DX-1 EE

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Revision as of 20:42, 20 November 2006 (view source) Sengelen (Talk | contribs) (→Dimensions propellant grains) ← Previous diff		Current revision as of 21:38, 22 March 2007 (view source) Admin (Talk | contribs) (→Dimensions engine)
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	||Diameter throat [mm]||  18		||Diameter throat [mm]||  18
	|-		|-
-	||Bolt holes diameter [mm] * #||4 x 8	+	||Bolt holes diameter [mm] * # ||4 x 8
	|-		|-
-	||Weight [kg]||	+	||Weight [kg]||0,896
	|-		|-
	!Casing:		!Casing:
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	||Length [mm]|| 770		||Length [mm]|| 770
	|-		|-
-	||Weight [kg]	+	||Weight [kg]|| 2,452
	|-		|-
	!Aft-closure:		!Aft-closure:
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	||Maximum diameter [mm]||  70		||Maximum diameter [mm]||  70
	|-		|-
-	||Bolt holes diameter [mm] * #||4 x 10	+	||Bolt holes diameter [mm] * # ||4 x 10
	|-		|-
-	||Weight [kg]||	+	||Weight [kg]||1,308
-	|}	+	|}
-		+
-		+
	==Dimensions propellant grains==		==Dimensions propellant grains==
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	|||||[mm]||[mm]||[mm]||[gram]||[gram]		|||||[mm]||[mm]||[mm]||[gram]||[gram]
	|-		|-
-	|KNO3 -sorbitol||65% - 35%||60||20||100||400||800	+	|KNO3 -sorbitol||||60||20||100||||
	|}		|}

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Current revision as of 21:38, 22 March 2007

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]	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

Components	Mix-ratio	Outer diameter	Inner diameter	Length Grain	Net Weight	mould weight
		[mm]	[mm]	[mm]	[gram]	[gram]
KNO3 -sorbitol		60	20	100

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