DX-1 EE

From Dare

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