Primeval substance delivery from Phobos to the Earth—the Phobos-Soil project: Ballistics,navigation, and flight control

This paper is concerned with the problems of ballistics, navigation, and flight control of the space craft (SC) in the Phobos-Grunt mission. We consider an insertion into the Earth-Mars transfer trajectory, the Earth-Mars transfer, the strategy of corrections, and the accuracy of the insertion of the SC into Martian orbit. During the orbital maneuvering stage in the sphere of influence of Mars, we set up a scheme that allows for the insertion of the SC, with the prescribed accuracy, into a point 80-km above the Phobos surface over the theoretical landing area. We specify the sequence for a controlled landing and provide methods for solving the problems of navigation and control during a self-c ontained landing. We also consider the liftoff from Phobos, insertion into the parking orbit, and the Mars-Earth transfer.     

子载波相位与BOC信号功率谱密度的关系研究

首先介绍了导航信号功率谱密度求解的一种通用方法,基于该方法,经过建模和推导,得到任意相位子载波BOC(二进制偏移载波)信号的功率谱密度显式表达式。通过仿真及分析表明,不同的子载波相位对应的BOC信号功率谱密度存在差别,正是这些差别影响了导航系统的性能,同时也为导航系统的信号体制设计带来了灵活性。文中得到的一些结论,可以给未来的导航信号体制设计中BOC信号子载波相位的选择提供一些借鉴。     

Mapping the CMB sky: THE BOOMERanG experiment

We describe the BOOMERanG experiment, a stratospheric balloon telescope intended to measure the Cosmic Microwave Background anisotropy at angular scales between a few degrees and ten arcminutes. The experiment has been optimized for a long duration (7 to 14 days) flight circumnavigating Antarctica at the end of 1998. A test flight was performed on 30 August 1997 in Texas. The level of performance achieved in the test flight was satisfactory and compatible with the requirements for the long duration flight.     

Measurement of a Peak in the Cosmic Microwave Background Power Spectrum from the North American Test Flight of Boomerang

We describe a measurement of the angular power spectrum of anisotropies in the cosmic microwave background (CMB) at scales of 0&fdg;3 to 5 degrees from the North American test flight of the Boomerang experiment. Boomerang is a balloon-borne telescope with a bolometric receiver designed to map CMB anisotropies on a long-duration balloon flight. During a 6 hr test flight of a prototype system in 1997, we mapped more than 200 deg(2) at high Galactic latitudes in two bands centered at 90 and 150 GHz with a resolution of 26&arcmin; and 16&farcm;5 FWHM, respectively. Analysis of the maps gives a power spectrum with a peak at angular scales of 1 degrees with an amplitude 70 μK(CMB).     

卫星导航定位系统中伪随机码的研究

伪随机码在扩频通信中得到广泛应用。目前的卫星导航定位系统大多采用扩频通信技术来传输导航信息 ,常用的伪随机码是平衡Gold码。对平衡Gold码的特性和产生方法作了研究 ,对全球定位系统 (GPS)粗码的平衡性作了分析 ,最后给出了在SystemView平台上相应的仿真结果。此研究对开展相关领域的研究工作具有借鉴意义     

Comparison of low-energy lunar transfer trajectories to invariant manifolds

In this study, transfer trajectories from the Earth to the Moon that encounter the Moon at various flight path angles are examined, and lunar approach trajectories are compared to the invariant manifolds of selected unstable orbits in the circular restricted three-body problem. Previous work focused on lunar impact and landing trajectories encountering the Moon normal to the surface, and this research extends the problem with different flight path angles in three dimensions. The lunar landing geometry for a range of Jacobi constants is computed, and approaches to the Moon via invariant manifolds from unstable orbits are analyzed for different energy levels.     

A long-duration balloon payload for hard X-ray and gamma-ray observations of the sun

We describe a balloon payload designed to study the processes of energy release, particle acceleration, and heating of the active corona, in hard X-ray microflares and normal flares. An array of liquid nitrogen-cooled germanium detectors together with large area phoswich scintillation detectors provide the highest sensitivity (∼500 cm²) and energy resolution (≤0.7 keV) ever achieved for solar hard X-ray (∼15–600 keV) measurements. These detectors were flown in February 1987 from Australia on a long duration RAdiation COntrolled balloON (RACOON) flight (LDBF) which provided 12 days of observations before cutdown in Brazil. The payload includes solar cells for power, pointing and navigation sensors, a microprocessor controlled data system with VCR tape storage, and transmitters for GOES and ARGOS spacecraft. This successful flight illustrates the potential of LDBF's for solar flare studies.

     

基于GPS接收机的程控目标跟踪方法的气球飞行试验

简要介绍了基于ＧＰＳ接收机的程控目标跟踪方法原理和１９９８ 年５ 月的一次气球飞行试验结果．成功的飞行试验证明该方法对于用准直器限制视场的Ｘ 射线和＄射线气球天文观测非常适用,可提高观测灵敏度和简化数据处理过程,特别是在长距离飞行时可做到多目标自动对准和跟踪的自主闭环系统     

Autonomous optical navigation using nanosatellite-class instruments: a Mars approach case study

This paper examines the effectiveness of small star trackers for orbital estimation. Autonomous optical navigation has been used for some time to provide local estimates of orbital parameters during close approach to celestial bodies. These techniques have been used extensively on spacecraft dating back to the Voyager missions, but often rely on long exposures and large instrument apertures. Using a hyperbolic Mars approach as a reference mission, we present an EKF-based navigation filter suitable for nanosatellite missions. Observations of Mars and its moons allow the estimator to correct initial errors in both position and velocity. Our results show that nanosatellite-class star trackers can produce good quality navigation solutions with low position (\(<300\,\text {m}\)) and velocity (\(<0.15\,\text {m/s}\)) errors as the spacecraft approaches periapse.     

On Choosing a Rational Flight Trajectory to the Moon

The algorithm for choosing a trajectory of spacecraft flight to the Moon is discussed. The characteristic velocity values needed for correcting the flight trajectory and a braking maneuver are estimated using the Monte Carlo method. The profile of insertion and flight to a near-circular polar orbit with an altitude of ~100 km of an artificial lunar satellite (ALS) is given. The case of two corrections applied during the flight and braking phases is considered. The flight to an ALS orbit is modeled in the geocentric geoequatorial nonrotating coordinate system with the influence of perturbations from the Earth, the Sun, and the Moon factored in. The characteristic correction costs corresponding to corrections performed at different time points are examined. Insertion phase errors, the errors of performing the needed corrections, and the errors of determining the flight trajectory parameters are taken into account.     

A novel approach to fireball modeling: The observable and the calculated

Estimating the mass of a meteoroid passing through the Earth's atmosphere is essential to determining potential meteorite fall positions. High‐resolution fireball images from dedicated camera networks provide the position and timing for fireball bright flight trajectories. There are two established mass determination methods: the photometric and the dynamic. A new approach is proposed, based on the dynamic method. A dynamic optimization initially constrains unknown meteoroid characteristics which are then used in a parametric model for an extended Kalman filter. The extended Kalman filter estimates the position, velocity, and mass of the meteoroid body throughout its flight, and quantitatively models uncertainties. Uncertainties have not previously been modeled so explicitly and are essential for determining fall distributions for potential meteorites. This two‐step method aims to automate the process of mass determination for application to any trajectory data set and has been applied to observations of the Bunburra Rockhole fireball. The new method naturally handles noisy raw data. Initial and terminal bright flight mass results are consistent with other works based on the established photometric method and cosmic ray analysis. A full analysis of fragmentation and the variability in the heat‐transfer coefficient will be explored in future versions of the model.     

Solution algorithm of a quasi-Lambert’s problem with fixed flight-direction angle constraint

A two-point boundary value problem of the Kepler orbit similar to Lambert’s problem is proposed. The problem is to find a Kepler orbit that will travel through the initial and final points in a specified flight time given the radial distances of the two points and the flight-direction angle at the initial point. The Kepler orbits that meet the geometric constraints are parameterized via the universal variable z introduced by Bate. The formula for flight time of the orbits is derived. The admissible interval of the universal variable and the variation pattern of the flight time are explored intensively. A numerical iteration algorithm based on the analytical results is presented to solve the problem. A large number of randomly generated examples are used to test the reliability and efficiency of the algorithm.     

关于"长河二号"导航系统的时间同步及授时

对“长河二号“导航系统的时间同步及快速恢复等问题作了讨论,提出了利用BPL长波信号、GPS共视或搬运钟等方法来实现时间同步和增加授时功能的方案.最后,给出了“长河二号“东海台链的主台信号与国家授时中心的UTC(NTSC)之间的同步实验结果.     

An evaluation of ionospheric probe performance—I. Evidence of contamination and clean-up of probe surfaces

The theoretical performance and accuracy of the Wilson type of electron temperature probe are discussed. Results from two ionospheric flights of this equipment are given, one being the first test of a modified version of the probe allowing detection and measurement of changes in the work functions of the electrodes. The relatively high levels of contamination that were observed were also found to vary markedly during flight, in a manner suggesting that smouldering rocket motors were partly responsible. An unexpected transient behavior of the probe was reproduced in laboratory tests that indicated that ion sheaths were playing an important role.     

导航战背景下的天文导航技术—天文导航技术的历史、现状及其发展趋势

综述近30年来我国内外天文导航技术及其相关理论和方法的进展，介绍世界各军事大国对天文导航的认识，并就天文导航在导航战背景下的显著优势进行论述。包括下列主要内容：（1）天文导航设备的历史和现状；（2）天文导航理论的新成果；（3）各军事大国对天文导航的态势；（4）天文导航的优势性；（5）天文导航自动化的主要关键技术，（6）天文导航自动化技术的发展趋势。     

嵌入式GPS/DR车载组合导航系统EKF算法软件设计

介绍一种嵌入式GPS／DR（全球定位系统／航位推算）车载组合导航（它通过GPS与DR的优势互补,提高了车辆导航系统定位数据的可靠性）的EKF（扩展卡尔曼滤波）算法软件设计方法。采用统计学原理剔除导航数据的粗差点,用扩展卡尔曼滤波进行导航参数的实时求解,采用EKF算法的GPS／DR组合导航系统有利于导航信息的稳定性、可靠性和实时性。     

Spacecraft intercept using minimum control energy and wait time

A new approach to the minimum energy impulse intercept problem for spacecraft in orbit is explored. The types of orbits investigated in this paper are not restricted to a particular one. The constrained optimization technique is formulated with the universal variable, which is used to describe orbit information with sufficient accuracy for general types of orbits. Two optimization problems are posed. First, a problem for minimum velocity change and time of flight for intercept are investigated with the constraint on the final position of two satellites. Next, the so-called wait time is also added as an additional parameter to be determined. Although a closed-form solution is not obtained, the Newton iteration technique is successfully applicable. Finally, by numerically comparing the proposed solution to the Hohmann transfer, the suggested approach is demonstrated to be a feasible technique applicable to a broad class of orbit transfer problems.     

PROBA2: Mission and Spacecraft Overview

Within the European Space Agency’s (ESA) General Support and Technology Programme (GSTP), the Project for On-Board Autonomy (PROBA) missions provide a platform for in-orbit technology demonstration. Besides the technology demonstration goal, the satellites allow to provide services to, e.g., scientific communities. PROBA1 has been providing multi-spectral imaging data to the Earth observation community for a decade, and PROBA2 provides imaging and irradiance data from our Sun to the solar community. This article gives an overview of the PROBA2 mission history and provides an introduction to the flight segment, the ground segment, and the payload operated onboard. Important aspects of the satellite’s design, including onboard software autonomy and the functionality of the navigation and guidance, are discussed. PROBA2 successfully proved again within the GSTP concept that it is possible to provide a fast and cost-efficient satellite design and to combine advanced technology objectives from industry with focussed objectives from the science community.     

利用卫星电视系统进行导航的基准站配置

在导航系统中,基准站配置的优劣直接关系到定位的精度及系统的可用性,对利用卫星电视系统进行导航可能采用的几种基准站配置进行了讨论,并对具体问题进行了分析计算,分析认为解决好基准站配置,合理地组合导航系统,可有效地提高定位的精度及系统的可用性。