IARU Amateur Satellite Frequency Coordination
 
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RSP-02 Updated: 01 Oct 2024   Responsible Operator Yasushi Setoguchi JE1HBB
Supporting Organisation Rymansat Project  
Contact Person setoro17@gmail.com.nospam  
Headline Details: A 1U CubeSat. Mission-1 With the aim of establishing a general-purpose communication module, a compact and lightweight Transmitter/Receiver (Uplink:430MHz band and Downlink:144MHz band) will be developed and demonstrated its performance in orbit. i) Outline of Demonstration Transmitter/Receiver Module: Demonstration module is 52x37mm size that can be mounted on CubeSat's 10cm square board. The module operates at 3.3 V (however, the final stage transmit amplifier may operate exceptionally at 5V for improved distortion characteristics..) •Supported radio formats are CW (transmission) and Data (GMSK transmission & AFSK reception for packet communication), •Dual redundant transmitters are integrated on the module for a better reliability. •Packet communication protocol improves communication efficiency by installing a new error correction and CCSDS method using turbo code LDPC in addition to the conventional AX25. (At the initial release stage, AX25, which has a proven track record, is used. And at an appropriate timing, it shifts to CCSDS by the switching command from the ground.) ii)Applications used in demonstration Store & Forward of messages by packet communication. The publicly available protocols and operating rules will be used to send and receive messages from unspecified amateur radio stations around the world. Sending images captured by the camera mounted on the RSP-02 to the ground The captured image is 1600 x 1200 pixels. Color tone 16 bit (Red:5, Green:6, Blue:5) JPEG compression of 34Mbyte/sheet for sending iii)Performance Measurements In principle, performance measurements are not performed autonomously in orbit; instead, evaluations are conducted by receiving operating status data on the ground. Power consumption during transmission is recorded in a log and transmitted to the ground as necessary. Since the antenna power itself is not measured, the output is inferred from the input power and compared with the signal strength on the ground. Measurement of performance degradation over time due to repeated charging and discharging is also a factor of interest. Improvements in error rate due to the application of CCSDS will be analyzed using data received by ground stations. Mission-2 Demonstration Test of the Release Mechanism for the Child Satellites i) Overview In orbit, the RSP-02 releases the two child satellites it carries outside the vehicle upon receiving a command from the ground station. To prevent the child satellites from becoming debris, they are constantly connected to the RSP-02 main body by wires. After receiving the command, the RSP-02 opens the door to the storage space for the child satellites using a motor, and the two child satellites are released by the repulsive force of a spring. The aim is to obtain the basic form of the mechanical structures, such as the door opening mechanism and the release mechanism, to enable the realization of more complex functions in the future. ii) Demonstration Method Log information of various operations after receiving the command can be sent to the ground to confirm that they were activated correctly (for example, if the door does not open, the release of the child satellites will not be initiated). The child satellites after release will also be photographed by the RSP-02 camera. The RSP- 02 main body can issue a command to turn on the LEDs of the child satellites, making it possible to confirm their presence even at night when sunlight does not reach them. Since they are connected by wires, they will not fly away. The captured images will be simply analyzed by the RSP-02 OBC to determine whether the satellite is visible or if the LED is lit, and a judgment score will be sent to the ground. Furthermore, the actual state can be confirmed by sending the selected image itself to the ground upon command from the ground station. Proposing a VHF downlink using CW or 9k6 GMSK downlink. Planning a launch from Tanegashima in July 2025 into a 380x420 km 51.6 degree orbit. More info at https://www.rymansat.com **A downlink on 145.910 MHz has been coordinated**
Application Date: 05 Aug 2024   Freq coordination completed on 01 Oct 2024

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