ASTROD-GW轨道设计

激光天文动力学引力波探测任务ASTROD-GW(ASTROD[AstrodynamicalSpace Test of Relativity Using Optical Devices Optimized for Gravitation WaveDetection)是ASTROD专注于探测引力波的优化方案,其航天器轨道在日地拉格朗日点L_3、L_4、L_5附近,构成一个接近等边的三角形阵列,干涉臂长约为2.6×10~8 km,其可探测的引力波波长可达LISA(Laser Interferometer Space Antenna)的52倍.文中综述ASTROD-GW轨道的设计和优化方法.轨道经优化后,其臂长差(在激光干涉测量中可称为干涉差)10 yr内的变化为10~(-4) AU量级、3个臂长方向的多普勒速度小于4 m/s,均小于LISA的要求,因此LISA发展的激光测距技术可用于ASTROD-GW.     

行星际电子及重核对ASTROD Ⅰ测试质量充电过程模拟的研究

在LISA,ASTROD I和ASTROD之类用于探讨引力波天文、天文动力学和相对论测试的深空激光探测计划中,暴露在空间粒子环境中的无拖曳测试质量将会受各种带电粒子的影响而带电,引起库伦力和洛伦兹力干扰,从而影响实验数据的精度.在先前的工作中,已用GEANT4工具包模拟了银河宇宙射线中质子和氦核以及太阳高能粒子事件对测试质量的充电过程.文章里,参数化了行星际电子和主要种类的重核,并模拟了由测试质量块在行星际电子和C,H,O等重核环境中的充电速率.行星际电子源主要是木星和银河,而重核主要来自于银河宇宙射线.经过模拟计算, ASTROD Ⅰ测试质量由行星际电子引起的充电速率大约是行星际质子在太阳活动最小值时的9%,在太阳活动最大值时的28%.行星际重核相对于行星际质子在太阳活动最小值和最大值时的贡献分别约是0.83%和1.64%.     

世界引力波探测网的现状

引力波是广义相对论的重要推论之一,迄今为止尚未被直接探测到。上世纪末共振棒引力波探测网曾联合运行.历经十余年的努力,世界激光干涉引力波探测网已经初步形成。今后一、两年将会同步运行。最新的关于中子双星的天文观测和分析给引力波探测带来了希望。     

OJ 287的引力波辐射研究

类星体OJ 287的研究已经有100多年的历史,它呈现周期性双峰爆发现象,爆发周期为12 yr,比较好地解释观测的模型是双黑洞模型,即次黑洞绕主黑洞运动,并撞击主黑洞吸积盘从而引起爆发.此模型合理地解释了OJ 287的光变曲线并正确预言了未来爆发时间,这间接证明了广义相对论进动效应以及引力波的存在.星系中心大质量黑洞是一类重要的引力波源,而精确确定了其内部组分运动学方程的星系非常少,由于双黑洞模型提供了精确的黑洞运动轨道,故可以在这个运动轨道基础上研究其引力波辐射.在已有工作基础上,采用后牛顿近似方法首次得到了引力波辐射功率和波形随时间的演化关系,根据目前引力波探测设备IPTA(International Pulsar Timing Array)的进展情况,未来十几年内对OJ 287的引力波直接探测将成为可能.     

时空的圆舞曲引力波

2015年9月14日,美国激光干涉引力波天文台(LIGO)捕捉到了距离地球13亿光年外的一对双黑洞并合产生的引力波信号(GW150914)。经过长达数月的数据分析,LIGO团队确证了激光干涉仪在该引力波信号穿过时产生的大约是一亿亿分之一厘米尺度的振荡变化,并于2016年2月11日对外公布了这项惊人发现。这是人类首次直接探测到爱因斯坦广义相对论预言的引力波信号,并证实了双黑洞的存在。引力波探测器为探测宇宙提供了不同于电磁波(光)的全新方法,现在我们不仅能用望远镜“看”缤纷多彩的宇宙,还能用引力波探测器“听”波澜壮阔的宇宙。2017年的诺贝尔物理学奖也因此颁给了对引力波探测作出杰出贡献的三位物理学家:雷纳·韦斯(Rainer Weiss)、基普·索恩(Kip Stephen Thorne)和巴里·巴里什(Barry Clark Barish)。     

引力波数据分析

以引力波探测为基础的引力波天文学是一门正在崛起的新兴交叉学科,它是继以电磁辐射为探测手段的传统天文学之后,人类观测宇宙的一个新窗口,对研究宇宙的起源和演化,拓展天文学的研究领域都有极其重要的意义。激光干涉引力波探测器的出现,更开辟了引力波探测的新纪元。引力波数据处理与分析已在世界各地迅速发展起来,为引力波天文学的研究提供了锐利的武器。系统地介绍了引力波数据分析中常用的工具软件,详细讨论了时间-频率分析、复合分析法、脉冲星计时分析法、匹配过滤器、模板、χ~2检验、蒙特卡罗模拟等引力波数据分析中使用的基本方法。     

lbb-用于射电天文VLBI基带数据读写的库

Library for Baseband (lbb)是一个自研的用于读取解析甚长基线干涉测量(Very Long Baseline Interferometry, VLBI)基带数据的工具库,主要用于VLBI观测中对终端基带数据的读取、解析及输出结果分析.该软件库通过对基带数据的自动判断,自动实现读取不同数据格式的功能,并提供了各种各样的API (Application Programming Interface)功能供用户调用.目前lbb软件库已经成功应用在了探月工程VLBI测轨任务中的硬件相关处理机配置项和测地VLBI观测数据的预处理.文章详细介绍了lbb软件库的设计、功能及用法.     

ASTROD 1中的望远镜前指量研究

单航天器激光天文动力学空间计划ASTROD1是激光天文动力学ASTROD的第一步,通过发射绕太阳的无拖曳航天器,并且当航天器处于太阳背面附近时,与地面站进行深空激光测距,以执行科学任务。该文计算了ASTROD12015年的轨道、提出了判断轨道精度是否满足任务需要的方法、分析了地球和航天器的位置同望远镜前指量之间的关系并且给出了望远镜前指量的结果。     

空间激光干涉引力波探测与早期宇宙结构形成

空间引力波探测是研究宇宙早期恒星演化和星系形成、黑洞和星系的共同成长等天文学和宇宙学重大问题的一条重要可能途径。经过两期科学院先导科技专项空间科学预研究课题的开展,通过权衡技术的可行性与科学的前瞻性,选择以高红移开始的中至大质量双黑洞并合系统、星团等稠密动力学环境中涉及中等质量黑洞的双黑洞引力波波源为主要科学目标,给出了我国毫赫兹至赫兹频段空间引力波探测任务计划的初步设计。以该任务设计建议为依据,简要介绍空间引力波探测及其作为一种新的天文观测手段的科学内涵,以及我国空间引力波探测任务设计的科学目标和探测潜力。     

Numerical simulation of time delay interferometry for TAIJI and new LISA

The success of LISA Pathfinder in demonstrating the LISA drag-free requirement paved the way for using space interferometers to detect low-frequency and middle-frequency gravitational waves(GWs). The TAIJI GW mission and the new LISA GW mission propose using an arm length of 3 Gm(1 Gm = 10~6 km) and an arm length of 2.5 Gm respectively. For a space laser-interferometric GW antenna,due to astrodynamical orbit variation, time delay interferometry(TDI) is needed to achieve nearly equivalent equal-arms for suppressing the laser frequency noise below the level of optical path noise, acceleration noise, etc in order to attain the requisite sensitivity. In this paper, we simulate TDI numerically for the TAIJI mission and the new LISA mission. To do this, we work out a set of 2200-day(6-year) optimized science orbits for each mission starting on 2028 March 22 using the CGC 2.7.1 ephemeris framework. Then we use the numerical method to calculate the residual optical path differences of the first-generation TDI configurations and the selected second-generation TDI configurations. The resulting optical path differences of the second-generation TDI configurations calculated for TAIJI, new LISA and eLISA are well below their respective requirements for laser frequency noise cancelation. However, for the first-generation TDI configurations, the original requirements need to be relaxed by 3 to 30 fold to be satisfied. For TAIJI and the new LISA, about one order of magnitude relaxation would be good and recommended; this could be borne on the laser stability requirement in view of recent progress in laser stability, or the GW detection sensitivities of the second-generation TDIs have to be used in the diagnosis of the observed data instead of the commonly used X, Y and Z TDIs.     

Time-delay Interferometry for ASTROD-GW

ASTROD-GW(ASTROD[Astrodynamical Space Test of Relativity using Optical Devices] optimized for Gravitational Wave detection) is an optimization of ASTROD to focus on the detection of gravitational waves. Three spacecraft in the mission are positioned respectively in the vicinity of the Sun- Earth Lagrange points L3, L4 and L5. They form a nearly equilateral interferometerarray with the arm lengths of about 260 million kilometers. A set of optimized 20-yr mission orbits of the ASTROD-GW spacecraft are worked out by us. And with this, we have performed the numerical simulation of time-delay interferometry under the CGC2.7 (CGC: Center for Gravitation and Cosmology) ephemeris framework.     

Design of ASTROD-GW Orbit

The ASTROD-GW (ASTROD [Astrodynamical Space Test of Relativity Using Optical Devices] Optimized for Gravitation Wave Detection), the mission of the laser astrodynamical gravitational wave detection, is the scheme of optimality of the gravitational wave detection on which the ASTROD is concentrated. Its spacecraft orbits form a triangular array close to an equilateral triangle in the vicinity of the solar-terrestrial Lagrangian points L₃, L₄ and L₅. The length of the interference arm is about 2.6 × 10⁸ km and the detectable wavelength of the gravitational wave is 52 times larger than that detected by the LISA (Laser Interferometer Space Antenna). In this article, the design and optimization method of the ASTROD-GW orbit are summarized. After the orbit is optimized, the variation in the arm length difference (which can be called the interference difference in laser interferometry) within 10 years is in the order of magnitude of 10⁻⁴ AU. The Doppler velocities in the three arm length directions are smaller than 4 m/s, and all of them are less than that required by the LISA. Therefore the laser ranging techniques developed by the LISA can be applied to the ASTROD-GW.     

Astrodynamical Space Test of Relativity using Optical Devices I (ASTROD I)—a class-M fundamental physics mission proposal for cosmic vision 2015–2025: 2010 Update

ASTROD I is a planned interplanetary space mission with multiple goals. The primary aims are: to test General Relativity with an improvement in sensitivity of over 3 orders of magnitude, improving our understanding of gravity and aiding the development of a new quantum gravity theory; to measure key solar system parameters with increased accuracy, advancing solar physics and our knowledge of the solar system; and to measure the time rate of change of the gravitational constant with an order of magnitude improvement and the anomalous Pioneer acceleration, thereby probing dark matter and dark energy gravitationally. It is envisaged as the first in a series of ASTROD missions. ASTROD I will consist of one spacecraft carrying a telescope, four lasers, two event timers and a clock. Two-way, two-wavelength laser pulse ranging will be used between the spacecraft in a solar orbit and deep space laser stations on Earth, to achieve the ASTROD I goals.For this mission, accurate pulse timing with an ultra-stable clock, and a drag-free spacecraft with reliable inertial sensor are required. T2L2 has demonstrated the required accurate pulse timing; rubidium clock on board Galileo has mostly demonstrated the required clock stability; the accelerometer on board GOCE has paved the way for achieving the reliable inertial sensor; the demonstration of LISA Pathfinder will provide an excellent platform for the implementation of the ASTROD I drag-free spacecraft. These European activities comprise the pillars for building up the mission and make the technologies needed ready. A second mission, ASTROD or ASTROD-GW (depending on the results of ASTROD I), is envisaged as a three-spacecraft mission which, in the case of ASTROD, would test General Relativity to one part per billion, enable detection of solar g-modes, measure the solar Lense-Thirring effect to 10 parts per million, and probe gravitational waves at frequencies below the LISA bandwidth, or in the case of ASTROD-GW, would be dedicated to probe gravitational waves at frequencies below the LISA bandwidth to 100?nHz and to detect solar g-mode oscillations. In the third phase (Super-ASTROD), larger orbits could be implemented to map the outer solar system and to probe primordial gravitational-waves at frequencies below the ASTROD bandwidth. This paper on ASTROD I is based on our 2010 proposal submitted for the ESA call for class-M mission proposals, and is a sequel and an update to our previous paper (Appouchaux et al., Exp Astron 23:491?C527, 2009; designated as Paper I) which was based on our last proposal submitted for the 2007 ESA call. In this paper, we present our orbit selection with one Venus swing-by together with orbit simulation. In Paper I, our orbit choice is with two Venus swing-bys. The present choice takes shorter time (about 250?days) to reach the opposite side of the Sun. We also present a preliminary design of the optical bench, and elaborate on the solar physics goals with the radiation monitor payload. We discuss telescope size, trade-offs of drag-free sensitivities, thermal issues and present an outlook.     

任务轨道设计

本文首先说明太空任务与轨道设计的关系 ,接着介绍轨道的基本性质。从地球重力势的观点看各种常用的绕地轨道 ,包括地球和太阳同步轨道及Molniya轨道。从扰动的观点看常用的星际轨道 ,包括LISA、ASTROD、SOHO轨道。最后对星际轨道设计 ,说明二点边界值问题的数值解法、飞掠星体的应用、最佳化的考虑 ,并用以设计 2 0 1 5年发射的ASTROD初步任务轨道。     

Astrodynamical Space Test of Relativity Using Optical Devices I (ASTROD I)—A class-M fundamental physics mission proposal for Cosmic Vision 2015–2025

ASTROD I is a planned interplanetary space mission with multiple goals. The primary aims are: to test general relativity with an improvement in sensitivity of over three orders of magnitude, improving our understanding of gravity and aiding the development of a new quantum gravity theory; to measure key solar system parameters with increased accuracy, advancing solar physics and our knowledge of the solar system; and to measure the time rate of change of the gravitational constant with an order of magnitude improvement and the anomalous Pioneer acceleration, thereby probing dark matter and dark energy gravitationally. It is an international project, with major contributions from Europe and China and is envisaged as the first in a series of ASTROD missions. ASTROD I will consist of one spacecraft carrying a telescope, four lasers, two event timers and a clock. Two-way, two-wavelength laser pulse ranging will be used between the spacecraft in a solar orbit and deep space laser stations on Earth, to achieve the ASTROD I goals. A second mission, ASTROD (ASTROD II) is envisaged as a three-spacecraft mission which would test General Relativity to 1 ppb, enable detection of solar g-modes, measure the solar Lense–Thirring effect to 10 ppm, and probe gravitational waves at frequencies below the LISA bandwidth. In the third phase (ASTROD III or Super-ASTROD), larger orbits could be implemented to map the outer solar system and to probe primordial gravitational-waves at frequencies below the ASTROD II bandwidth.

Halo orbit transfer trajectory design using invariant manifold in the Sun-Earth system accounting radiation pressure and oblateness

In this paper, we study the invariant manifold and its application in transfer trajectory problem from a low Earth parking orbit to the Sun-Earth \(L_{1}\) and \(L_{2}\)-halo orbits with the inclusion of radiation pressure and oblateness. Invariant manifold of the halo orbit provides a natural entrance to travel the spacecraft in the solar system along some specific paths due to its strong hyperbolic character. In this regard, the halo orbits near both collinear Lagrangian points are computed first. The manifold’s approximation near the nominal halo orbit is computed using the eigenvectors of the monodromy matrix. The obtained local approximation provides globalization of the manifold by applying backward time propagation to the governing equations of motion. The desired transfer trajectory well suited for the transfer is explored by looking at a possible intersection between the Earth’s parking orbit of the spacecraft and the manifold.     

Sun–Earth L_{1} and L_{2} to Moon transfers exploiting natural dynamics

This paper examines the design of transfers from the Sun–Earth libration orbits, at the \(L_{1}\) and \(L_{2}\) points, towards the Moon using natural dynamics in order to assess the feasibility of future disposal or lifetime extension operations. With an eye to the probably small quantity of propellant left when its operational life has ended, the spacecraft leaves the libration point orbit on an unstable invariant manifold to bring itself closer to the Earth and Moon. The total trajectory is modeled in the coupled circular restricted three-body problem, and some preliminary study of the use of solar radiation pressure is also provided. The concept of survivability and event maps is introduced to obtain suitable conditions that can be targeted such that the spacecraft impacts, or is weakly captured by, the Moon. Weak capture at the Moon is studied by method of these maps. Some results for planar Lyapunov orbits at \(L_{1}\) and \(L_{2}\) are given, as well as some results for the operational orbit of SOHO.     

The Sun–Earth saddle point: characterization and opportunities to test general relativity

The saddle points are locations where the net gravitational accelerations balance. These regions are gathering more attention within the astrophysics community. Regions about the saddle points present clean, close-to-zero background acceleration environments where possible deviations from General Relativity can be tested and quantified. Their location suggests that flying through a saddle point can be accomplished by leveraging highly nonlinear orbits. In this paper, the geometrical and dynamical properties of the Sun–Earth saddle point are characterized. A systematic approach is devised to find ballistic orbits that experience one or multiple passages through this point. A parametric analysis is performed to consider spacecraft initially on \(L_{1,2}\) Lagrange point orbits. Sun–Earth saddle point ballistic fly-through trajectories are evaluated and classified for potential use. Results indicate an abundance of short-duration, regular solutions with a variety of characteristics.     

Non-Keplerian orbits for electric sails

An electric sail is capable of guaranteeing the fulfilment of a class of trajectories that would be otherwise unfeasible through conventional propulsion systems. In particular, the aim of this paper is to analyze the electric sail capabilities of generating a class of displaced non-Keplerian orbits, useful for the observation of the Sun’s polar regions. These orbits are characterized through their physical parameters (orbital period and solar distance) and the spacecraft propulsion capabilities. A comparison with a solar sail is made to highlight which of the two systems is more convenient for a given mission scenario. The optimal (minimum time) transfer trajectories towards the displaced orbits are found with an indirect approach.