Second-generation solar sensor developed for ultra-small satellites, CubeSats.
This is a solar sensor for ultra-small, lightweight, high-performance CubeSats. This solar sensor uses a CMOS image sensor, with a field of view (FOV) of 166° and an accuracy of <0.2° (2σ).
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basic information
The main specifications of the small solar sensor are as follows: FOV: 166° Update frequency: ≤2 Hz Accuracy (2σ): <0.2° Slew rate: 70°/sec Mass: 15 g Power consumption: 100 mW (average), 174 mW (maximum) Supply voltage: 3.3 V Dimensions: 35 x 24 x 22 mm Operating temperature range: -20°C to +80°C Interface: CAN, UART, RS485, I2C (optional) Radiation resistance: 24 kRad
Price information
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Delivery Time
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Applications/Examples of results
We have a wealth of experience in using solar sensors for ultra-small satellites, such as CubeSats.
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Company information
The Advanced Technology Research Institute is an engineering company that supports space development and utilization, including rockets and artificial satellites, in Japan and around the world. We conduct a wide range of activities from the design and development of space systems, subsystems, and components for satellites and rockets, both small and large, to the sale of overseas space equipment. Additionally, we sell solar cells for space and ground use, and we design and develop solar cell panels for space as well as sell solar power generation modules and systems for ground use. For small satellites, including CubeSats, we provide system development from 1U to 12U, offer bus components, design and develop bus equipment, assemble satellites, and conduct integration and testing of satellites, including payloads. We also design, develop, and sell small electric propulsion systems for CubeSats and small satellites.