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Both ZDPS-2A and ZDPS-2B are 25 cm × 25 cm × 25 cm cube-shaped and weigh around 12 kg. The satellites are equipped with tri-junction Ga-As solar cells as the primary power, tiled on all six planes of the satellite body, which have a 26.8% theoretical efficiency, and a Li-ion battery pack of ten cells from Sanyo serves as the secondary power. The transceiver works under the Universal S-Band (USB) TTC system, with uplink data rates of 2 kbps and adjustable downlink data rates of 1 kbps to 64 kbps. The on-board computer(OBC) is composed of multi-CPU with FPGA, providing a universal computing, storage, management platform for command execution, TT&C, attitude and orbit control, payloads, etc. Sub-degree level attitude measurement will be achieved through a 3-axis magnetometer, a 3-axis MEMS gyroscope, four-quadrant analog sun sensors mounted on six surfaces and a digital sun sensor. Attitude control utilizes a momentum wheel, installed on the pitch axis, to provide both momentum bias and reaction actuation for pitch attitude maneuver, and three orthogonally mounted magnetic coils provide active control torque for detumbling and three-axis stabilization, with pointing accuracy of better than 2° and steady precision 0.1°/s. In order to obtain an accurate absolute position and velocity measurement, ZDPS-2 carries two GPS receivers. A UNICORE dual-frequency GPS receiver provides singlepoint positioning accuracy of 2 m (RMS), with observational data updating rate up to 10 Hz. A Zhejiang University developed GPS receiver provides absolute position accuracy of 2 m and velocity of 0.2 m/s. A dual-frequency GPS antenna is mounted on the zenith face. ZDPS-2A and B are each equipped with an S-Band inter-satellite communication transceiver to exchange position and velocity data, capable of providing data transmission rate of 8kbps and maximum communication range of 5 km. In addition, an S-Band PN code ranging system is designed to provide PN code rate of no more than 2Mcps, and ranging accuracy of 4 cm for 1Mcps code rate.

Both satellites carried a deployable structure experiment, which was deployed in orbit.

ZDPS-2A and B are both equipped with propulsion system, either of them can be treated as chief or deputy. The system uses liquid ammonia as a propellant with ISP greater than 900 Ns/kg. With the fuel mass of 0.318kg and the satellite mass of below 12kg, the system can provide a total ¿V of 24 m/s.

Alternate Names

  • 40901
  • ZDP2A

Facts in Brief

Launch Date: 2015-09-19
Launch Vehicle: Long March 6
Launch Site: Taiyuan, Peoples Republic of China


  • Technology Applications

Additional Information

Questions and comments about this spacecraft can be directed to: Coordinated Request and User Support Office

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