DX-1 EE
From Dare
(Difference between revisions)
| Line 24: | Line 24: | ||
!Nozzle: | !Nozzle: | ||
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| - | ||Total length [mm]||62 | + | ||Total length [mm]|| 62 |
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| - | ||Length expansion part [mm]||35 | + | ||Length expansion part [mm]|| 35 |
|- | |- | ||
| - | ||Maximum diameter [mm]||70 | + | ||Maximum diameter [mm]|| 70 |
|- | |- | ||
| - | ||Length throat [mm]||?? | + | ||Length throat [mm]|| ?? |
|- | |- | ||
| - | ||Diameter throat [mm]||18 | + | ||Diameter throat [mm]|| 18 |
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|||| | |||| | ||
| Line 43: | Line 43: | ||
!Casing: | !Casing: | ||
|- | |- | ||
| - | ||Outer diameter [mm]||70 | + | ||Outer diameter [mm]|| 70 |
|- | |- | ||
| - | ||Length [mm]||770 | + | ||Length [mm]|| 770 |
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||Weight [kg] | ||Weight [kg] | ||
| Line 52: | Line 52: | ||
!Aft-closure: | !Aft-closure: | ||
|- | |- | ||
| - | ||Total length [mm]||54 | + | ||Total length [mm]|| 54 |
|- | |- | ||
| - | ||Maximum diameter [mm]||70 | + | ||Maximum diameter [mm]|| 70 |
|- | |- | ||
||Bolt holes diameter [mm] * #||4 x 10 | ||Bolt holes diameter [mm] * #||4 x 10 | ||
Revision as of 18:49, 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
