| Name | WVSAT A |
|---|---|
| Form factor | ThinSat |
| Units or mass | ThinSat 1x2T+3x1T |
| Status | not launched, expected in 2024 |
| Launcher | Falcon 9, (Spaceflight Sherpa) |
| Organization | NearSpace Launch |
| Institution | Company |
| Entity type | Commercial |
| Country | US |
| Manufacturer | AIVT by NearSpace Launch |
| Operator | NearSpace Launch |
| Oneliner |
Deploy small satellites with two form factors, to test ground station radar tracking, and demonstrate rapid turnaround and deployment of these satellites. |
| Description |
The experiment will use a total of 4 satellite, 2 ThinSats and 2 1U CubeSats, launched as a secondary payload aboard NG16, from the mid - Atlantic Regional Spaceport. The satellites will be inserted into Low Earth Orbit ( LEO), at 260 km apogee and 180 km perigee. They are deployed from a single Canisterized Satellite D ispenser (CSD) mounted on the Antares second stage of the launch vehicle. The ThinSats unfold accordion style as they exit the CSD; the two CubeSats are separate from the ThinSats. Transmission will begin upon deployment, and cease when de-orbiting occurs. Each ThinSat spacecraft is comprised of multiple ThinSat units. Each spacecraft will carry the following subsystems. Guidance, Navigation and Control (GNC) Subsystem: Navigation sensors consist of the VEML3328 Single Pixel IR Horizon sensor on each unit, a Grid IR 8x8 Pixel Sensor, a High Quality 32x24 Pixel, Infrared sensor, and a GPS unit. Each module in each spacecraft, will contain one EyeStar-S3F transmitter, transmitting to the Globalstar constellation; an S3F antenna; and VEML3328 single pixel IR horizon sensor associated with the transmission enable logic. |
| Sources | [1] [2] [3] |
| Photo sources | [1] |
| COTS subsystems |
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| Keywords | Globalstar or Iridium or Inmarsat |
Last modified: 2024-05-29
