DX-1 EE

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==Dimensions engine==
==Dimensions engine==
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{-border="1"
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{| border="1"
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!Nozzle:
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!Nozzle:
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||Total length [mm]||62
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|-
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||Total length [mm]|| 62
|-
|-
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||Length expansion part [mm]||35
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||Length expansion part [mm]|| 35
|-  
|-  
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||Maximum diameter [mm]||70
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||Maximum diameter [mm]|| 70
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|-
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||Length throat [mm]||??
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||Length throat [mm]|| ??
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|-
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||Diameter throat [mm]||18
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||Diameter throat [mm]|| 18
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|-
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||||
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||Bolt holes diameter [mm] * # ||4 x 8
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|-
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||Bolt holes diameter [mm] * #||4 x 8
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|-
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||Weight [kg]||
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|-
|-
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||Weight [kg]||0,896
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|-
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!Casing:
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!Casing:
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||Outer diameter [mm]||70
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|-
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||Outer diameter [mm]|| 70
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|-
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||Length [mm]||770
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||Length [mm]|| 770
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|-
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||Weight [kg]
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||Weight [kg]|| 2,452
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|-
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!Aft-closure:
|-
|-
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!Aft-closure:
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||Total length [mm]|| 54
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||Total length [mm]||54
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|-
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||Maximum diameter [mm]||70
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||Maximum diameter [mm]|| 70
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||Bolt holes diameter [mm] * #||4 x 10
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|-
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||Weight [kg]||
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||Bolt holes diameter [mm] * # ||4 x 10
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|}
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|-
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||Weight [kg]||1,308
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|}
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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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{|border="1"
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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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|-
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KNO3 -sorbitol 35% - 65% 60 20 100 400
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|||||[mm]||[mm]||[mm]||[gram]||[gram]
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|-
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Performance (as designed)
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|KNO3 -sorbitol||||60||20||100||||
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|}
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Maximum thrust [N] 1645
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==Performance (as designed)==
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Burn time [s] 2.2
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{|border="1"
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Total Impulse [Ns] 2859
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|Maximum thrust [N]|| 1645
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Specific Impulse [s] 109
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|-
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Massa ratio [empty/loaded] 2/3
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|Burn time [s]|| 2.2
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Maximum pressure [N/m2] 5.48*106
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|-
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Maximum temperature [C˚] 1520
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|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
 +
|}
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Test data
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==Test data==
Most important data of the test performed in august 2006 (reference: test report):
Most important data of the test performed in august 2006 (reference: test report):
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{|border="1"
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Maximum thrust [N] 1640
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|Maximum thrust [N]|| 1640
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Burn time [ms] 2500
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|-
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Total Impulse [Ns] 2400
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|Burn time [ms]|| 2500
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Specific Impulse [s] 102
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|-
 +
|Total Impulse [Ns]|| 2400
 +
|-
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|Specific Impulse [s]|| 102
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|}

Current revision as of 21:38, 22 March 2007

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]0,896
Casing:
Outer diameter [mm] 70
Length [mm] 770
Weight [kg] 2,452
Aft-closure:
Total length [mm] 54
Maximum diameter [mm] 70
Bolt holes diameter [mm] * # 4 x 10
Weight [kg]1,308

Dimensions propellant grains

ComponentsMix-ratioOuter diameterInner diameterLength GrainNet Weightmould weight
[mm][mm][mm][gram][gram]
KNO3 -sorbitol6020100

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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