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| Visual Indicator Visibility Verification Test |
In February 2004, the visibility verification test for the Visual Indicator of the Space Environment Data Acquisition Equipment-Attached Payload (SEDA-AP) was conducted.
SEDA-AP is planned to be the first laboratory equipment to be installed on the Japanese Experiment Module (JEM) "Kibo" Exposed Facility. It will quantitatively measure the space environment of the ISS. In addition, it will conduct experiments on exposed materials and verification tests on electronic components, as well as researching how the space environment affects components and materials.
What is the Visual Indicator?The H-II Transfer Vehicle (HTV) will be used to retrieve and dispose of SEDA-AP after the completion of the experiment. SEDA-AP also has an option to be installed on the Experiment Logistics Module Exposed Section (ELM-ES) to be collected by the Space Shuttle. Experiments will be conducted using one meter placed on the extension mast while being attached to the ISS. The extension mast will need to be stored and launch-locked* during the launch and recovery by the Space Shuttle.
* Launch-lock: equipment for fixing and protecting the removable parts and connected parts to avoid damage from any vibration during launch and recovery.
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| Visual Indicator | Expansion of the Visual Indicator |
The Visual Indicator (VI) attached to the JEM is a display used to confirm the storage condition of the extension mast and the launch lock mechanism by the Extravehicular Activity (EVA) crew and the camera of the remote manipulator system (RMS). It is equipped on the upper surface of the SEDA-AP. Using the VI from outside ensures that the extension mast is stored and the launch lock is locked to be recovered by the Space Shuttle.
Visibility Verification Test |
| SEDA-AP being tested |
When looking at the VI display images from the camera will be shown on the RMS console in the JEM Pressurized Module (JEM PM) or on the monitor at ground control. However there could be difficulty in seeing the VI display due to the reflection of the light. Shadows in the dark space, may also cause a distorted image to be sent down to ground control.
The visibility verification test simulated the actual operation on orbit. The test was conducted to confirm the condition of the VI display from the image obtained by the RMS, and to identify the optimum location of the RMS camera and lighting to capture the VI display. Images obtained from the experiment will be utilized in technical assessments and future operations training.
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