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
| 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 | mould weight
|
| | [mm] | [mm] | [mm] | [gram] | [gram]
|
| KNO3 -sorbitol | 35% - 65% | 60 | 20 | 100 | 400 | 800
|
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
