PRECURSOR satellite

Source: https://iaru.amsat-uk.org/formal_detail.php?serialnum=916

PRECURSOR Updated: 28 May 2023   Responsible Operator Mario Lorenz DL5MLO Supporting Organisation Spectrum Aerospace Technologies UG Contact Person dl5mlo@amsat-dl.org.nospam Headline Details: PRECURSOR is 15cm x 30cm x 60cm, 18kg weight (including propellant). \it is planned to be launched on an experimental/test flight on a LandSpace ZQ-2 to a geosynchronous orbit in 460km altitude. Current estimates predict a mission lifetime between 1 and 5 years, depending mainly on solar activity and success in the primary mission. The primary mission of PRECURSOR is the in-orbit- verification of an electric propulsion system within ~ 6 months after launch. Due to the power demands of the electric propulsion system, the satellite includes significant electrical power collection capabilities. Once the propellant (reaction mass) for the propulsion system is used up, the power budget allows for several secondary missions: Amateur Radio: - Provide an U/V amateur radio transponder - Enable S/C tracking using telemetry - Provide a software defined wideband L/S amateur radio transponder and/or signal source Educational experiments: - an onboard computer using an intra-satellite wireless bus system (University of Wuerzburg) - radiation sensors - GNSS experiments including a software defined GNSS system (ETH Zurich, Fraunhofer IIS Erlangen) - LPWAN technology verification (Fraunhofer IIS Erlangen) - two cameras - various antenna systems.Other than collecting telemetry and learning about satellite operating environment, an 25kHz linear, bent- pipe Mode U/V will support direct amateur radio operation and involvement. A software-defined wideband L/S transponder will allow for direct amateur radio operation and involvement. Being software-defined, its characteristics can be modified while it is in orbit by uploading new software. On a time-shared basis, this transponder can be used as a bent-pipe transponder, a regenerating transponder, or as a signal source carrying telemetry or live video. For a typical user station, a 250kbit/s link is planned, sufficient for narrowband DATV operations. Stations putting more effort into their ground stations could benefit from higher bandwidths, enabling (2..5 MHz). Other than a purely linear transponder, regenerative transponders of varying modes can be experimented with. This would include 5G and IoT waveforms. We expect to turn on the U/V transponder after initial checkout of spacecraft, about 1 month after launch. L/S transponder will be operated on a time-share basis depending on available power and mission requirements. Proposing VHF and S Band downlinks with 9k6 GMSK telemetry with CCSDS formatting. Planning a launch from Jiuquan Satellite Launch Center in Q4 2023. More info at http://precursor.space/#_SATELLITE_DESCRIPTION Application Date: 23 May 2023 Freq coordination completed on 01 Jan 1970

Infos:

http://precursor.space/

I think there is something wrong with the orbit specification.

But WOW, this will be a next super HAM satellite

Hallo Peter

In the SATELLITE DESCRIPTION you can read "The main experiment is a new generation propulsion system for Orbital Plane Change (inclination) and/or Orbital Altitude Change and uses green propellant." I think the sat will be shot from LEO in a higher orbit. Further infos will follow, hopefully.

CU in Friedrichshafen

I met the designer of the propulsion system and Mario, DL5MLO, in Friedrichshafen at the AMSAT-DL stand. The system is a test unit and brings the satellite only in a 20 - 30 km higher orbit (LEO).

The following frequencies have been coordinated:

For linear transponder U/V uplink 435.025 MHz +/- 12.5 kHz,

for linear transponder U/V downlink 145.975 MHz +/- 12.5 kHz, emission designator 25K0W9WWW, EIRP 36.5 dBm,

for VHF beacon/telemetry 144.015 MHz,

for linear transponder L/S uplink 1261.500 +/ 250 kHz,

for linear transponder L/S downlink and beacon 2400.850 MHz.

https://iaru.amsat-uk.org/finished_detail.php?serialnum=916