Preliminary Design Review “The Distribution of Ionizing Radiation with Altitude”. Left to Right: Tom L.- Payload James Z.-Construction Izzy S.- Audio Visual Youssef B.- Program Manager Dr. Marintsch - Head Mentor Randall H. - Safety Aldo F. - Outreach/Publicity
Preliminary Design Review
“The Distribution of Ionizing Radiation with Altitude”
Left to Right:
Tom L.- Payload
Izzy S.- Audio Visual
Youssef B.- Program Manager
Dr. Marintsch - Head Mentor
Randall H. - Safety
Aldo F. - Outreach/Publicity
Paul T. - Rocket design
Not in Photo: Mr. D. Laney,
Mr. M. Loughlin
St. Thomas High School, Houston, TX
•Mission Statement and Goals
•Launch Vehicle and Payload Summary
•Vehicle Body System
•Planning of System Tests
•Budget and Outreach
mission statement and goals
Our mission is to supply accurate data about cosmic radiation by building a safe and functioning rocket that can provide ample time for data collection.
•Reach an altitude of one mile.
•Payload records data on ionizing radiation.
•Both parachutes deploy at predetermined altitudes.
•Land within one square mile.
•Rocket retrievable with payload intact.
•Shed light on radiation variation with altitude.
launch vehicle and payload summary
Length - 90”Mass with Motor - 10,038 g
Diameter - 5.40”Stability Margin - 2.11
Motor - K560WLaunch System - 1.5”x1.5” (10’)
Drogue – 28” at Apogee
Main – 120” at 1500 ft.
Payload Experiment Summary:
Measure levels of cosmic radiation with altitude through the use of Geiger Mueller Tubes whose data will be correlated with time and altitude.
(1) Vehicle Body System
•Modified LOC Precision Magnum 3e
•Three Body Tubes (5.40”- size needed for payload)
Lower (31”) – K560W, Drogue, G10 Fins, Camera
Middle (28”) – Payload Bay, Canards
Upper (11”) – Main Chute
•Nose Cone (21”)
(2) Propulsion System
•Motor: Aerotech K560W
•Thrust / Weight: 5.7:1(Thrustcurve) [560N / (10 kg x 9.8m/s2)]
5.1:1(Rocksim) [497N / (10 kg x 9.8m/s2)]
•Velocity off Launch Rod:59.5 ft/s
•Rail Length:10 ft
•Burn Time:4.6 s
(3) Recovery System
• 28” LOC Precision
•Deployed at Apogee (18.3 s)
•Perfectflite Dual Deployment Altimeter
•120” Public Missiles
•Deployment at 1500 ft (70.8 s)
•Perfectflite Dual Deployment Altimeter
•Landing at 158 s
•Velocity at Landing: 19.3ft/s(V); 10.3ft/s(H); 21.9ft/s(M)
Within Middle Body Tube
•Bay #1 - Geiger Mueller Tubes.
•Bay #2 - Circuit Board and Processor, Gamma-Scout Geiger Counter.
•Bay #3 - Two Altimeters – Linked to ejection charges at either end of Payload Bay.
Within Nose Cone
Outside of Lower Body Tube
After consideration of the effects due to terrestrial radiation, we would expect the counts to increase with elevation as the net absorption of Secondary Cosmic Radiation by the atmosphere decreases.
(1) Radiation is measured with altitude using 12”-long Geiger Mueller Tubes expected to record up to 400 cpm over 140 s of descent and 18 s of ascent.
(2) Radiation levels are suggested to be associated with changes in atmospheric conditions (such as cloud formation and global warming; chlorine production and ozone depletion)
(3) Radiation levels are linked to the breakdown of DNA in organic tissue and so merit further study.
planning of system tests
•Payload – Geiger Counters and (a) consistency of data collection, (b) background counts, (c) isolation of ray sources.
•GPS – Locality tracking.
•Recovery – Ejection charges and chute deployment. Safety and RF Signals.
•Propulsion – (a) Inspection of parts, (b) assembly supervision.
•Vehicle – Scale model launch.
•Camera – Video testing.
Prior to each project phase:
Review system risks and mitigations.
Review Safety Codes.
Pass test on Safety Procedures.
Sign Safety Statement.
budget and outreach
Current major purchases
• Geiger Counter with data storage ($445) • Rocket Parts ($295)
• Geiger Mueller tubes ($200) • GPS System ($450)
• 120” parachute ($190) • Video camera ($100)
• Five additional GM tubes ($570) Subtotal $860
• Continued exploration of fund raising strategies. Current preparation of Informational Flyers/Brochures.
• Formulation of presentation/workshop strategies.