one might address the issue of “why” the dimensionless constants of Nature have the particular values that they are observed to have. Both the general historical trend, in physics, of replacing a-priori-given, absolute structures by dynamical entities, and anthropic considerations, suggest that coupling “constants” have a dynamical nature. This hints at the existence of observable violations of the Equivalence Principle at some level, and motivates the need for improved tests of the Equivalence Principle.     

THE JOINT SCIENCE OPERATIONS CENTRE

The Joint Science Operations Centre (JSOC) has been established to provide the operational interface between the Instrument Principal Investigators (PIs) and the European Space Operations Centre (ESOC). Its key task will be to merge inputs from the Cluster instrument teams and to generate the coordinated command schedule for operation of the scientific payload. In addition, it will collect and process data needed to plan those operations and will monitor the performance of the mission and individual instruments. This paper outlines the JSOC subsystems that have been built to carry out these tasks and highlights points of scientific or technical interest within these systems.     

Satellite Skin-Force Modelling for Atmospheric Drag Calculations

Satellites in low Earth orbits are influenced by the Earth’s atmosphere. The interactions between the molecules and the spacecraft cause the highest non-gravitational force, which in magnitude is comparable to planetary disturbances. Therefore the modelling of atmospheric drag effects is important for many missions with a scientific background like STEP (Satellite Test of Equivalence Principle). With the STEP mission variations between gravitational and inertial mass shall be measured with an accuracy of 10^?18. The results are of great interest for cosmological and gravitational theories. To achieve the aimed accuracy, a precise model of external disturbances is necessary. In this article the method of Ray-Tracing is used to quantify the atmospheric drag forces and torques for spacecrafts of arbitrary shape.     

Leasecraft: An Innovative Space Vehicle

The Leasecraft system is an innovative means to provide a permanent mobile platform in low Earth orbit and the related launch, integration, test, operation, and in-orbit servicing for payloads of industrial and government users. The Leasecraft system is being funded and developed by Fairchild Industries and furthers the industrialization of space with its significant business potential. The technology and techniques underlying this venture are derived from the shuttle compatible multimission modular spacecraft (presently used for the NASA solar maximum mission and Landsat-D/D' mission) and the upcoming demonstration of shuttle repair to be performed on the solar maximum satellite in the first quarter of 1984. Leasecraft can be identified as a system, comprising a low orbit space platform, an operations control center, user accommodations, and services such as payload interfaces, documentation, and ground support equipment and procedures. The combination of these elements facilitates the use of the space environment by both the space and nonspace oriented user. Early potential applications of Leasecraft include the processing of pharmaceuticals and materials, satellite-aided search and rescue, data collection, and support of NASA's astrophysics programs. Initial assessments made concerning the benefits to users and the cost of providing these benefits indicates that Leasecraft can provide needed services at very competitive rates. The leasing arrangement is cost effective as compared with present spacecraft platform development and cost assessment techniques.     

Laboratory Tests of the Equivalence Principle at the University of Washington

Equivalence principle tests are probes for new fundamental physics. We have conducted several laboratory experiments to test the equivalence principle with unprecedented precision and generality using a torsion balance placed on a continuously rotating turntable. We present preliminary results comparing the differential accelerations of Ti, Be, and Al towards local masses, the earth and the center of our galaxy.     

The Confrontation Between General Relativity and Experiment

We review the experimental evidence for Einstein’s general relativity. A variety of high precision null experiments confirm the Einstein Equivalence Principle, which underlies the concept that gravitation is synonymous with spacetime geometry, and must be described by a metric theory. Solar system experiments that test the weak-field, post-Newtonian limit of metric theories strongly favor general relativity. Binary pulsars test gravitational-wave damping and aspects of strong-field general relativity. During the coming decades, tests of general relativity in new regimes may be possible. Laser interferometric gravitational-wave observatories on Earth and in space may provide new tests via precise measurements of the properties of gravitational waves. Future efforts using X-ray, infrared, gamma-ray and gravitational-wave astronomy may one day test general relativity in the strong-field regime near black holes and neutron stars.     

Low cost satellite ground control facility design

A design approach common to the areas of satellite operations command and control, tracking, subsystem analysis, system planning and scheduling, orbit determination and maintenance, and data routing and control is discussed. Specific satellite mission applications and operations are isolated from the remainder of the design to allow application to a broad variety of satellite systems. Discussions of specific satellite missions are limited to the context of understanding the general magnitude and scope of what a ground control facility is required to support. By isolating the common satellite operational functions, a low cost generic approach that allows for phased implementation of system changes with minimal impact to on-orbit assets and mission performance is developed. The goals of this approach are to provide the capability for growth, maintainability, and operability of the satellite system. A brief discussion of satellite systems followed by the introduction of the general function of any satellite control facility sets the stage for the overall design approach. The factors that define the design along with the key design features are presented, with a discussion of each product available in each functional area     

Orbital and Attitude Prediction Accuracy Requirements for Satellites

This paper examines the criteria for selecting the orbital and attitude prediction accuracy requirements for communications satellites. The accuracy requirements have been analyzed in terms of the various space operations involved, e.g., satellite acquisition, guidance and control, communications, telemetry, and command. It is hoped that the findings of this investigation will prove useful in satellite mission planning and design, thereby facilitating a judicious choice of the various satellite and ground components of the related subsystems.     

MESSENGER Mission Overview

The MErcury Surface, Space ENvironment, GEochemistry, and Ranging (MESSENGER) spacecraft, launched on August 3, 2004, is nearing the halfway point on its voyage to become the first probe to orbit the planet Mercury. The mission, spacecraft, and payload are designed to answer six fundamental questions regarding the innermost planet: (1) What planetary formational processes led to Mercury’s high ratio of metal to silicate? (2) What is the geological history of Mercury? (3) What are the nature and origin of Mercury’s magnetic field? (4) What are the structure and state of Mercury’s core? (5) What are the radar-reflective materials at Mercury’s poles? (6) What are the important volatile species and their sources and sinks near Mercury? The mission has focused to date on commissioning the spacecraft and science payload as well as planning for flyby and orbital operations. The second Venus flyby (June 2007) will complete final rehearsals for the Mercury flyby operations in January and October 2008 and September 2009. Those flybys will provide opportunities to image the hemisphere of the planet not seen by Mariner 10, obtain high-resolution spectral observations with which to map surface mineralogy and assay the exosphere, and carry out an exploration of the magnetic field and energetic particle distribution in the near-Mercury environment. The orbital phase, beginning on March 18, 2011, is a one-year-long, near-polar-orbital observational campaign that will address all mission goals. The orbital phase will complete global imaging, yield detailed surface compositional and topographic data over the northern hemisphere, determine the geometry of Mercury’s internal magnetic field and magnetosphere, ascertain the radius and physical state of Mercury’s outer core, assess the nature of Mercury’s polar deposits, and inventory exospheric neutrals and magnetospheric charged particle species over a range of dynamic conditions. Answering the questions that have guided the MESSENGER mission will expand our understanding of the formation and evolution of the terrestrial planets as a family.     

基于离子电推进系统的航天器有效载荷能力分析

为预估与提高航天器有效载荷能力,结合航天运输系统理论与离子推力器放电模型,对深空探测任务中以离子电推进系统为主要动力来源的航天器有效载荷能力进行了分析。通过理论推导,构建并揭示了有效载荷分数与深空探测任务参数和电推进系统性能参数的函数关系与潜在联系。结果表明:动力装置单位质量越小,航天器所能达到的最佳有效载荷分数越大;有效载荷分数的高低与离子引出份额、原初电子利用率参数的大小以及任务时间的长短呈正相关;当离子电推进系统可以达到更高的载荷比时,则需要更高的工质利用率作为支持。     

InSight Mars Lander Robotics Instrument Deployment System

The InSight Mars Lander is equipped with an Instrument Deployment System (IDS) and science payload with accompanying auxiliary peripherals mounted on the Lander. The InSight science payload includes a seismometer (SEIS) and Wind and Thermal Shield (WTS), heat flow probe (Heat Flow and Physical Properties Package, HP³) and a precision tracking system (RISE) to measure the size and state of the core, mantle and crust of Mars. The InSight flight system is a close copy of the Mars Phoenix Lander and comprises a Lander, cruise stage, heatshield and backshell. The IDS comprises an Instrument Deployment Arm (IDA), scoop, five finger “claw” grapple, motor controller, arm-mounted Instrument Deployment Camera (IDC), lander-mounted Instrument Context Camera (ICC), and control software. IDS is responsible for the first precision robotic instrument placement and release of SEIS and HP³ on a planetary surface that will enable scientists to perform the first comprehensive surface-based geophysical investigation of Mars’ interior structure. This paper describes the design and operations of the Instrument Deployment Systems (IDS), a critical subsystem of the InSight Mars Lander necessary to achieve the primary scientific goals of the mission including robotic arm geology and physical properties (soil mechanics) investigations at the Landing site. In addition, we present test results of flight IDS Verification and Validation activities including thermal characterization and InSight 2017 Assembly, Test, and Launch Operations (ATLO), Deployment Scenario Test at Lockheed Martin, Denver, where all the flight payloads were successfully deployed with a balloon gravity offload fixture to compensate for Mars to Earth gravity.     

一种单低轨星北斗备份与辅助方法及在轨验证

在低轨卫星上搭载导航载荷,为北斗系统提供有效的备份及辅助性能提升手段,是近年来卫星导航领域专家学者探讨的热点问题.针对全球卫星导航系统信号在恶劣电磁环境下的受扰问题,提出了一种利用单颗低轨卫星实现北斗备份和辅助的方法.北斗备份是指通过单颗低轨星独立为地面用户提供导航服务.北斗辅助是指利用单颗低轨星信号及信息,为地面用户...     

一种无塔校准方法研究

在地面卫星测控系统中,目前使用较多的有塔校准技术具有一定的局限性,为了克服这种局限性,本文针对已有的卫星测控系统设备提出一种无塔校准方法,给出了具体无塔校相和无塔校零的实现方法.