The ROSAT mission

A primary scientific objective of the ROSAT mission is to perform the first all-sky survey with an imaging X-ray telescope leading to an improvement in sensitivity by several orders of magnitude compared with previous surveys. A large number of new sources (? 10⁵) will be discovered and located with an accuracy of 1 arcmin or better. These will comprise almost all astronomical objects from nearby normal stars to distant quasistellar objects. After completion of the survey which will take half a year the instrument will be used for detailed observations of selected sources with respect to spatial structure, spectra and time variability. In this mode which will be open for guest observers ROSAT will provide substantial improvement over the imaging instruments of the Einstein observatory.The main ROSAT telescope consists of a fourfold nested mirror system with 83 cm aperture having three focal plane instruments. Two of them will be imaging proportional counters (0.1 – 2 keV) providing a field of view of 2°, an angular resolution of ≈ 30″ in the pointing mode and a spectral resolution ^ΔE/E ≈ 45% FWHM at 1 keV. The third focal instrument will be a high resolution imager (≈ 3″). The main ROSAT telescope will be complemented by a parallel looking Wide Field camera which extend the spectral coverage into the XUV band.     

The SIGMA mission

SIGMA, a hard X-ray/medium energy gamma ray (30 keV-2 MeV) imaging experiment, is being designed and constructed to attain an angular resolution of the order of 1 arcminute, and a sensitivity of several milliCrabs. The instrument uses a position sensitive detector of the Anger camera variety, and a two dimensional coded mask. The results of the instrument definition study are presented; a flight model will be constructed for a late 1987 launch.     

The tenma mission

Tenma, the second X-ray astronomy satellite of Japan launched in February 1983, is outlined. The main instrument of Tenma is a large-area gas scintillation proportional counter array. Some of the highlights of the results thus far obtained are briefly discussed.     

The exosat mission

Exosat, the European X-ray Observatory, was placed in orbit on 26 May 1983. The spacecraft, stabilized axes in three to a few arc second, carries four instruments, two one-metre focal length imaging telescopes, a large area proportional counter array and a gas scintillation proportional counter spectrometer. The salient features of the instrumentation, the sensitivities achieved in orbit and the status after the first year of orbital operation are described. Three specific observations, VO332+53, SCO X–1 and M.83 are discussed to demonstrate the power of the EXOSAT instrumentation and the operational flexibility of the spacecraft and ground system.     

The SAX mission

SAX denotes the X-Ray Astronomy Satellite selected by the Italian National Space Plan for inclusion in the Science Programme. The purpose of SAX is to perform spectroscopic, spectral and time variability studies of celestial X-Ray sources in the energy band from 1 to 200 KeV. It is intended to continue and expand upon previous observations of such sources. The instrumentation consists of four X-Ray imaging concentrators sensitive from 1 to 10 KeV (one of them extending down to 0.1 KeV), one Gas Scintillation Proportional Counter sensitive from 3 to 120 KeV, a Sodium Iodide Scintillator Crystal in Phoswich configuration operating from 15 KeV to 200 KeV; these detectors are coaligned to a common pointing axis. Three Wide Field Cameras (2–30 KeV) with axis at 90° to that of the narrow field instruments complete the payload.The Satellite launch is foreseen for 1988, in a low altitude (500 Km), low inclination (12°) orbit.The SAX scientific programme is carried out by a Consortium of Italian Institutes, in cooperation with Institutes from Holland; a partecipation of the Space Science Department of ESA is also foreseen.     

The solar orbiter mission

Approved in October 2000 by ESA's Science Programme Committee as a flexi-mission, the Solar Orbiter will studythe Sun and unexplored regions of the inner heliosphere from a unique orbit that brings the probe to within 45 solar radii (0.21 AU) of our star, and to solar latitudes as high as 38°. This orbit will allow the Solar Orbiter to make fundamental contributions to our understanding of the acceleration and propagation of energetic particles in the extended solar atmosphere. During quasi-heliosynchronous phases of the orbit, Solar Orbiter will track a given region of the solar surface for several days, making possible unprecedented studies of the sources of impulsive and CME-related particle events. The scientific payload to be carried by the probe will include a sophisticated remote-sensing package, as well as state-of-the-art in-situ instruments. The multi-wavelength, multi-disciplinary approach of Solar Orbiter, combined with its novel location, represents a powerful tool for studies of energetic particle phenomena.     

The Swift GRB MIDEX mission

Swift is a first-of-its-kind multiwavelength transient observatory for γ-ray burst astronomy. It has the optimum capabilities for the next breakthroughs in determining the origin of γ-ray bursts and their afterglows, as well as for using bursts to probe the early Universe. Swift will also monitor the soft gamma repeaters and perform the first sensitive hard X-ray survey of the sky. The mission is being developed by an international collaboration and consists of three instruments, the Burst Alert Telescope (BAT), the X-ray Telescope (XRT), and the Ultraviolet and Optical Telescope (UVOT). The BAT, a wide-field γ-ray detector, will detect >100 γ-ray bursts per year with a sensitivity 5× that of BATSE. The sensitive narrow-field XRT and UVOT will be autonomously slewed to the burst location within 20–70 s to determine 0.3–5.0″ positions and perform optical, UV, and X-ray spectrophotometry. Strong education/public outreach and follow-up programs will help to engage the public and the astronomical community. Swift launch is planned for late 2004.     

The comet rendezvous asteroid flyby mission

The Comet Rendezvous Asteroid Flyby (CRAF) mission is the next step in the exploration of comets as well as the first of NASA's new generation of spacecraft for primitive body and outer-planet missions. If launched in September 1992, CRAF will fly by one or two asteroids en route to a rendezvous with P/Tempel 2 in December, 1996. The post-rendezvous mission profile includes: (1) a reconnaissance phase to assess the cometary environment and to determine the mass of the nucleus; (2) a nucleus observation phase, lasting over a year, with emphasis on determining the physical and chemical properties of the nucleus and the changes associated with the onset of cometary activity; and (3) a perihelion phase with emphasis on studying the nature and dynamics of the dust, gas, and plasma in the coma and tail.     

The Giotto mission to Halley''s comet

ESA's Giotto mission to Halley's comet is a fast flyby in March 1986, about four weeks after the comet's perihelion passage when it is most active. The scientific payload comprises 10 experiments with a total mass of about 60 kg: a camera for imaging the comet nucleus, three mass spectrometers for analysis of the elemental and isotopic composition of the cometary gas and dust environment, various dust impact detectors, a photopolarimeter for measurements of the coma brightness, and a set of plasma instruments for studies of the solar wind/comet interaction. In view of the high flyby velocity of 68 km/s the experiment active time is very short (only 4 hours) and all data are transmitted back to Earth in real time at a rate of 40 kbps. The Giotto spacecraft is spin-stabilised with a despun high gain parabolic dish antenna inclined at 44.3° to point at the Earth during the encounter while a specially designed dual-sheet bumper shield at the other end protects the spacecraft from being destroyed by hypervelocity dust impacts. The mission will probably end near the point of closest approach to the nucleus when the spacecraft attitude will be severely perturbed by impacting dust particles leading to a loss of the telecommunications link.     

The first results from the Herschel-HIFI mission

This paper contains a summary of the results from the first years of observations with the HIFI instrument onboard ESA’s Herschel space observatory. The paper starts by outlining the goals and possibilities of far-infrared and submillimeter astronomy, the limitations of the Earth’s atmosphere, and the scientific scope of the Herschel-HIFI mission. The presentation of science results from the mission follows the life cycle of gas in galaxies as grouped into five themes: Structure of the interstellar medium, First steps in interstellar chemistry, Formation of stars and planets, Solar system results and Evolved stellar envelopes. The HIFI observations paint a picture where the interstellar medium in galaxies has a mixed, rather than a layered structure; the same conclusion may hold for protoplanetary disks. In addition, the HIFI data show that exchange of matter between comets and asteroids with planets and moons plays a large role. The paper concludes with an outlook to future instrumentation in the far-infrared and submillimeter wavelength ranges.     

The coronal dynamics imagers for the KuaFu mission

The Space Weather Explorer – KuaFu mission will provide simultaneous, long-term, and synoptic observations of the complete chain of disturbances from the solar atmosphere to the geospace. KuaFu-A (located at the L1 liberation point) includes Coronal Dynamics Imagers composed of a Lyman-α coronagraph (from 1.15 to 2.7 solar radii) and a white light coronagraph (out to 15 solar radii), in order to identify the initial sources of Coronal Mass Ejections (CMEs) and their acceleration profiles. The difficulty of observing the lower corona should not be underestimated since instrumental stray light remains a critical issue in the visible because of the low contrast of the corona with respect to the Sun. Observing the corona in the Lyman-α line is a valid alternative to white light observations. This approach takes advantage of both the intrinsic higher contrast of the corona with respect to the solar disk in this line compared to the visible, and the absence of F-corona at 121.6 nm. Furthermore, it has been convincingly shown that the coronal structures seen in Lyman-α correspond to those seen in the visible and which result from Thomson scattering of the coronal ionized gas. This is because the plasma is still collisional in the lower corona so that the hydrogen neutral atoms are coupled to the protons. A classical, all-reflecting internally-occulted Lyot coronagraph is required so as to preserve the image quality down to the inner limit of the field-of-view. A narrow band interference filter located in a collimated beam allows isolating the Lyman-α line. The visible coronagraph will adopt the approach of a single instrument having a large field-of-view extending from 2.5 to 15 solar radii. Such a design is based on refractive externally-occulted coronagraphs built for recent past missions, essentially the LASCO-C2 and C3 instruments and the SECCHI/COR 2 of the STEREO mission, which is itself a combination of the C2 and C3 instruments.     

The L5 mission for space weather forecasting

We have studied a number of interplanetary space mission scenarios for space weather research and operational forecasting experiments and concluded that a spacecraft should be deployed at the L5 point of the Sun–Earth system to enable remote sensing of the Sun and interplanetary space and in situ measurements of solar wind plasma and high energy solar particle events. The L5 point is an appropriate position for making side-view observations of geo-effective coronal mass ejections and interplanetary plasma clouds.Here, we describe briefly the mission plan and the ongoing BBM development of important subsystems such as the wide field coronal imager (WCI) and the mission processor. The WCI will have a large CCD array with 16-bit sampling, to achieve a dynamic range of several thousand in order to detect very small deviations due to plasma clouds under zodiacal light contaminations a hundred times brighter than the clouds. The L5 mission we propose will surely contribute to the construction of an international space weather observation network.     

Planet-A mission to Halley

Looking at the chance of the next apparition of the Halley comet in 1986, ISAS decided to send a first Japasanese interplanetary spacecraft for the study of cometary hydrogen coma and solar wind. The Planet-A spacecraft which carries VUV imaging camera and solar wind plasma analyser will be launched in August 1985 and flyby the Halley comet in early March 1986 with the distance of several million kilometers from the comet nucleus. This mission is not only self-consistent but collaborative with other space mission as well as earth-bound observations. In the present paper, the Planet-A mission to Halley is described with brief explanation of the spacecraft.     

The gamma-ray observatory mission objectives and its significance for gamma-ray astronomy

The Gamma Ray Observatory (GRO) is an approved NASA mission, programmed for launch in 1988. Its complement of four detectors has established goals: 1) to study the nature of compact γ-ray sources such as neutron stars and black holes, or objects whose nature is yet to be understood; 2) to search for evidence of nucleosynthesis especially in the regions of supernovae; 3) to study structural features and dynamical properties of our galaxy; 4) to explore other galaxies, especially the extraordinary types such as radio, Seyferts, and quasars; and 5) to study cosmological effects by examining the diffuse radiation in detail. This paper discusses the design, objectives, and expected scientific results of each of the GRO instruments in view of the GRO mission goals.     

The LET spectrum and its uncertainty during the CRRES mission.

We present Linear Energy Transfer (LET) spectra calculated for the 1990-1991 CRRES mission using the galactic cosmic ray (GCR) and solar energetic particle (SEP) models developed for the CRRES/SPACERAD program and presented by Chen, et al. 1992 at this conference. We discuss how the spectra vary with changes in the galactic cosmic ray and solar energetic particle models. Finally, we illustrate the application and significance of these results by using them to predict single event upset event rates in a sample integrated circuit memory device, a 256 x 4-bit bipolar static RAM (93L422).     

The high-LET radiation component measured during the EUROMIR-94 mission.

Stacks of CR-39 plastic nuclear track detectors were mounted inside the MIR-station during the EUROMIR-94-mission. We present LET-spectra determined separately for long range cosmic ray heavy ions and for short range target fragments produced in nuclear interactions of cosmic rays and measured charge distributions for relativistic and stopping particles.     

The Japanese lunar mission SELENE: Science goals and present status

The Japanese lunar mission SELENE (SELenological and ENgineering Explorer) has been in development to target launch scheduled 2007 summer by H-IIA rocket. The SELENE is starting final integration test after SAR (System Acceptance Review), SRR (System Reliability Review) and instrument environment test. The SELENE is a remote-sensing mission orbiting 100 km altitude of the Moon for nominal one year and extended some months to collect the data for studying the origin and evolution of the Moon. Fourteen instruments and experiment systems are preparing for studies of the Moon, in the Moon, and from the Moon; global element and mineral compositions, topological structure, gravity field of whole moon, and electromagnetic and particle environment of the Moon. The new data center SOAC (SELENE Operation and data Analysis Center) are completed to construct in JAXA Sagamihara campus, and end-to-end test will be carried out between SOAC and data downlink stations.     

Planet-B mission to Mars - 1998

PLANET-B is the Japanese Mars orbiter program. The primary objective of the program is to study the Martian aeronomy, putting emphasis on the interaction of the Martian upper atmosphere with the solar wind. The launch of the spacecraft is scheduled for August, 1998. The periapsis altitude and the apoapsis are 150 km and 15 Mars radii, respectively. The dry weight of the orbiter is 186 kg including 14 science instruments. Advanced technologies are employed in the design of the spacecraft in order to overcome the weight limitation. This paper describes the scientific objectives of the PLANET-B program and outline of the spacecraft system.