Tianwang-1A, -B, -1CShanghai Engineering Center for Microsatellites
The Tianwang-1 mission is composed by three small satellites that will demonstrate formation flying and inter satellite communication between the three satellites in orbit.
TW-1A NASA-Catalog: 40928
TW-1B NASA-Catalog: 40927
TW-1C NASA-Catalog: 40926
TW-1A 435.645 MHz 4k8/9k6 GMSK, 1W, 10 second transmit interval
TW-1B 437.645 MHz 4k8/9k6 GMSK, 1W, 20 second transmit interval
TW-1C 435.645 MHz 4k8/9k6 GMSK, 1W, 10 second transmit interval
NORAD 40958 COSPAR designator 2015-057-A Inclination 98.040 RA of A. Node 15.164 Eccentricity 0.0018317 Argument of Perigee 171.492 Revs per day 14.72727619 Period 1h 37m 46s (97.77 min) Semi-major axis 7 031 km Perigee x Apogee 640 x 665 km BStar (drag term) 0.000082960 1/ER Mean anomaly 188.660
The mission’s main goal is to experiment with software defined radio technology in space. The Amateur Radio payloads, which do not include any transponders, will serve to exchange telemetry, tracking, and command information with the ground control station. Telemetry data will be made public, so that radio amateurs around the world may track and monitor the health of the satellites.
Other payloads include a video camera, along with receivers for dual-band GPS/BeiDou, Maritime Automatic Identification System, and Aeronautical Automatic Dependent Surveillance Broadcast. Using MEMS based cold-gas micropropulsion, it is planned to demonstrate formation flying by two of the CubeSats along with inter-satellite communication using GAMALINK 2.4 GHz spread spectrum technology from Portugal.
3U CubeSat Dimensions: 10cm×10cm×30cm Mass:3.7Kg Antennas: stabilized (1 GPS/BD antenna +deployable VHF/UHF antennas)
2U CubeSat Dimensions: 10cm×10cm×20cm Mass:2.1Kg Antennas: stabilized (1 GPS/BD antenna +deployable VHF/UHF antennas) Antenna placement : the same as Sat-A expect for the AIS antenna mounted on the -X face.
2U CubeSat Dimensions: 10cm×10cm×20cm Mass: 2.1Kg Antennas: stabilized (1 GPS/BD antenna+ deployable VHF/UHF antennas)
The three satellites share the same subsystems and they are Structure, Thermal control, Attitude Determination and Control Subsystem (ADCS), Electrical Power Subsystem (EPS), On-Board Data Handling (OBDH), Telemetry, Tracking and Command (TT&C) subsystem.
Three-axis stabilization and control are realized by applying a momentum wheel combined with the active magnetic control. Also a new GPS/BD receiver will play an important role in the subsystem.
The power supply system consists of 4 solar cell string panels and 4 battery string power pack. The system have 3 input channels with independent power-point setting giving an input power capacity of 30 W, the average input conversion efficiency approaches to 93%. Two regulated power buses with 3.3V@5A and 5V@4A are provided. And a battery under-voltage and over-voltage protection is designed.
The mission computer is based on the 32-bit ARM architecture and freeRTOS real-time operating system.
Structure, Thermal control
For Sat-A, a 10 10 30 cm3 3U CubeSat structure is choose and two 10 10 20 cm3 2U CubeSat structures are choose for Sat-B and Sat-C. Passive control methods in the form of thermal coatings and insulation are preferred to control the heat radiation and absorption.
The TT&C subsystem is consist of one half-duplex transceiver and one deployable antenna. The transceiver combines telemetry, tele-command and beacon capability in a single board and is available in 9.6 kbps GMSK downlink/ uplink. Also it can also transmit CW beacon periodically. For the convenience of most of the amateurs to listen to the satellites, we will prefer the CW beacon containing the basic information of the satellites as well as some HK. The deployable antenna system consists of four monopole aerials combined in a phasing network in order to form a signal circular polarized antenna. The antenna radiation pattern is close to omnidirectional. And they will deploy from all four sides of the structure upon command.