DX-1 EE
From Dare
| Line 1: | Line 1: | ||
| - | Engine Specification Form (ESF) | + | ==Engine Specification Form (ESF)== |
| - | + | {| border="1" | |
| - | Engine Name: DX-EE | + | ||Engine Name:||DX-EE |
| - | Type: Solid | + | |- |
| - | Propellant: KNO3 + Sorbitol | + | ||Type: ||Solid|- |
| + | ||Propellant:||KNO3 + Sorbitol|- | ||
Designers: Mark Uitendaal | Designers: Mark Uitendaal | ||
Daan Maessen | Daan Maessen | ||
Revision as of 18:37, 27 October 2006
Engine Specification Form (ESF)
| Engine Name: | DX-EE | ||
| Type: | - | Propellant: | -
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
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
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 |
