DX-1 EE

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Line 84:		Line 84:
	||Specific Impulse [s]|| 109		||Specific Impulse [s]|| 109
	|-		|-
-	||Massa ratio [empty/loaded]| 2/3	+	||Massa ratio [empty/loaded]||2/3
	|-		|-
-	||Maximum pressure [N/m2]| 5.48*106	+	||Maximum pressure [N/m2]|| 5.48*106
	|-		|-
-	||Maximum temperature [C˚]| 1520	+	||Maximum temperature [C˚]|| 1520
	|}		|}
-	Test data	+	==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):
-		+	{|border="1"
-	Maximum thrust [N] 1640	+	|Maximum thrust [N]|| 1640
-	Burn time [ms] 2500	+	|-
-	Total Impulse [Ns] 2400	+	|Burn time [ms]|| 2500
-	Specific Impulse [s] 102	+	|-
		+	|Total Impulse [Ns]|| 2400
		+	|-
		+	|Specific Impulse [s]|| 102
		+	|}

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Revision as of 18:57, 27 October 2006

Contents 1 Engine Specification Form (ESF) 2 Dimensions engine 3 Dimensions propellant grains 4 Performance (as designed) 5 Test data

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