DX-1 EE

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	||Weight [kg]||		||Weight [kg]||
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	!Casing:		!Casing:
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	||Weight [kg]		||Weight [kg]
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	!Aft-closure:		!Aft-closure:
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-	Dimensions propellant grains	+	==Dimensions propellant grains==
-	Components Mix-ratio Outer diameter Inner diameter Length	+	{|border="1"
-	Grain Net Weight	+	!Components!!Mix-ratio!!Outer diameter!!Inner diameter!!Length Grain!!Net Weight!!mould weight
-	[mm] [mm] [mm] [gram]	+	|-
-	KNO3 -sorbitol 35% - 65% 60 20 100 400	+	|||||[mm]||[mm]||[mm]||[gram]||[gram]
		+	|-
		+	|KNO3 -sorbitol||35% - 65%||60||20||100||400||800
		+	|}
-	Performance (as designed)	+	==Performance (as designed)==
-		+	{|border="1"
-	Maximum thrust [N] 1645	+	|Maximum thrust [N]|| 1645
-	Burn time [s] 2.2	+	|-
-	Total Impulse [Ns] 2859	+	|Burn time [s]|| 2.2
-	Specific Impulse [s] 109	+	|-
-	Massa ratio [empty/loaded] 2/3	+	|Total Impulse [Ns]||2859
-	Maximum pressure [N/m2] 5.48*106	+	|-
-	Maximum temperature [C˚] 1520	+	||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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Revision as of 18:56, 27 October 2006

Contents 1 Engine Specification Form (ESF) 2 Dimensions engine 3 Dimensions propellant grains 4 Performance (as designed)

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	mould weight
		[mm]	[mm]	[mm]	[gram]	[gram]
KNO3 -sorbitol	35% - 65%	60	20	100	400	800

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