This is the data so far for publication related to the test of the SMARAGD rocket, designed by Peter Madsen. The double test was done Nov 26, 2011. This idea of creating and launching this rocket, which is a minor Copenhagen Suborbitals rocket compared to size and thrust of earlier engines, is to perform a data and telemetry test at altitudes of 30-60 km .
You might want to read this blog post first for additional information.
SMARAGD stage 1 engine: Mass oxidizer (LNOX): 28 kg Mass fuel (Polyurethane): 5.3 kg O/F: 5.3 Grain ports: 19 @ 25 mm each Grain length: 300 mm Injector canals: 32 @ 5 mm each Total impuls = 70500 Ns ISP = 216 s (based on Cf = 1.4) C* = 1512 m/s Thrust phase: 3.4 s (pressure below 1.5 bar) Thrust: 30kN Additional info: No active valves.
SMARAGD stage 1 engine. Ignition zoom. Copenhagen Suborbitals
SMARAGD stage 1 ready to rock. Image: Kristian von Bengtson
SMARAGD stage 1. After math, Nozzle and 19 port grain. Image: Copenhagen Suborbitals
SMARAGD stage 1. Left: injector. Right: Passive valve plug released during pyro ignition phase (tied with string to the oxidizer tank). Image: Copenhagen Suborbitals
SMARAGD stage 1 engine: Mass oxidizer (LNOX): 9 kg Mass fuel (Polyurethane): 1.5 kg O/F: 6 Grain ports: 1 @ 40 mm Grain length: 500 mm Injector canals: 1 @ 3.5 mm Total impuls = N/A ISP = N/A Thrust: Maybe just take a look at the graph below Additional info: No active valves
SMARAGD stage 2 engine. Tested Nov 26, 2011 14:00. Copenhagen Suborbitals
SMARAGD stage 2 engine. Grain cut open for inspection. Image: Copenhagen Suborbitals
I also suggest interested readers to check out the following image links for further details during burn phases, operation and inspection. Enjoy!
Official Copenhagen Suborbitals link Steffen Pedersen private photos link
Ad Astra Kristian von Bengtson
