DX-1 EE

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Revision as of 18:45, 27 October 2006 by Frank E (Talk | contribs)

Engine Specification Form (ESF)

Engine Name:DX-EE
Type: Solid
Propellant:KNO3 + Sorbitol
Designers:Mark Uitendaal
Daan Maessen
Flown in rockets:CanSat Launcher V2
CSL V3
Tested?:Yes (two static tests + two instrumental tests
Documentation:Test report

Dimensions engine

Nozzle:
Total length [mm]62
Length expansion part [mm]35
Maximum diameter [mm]70
Length throat [mm]??
Diameter throat [mm]18
Bolt holes diameter [mm] * #4 x 8
Weight [kg]
Casing:
Outer diameter [mm]70
Length [mm]770
Weight [kg]
Aft-closure:
Total length [mm]54 Maximum diameter [mm]70 Bolt holes diameter [mm] * #4 x 10 Weight [kg]


Dimensions propellant grains Components Mix-ratio Outer diameter Inner diameter Length Grain Net Weight [mm] [mm] [mm] [gram] KNO3 -sorbitol 35% - 65% 60 20 100 400

Performance (as designed)

Maximum thrust [N] 1645 Burn time [s] 2.2 Total Impulse [Ns] 2859 Specific Impulse [s] 109 Massa ratio [empty/loaded] 2/3 Maximum pressure [N/m2] 5.48*106 Maximum temperature [C˚] 1520


Test data

Most important data of the test performed in august 2006 (reference: test report):

Maximum thrust [N] 1640 Burn time [ms] 2500 Total Impulse [Ns] 2400 Specific Impulse [s] 102

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