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.
|Diameter||6 inches (150mm)|
|Length||14 feet (4.2m)|
|Recovery||Parachute at apogee|
|Fin Geometry||3 Clipped Deltas|
|Motor Type||AeroTech Solid Rocket Motor Cluster|
|Total Impulse||3240 Newton seconds|
|Burn Time||3.5 seconds|
|Avionics & Payloads|
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)