The putative mechanical strength of comet surface material applied to landing on a comet

The comet lander PHILAE (part of the ESA mission ROSETTA) is going to touch down on comet 67P/Churyumov–Gerasimenko in 2014. Landing dynamics depend on the mechanical strength of the surface material: in an extremely soft material, the lander (100 kg, 1 m/s touch-down velocity) may sink in too deep for successful operation while on a very hard surface the probability for bouncing and overturning increases. It is shown that direct knowledge on the strength of cometary surface material is very limited. In our view, even the Deep Impact experiment could not provide a reliable value of the mechanical strength of comet Tempel 1. We discuss the definition of “strength” and revise the ideas on cometary surface strength and theories that describe the low-velocity (≈1 m/s) impact of blunt bodies into dust-rich, fluffy cometary materials. Available direct and indirect measurements and data are critically reviewed. Lessons learnt from laboratory measurements to verify our equations of motion are presented as well. Conclusions for Philae are drawn: most likely, the soft landing will lead to a typical penetration of the lander's feet of up to 20 cm.     

A global geographical survey of received signal strength in the VHF band

Sumbandila (SO-67) is an 81 kg LEO satellite launched on 17 September 2009. Its primary payload is a multi-spectral imager with a ground sampling distance of 6.25 m at an orbit altitude of 500 km. Its two command transceivers operate in the commercial and amateur radio VHF and UHF bands and one of them provides a VHF to UHF repeater service to radio amateurs. This paper presents initial results of a global three week monitoring period of two VHF frequency ranges. The data is obtained by executing on-board flight control procedures to select the frequencies to measure. The existing on-board telemetry gathering system is employed to record the data, most notably the received signal strength for the selected frequency. The data is downloaded using an adaptation of the imagery data download path. We determine regions of high signal levels by distributing individual measurements over cells in the satellite footprint before averaging over the cells. The data is then plotted on a geographical signal strength heatmap. We compare our results with that of a similar study of the late 1990s and point out changes since then. The data provides useful information for selecting future ground station locations for minimum interference. It further gives an indication of frequencies to use for command and telemetry communication at existing ground stations. We propose that including a receiver capable of measuring frequency interference across a desired frequency range is very useful to future missions for selecting communication frequencies from this range for ground station locations.     

Antenna for precise orbit determination

The ESA SWARM mission will consist of three satellites that will measure the Earth magnetic field. The system calls for metre accuracy knowledge of the measurement locations. To achieve this a GPS receiver is used. At least four GPS signals are tracked to determine the code and carrier ranges, from which the position can be derived. The accuracy improves when using more GPS satellites and by averaging over many measurements. The latter is achieved in ground processing with a model-based orbit prediction, resulting in cm accuracy. The main error contributions in the processing are often measurement errors due to satellite multi-path effects. The multipath effects are characterized by measuring the antenna on a 1.5 m mock-up, representing the 9 m long satellite. In order to verify that the mock-up is representative, extensive electromagnetic simulations were made. The simulations included the antenna and the complete satellite and were then reduced to the antenna and a section of the satellite. The actual design of the antenna was performed with several levels of software. First, a fast bodies-of-revolution simulation found a geometry with the right coverage. Then, a finite element method simulation allowed us to match the antenna at two frequencies simultaneously.     

Switzerland and space – how a small country succeeds

Is it possible for small nations to get their concerns aired or improve their industries and economies in the field of space activities? In this edited version of a speech to the international symposium on ‘The History of the European Space Agency’, held in London, 11–13 November 1998, the author demonstrates that, through judicious cooperative endeavour within the framework of ESA, and a willingness to put forward solutions rather than harping on problems, it is. Switzerland’s role in the foundation of ESA is discussed, along with various successful initiatives taken by the country. The particular difficulties presented by the country’s constitution – and how they have been overcome – are also examined. The author concludes with some thoughts on the present and futute state of space affairs in Europe.     

The Future of Public–Private Partnerships in Satellite Communications

Around 50 leaders and experts from space industry, governmental and financial institutions participated in an ESA conference on “The Future of Public–Private Partnerships in Satellite Communications” in Vienna in March 2009. An increasing portion of commercial and institutional space projects are operated under the provisions of service contracts, with public–private partnerships (PPPs) becoming a significant source of financing for space programmes. The conference was based on a study initiated by ESA and performed by Euroconsult, Milbank and ESPI, outlining the main perspectives of modern PPP models in the European satellite communications sector.     

Antenna for precise orbit determination

The ESA SWARM mission will consist of three satellites that will measure the Earth magnetic field. The system calls for metre accuracy knowledge of the measurement locations. To achieve this a GPS receiver is used. At least four GPS signals are tracked to determine the code and carrier ranges, from which the position can be derived. The accuracy improves when using more GPS satellites and by averaging over many measurements. The latter is achieved in ground processing with a model-based orbit prediction, resulting in cm accuracy. The main error contributions in the processing are often measurement errors due to satellite multi-path effects. The multipath effects are characterized by measuring the antenna on a 1.5 m mock-up, representing the 9 m long satellite. In order to verify that the mock-up is representative, extensive electromagnetic simulations were made. The simulations included the antenna and the complete satellite and were then reduced to the antenna and a section of the satellite. The actual design of the antenna was performed with several levels of software. First, a fast bodies-of-revolution simulation found a geometry with the right coverage. Then, a finite element method simulation allowed us to match the antenna at two frequencies simultaneously.     

Balloon-borne air traffic management (ATM) as a precursor to space-based ATM

The International Space University—Balloon Air traffic control Technology Experiment (I-BATE¹) has flown on board two stratospheric balloons and has tracked nearby aircraft by receiving their Automatic Dependent Surveillance-Broadcast (ADS-B) transmissions. Air traffic worldwide is facing increasing congestion. It is predicted that daily European flight volumes will more than double by 2030 compared to 2009 volumes. ADS-B is an air traffic management system being used to mitigate air traffic congestion. Each aircraft is equipped with both a GPS receiver and an ADS-B transponder. The transponder transmits an equipped aircraft's unique identifier, position, heading, and velocity once per second. The ADS-B transmissions can then be received by ground stations for use in traditional air traffic management. Airspace not monitored by these ground stations or other traditional means remains uncontrolled and poorly monitored. A constellation of space-based ADS-B receivers could close these gaps and provide global air traffic monitoring. By flying an ADS-B receiver on a stratospheric balloon, I-BATE has served as a precursor to a constellation of ADS-B-equipped Earth-orbiting satellites. From the ～30 km balloon altitude, I-BATE tracked aircraft ranging up to 850 km. The experiment has served as a proof of concept for space-based air traffic management and supports a technology readiness level 6 of space-based ADS-B reception.     

Flight performance analysis of GRACE K-band ranging instrument with simulation data

A dual one-way ranging (DOWR) system provides very high accuracy range measurements between two satellites. The GRACE satellite mission implements the DOWR, called KBR (K-band ranging), to measure very small inter-satellite range change in order to map the Earth gravity field. The flight performance of the KBR is analyzed by using a hybrid software simulator that incorporates actual satellite orbit data into a comprehensive KBR simulator, which was earlier used for computing the GRACE baseline accuracy. Three types of experiments were performed. First is the comparison of the flight data with the simulated data in spectral domain. Second is the comparison of double differenced noise level. Third is the comparison of the range-rate difference with GPS clock estimates. The analysis shows a good agreement with the simulation model except some excessive high frequency noise, e.g. 10⁻⁴ m/√Hz at 0.1 Hz. The range-rate difference shows 0.003 cyc/s discrepancy with the clock estimates. These analyses are helpful to refine the DOWR simulation model and can be benefit to future DOWR instrument development.     

A pilot survey of attitudes to space sciences and exploration among British school children

Over 200 school children in eight schools in the east of England were surveyed to determine their interest in space exploration and awareness of current space activities. Of those surveyed, 33% were interested in space to ‘discover a new planet’, and 24% to find life on another planet. When asked to list space exploration organisations 77% listed NASA. Six of those surveyed listed ESA (<0.5%). The data bring starkly to light, despite the Huygens landing on Titan and Mars Express, the lack of awareness of the existence of ESA among a new generation of European school children. These data suggest that further surveys are merited to determine the factors that influence interest in space sciences and related disciplines among school children, and the source of their information.     

Norway's future in space

Norway has recently published its national long-term plan for space activities (1993–1996) and the main points of this are reproduced here. While telecommunications, positioning and navigation and Earth observation are understandably given a high priority, there is also an emphasis on space transportation and space science, and a belief that Norwegian industry and research institutes are capable of gaining contracts beyond the agreed scope of the country's participation in ESA.     

Index: piggy-back satellite for aurora observation and technology demonstration

This paper describes outline of the piggy-back satellite “INDEX” for demonstration of advanced satellite technologies as well as for observation of fine structure of aurora. Aurora observation will be carried out by three cameras(MAC) with a monochromatic UV filter. Electron and ion spectrum analyzer (ESA/ISA) will measure the particle phenomena together with the aurora imaging. INDEX satellite will be launched in 2002 by Japanese H2-A. The satellite is mainly controlled by the high-speed, fault-tolerant on-board RICS processor (three-voting system of SH-3). The attitude control is a compact system of three-axis stabilization. Although the size of INDEX is small (50Kg class), several newly-developed technologies are applied to the satellite system, including silicon-on-insulator devices, variable emittance radiator, solar-concentrated paddles, lithium-ion battery, and GPS receiver with all-sky antenna-coverage.     

The navigational experiments on microgravitational space platform “FOTON-M2”

This paper presents the review of results of the navigating experiments which have been carried out during flight of microgravitational space platform (MSP) Foton-M2 in May–June 2005. The brief characteristic of the created MIRAGE–M equipment consisting from magnitometric system and satellite radionavigation receiver is given. The measurements have allowed to restore unguided MSP movement and to estimate a level of microaccelerations (microgravitations) onboard during flight, and have provided precision time-position binding of the research experiments. The data from the equipments transmitted on the telemetering channel have allowed testing the information technologies of virtual support of experiments in space. Flight testing of the equipment has allowed make a conclusion on usefulness of accommodation onboard the small-sized auxiliary navigating system focused for work with users of research experiments. The experiments on MSP Foton-M2 are the development of experiments with MIRAGE equipment carried out in 1999 during flight time of MSP Foton-12 [N.D. Semkin, V.V. Ivanov, V.I. Abrushkin, V.L. Balakin, I.V. Belokonov, K.E. Voronov, The experiments with magnetic fields formed by technical equipment inside Foton-12 spacecraft: the results of the MIRAGE experiments, in: Proceedings of International Conference “Scientific and Technological Experiments on Russian Foton/Bion Recoverable Satellites: Results, Problems and Outlooks”, 25–30 June 2000, pp. 116–122; V.L. Balakin, I.V. Belokonov, V.V. Ivanov, “Determination of motion of spacecraft Foton-12 as a result of magnetic fields measurement in MIRAGE experiment”, pp. 231–238 (published in the same place)].Paper is executed within the framework of the grant of the Russian Fund of Fundamental Researches 06-08-00244.     

The effect of vibrations on heterogeneous fluids: Some studies in weightlessness

Under weightlessness, the effect of harmonic vibrations can easily induce average motions in fluids with density inhomogeneities. We will consider more particularly pure fluids near their gas–liquid critical point, where the temperature variation of all important parameters (e.g. interfacial tension, density difference) follows universal, scaling laws. We will thus study, below the critical point, the ordering of the gas–liquid interfaces (at equilibrium and during the phase separation) and, above the critical point, some thermovibrational instabilities. These studies have been performed in the Russian MIR station and in the MiniTexus and Maxus rockets of ESA and under magnetic compensation of gravity on earth.     

Solar Orbiter—Heat shield and system technology

Solar Orbiter will enhance our knowledge of the Sun by observations and in situ measurements as close as 0.22 AU from our star. Placed on an orbit with a period two-thirds the one of Venus, Solar Orbiter will use the many encounters with the planet to gradually incline its orbit and gain view on the Sun's poles. The permanent in situ observations will be associated to remote-sensing observations over large parts of the orbits.ESA Science Directorate has awarded in parallel two Solar Orbiter Heat Shield and System Technology contracts to industry. This paper presents the achievements of Thales Alenia Space thanks to one of these two ESA contracts.It shows how the main technical challenge brought by the heat flux of 20 solar constants has been addressed by the system and heat shield design. The design and manufacturing of a breadboard of the heat shield in view of thermal test verification is then reported. The main technological developments and residual risks are assessed, paving the way for the definition phase of the program.     

The activities of ocean colour remote sensing in China

This article reviews the development of ocean colour remote sensing over the past decade in China. China launched its first remote sensing satellite FY-1A on 7 September 1988 and its second, FY-1B on 3 September 1990. Both of them had a Very High Resolution Scanning Radiometer (VHRSR) which involved two channels (0.48–0.53 and 0.53–0.58 u) for measuring ocean colour. A new polar orbiting satellite FY-1-02 was scheduled to be in orbit by 1998 with an improved VHRSR which has more (10) channels and is more sensitive for ocean colour remote sensing. The special programme of the ocean colour satellite HY-1 has been approved by the Chinese government, as has the planning of another new generation polar orbiting remote sensing satellite, FY-3. A type of sensor has been developed known as the Chinese Moderate Imaging spectroradiometer (CMODIS). Following its review, the article will describe the future activities of ocean colour remote sensing in China and explain their scientific goal.     

Microgravity research and user support in the Space Station era: The Microgravity User Support Centre

Future space systems, such as Columbus, the planned European contribution to the International Space Station, offer ample possibilities for microgravity research and application. These new opportunities require adequate user support on ground and novel operational concepts in order to ensure an effective utilization. Extensive experience in microgravity user support has been accumulated at DFVLR during the past Spacelab 1 and D1 missions. Based on this work, a Microgravity User Support Centre (MUSC) has been built and is active for the forthcoming EURECA-A1 and D2 missions, to form an integrated support centre for the disciplines life sciences and material sciences in the Space Station era. The objective of the user support at MUSC is to achieve:

&#x02022; easy access to space experiments for scientific and commercial users,

&#x02022; efficient preparation of experiments,

&#x02022; optimum use of valuable microgravity experimentation time,

&#x02022; cost reduction by concentration of experience.

This is implemented by embedding the MUSC in an active scientific environment in both disciplines, such that users can share the experience gained by professional personnel. In this way, the Space Station system is operated along the lines established on ground for the utilization of large international research facilities, such as accelerators or astronomical observatories. In addition, concepts are developed to apply advanced telescience principles for Space Station operations.     

一种宽带测向接收机高频前端设计

介绍了一种0．2-20GHz干涉仪测向接收机微波前端研制思路。分析了测向天线阵设计布局和宽频段微波通道超外差实现方案,中频采用宽带和窄带两种带宽切换,并针对窄带通道易受测频误差和频综分辨率偏差影响,采用两级搜索方式消除误差以准确侦收辐射源信号。理论分析和工程试验结果表明该接收机具有灵敏度高、截获概率大、测向精度高、体积小等优点。     

The Phoenix signal detection system

The Phoenix system is based on that developed for the Targeted Search element of the former NASA High Resolution Microwave Survey (HRMS). The Phoenix system was used at the Parkes 64 m and Mopra 22 m antennas of the Australian Telescope National Facility in the first part of 1995. The system consists of: (1) an RF/IF subsystem providing 1–3 GHz coverage; (2) a search subsystem with a 20 MHz, dual-polarization search bandwidth; (3) a two-site, pseudo-interferometric follow-up subsystem that reobserves interesting signals found by the search subsystem; and (4) a control subsystem capable of automatic searching.     

Formation of a Polarization Jet during the Expansion Phase of a Substorm: Results of Ground-Based Measurements

The ground-based polarization jet measurements at the Yakutsk ionosphere station (L= 3.0) for the years 1989–1991 (110 events) are compared with variations of the AE-index and with parameters of the local magnetic activity. It is shown that polarization jet development in the near midnight sector can occur during a period of no longer than 10 min on the expansion phase of a substorm. The formation of the polarization jet is accompanied by a specific magnetic field variation corresponding in shape to a fast passage of the Harang Discontinuity above the station. Statistical data are given on ground level observations of the polarization jet, which are close to those measured from satellites. The mean delay (averaged over the full data bank) between the onset of a substorm with AE 500 nT and the moment of the polarization jet appearance at L= 3.0 is equal to 0.5 h near midnight and to 1.0 – 1.5 h in the evening sector. Estimations show that the duration of the polarization jet formation when energetic ions are injected into the Harang Discontinuity region above the ground station can last for about 10 min, and during this time the Harang Discontinuity can be shifted to the west. This is in qualitative agreement with the described observations.     

Simultaneous Response of the Mid-Latitude Ionosphere to a Sudden Commencement of Strong Magnetic Storms

Using the new technology of global GPS detection of ionospheric disturbances (GLOBDET), it is found that a sharp increase of the time derivative of the magnetic field strength during magnetic storms is accompanied by a simultaneous decrease of the mid-latitude total electron content (TEC) over the entire dayside of the globe. The corresponding negative correlation coefficient is no less than 0.8, and the delay relative to the sudden commencement of magnetic storm is about 3–10 min. The effect is especially clearly pronounced for magnetic storms with sudden commencements (SSC). The analysis is carried out for a set of 90 to 300 GPS stations for 10 days (January 6 and April 23, 1998; April 6, June 8, July 13, 14, and 15, 2000; March 31, April 4 and 11, 2001) with various levels of geomagnetic activity (D _st and K _p varied from –6 to –295 nT and from 0 to 9, respectively). The amplitude of the response in the total electron content for the events considered was 0.1–0.4 × 10¹⁶ m^–2 (which is a deviation of 0.2–2.6% from the TEC background value). The velocity of the disturbance motion from the dayside to the nightside was about 10–20 km/s. The results obtained agree with the data of ionospheric parameter measurements conducted earlier by methods with high temporal resolution.