北京时间2016年8月16日1时40分,长征二号丁运载火箭从酒泉卫星发射中心将中国科学院的量子科学试验卫星成功送入预定轨道。此次任务中,中国长城工业集团有限公司(简称“长城公司”)搭载发射了一颗由西班牙加泰罗尼亚理工大学小卫星实验室设计研制的6U立方体卫星, 6U小卫星在主星分离后33秒与运载火箭分离,发射取得圆满成功。

    此次发射的6U小卫星为科研卫星,放置在荷兰Innovative Solution In Space(ISIS)公司研制的6U立方星分离机构完成发射,这是荷兰ISIS公司继2013年搭载发射3颗立方体小卫星后第二次与长城公司进行合作。


On-Board Computer and Flight Software

The 3Cat-2's On-Board Computer is based on an ARM7 microcontroller running at 40 MHz and using up to 2MB of RAM. The system runs FreeRTOS, an open source real time operative system based on a very simple kernel. The OBC is integrated in a commercial available board which also includes a low power 3-axis magnetometer, which is used for the attitude determination purposes, and  a microSD slot fitted with a 2 GB card containing the satellite's file system, which is based in FAT16.

On top of the FreeRTOS runs the flight software which is charge of the satellite control including: sensors reading, communication protol stack, attitude determination and control algorithms, payload managing and command and data handling. Being both a very simple microcontroller and software, the system is robust and predictible, reducing the mission risks.

Electric Power Subsystem

The ³Cat-2's Electrical Power System is in charge of harvesting energy via solar panels to then manage and store it in batteries. The 3Cat-2 has a total of 5 surfaces covered with Triple Junction Gallium Arsenide solar cells from AzurSpace with an effiency of 30% in BOL. To store the energy the satellite has a 7.4 V Lithium-Ion battery pack with a total capacity of 7000 mAh.

Communication Subsystem

The communication system is based on available comercial systems for CubeSats and is split in a total of three diferent links integrating the amateur protocol AX.25. A UHF link working at 1200 bps and modulated in AFSK (Bell 202 standard) is in charge of the uplink while the downlik relais on a VHF link transmitting at 9600 bps and an S-Band link transmitting at 115200 bps, both modulated in BPSK. 

 The UHF and VHF links are working together as a full-duplex system and controlled by a Selective Repeat protocol, which is able to reliable upload and download files. UHF-VHF system is in charge of telemetry and command upload, and for that reason two UHF-VHF  transceivers are placed in the satellite, as redundancy of the system. On the other hand, the S-Band downlink is a “blind” link, which gives the user the possibility of downlink a file without any uplink command. For that reason, an erasure code is used on top of the file sent. In this case a LDPC-Staircase is used for the mission, which encapsulates the scientific payload data generated and sends towards the Earth at pre-defined times.

In addition, the coomunication system also includes a beacon in the VHF band which periocally transmits a set of telemetry data in an open format and can be easily received from Earth following these simple steps.

Attitude Determination and Control Subsystem

The attitude determination and Control System is responsible for orientating and stabilizing the spacecraft towards a desired target attitude. In order to achieve this, a set of sensors and actuators will be used to know the current orientation of the spacecraft, perform slew maneuvers, and counteract orbital disturbances.

On the one hand, 3Cat-2 employs a set of three orthogonal magnetic torquers (0.24 Am2 each) as actuators. This type of actuation relies on controlling the spacecraft dynamics by generating a torque owing to the interaction between the Earth’s magnetic field and a local dipole moment from the magnetic torquers. On the other hand, the sensors selected for 3Cat-2 are two 3-axis magnetometers (fine and coarse) to measure the Earth’s magnetic field, one 3-axis MEMS gyroscope to measure angular rates, and a set of six photodiodes mounted on each face of the nanosatellite to determine the Sun’s position. Additionally, an in-house, experimental star tracker is to be tested on orbit (not included in on-board determination algorithms) to assess its performance in space.


3Cat-2 is carrying up to 4 payloads, the main payload, PYCARO, followed by the star tracker Mirabilis, the eLISA magnetometer developed by IEEC and finally a compression algorithm for the scientific data downlink developed by DAPCOM, the FAPEC Compression Algorithm.

    PYCARO GNSS-R main payload:  PYCARO from P(Y) and C/A ReflectOmeter,  is the main payload of 3Cat-2, based on the technology GNSS-R. GNSS-R is based on collecting the opportunity signals sent by the GPS, Galileo, Glonass and BeiDou constellations to perform reflectometry. The final go of the scientific data of a GNSS-R mission is to perform altitude maps of the Earth, wind surface over the sea, deforestation... The payload is a dual polarization, RHCP and LHCP, working in both L1 and L2 bands of GPS but also works for any of the acutal GNSS constellations.

    Mirabilis Star Tracker: The Mirabilis is an experimental star tracker developed by the NanoSat Lab. This star tracker, which is not included on the attitude determination algorithms, flies in the ³Cat-2 mission in order to be validated for future Nanosat Lab missions such as ³Cat-3.

    IEEC AMR eLisa magnetometer: This magnetometer, developed by the Insitut d'Estudis Espacials de Catalunya (IEEC) will be included in the future ESA's LISA mission and for this reason, it's behavior will be analysed and validated during the ³Cat-2 mission.

    FAPEC compression algorithm by DAPCOM: The FAPEC is a compressions algorith by DAPCOM which is in charge of compressing the scientific data generated by the ³Cat-2 payloads. It is the first time this algorithm is used in a space mission

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