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From Dare

(Difference between revisions)
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! Name  !! mass !! motor/engine!!succesfull recovery !! retrieved !! launchdate
! Name  !! mass !! motor/engine!!succesfull recovery !! retrieved !! launchdate
|-
|-
-
! SRP I   
+
! [SRP I]  
|||40mm pvc||||yes||2003
|||40mm pvc||||yes||2003
|-
|-
-
! SRP II
+
! [SRP II]
|||40mm pvc||no||yes||7-5-2004
|||40mm pvc||no||yes||7-5-2004
|-
|-
-
! SRP III
+
! [SRP III]
|||40mm pvc||no||no||7-10-2005
|||40mm pvc||no||no||7-10-2005
|-
|-
-
! RVD  
+
! [RVD]
|||50mm Aluminium||yes||yes||2003
|||50mm Aluminium||yes||yes||2003
|-
|-
-
! Booster Project
+
! [Booster Project]
|||3 X 40mm pvc||no||yes||27-5-2005
|||3 X 40mm pvc||no||yes||27-5-2005
|-
|-
-
! DX-1
+
! [DX-1]
|||DX-1 motor||yes||yes||2003
|||DX-1 motor||yes||yes||2003
|-
|-
-
! DX-1
+
! [DX-1]
|||DX-1 motor||yes||yes||5-7-2004
|||DX-1 motor||yes||yes||5-7-2004
|-
|-
-
! DX-1
+
! [DX-1]
|||DX-1 motor||no||no||10-7-2005
|||DX-1 motor||no||no||10-7-2005
|-
|-
-
! [http://editthis.info/cansat_launcher/Main_Page Wiki CanSat Launcher V1]
+
! [CanSat Launcher V1]
|||DX-1 motor||no||yes||28-4-2006
|||DX-1 motor||no||yes||28-4-2006
|-
|-
-
! CanSat Launcher V2
+
! [CanSat Launcher V2]
|||DX1-EE motor||no||yes||11-5-2006
|||DX1-EE motor||no||yes||11-5-2006
|-
|-
-
! CSL V3
+
! [CSL V3]
|||DX1-EE motor||yes||yes||6-10-2006
|||DX1-EE motor||yes||yes||6-10-2006
|-
|-
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! Name !! Total impulse !! Burntime !! Dry mass !! Propellant mass !! Propellant
! Name !! Total impulse !! Burntime !! Dry mass !! Propellant mass !! Propellant
|-
|-
-
! SRP (PVC)
+
! [SRP] (40mm PVC)
| 180 Ns || 1 s
| 180 Ns || 1 s
|-
|-
-
! RVD (aluminium)
+
! [RVD] (50mm aluminium)
|300 Ns || 1.4 s
|300 Ns || 1.4 s
|-
|-
-
! DX-1
+
! [DX-1]
| 1250 Ns || 1.4 s || 2.7 kg? || 1.2 kg || KNO3/Sucrose
| 1250 Ns || 1.4 s || 2.7 kg? || 1.2 kg || KNO3/Sucrose
|-
|-
-
! DX-1 EE
+
! [DX-1 EE]
| 2500 Ns || 1.4 s || 2.7 kg? || 2.5 kg || KNO3/Sorbitol
| 2500 Ns || 1.4 s || 2.7 kg? || 2.5 kg || KNO3/Sorbitol
|-
|-
-
! BigBoy
+
! [BigBoy]
| 11000 Ns || 5 s || 25 kg? || 11 kg || KNO3/Sorbitol
| 11000 Ns || 5 s || 25 kg? || 11 kg || KNO3/Sorbitol
|-
|-
-
! DEIMOS I
+
! [DEIMOS I]
| (50000) Ns || 30 s max || 6 kg || (indefinite) || LCH4/LOX
| (50000) Ns || 30 s max || 6 kg || (indefinite) || LCH4/LOX
|}
|}
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[http://editthis.info/cansat_launcher/Main_Page Wiki CanSat Launcher]
[http://editthis.info/cansat_launcher/Main_Page Wiki CanSat Launcher]
-
[[cansat_launcher]]
 
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Revision as of 16:44, 14 October 2006

Welkom bij de DARE wiki. De dingen hieronder heb ik nog maar even laten staan omdat er nog wel een paar handige tips in staan.

image:DARE-logo-web.jpg

Delft Aerospace Rocket Engineering (DARE) is een studentenvereniging met als doel studenten de gelegenheid te geven om zelf amateur raketten te ontwerpen, bouwen en lanceren. DARE is verbonden aan de vliegtuigbouwkundige studie vereniging Leonardo Da Vinci van de faculteit Luchtvaart- en ruimtevaarttechniek (L&R) van de Technische Universiteit Delft. (TU Delft).


Contents

History

DARE was created in 2001 by six enthousiast Aerospace Engineering students, studying at the Technical University of Delft. These students had a craving to apply the gained knowledge during their curriculum in practise, by building rockets.

Rockets

In the last years the following rockets were build and lauched

Rockets
Name mass motor/enginesuccesfull recovery retrieved launchdate
[SRP I] 40mm pvcyes2003
[SRP II] 40mm pvcnoyes7-5-2004
[SRP III] 40mm pvcnono7-10-2005
[RVD] 50mm Aluminiumyesyes2003
[Booster Project] 3 X 40mm pvcnoyes27-5-2005
[DX-1] DX-1 motoryesyes2003
[DX-1] DX-1 motoryesyes5-7-2004
[DX-1] DX-1 motornono10-7-2005
[CanSat Launcher V1] DX-1 motornoyes28-4-2006
[CanSat Launcher V2] DX1-EE motornoyes11-5-2006
[CSL V3] DX1-EE motoryesyes6-10-2006

Engines

DARE uses home built and designed rocket engines. Over the years, the following engines have been built and tested.

Engines
Name Total impulse Burntime Dry mass Propellant mass Propellant
[SRP] (40mm PVC) 180 Ns 1 s
[RVD] (50mm aluminium) 300 Ns 1.4 s
[DX-1] 1250 Ns 1.4 s 2.7 kg? 1.2 kg KNO3/Sucrose
[DX-1 EE] 2500 Ns 1.4 s 2.7 kg? 2.5 kg KNO3/Sorbitol
[BigBoy] 11000 Ns 5 s 25 kg? 11 kg KNO3/Sorbitol
[DEIMOS I] (50000) Ns 30 s max 6 kg (indefinite) LCH4/LOX

Raket stabiliteit

De stabiliteit van een raket is de neiging van de raket om terug te keren naar zijn evenwichtspositie. Een amateur-raket werkt meestal met passieve stabiliteit. Deze kan worden verkregen door het bevestigen van vinnen aan de raket. Voor de stabiliteit van een raket zijn twee punten van belang, het zwaartepunt en het aërodynamische drukpunt.

links

homepage DARE


Wiki CanSat Launcher






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