DX-1 EE
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- | Engine Specification Form (ESF) | + | ==Engine Specification Form (ESF)== |
+ | {| border="1" | ||
+ | ||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]||0,896 | ||
+ | |- | ||
+ | !Casing: | ||
+ | |- | ||
+ | ||Outer diameter [mm]|| 70 | ||
+ | |- | ||
+ | ||Length [mm]|| 770 | ||
+ | |- | ||
+ | ||Weight [kg]|| 2,452 | ||
+ | |- | ||
+ | !Aft-closure: | ||
+ | |- | ||
+ | ||Total length [mm]|| 54 | ||
+ | |- | ||
+ | ||Maximum diameter [mm]|| 70 | ||
+ | |- | ||
+ | ||Bolt holes diameter [mm] * # ||4 x 10 | ||
+ | |- | ||
+ | ||Weight [kg]||1,308 | ||
+ | |} | ||
- | Dimensions | + | ==Dimensions propellant grains== |
- | + | {|border="1" | |
- | + | !Components!!Mix-ratio!!Outer diameter!!Inner diameter!!Length Grain!!Net Weight!!mould weight | |
- | + | |- | |
- | + | |||||[mm]||[mm]||[mm]||[gram]||[gram] | |
- | Length | + | |- |
- | + | |KNO3 -sorbitol||||60||20||100|||| | |
- | + | |} | |
- | + | ||
- | + | ||
- | Weight | + | |
- | + | ||
- | + | ||
- | + | ||
- | + | ||
- | + | ||
- | + | ||
- | + | ||
- | + | ||
- | + | ||
- | + | ||
- | + | ||
- | + | ||
- | + | ||
- | + | ==Performance (as designed)== | |
- | + | {|border="1" | |
- | + | |Maximum thrust [N]|| 1645 | |
- | + | |- | |
- | + | |Burn time [s]|| 2.2 | |
- | + | |- | |
- | Performance (as designed) | + | |Total Impulse [Ns]||2859 |
- | + | |- | |
- | Maximum thrust [N] 1645 | + | ||Specific Impulse [s]|| 109 |
- | Burn time [s] 2.2 | + | |- |
- | Total Impulse [Ns] 2859 | + | ||Massa ratio [empty/loaded]||2/3 |
- | Specific Impulse [s] 109 | + | |- |
- | Massa ratio [empty/loaded] 2/3 | + | ||Maximum pressure [N/m2]|| 5.48*106 |
- | Maximum pressure [N/m2] 5.48*106 | + | |- |
- | Maximum temperature [C˚] 1520 | + | ||Maximum temperature [C˚]|| 1520 |
+ | |} | ||
- | Test data | + | ==Test data== |
Most important data of the test performed in august 2006 (reference: test report): | Most important data of the test performed in august 2006 (reference: test report): | ||
- | + | {|border="1" | |
- | Maximum thrust [N] 1640 | + | |Maximum thrust [N]|| 1640 |
- | Burn time [ms] 2500 | + | |- |
- | Total Impulse [Ns] 2400 | + | |Burn time [ms]|| 2500 |
- | Specific Impulse [s] 102 | + | |- |
+ | |Total Impulse [Ns]|| 2400 | ||
+ | |- | ||
+ | |Specific Impulse [s]|| 102 | ||
+ | |} |
Current revision as of 21:38, 22 March 2007
Contents |
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] | 0,896 |
Casing: | |
Outer diameter [mm] | 70 |
Length [mm] | 770 |
Weight [kg] | 2,452 |
Aft-closure: | |
Total length [mm] | 54 |
Maximum diameter [mm] | 70 |
Bolt holes diameter [mm] * # | 4 x 10 |
Weight [kg] | 1,308 |
Dimensions propellant grains
Components | Mix-ratio | Outer diameter | Inner diameter | Length Grain | Net Weight | mould weight |
---|---|---|---|---|---|---|
[mm] | [mm] | [mm] | [gram] | [gram] | ||
KNO3 -sorbitol | 60 | 20 | 100 |
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 |