Design and Launch of a Balloon Re-entry Vehicle for Free Fall Experimentation
Introductions
Introduction• High altitude airborne developments have presented huge
advantages in the US military’s arsenal through:• environmental monitoring• precision navigation• Communication• missile warning• intelligence surveillance and reconnaissance (ISR)
platforms.
• However conventional aircraft have a practical upper altitude limit (60000-80000 ft above the sea level) where engine efficiency greatly diminishes.
• High-altitude maneuvering lighter-than-air platforms use
the principle of buoyancy. These mechanisms became potential platforms for:
• ISR, precision navigation• environmental monitoring• communication relays• missile warning, and weapon delivery.
Introduction Cont. In 2005, the Wright State University High Altitude
Balloon Team began its first development of high altitude mechanisms while being funded by the Ohio Space Grant Consortium.
The team, including students, staff and recent graduates, since then has had over 17 successful launches and recoveries over 100,000 feet while being funded by the National Science Foundation.
During these launches, experiments have been conducted containing: temperature sensors Cameras video transmitters/recorders actuation devices.
Ballute “Ballute aerodynamic decelerators have been
studied since early in space age (1960’s), being proposed for aerocapture in the early 1980’s” (Braun).
The Goodyear Aerospace Corporation coined the
term “ballute” (a contraction of “balloon” and “parachute” which the original ballute closely resembles) for their cone balloon decelerator in 1962.
Objective
Image: Andrews Space, INC
Martian atmospheric entry vehicle for NASA
Design ParametersDesign parameters include but are not limited to:
• A maximum weight per payload of six pounds, total of two payloads (per FAA regulations)
• An altitude parachute deployment of 65,000 feet
• Design of parachute to withstand a drag of 125 mph
• GPS, Beacon, and APRS needed to relocate upon re-entry
• Accelerometer used to record data on free-fall characteristics
• All components function in a low pressure low temperature environment (1 KPa and -70 degrees Celsius
19 Mile High Club Presentation
… 21 Miles ?
Design Considerations - Structural Light Stable Strong Impact Absorbent Modular Aerodynamic
Design Considerations – Structural
Proper Material Selection Wood Foam Carbon Fiber
Proper Shape Aerodynamic Smooth
All constraints are very related
Design Considerations - ElectricalTrackingCommandData Acquisition
Design Considerations – ElectricalTracking Testing
• Automatic Packet Reporting System (APRS)
Design Considerations – ElectricalCommand
Design Considerations – ElectricalCommand Testing
Design Considerations - Harnessing
Design Considerations – Total Assembly
Final Design
ModularToughWithin Specs
Launch 019
Bullute launched on May 5th from Wright State Lake Campus
Flight Prediction showed a landing near Marysville, OH
Flight Prediction
Flight Prediction
Video of Launch
Results - Electrical
Communication Failure Possible Reasons
▪ Radio ▪ Antenna Failure▪ Radio Battery Case
Failure
Results - Electrical
Communication Failure Possible Reasons
▪ GPS Failure
0:00 0:28 0:57 1:26 1:55 2:24 2:52 3:21 3:500.00
20000.00
40000.00
60000.00
80000.00
100000.00
120000.00f(x) = 834213.01673875 x − 1049.11819389577R² = 0.997172807552846
Altitude vs. Time
Time (min)
Altit
ude
(ft)
Results - Electrical
Communication Failure Possible Reasons
▪ Battery Failure
Electrical Load Anaylsis
Performed to determine if batteries died during flight
Calculated total power consumption of all devices
Used V=IR to find current draw on battery pack
Hours battery could operate = Amp hour rating of battery divided by current draw on battery
Electrical Load Anaylsis
Reduced calculated run time by 50% Accounts for cold operating environment
Main battery pack should have lasted 12.64 hours
Radio battery pack should have lasted 5-6 hours
Batteries likely did not die
Results - Flight
Flight Predictions
Results - Flight
Balloon Performance
Ascent Rate▪ 562.13 ft/min.▪ Slower than Ideal
Max Alt.▪ 111,302 ft▪ School Altitude
Record!
Results - Flight
Destination Possibilities
Flooded Field
Lake (most likely)
Conclusions
Mechanical Working Modular
Design Electrical
Communication Breakdown
Flight 111,302 ft
Splashdown! Most Reasonable Result
Acknoledgements
Thanks to Bruce RahnThanks to our pilot & launch advisor
Nick BainesThanks to Mark Spoltman & Josh
Horn of Hartzell PropellerThanks to Eleanor Mantz for sewing
the parachute
Sponsors
The Ohio Space Grant Consortium
Wright State University Curriculum Development Grant
The National Science Foundation
Questions ?
Budget
Gantt Chart