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 CanSat Launcher V3 (DX-CSL_v3.01) 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