DX-1 EE

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	==Dimensions engine==		==Dimensions engine==
	{| border="1"		{| border="1"
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	||Total length [mm]||62		||Total length [mm]||62
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	||Outer diameter [mm]||70		||Outer diameter [mm]||70
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	||Total length [mm]||54		||Total length [mm]||54
	||Maximum diameter [mm]||70		||Maximum diameter [mm]||70

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Revision as of 18:45, 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

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