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| Subsystem | Main components | Key specifications |
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| Structure | Hemispherical frame (HF), payload cabin (PC), central connection ring (CCR), releasing device (RD) | 2A12-H112 aluminum alloy |
| Payload | Dual-frequency GPS (D-GPS), single-frequency GPS (S-GPS), micro camera (MC) | Real-time positioning (velocity) precision: less than 20 m (0.2 m/s) |
| Attitude control | Inertial measurement unit (IMU), integrated full field sun sensor (IFFSS), magnetometer, flywheel, magnetorquer | Attitude determination precision: 0.5° |
| Attitude control precision: 2° |
| Power | Solar cell array (SCA), power controller unit (PCU), battery (BAT) | SCA: 931 cells of triple-junction GaAs (29.5%) |
| BAT capacity: 8.8 Ah |
| Bus voltage: 6.9–8.2 V |
| Secondary voltage: 12 V, 3.3 V, 5 V |
| Power consumption: 11.45 W (steady state) |
| Integrated electronic | Onboard computer (OBC), attitude control computer (ACC), integrated electronic circuit board (IECB) | Processing chip: LPC2294 |
| Telemetry, telecontrol, and data transition | Unified S-band (USB), industrial scientific medical (ISM) band, power amplifier (PA), combiner | USB: Telemetry: 2000 bps |
| Telecontrol: 4096 bps |
| Data transition: 0.5 Mbps |
| ISM: 115.2 kbps |
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