Kazuya Ishizaka
(Tokyo Institute of Technology, Japan)

The Laboratory for Space Systems (LSS), Matunaga Laboratory at the Tokyo Institute of Technology has so far developed and launched three small satellites successfully; CUTE-I, Cute-1.7+APD and Cute-1.7+APD II. The fourth small satellite TSUBAME, which is a demonstration satellite for Earth and astronomical observation technology is currently under development by the TSUBAME development team, which is mainly organized by LSS. It is planned that TSUBAME will be launched into a sun-synchronous orbit, and its size will be about 50cm x 50cm x 50cm with a total mass of about 48kg. The objectives of TSUBAME are as follows: 1) on-orbit demonstration of newly developed Micro Control Moment Gyroscopes (CMGs), 2) polarized gamma-ray burst (GRB) observation using a Hard X-Ray Compton Polarimeter (HXCP) and Wide field Burst Monitors (WBMs) with high-speed attitude maneuvering using Micro-CMGs, 3) Earth observation with a small high-resolution optical camera. By combining a characteristic of a small satellite which has small mass and high torque that CMG can generate, each mission can be achieved. In this paper design of a pre-flight model for TSUBAME will be explained. The progress of its integration will be also reported, and TSUBAME development team pursues the goal of launching it in 2012.

Freddy Pranajaya
(University of Toronto Institute for Aerospace Studies, Canada)

The NEMO (Nanosatellite for Earth Monitoring and Observation) bus is the next evolution to the Generic Nanosatellite Bus (GNB) technology from the Space Flight Laboratory (SFL) at the University of Toronto Institute for Aerospace Studies (UTIAS). The NEMO bus implements existing GNB technology in an innovative high-performance architecture. The bus has a 20 cm by 20 cm by 40 cm primary structure, a 15 kg design mass, and a 80W peak power generation. A minimum of 45W is available to the payload, sufficient for supporting a powerful computer as well as a dedicated state-of-the-art high speed transmitter. Up to 9 kg can be dedicated to the payload and payload-specific hardware. NEMO spacecraft can be configured with passive stabilization or full three-axis control using three reaction wheels. Up to 1 arcmin of pointing stability can be realized through the use of a star tracker. NEMO-AM is the first NEMO spacecraft and will carry a dual-polarization, multi-spectral, multi-angle optical instrument for observing atmospheric aerosols. NEMO-AM is being built under a collaborative agreement between SFL and the Indian Space Research Organization (ISRO), with a target completion in 2011. This paper outlines the innovative aspects of the NEMO bus and the NEMO-AM mission.

Stephan Roemer
(Astro- und Feinwerktechnik Adlershof GmbH, Germany)

The TET-satellite-bus is designed as modular and flexible microsatellite for LEO-applications and inclination between 53 and SSO. The typical launch of a satellite based on the TET-satellite-bus is as a piggyback-payload. The satellite bus technology is based on the technology of the space proven BIRD-satellite-bus but with high improvement in performance and reliability. This results in an overall envelope of 670x580x880mm and a satellite mass of 120kg. With 70kg satellite-bus mass the satellite bus is able to provide a payload-capacity of 50kg with an envelope of 460x460x428mm. To support different kind of missions the bus contains the nominal satellite bus and a payload-support-system, which is on its payload interface side adaptable to the data and power interface requirements, data storage requirements and payload control requirements. So the nominal satellite bus will be in normal cases unchanged, but can adapted in parts, like an upgrade to X-Band transmission if higher data rates are required. The TET-1-satellite will be launched in 2011. We will present actual flight data from the LEOP-phase. Additional we will present the results of the TET-X upgrade-program, to equip the satellite bus with more payload mass/volume (70kg), more power (up to 400W) and more data-downlink-capacity (up to 1Gbit/sec).

Kenta Okamoto
(Shinshu University, Japan)

The area of forest land in Japan accounts for about 66% and about 40% of them are man-made forests. They are composed of conifers including Chamaecyparis obtuse, Pinus densiflora, Larix Kaempheri, and Cryptomeriz japonica. At present, these main plantations with about 50-year-old trees must be managed by thinning or selection cutting. For that purpose, high-resolution data based on an individual tree crown are necessary. Satellites make it possible to obtain data on several areas simultaneously. Shinshu university has been studying a 50 kg-class micro-satellite with 5 m spatial resolution for forest remote sensing, especially for observing the tree crowns of Cahmaecyparis obtuse . We designed a microsatellite for earth observation named KOMOREBI. The size of KOMOREBI is 460x460x410 mm and the mass is 44.6 kg including 5 kg margin. The aperture of the optical telescope is 152 mm and the focal length is 1524 mm. KOMOREBI has two missions. The one is the forest observation using a high resolving optical system with 5 m GSD. The other is a new visible light communications(VLC) using eight power LEDs. This paper summarizes the outline of the bus system and the missions of KOMOREBI.

Kenichi Saito
(NEC Corporation, Japan)

This presentation shows an overview of the ASNARO satellite, being developed by NEC and USEF under the contract with NEDO, mainly focusing on its observation ability. ASNARO, Advanced Satellite with New system ARchitecture for Observation, is a 450 kg class LEO (SSO) earth observation satellite with a sub-meter optical sensor. The main purpose of this project is to develop a system for optical earth observation, adopting NEC's small standard satellite bus module, "NEXTAR". The Japanese government evaluates ASNARO as an essential step to bring space systems competitive in the commercial market. ASNARO has high agility in pointing control which improves the frequency of observing point of interests. This enables ASNARO to take images in wider area despite its small satellite size, keeping small GSD (Groud Sampling Distance). As for the observation ability of the ASNARO Satellite, specification of the agility/ maneuverability will be introduced, followed by a detailed analysis of an observation sequence. The analysis argues the point of interests, up-link/ down-link conditions, and optimization of sequence planning. For a sample case, an orbit over Japan is chosen. Hokkaido and Okinawa Ground Stations are selected for the up-link of telecommands and down-link of observation data, respectively.