DX-1 EE

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Dimensions propellant grains
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==Dimensions propellant grains==
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Components Mix-ratio Outer diameter Inner diameter Length
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Grain Net Weight
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!Components!!Mix-ratio!!Outer diameter!!Inner diameter!!Length Grain!!Net Weight!!mould weight
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[mm] [mm] [mm] [gram]
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KNO3 -sorbitol 35% - 65% 60 20 100 400
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Performance (as designed)
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==Performance (as designed)==
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Maximum thrust [N] 1645
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|Maximum thrust [N]|| 1645
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Burn time [s] 2.2
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Total Impulse [Ns] 2859
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|Burn time [s]|| 2.2
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Specific Impulse [s] 109
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Massa ratio [empty/loaded] 2/3
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|Total Impulse [Ns]||2859
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Maximum pressure [N/m2] 5.48*106
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Maximum temperature [C˚] 1520
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||Specific Impulse [s]|| 109
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||Massa ratio [empty/loaded]| 2/3
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||Maximum pressure [N/m2]| 5.48*106
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||Maximum temperature [C˚]| 1520
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Revision as of 18:56, 27 October 2006

Contents

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

ComponentsMix-ratioOuter diameterInner diameterLength GrainNet Weightmould weight
[mm][mm][mm][gram][gram]
KNO3 -sorbitol35% - 65%6020100400800

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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