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