![\"\"](\"https:\/\/www.verticallimits.nl\/wp-content\/uploads\/\/DECA-II-2010.jpg\" "\\"DECA")
Diameter: 58mm payload \/ 54mm rocket body<\/p>\nDiameter: 58mm payload \/ 54mm rocket body<\/p>\n
Length: 2200mm<\/p>\n
Weight fully loaded: 6000gr (of which aproximately 1100gr ballast)<\/p>\n
Motor: DECA\u00a08 grain\u00a0KNDX<\/p>\n
.<\/p>\n
Rocket was sucessfully launched during\u00a0the NERO Launch Day 07-05-2010<\/a><\/p>\n Motor:<\/strong><\/p>\n Motor\u00a0is the DECA 8 grain. A 54mm motor with 8 bates grains and a total impuls of\u00a0 approximately 1400Ns. The nozzle has a 16mm throat and\u00a0is optimised for the 20mm core Bates grains\u00a0(core-to-throat ratio of about 1,5:1 to avoid erosive burning). Ae\/At ratio is 6,0:1. The nozzle is held in place with 2 rows of 6x –\u00a0M3\u00a0countersunk hex socket bolts. Forward bulkhead is retained by the coupler which is secured the same way as\u00a0the nozzle.<\/p>\n 27.03.10<\/strong> – 2nd Static\u00a0test DECA 14 motor <\/a>–\u00a0full data recording and suitable for launch at NLD 2010.<\/p>\n 13.03.10<\/strong> – Static\u00a0test DECA 14 motor <\/a>– no data.<\/p>\n 20.02.10<\/strong> – Static pressure tested\u00a0the casing to 150% op MEOP – 90bar.<\/p>\n Fin can:<\/strong><\/p>\n Same as used with the first\u00a0DECA rocket in 2009<\/p>\n Fin can mass: 152gr. CoG @ 76mm from short end<\/p>\n Body tube:<\/strong><\/p>\n Similar to the first DECA rocket, this rocket will break up above the motor for first stage tumble recovery. This rocket has a revised design\u00a0that the coupler has been incorperated into the forward bulkhead retention design of the motor.\u00a0 This will simplify the rocket lay out with less tube butt-to-butt connections. The 850mm long aluminium body tube cointains (motor-to-nose cone shoulder):<\/p>\n Second stage recovery will either eject a\u00a0nose cone or\u00a0a stand alone payload made out of HPR materials.<\/p>\n Recovery<\/strong><\/p>\n Main parachute 800mm diameter + 1m tubular kevlar with end pliced for connection to d-shackle.\u00a05m\u00a0 tubular kevlar with both ends spliced\u00a0for d-shackle. Payload with M6 eyebolt for connection to d-shackle.<\/p>\n Burrito style parachute bag. Kevlar cloth\u00a0350 x 235mm. Length\u00a0= spare (60mm) +\u00a0length parachute (150mm) +GPS tracker (70mm) + overlap (70mm) = 350mm. Width = 1,5 \u00b7 \u03c0 \u00b7 ID tube = 235mm.<\/p>\n 18.04.10 <\/strong>– Main parachute ejection test with 1,0gr BP in a latex finger. No confident separation: 54mm, DECA II rocket, main parachute test – 19.04.10<\/a>. Next test will use the proven 1,0gr\u00a0BP\u00a0straw igniter.<\/p>\n 02.05.10 –<\/strong> Assembled rocket & payload. Determined Cp & Cg. Added 1100gr of ballast to keep under the 2km limit and now has a static margin of 1,25 cal.\u00a0\u00a0<\/p>\nngg_shortcode_1_placeholder\n Length:<\/p>\n Glass Body tube<\/p>\n Glass\u00a0Coupler tube<\/p>\n Machining the glass tube to length: While cutting square on lathe don’t go all the way and leave 0,4mm wallthichness remaining. Final cut by hand with sharp hobby knife. This to prevent glass fiber weave to catch up with cutting tool thereby causing delamination of inner layer.<\/p>\n >>>Motor mass full: 2624 – 2633gr (2572 SolidWorks). CoG @ 385mm from top casing \/\u00a0338 from nozzle (340 SW).\u00a0\u00a0Length motor (top casing to nozzle end) =\u00a0723mm.<<<<\/p>\n >>>Recovery electronics & body tube mass: 1402gr (1399 SW). CoG @\u00a0465 from top \/ 385mm from end.\u00a0 CoG from nozzle = 1108mm (1110 SW). Length body tube = 850gr.<<<<\/p>\nngg_shortcode_2_placeholder\n Introduction Diameter: 58mm payload \/ 54mm rocket body Length: 2200mm Weight fully loaded: 6000gr (of which aproximately 1100gr ballast) Motor: DECA\u00a08 grain\u00a0KNDX . Rocket was sucessfully launched during\u00a0the NERO Launch Day 07-05-2010 Goals Prove of concept: modular\u00a0built with\u00a0stand alone\u00a0payload. Achieve a peak altitude of approximately 2km Determine the usefulness of an on-board\u00a0GPS tracker for rocket<\/p>\nGoals<\/h3>\n
\n
Design & Construction<\/span><\/h3>\n
\n
Payload<\/h3>\n
Notes<\/h3>\n
\n
\n
\n
Conclusion<\/h3>\n
\n
Post flight analysis of Flight I\u00a0– 07-05-2010 –\u00a0by BO<\/h3>\n
\n
Library<\/h3>\n
\n