GökTürk-2 Pyro Drive Module (PDM)

Against strong international competition, SpaceTech has been awarded a contract by the Turkish government institute TÜBITAK UZAY to deliver the GökTürk-2*) solar array system consisting of

  • 3 solar panels including the photovoltaic assembly
  • the solar panel deployment mechanisms
  • the pyro drive module (PDM) electronics executing the deployment sequence of the mechanism

SpaceTech's PDM development

The PDM development including 1 mass dummy, 1 qualification model and 1 flight model has been performed with support from APCON.

The main task of the PDM is to provide regulated current for a predefined period to release the solar panel deployment mechanisms by activating thermal knifes. The electronics is implemented in cold redundancy (electronic part) and, via internal cross-coupling) allows access to both hot redundant power stages. For safety reasons a three-level inhibit system is implemented.

  Pyro Drive Module Architecture (Nominal Chain Only)

The PDM operates in different modes that are directly related to the safety inhibits.

PDM Modes and Transitions

The PDM is characterized by a low mass and volume. The design can easily be adapted for a higher number of activation chains, different types of actuators, e.g. pyros, and a different communication interface to the on-board computer.

GökTürk-2 Pyro Drive Module Performance Summary

The qualification and flight models of the solar array system have been delivered to Turkey in 2010 and 2011, respectively. The satellite has been launched and the solar array successfully deployed in December 2012.

*) GökTürk-2 is an earth observation satellite program initiated by the Turkish government institute TÜBITAK UZAY in an effort to develop its satellite system and subsystem design and development capabilities as well as to establish a bus platform for future remote-sensing missions. The main payload consists of a multi-spectral imager (MSI). The spacecraft is specified for an operational life time of 5 years in a sun-synchronous orbit at an altitude of approximately 700 km and a local time of descending node between 10:30 and 11:30 a.m.