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TOP > Report & Column > The Forefront of Space Science > 2006 > Quick Release on Experiment Results of Mesh Deployment and Phased Array Antenna by S-310-36

The Forefront of Space Science

Quick Release on Experiment Results of Mesh Deployment and Phased Array Antenna by S-310-36
Shinichi NAKASUKA - Professor, Graduate School of Engineering, University of Tokyo -
Nobuyuki KAYA - Professor, Department of Computer and Systems Engineering, Faculty of Engineering, Kobe University -
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Mesh-deployment experiment

Figure 2
Figure 2. Images just after sub satellite release

Fig. 2 shows camera images down-linked by Ku telemetry. Image No. 1 was taken by the main satellite’s L-facing camera, No. 2 by its R-facing camera, and No. 3 by sub satellite T’s camera. The photographs show the status just after release of the sub satellites from the main satellite, and prove that separation was normal and mesh deployment had just started. In image No. 3, we can see the main and L and R sub satellites separating the main satellite against the earth. With these images and gyro data, we confirmed previously that the main satellite’s wheel had functioned normally to stop the rotation of the entire experiment system.

Figure 3
Figure 3. Images just before the completion of mesh deployment

Straws were used to house the mesh, which was an idea to prevent raveling and high resistance at deployment. Based on the images and data from accelerometers, we judge that there was little deceleration of all three sub satellites by friction resistance on mesh deployment, and that they reached their maximum distance 10m from the main satellite about 8sec after separation. At that time, it is likely that mesh deployment to an equilateral triangle with sides of around 17m was completed. Fig. 3 shows the images just before completion of deployment. The main satellite’s L- and R-facing cameras shot the fine mesh provided for the on-the-mesh moving system, which was pulled out during the final stage. Fig. 4 shows the records of sub satellite L’s angular velocity and acceleration. Apart from the main satellite’s wheel axis (Gz), two-axis coupled-rotation motion is visible. We can discern that the motion was gradually interrupted by disturbances from the mesh. From the acceleration records, we can see resistance forces caused by friction during deployment, etc., the reactive force of the mesh reaching maximum extension, and thruster-system control to prevent bound back. Based on telemetry data, we are now creating a detailed analysis of 3D position, velocity and attitude. We will examine the dynamics and control of the sub satellites as soon as the analysis is complete.

Figure 4-1

Figure 4-2
Figure 4. Profile of angular velocity and acceleration of sub satellite L

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