The 15KG Satellite Platform is a technologically mature and highly reliable high-precision microsatellite with extensive flight experience. It features a high-precision Attitude Determination and Control System (ADCS) and robust overall maneuverability.
This platform can accommodate payloads up to 2.5U (4KG), offering faster data transmission rates and higher power availability for payload use.
Key Features:
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High Precision Attitude Control:
The platform achieves precise ±35° yaw maneuvers, making it suitable for aerospace missions with stringent attitude requirements such as high-resolution remote sensing, communication, scientific experiments, and payload verification.
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POD Separation Capability:
The satellite can utilize Payload Orbital Delivery (POD) for separation from the launch vehicle, ensuring stable environmental conditions during rocket launch and reducing separation costs.
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Redundancy and Reliability:
Designed with redundant backup systems, the platform ensures high reliability. It has successfully completed 6 flight missions, validating its technological capabilities in orbit.
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Applications:
The 15KG Satellite Platform is ideal for a wide range of applications including:
- High-resolution remote sensing
- Communication services
- Scientific experimentation
- Payload validation missions
Conclusion:
With its advanced ADCS, robust maneuverability, and proven reliability through multiple missions, the 15KG Satellite Platform is poised to deliver exceptional performance for demanding space missions. For more information on how our platform can meet your specific mission needs, please contact us.
Additional Information:
| Payload carrying mass | 3-4KG |
|---|---|
| Load capacity | 100 x 100 x 200 mm³ |
| Load available power | 25W |
| Available voltage for load | 3.3V / 5V / 12V |
| Available interfaces for payloads | CAN / RS422 / LVDS / Camera-Link / IIC / SPI |
| Whole star mass | About 15Kg |
| Standard sizes | （425mmx245mmx130mm） |
| Whole star power consumption | Long-term power consumption <25W, peak power consumption 60W |
| Design life | >3 years |
| Total thrust | > 80μN |
| Total charge | ≥600Ns |
| Specific impulse | ≥2700s |
| Postural stability form | Three-axis stabilization |
| Pointing accuracy | 0.1° |
| Measurement accuracy | 0.03° |
| Postural stability | 0.05°/s |
| Side swing range | ±35° |
| Attitude maneuver response time | 10°/20s |
| Positioning accuracy | 5m(3σ) |
| Time accuracy | 100ns |
| Speed accuracy | 0.1m/s (3 axes) |
| Solar array | Third-order gallium arsenide, power input 70W |
| Bus voltage | 14~16.8V |
| Battery pack | 10Ah (configurable) |
| Data rate | 5~40Mbps, with breakpoint resume capability |
| In-satellite temperature | 12℃~20℃(adjustable) |