Deimos 2

The Deimos-2 Systems Test Vehicle Programme was conceived as a way of flight testing an analog of the actual hybrid powered Deimos-2, just to ensure that the vehicle was stable during flight, and to provide experience and feedback with various payload configurations and recovery configurations. To this end, the programme was a resounding success, with 3 low altitude flights being carried out in 1999. The feedback from these flight tests was then fed back into the work on the main Deimos-2 rocket to enable any modifications to be carried out (e.g. payload configuration and access).

Flight Test Date Test Purpose Successful Launch Successful Recovery
#1 June 1999 Stability Test Yes Yes
#2 August 1999 Recovery Test with extended recovery bay Yes Yes
#3 November 1999 Payload Test Yes Yes

Flight test 1 was merely a stability test, to ensure that the simulations that had been carried out during the design phase were correct.

Flight test 2 added to the flight testing of the stability with an extended recovery bay, to evaluate a different recovery configuration.

Flight test 3 added to the flight testing of the stability and the recovery with a larger payload bay with a number of altimeters.

General Specifications
Diameter 6 inches (150mm)
Length 14 feet (4.2m)
Recovery Parachute at apogee
Fin Geometry 3 Clipped Deltas
Nosecone Tangential Ogive
Motor Type AeroTech Solid Rocket Motor Cluster
Total Impulse 3240 Newton seconds
Nozzle Cast Phenolic
Burn Time 3.5 seconds
Avionics & Payloads
  • AED Classic R-DAS
  • G-Wiz LC Deluxe
  • Black Sky Research Timer-2B Timer

  • Flight Data from the 3rd Deimos-2 Systems Test Vehicle rocket flight.
    (Note: the data is taken directly from the R-DAS Flight Computer data carried onboard the Deimos-2 STV rocket - sampled at 200 Hz)