DX-1 EE

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-	Dimensions engine	+	==Dimensions engine==
-	Nozzle:	+	{-border="1"
-	Total length [mm] 62	+	!Nozzle:
-	Length expansion part [mm] 35	+	||Total length [mm]||62
-	Maximum diameter [mm] 70	+	|-
-	Length throat [mm] ??	+	||Length expansion part [mm]||35
-	Diameter throat [mm] 18	+	|-
-		+	||Maximum diameter [mm]||70
-		+	|-
-	Bolt holes diameter [mm] * # 4 x 8	+	||Length throat [mm]||??
-	Weight [kg]	+	|-
-		+	||Diameter throat [mm]||18
-	Casing:	+	|-
-	Outer diameter [mm] 70	+	||||
-	Length [mm] 770	+	|-
-	Weight [kg]	+	||Bolt holes diameter [mm] * #||4 x 8
-		+	|-
-	Aft-closure:	+	||Weight [kg]||
-	Total length [mm] 54	+	|-
-	Maximum diameter [mm] 70	+	|-
-	Bolt holes diameter [mm] * # 4 x 10	+	!Casing:
-	Weight [kg]	+	||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]||
		+	|}

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Revision as of 18:44, 27 October 2006

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

{-border="1" !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