Koji Nakaya

Tokyo Tech CubeSat: CUTE-I - Design & Development of Flight Model and Future Plan -

Laboratory for Space Systems, Tokyo Institute of Technology finished development of CUTE-I and is waiting for its launch on June 30, 2003. CUTE-I is the first CubeSat of Tokyo Institute of Technology, that is a 10 cm-edge cube-sized satellite of less than 1kg mass. CUTE-I has three missions such as communication, attitude sensing and deployment. to establish a bus component design for pico satellites like the CubeSat. In parallel with the CUTE-I development, we also developed a separation mechanism that is used to separate CUTE-I from the launcher on orbit. In this paper, we describe the design of CUTE-I and the separation mechanism as well as results of environment tests such as long-range communication test, thermal vacuum test, vibration test and separation test. We also mention a Tokyo Tech future plan on our satellite development.

NEW SPINNING DEPLOYMENT METHOD OF LARGE THIN MEMBRANES WITH TETHER CONTROL

In this paper, we propose one membrane deployment method: tether-controlled spinning deployment. Very large, thin and flexible membrane (sail) is packed and then is deployed in orbit. In the process of membrane deployment, we use controlled tethers to stably deploy the membrane. Some types of the system are proposed, and the characteristics and technical issues are briefly mentioned. Numerical simulation results using a distributed mass-tether network model show the potential advantage of the proposed method. An experimental set-up of the proposed deployment using the two-dimensional micro-gravity simulators developed at Tokyo Institute of Technology is introduced, and the result of preliminary deployment experiments with a thin membrane of 1m-sized is shown.

On Attitude Maneuver of Spinning Tethered Formation Flying Based on Virtual Structure Method

This paper discusses attitude maneuvers of spinning tethered formation flying system. A virtual structure method is applied to control the formation. Modeling, formulation and attitude maneuver control architecture are explained. In this paper, the spinning tethered formation flying is assumed to be operated around the Earth. Numerical simulations are conducted for the maneuvers of the system keeping circular formation. Results of numerical simulations are considered in terms of accuracy of the formation, thruster force, tether tension and fuel consumption. Validity of the proposed control is indicated via results of the simulations. } }

Tokyo Tech 1kg Pico-Satellite CUTE-I-Development, Launch & Operations

Abstract Tokyo Institute of Technology, Laboratory for Space Systems had developed a 1 kg pico-satellite CubeSat, CUTE-I, and it was successfully launched on June 30 2003 by a Eurockots rocket. CUTE-I is one of the first launched CubeSats and also the smallest civilian satellites in the world, which are able to make dual-directional communications with the ground stations. In this paper, the total design of CUTE-I flight model and operation results focused on its attitude analyses are explained.

Retrieving Dynamics and Control of Tethered Sampling Method for Minorbody Exploration

In this paper, dynamics behavior of tether retrieval with a reel mechanism in a tethered sampling method in deep space is discussed. The tethered sampling method proposed by authors is investigated as a candidate for soil sample collection method of minorbodies for the next minorbody exploration mission. The method consists of three phases: 1) shooting a corer together with a tether, 2) inserting the corer into a surface and collecting soil in the corer, 3) pulling back and retrieving the corer with the tether. This paper mainly deals with dynamics of the tether and corer in the recovery phase, and numerical simulations and fundamental experiments of the tether dynamics are conducted using a tether control mechanism. A tether tension control is proposed and tether and corer coupled dynamics are made clear by the numerical simulation. Moreover, experimental investigations are conducted by using a sampler horn and a reel mechanism which can control the tether tension and measure the tether length and velocity. The results of the experiments are compared with the results of the numerical simulation to show the feasibility of the proposed method.

Titech CanSat Project 2000: Report of Sub-orbital Flight and Balloon Experiment

We have participated in the ARLISS (A Rocket Launch International Student Satellite) project since 1999 to design, manufacture and operate small satellites on students’ initiative. These satellites called CanSat are the size of soft drink can (350ml). We launch CanSats from the Black Rock desert in Nevada to 12,000ft using an amateur rocket, and drop them with a parachute. In this paper, we describe the subsystem design, mission and some results of the experiments on each CanSat, and report the results of an additional experiment using a balloon.