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Narrative Descriptions

General Description: The PML Ultimate Endeavor Kit was used as the

base for creating Eagle 1. This kit has been modified to accommodate the unique features and needs of Eagle 1. Major modifications to the PML kit include; upgrading the body tube material from phenolic tubing to PML fiberglass phenolic tubing. Additionally, fin material was upgraded to G10 fiberglass fins with a thickness of 0.125". Next, the total length of the rocket was modified to accommodate the Hypertek Armageddon 4630 cc motor (M1010) and XXL SkyAngle Parachute. Basically, an additional forward section was added to Eagle 1, which is 42.24" in length and the booster section was increased by 23.00". The avionic bay included with the kit was modified to accommodate two computers and an experimental package. Also, and additional avionic bay was added to the nose cone to carry an R-DAS flight computer system. Next, shock cords were upgraded from nylon to 5/8" tubular Kevlar. Finally, launch lugs were replaced with launch rail buttons. Final dimensions of Eagle 1 will be a rocket that stands 12.5 feet high and has a diameter of 6". When loaded with engine the rocket will weigh approximately 53.815 lbs. Finally, Eagle 1 will be launched using an Armageddon 4630 cc (M1010) motor built by Hypertek.

Flight Operations: After running several simulations on RocSim 6.0 the

expected altitude of Eagle 1 will be approximately 12,264 ft. Eagle 1 should achieve a maximum vertical velocity of around 604 mph. Recovery of the Eagle 1 will be classified as dual deployment. Two avionic computers will control recovery/data collection functions. The main avionic computer will be a BlackSky AltAcc 2C and the redundant computer will be the CPR 3000 by PML. Deployment of the 36" drogue chute will occur at apogee and deployment of the Skyangle XXL Level III Certification Parachute by B2 Rocketry will be deployed approximately at an altitude of 1200 ft. Separate charge wells will be used for each computer. Each computer will have the capability of deploying both the drogue and main parachutes.

Novel/Unique Design Features: Ranking #1 on the novelty list will be a “home-made” altimeter that will be flown as an experimental package in the main avionic bay. This altimeter will determine the apogee of Eagle 1 using fishing line and a rubber glove. The expected accuracy will be within 5% of the apogee readings recorded by Eagle 1 avionic computers. Unique design features include the avionic bay located in the nose cone. This bay will house an R-DAS computer system that will be used to collected performance data. When funds allow, a “real-time” data transmission to a laptop computer on the ground will be possible.

Major Risk: Failure of recovery system deployment is at the top of risks.

Mitigating this risk has been the inclusion of two avionic computers to control deployment. Additionally, dealing with specific computer limitations has resulted in separate ejection charge wells for each computer. Since Eagle 1 will be traveling at speeds near MACH 1 steps have been taken to ensure a successful flight. Upgrading the body tube to fiber-glassed phenolic tubing, increasing the thickness of the fins to 0.125" (G10 fiberglass); filet joints connecting fins to the outside and inside of the body tube and to the motor mount have been included. The final step in ensuring “rock solid” fin attachment was the insertion of expandable foam into voids located between the motor mount and inside wall of the body tube. This has greatly strengthened the bonding of fins. Documentation of avionic computers failing to detect launch when using large Hypertek motors has been addressed. The PML CPR 3000 computer uses barometric pressure to sense launch detection and the 2C version of the BlackSky AltAcc has been included. This computer has a new processor that successfully deals with oscillation problems created by Hypertek motors. Finally, double wall phenolic tubing was used to make couplers and pistons.

Construction Package

Airframe Materials o Body Tubes and Fuselage: The body tube of Eagle 1 was constructed with

6” diameter fiber-glassed phenolic tubing sold by PML. o Fins: Fins are made of 0.125” G-10 fiberglass. o Centering Rings: All centering rings and bulk-head plates were made of

.5” Birch Plywood provided by PML. o Launch Lugs: Two Black-sky aluminum rail buttons are being used to

guide the rocket up the 144” Black-sky HPR rail. One button is attached to the rocket at the rear centering ring and the forward button is attached to the rocket about 1 caliber below the CG. Both buttons are backed by pieces of birch-plywood.

o Reinforcement Materials Epoxy Filet Joints: All fin attachments were reinforced using

triple filet joints made of slow setting epoxy glue. Each filet joint was around 3/16” in depth. Filet joints exist on the outside of the body tube, inside of the body tube meeting and along the motor mount.

• Note: Epoxy filets were also used to reinforce the attachments of centering rings, avionics parts, etc…,

PML Expandable Foam: Voids between the motor mount, fins and inside body tube were filled with PML expandable foam. This attached to all inside surfaces including fins, body tube and motor mounts, thus reinforcing fin attachments.

Birch-Plywood Centering Ring Segments: Pieces of centering rings were used to reinforce the launch button anchors as shown in the photographs attached to this package.

o Adhesives Epoxy Glue: West System Epoxy was used for fin attachments

and filet joints. Slow setting epoxy was used in critical areas to increase bonding strength.

o Nose Cone: This item is made of fiberglass and gel-coated. The nose cone was provided by PML in the rocket kit.

Construction Techniques o Fin Mounting Method

First a fin alignment guide was constructed as shown in the photographs attached. This guide was designed to insure when fins were aligned with the guide during installation each fin set would be exactly 1200 from each other. Visual inspection including a level was used to insure fins within each fin set were both correctly aligned along each fin’s X, Y and Z axis.

Fins were then attached to the motor mount by inserting them through fin slots and attaching fins with slow setting epoxy glue. Fin root edges and the motor surface were sanded with “ruff” grit

sandpaper to increase bond strength. Next, fins were reinforced by installing external filet joints with slow setting epoxy glue. Again, all important surfaces were prepared to maximize glue bonding. Fin to internal body tube and fin to motor mount filet joints were installed in the same manner as described above. A special epoxy application tool was designed to insure sufficient epoxy glue was installed for internal filet joints with as few bubbles as possible. This tool was made using a 2’ glass rod, rubber hose and a hand held vacuum pump. Photographs of this tool and its use are attached. Finally, fins were reinforced as described above by inserting PML Expandable Foam into all internal voids between the body tube, motor mount and fin tabs.

o Reinforcement Areas Fins/Centering Rings/Rail Buttons/Avionics: Areas needing

reinforcing included fins, centering rings, launch rail buttons, avionic parts etc…, mostly, epoxy glue was used to accomplish these task. Using fiber glass to reinforce fin attachments was not possible due the limited space available between the rocket’s inner body tube and motor mount (less than 2 inches). Thus, foaming as described earlier was used for additional reinforcement.

Shock Cords: Reinforcement along shock cords were accomplished using “Bar Tacks” and epoxy.

Epoxy glue was applied to the ends of bolt and nut attachments where applicable to insure proper torque on bolts is maintained.

Launch Rail Guides needed “backing plates” which were made using pieces of left over centering rings. These pieces were attached to above and below centering rings where buttons were installed. Also, a similar piece was glued to the inside of the airframe where the forward button was attached. Inserted into the rocket in these areas were the anchors for the buttons. Anchors were further reinforced using epoxy glue to secure them in anchor holes.

Avionic bay attachment was accomplished using #6 self tapping screws that were screwed through the body tube and avionic bay wall into avionic bay bulk head centering rings.

Shear pins were inserted into small holes drilled in bulk head plates. Attached shear pin holes were small pieces of brass plate with shear pin holes drilled through the plates. The plates were installed to insure shear pins are cut during recovery system deployment.

o Frangible or Breakaway Components: Eagle 1 is using a dual deployment recovery system, thus at some point in the rocket’s flight it will be descending in three sections which are all attached by 5/8” tubular Kevlar shock cord. Insuring sections of rocket do not prematurely separate during flight will be accomplished via the insertion of shear pins made of styrene rod (1.6 mm diameter) along tube coupler sections designated for

separation. At each of these areas 4 shear pins will be installed 900 apart from each other as described in the reinforcement section. Sections of the rocket will separate due to high internal pressure created by ejection charges. As the sections of rocket are forced apart shear pins will be cut smoothly with the brass plate pieces installed over shear pin housings.

Drawing Showing Interior layout of components/airframe assembly: See Drawing # 2 in Scaled Drawing Package

Photographs: construction techniques discussed can be observed by viewing photographs in Photo Package.

Recovery Systems Package

Operation Description o Deployment Sequence:

Initial launch, boost and coast phases of flight. • PML CPR 3000 will detect launch after a 300 ft elevation

change relative to the rest altitude. • AlttAcc2C launch trigger detects launch after the rocket is

launched and 1 G of acceleration (relative to the at-rest values) is sensed for 0.25 seconds.

Apogee of flight detected, lower airframe separation and drogue chute deployed.

• AltAcc2C will deploy the drogue chute when the integrated value (+ and – acceleration) reaches zero and Eagle 1 is at minimal velocity.

• PML CPR 3000 will deploy drogue chute when apogee is detected sensed by an increase in barometric pressure.

Rapid, controlled descent phase to pre-programmed main chute deployment level.

• AltAcc2C will deploy main chute when an altitude of 1200 ft. relative to the resting pressure is detected.

• PML CPR 3000 will deploy main chute when an altitude of 800 ft relative to the resting altitude of Eagle 1 is detected.

Nosecone/payload section separation, main parachute deployment and touchdown.

o Avionic Mounting: a total of 3 avionic computers will be onboard Eagle 1. RDAS: This avionic computer system will be riding in the payload

section of the nose cone. It is mounted by way of ¼” risers on an avionic mounting plate made of 3/16” bass wood.

AltAcc2C is mounted in the main avionic bay as shown in the attached photos and diagrams. This avionic bay was designed by PML and is known as their CPR 3000 system. Thus, the AltAcc2C is attached to fore and aft ejection wells by way of a CPR 3000 adapter sold by Blacksky. The AltAcc2C is located in its own avionic tube with its own drogue/main ejection wells.

Finally, the PML CPR 3000 computer is attached in a similar fashion as the AltAcc2C and is located in its own avionic tube inside the main avionic bay.

o Parachute Compartments and Closures Main Parachute:

• Location: o Main Parachute: An XXL Sky Angle Cert. 3

Parachute is located in the forward section of Eagle 1. This section of Eagle 1 is 42.240 inches in length. The parachute is installed in a deployment

bag made by Sky Angle. The parachute is attached to the main piston by way of a 30 ft long shock cord made of 5/8” tubular Kevlar.

o Drogue Parachute: A Sky-angle 36” Classic II parachute will be used as the drogue. It is located in the mid section of Eagle 1 and attached to a piston by way of a 20 ft shock cord made of 5/8” tubular Kevlar.

• Closures: o Main Parachute: The forward section contains two

closures. The main closure is formed by forward end of the main avionic bay bulk head located in the aft end the forward section of the airframe. The avionic bay is fastened to the forward airframe of Eagle 1 by way of screws. The forward closure is formed by the bulkhead attached to the shoulder of the nose cone. The nose cone is temporarily fastened to Eagle 1 by way of 4 shear pins (made of 1.6 mm styrene rod).

Ejection gas protection for the main chute is provided by way of a piston. Also, backup to this system is the deployment bag the main chute is packed in.

o Drogue Parachute: the aft end bulk head of the main avionic bay forms the forward closure of the mid section of Eagle 1. The aft closure for this section is formed by the bulk head plate mounted to the lower airframe of Eagle 1 (Hypertek Motor located in this section).

Ejection gas protection is provided by way of a piston. No deployment bag will be used for this chute.

o Compartment Venting Forward Airframe: a 3/16” hole will be

located 12” aft of the top of this section. Mid Airframe: a 3/16” hole will be located

12” above the rear of this section. o Descent Rates

Provided by RocSim 6.0: descent rates provided by simulation for actual launch conditions that will be experienced in Argonia, KS in July 2003. Assumptions are that the altitude of the site above sea level is about 1200 ft, humidity will be around 70% and the temperature will be around 950 F.

• Descent Rate at deployment of drogue chute will be 0.019 mph.

• Descent Rate at deployment of main parachute at 1200 ft will be 50.68 mph.

• Descent Rate at landing will be 15.149 mph. Descent rate of Eagle 1 with NO Chutes DEPLOYED: using

equation provided by Dean Roth found on Info Central of Rocketry Online. Note Mr. Roth assumed the temperature was 700 and the rocket would not fly much more than 1 mile in altitude. Thus, this equation is simply an estimate. Eagle 1 is expected to fly over 2 miles high. The temperature in Kansas in July will probably be around 950 F. Finally, Eagle 1 is 6 inches in diameter and 12.5 feet long.

• Vt = (2 x W / (Cd x Datm x A))1/2 o Vt = terminal velocity vertically o Cd = coeifficent of drag o Datm = atmospheric density (0.0024 at sea level) o A = surface area in square feet assuming the rocket

falls nose first. A = pi x r2

• A = 3.14 x 32 = 28.2743 inches2 • A = 28.2743 inches2 x 1 ft2/144inch2

= .19635 ft2 • Vty = ((2 x 6) /(0.75 x .0024 x .19635))1/2 = 585.54 feet/sec • Vth = ((2x6)/(.75 x .0024 x 9.81748))1/2 = 26.0591 ft/sec

o Vth = Terminal Velocity if rocket falls horizontally. Assumption is that the surface area of the rocket exposed is: A = pi x r x l for Eagle 1 would be A = 3.14 x 3 x 150 inches = 1413.72 inches2 . This is equivalent to 9.81748 ft2 (1413.72/144 = 9.81748)

Descent Rates calculated with the descent calculator located at

http://www.onlinetesting.net/cgi-bin/descent3.3.cgi: • 54” PML Drogue Chute deployed descent rate = 55 ft/sec. • XXL Skyangle Main Chute deployed descent rate = 14.72

ft/sec. Components

o Control Devices: redundant avionic computers will be used with Eagle 1 as described previously.

Blacksky AltAcc2C • Sensing Method: AlttAcc2C launch trigger detects launch

after the rocket is launched and 1 G of acceleration (relative to the at-rest values) is sensed for 0.25 seconds. (Acceleration Sensing with special processor to eliminate oscillations errors caused by use of Hypertek motors)

• Power Source: One 9V battery • Safe and Arm Control: provided by way of an arm switch

in which a screw is tightened to arm.

• Mounting Method: AltAcc2C is mounted in the main avionic bay as shown in the attached photos and diagrams. This avionic bay was designed by PML and is known as their CPR 3000 system. Thus, the AltAcc2C is attached to fore and aft ejection wells by way of a CPR 3000 adapter sold by Blacksky. The AltAcc2C is located in its own avionic tube with its own drogue/main ejection wells.

• Wiring Schematic: see Electrical Schematic Showing E Match Safety Logic word document.

CPR 3000 • Sensing Method: PML CPR 3000 will detect launch after a

300 ft elevation change relative to the resting altitude (Barometric Sensing).

• Power Source: One 9V battery • Safe and Arm Control: provided by way of an arming

switch located on the outside of the airframe. This switch provided by PML. The on position is when the switch is placed in the down position.

• Mounting Method: Finally, the PML CPR 3000 computer is attached in a similar fashion as the AltAcc2C and is located in its own avionic tube inside the main avionic bay.

• Wiring Schematic: see attached diagram. o Parachutes

Drogue: A Sky-angle 36” Classic II parachute will be used as the drogue. This parachute is manufactured out of rip stop 1.9 oz zero porosity balloon cloth. It has three 3/8” mil-spec woven tubular nylon (950 lbs tensile) suspension lines sewn in a continuous, uninterrupted path around the canopy. Each suspension line is 36” in length. A 1500 lb nickel-plated swivel is used for attachment to the riser. The coefficient of drag for this chute is 1.34.

Main: An XXL Sky Angle Cert. 3 Parachute made of 1.9 oz rip-stop nylon will be used. This parachute has a diameter of 104.534” and a coefficient of drag of 1.40. Four shroud lines made of 70 lb Kevlar line are attached to this chute. Each line is 120” long.

• Deployment Bag: A XXL Cert. 3 deployment bag made by B2 Rocketry (Skyangle) will be used with the main chute.

o Risers: both risers are made of 5/8” tubular Kevlar (breaking strength > than 5000 lb). The ends of each riser form loops that were sewn using gortex thread. At least 3 bar-tacks each ¾” wide were sewn to form each loop. Inserted into loops for attachment to the rocket are large quick links (5/16” diameter shafts).

Drogue Riser: 20 ft long Main Riser: 30 ft long

o Mounting Hardware Avionics: manufactured by PML. See attached photographs.

Basically, each computer is mounted by way of four screws to

PML altimeter mounts. The AltAcc2C also required custom metal plates to adapt this computer to the CPR 3000 mounts.

Piston straps were attached to main avionic bay by way of epoxy according to PML directions.

Risers are attached to pistons via large quick links made of 5/16” diameter steel shafts.

6/7.5/11 inch U bolts provided by PML are attached to the lower airframe and nose-cone bulkheads. Risers are attached to these bolts by way of quick links. All nuts attaching U bolts received epoxy glue to ensure they do not loosen.

The main avionic bay is attached to the airframe by way of #6 self tapping screws. There are a total of 32 screws attaching the avionic bay to the airframe. 16 screws attach the upper air frame to the bay and 16 attach the bay to the mid section. 8 screws on each end penetrate into the main avionic bay bulkheads and the other 8 screws on each end penetrate through the side wall of the airframe and avionic bay.

Motor Mount: the motor mount provided by Hypertek is mounted to the rear centering ring via screws and bolts provided by Hypertek.

Launch lugs are aluminum and manufactured by Blacksky. Each launch lug is screwed into counter sinks located in backing plates made of ½” birch plywood.

o Pyrotechnic Devices Quantity:

• Main: On July 5, 2003 ejection test were performed. Results yielded that 2.5 grams of 4 F gunpowder caused nose cone separation and sheer pins to cleanly severed, but the charge was not able to push the main parachute out of the body tube. Thus, the charge was increased to 4.0 g of 4F gunpowder resulting in an energetic deployment of the main chute and nose cone. The nose cone and main chute were ejected over 20 ft away from Eagle 1, which was inclined at a 35 deg angle. 5g of 4F will be used for the launch for the main chute charges to ensure energetic deployment.

• Drogue: 4g of 4F gunpowder will be used for deployment charges based on information obtained from ejection test for the main parachute. The midsection of Eagle 1 carrying the drogue chute is only 23 inches in length versus the 42 inch upper section in which a heavy XXL Cert III Skyangle chute is located. Thus, this size charge will produce a safe and energetic deployment of the drogue chute.

Bridgewire: Electric matches will be used to ignite gunpowder. These matches were purchased from Rocket Silo2.0.

Main and redundant charges are separate. Each computer contains its own separate charge canisters manufactured by PML.

• Method for Determining Charge Amounts: This amount was determined via advice provided on the PML website and speaking to the owner of PML, Frank Uroda who has extensive experience at flying rockets manufactured by his company. Basically, 50% of the amount of 4F gunpowder recommended by the calculator located on Info Central found on Rocketry Online will be used for each charge.

o Testing and Operation Verification All three avionic computers that will be flying aboard Eagle 1 were

tested according to the manufactures recommendations. All computers are “good to go!”

Ground Test: performed on July 5, 2003 as described above under Pyrotechnic Devices.

Stability Package

Launch Pad Description: The launch pad being used is a Quad 4 provided by Impulse Aerospace. Attached to this pad via adapters will be a 12’ standard HPR launch rail manufactured by Blacksky. The launch rail is constructed of two 6 ft sections.

Center of Pressure: this figure was calculated by RockSim 6.0 software using Barrowman and RockSim equations.

o CP location according to Barrowman Equations = 119.751 inches aft of the nose cone tip.

o CP location according to RockSim Equations = 124.773 inches aft of the nose cone tip.

Center of Gravity: is located 98.310 inches aft of the nose cone tip according to both Barrowman and RockSim equations. This figure is when the engine is loaded into the rocket and full of Nitrous.

Static Margin of Stability o Barrowman = 3.52 o RockSim = 4.34

Level III Certification Package: John Sorrel Expected Performance Profile

Flight Parameters

o Launch Weight = 53.815 lbs o Motor Type

Motor Designation = M 1010 Motor Impulse 9222.78 Ns Motor Certified by NAR and/or TRA = yes

o Estimated Drag Coefficient = 0.49145 o Lift-off Velocity = 42.794 mph o Maximum Altitude = 12264 ft o Maximum Velocity = 603.567 mph o Maximum Acceleration = 316.965 ft/sec2

Launch Profiles Generated by RockSim 6.0 o Profile 1

Launch altitude = 1200 ft Humidity = 70 % Temperature = 85 deg F Barometric Pressure = 29.914 Head Wind = 0 mph starting at launch altitude

o Profile 2 Launch altitude = 1200 ft Humidity = 70% Temperature = 85 deg F Barometric Pressure = 29.914 Head Wind = 5 mph starting at launch altitude

o Profile 3 Launch altitude = 1200 ft Humidity = 70% Temperature = 85 deg F Barometric Pressure = 29.914 Head wind = 10 mph starting at 8000 ft.

Program used to perform simulations = RockSim 6.0

Level III Certification: John Sorrel Avionic Computer Circuit Board Schematic Diagrams

Schematic Diagram 1: Key Components of the A

chematic Diagram 2: AltAcc2C Power Scheme

ltAcc 2C

S

Schematic Diagram 3: PML CPR 3000 Co-Pilot

Level III Certification: John Sorrel Riser Diagrams for Parachutes

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Level III Certification Package: Photographs John D. Sorrel, Jr.

TRA #8504 NAR #80248 Photo 1: Filet Joints

Photo 2: Internal Filet-Motor Mount to Root Edge of Fin

Level III Certification: Photo Package: John Sorrel Photo 3: Rail Button Backing

Photo 4: Motor Mount Centering Ring Filet

Level III Certification: Photo Package: John Sorrel Photo 5: Foam applied to internal voids between motor mount and body tube

Photo 6: Fin alignment guide constructed by Colonel Sorrel

Level III Certification: Photo Package: John Sorrel

Photo 7: Size reference showing aft end of Eagle 1

Photo 8: Size reference showing external fin filet thickness

Level III Certification: Photo Package: John Sorrel Photo 9: Measurement Reference for aft end of Eagle 1

hoto 10: Measurement Reference for entire rocket: Natasha (daughter) holding a 8” level. Joey and Ryan (Red Rocket Team) holding an 8’ long aluminum straight dge. Thus, Eagle 1 is slightly larger then 12’.

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Level III Certification: Photo Package: John Sorrel Photo 11: Measurement Reference showing aft 36” section of booster section of Eagle 1.

Photo 12: Measurement reference showing 23” extension for booster section of Eagle 1.

Photo 13: Measurement reference showing 23” mid section of Eagle 1.

Level III Certification: Photo Package: John Sorrel Photo14: Measurement reference showing 2” section of Eagle 1 where arming switches are mounted and access to E-match wire breaks are located. After removing a switch access to the E-match break wires can be obtained. Photo 15: Measurement reference showing 42” forward section of Eagle 1. This section contains the main parachute and piston.

Photo 16: Measurement reference showing the 24” nose cone made by PML out of G10 fiberglass. The nose cone will contain the payload avionic bay caring an R-DAS computer system.

Level III Certification: Photo Package: John Sorrel Photo 17: Measurement reference showing payload avionic bay containing an R-DAS computer system for scientific data collection. Photo 18: Measurement reference showing main avionic bay with pistons attached. Not the arrangement of the three altimeters. The two altimeters located across from each other are the PML CPR 3000 on the left and Black-sky AltAcc2C located on the right. The altimeter slot located on the bottom will contain the Cajun Altimeter made by students from NHS. This altimeter will simply determine the height of apogee.

Level III Certification: Photo Package: John Sorrel Photo 19: Main avionic bay with an altimeter tube removed to expose slot cut in the side of the tube. This slot is where wires for the E-matches and Arming switches pass to the outside of the rocket. Note arming switch located on the body tube section of the avionic bay. This switch arms the CPR 3000 and when removed gives access to the E-match breaking wires. Photo 20: shows Kevlar riser made of 5/8” Kevlar tubbing. Also photo shows three 1” wide tack bars sewn to secure the loop at the end of the riser where the quick disconnect link is attached. Note the quick link is attached the bulk head of the aft section of Eagle 1.

Level III Certification: Photo Package: John Sorrel Photo 21: showing Hypertek M 1010 motor mounted in Eagle 1 via mounting hardware attached to the motor and the aft centering ring. Also, one of the red rail buttons can be seen in this photograph. Finally, this photograph also demonstrates good fin alignment. Photo 22: shows the booster section of Eagle 1 with red launch rail buttons attached. Also, the Hypertek M1010 motor is leaning against the rocket. The lower part is the oxidizer tank. Next, is the fuel bell which attaches the upper (black) motor cartridge to the oxidizer tank Finally, notice the blue vent hose running from the injection bell (fuel bell) to the rear motor mount that is attached to the aft centering ring of Eagle 1.

Level III Certification: Photo Package: John Sorrel Photo 23: showing the end of the rocket motor hanging out of the motor mount of Eagle 1. Also, notice the rail button attachment location. Finally, notice the motor mount rings and venting tube attachement. Photo 24: Natasha Sorrel running with the main parachute, which is an XXL Cert III chute that was custom designed for Eagle 1 by Skyangle.

Level III Certification: Photo Package: John Sorrel Photo 25: showing a 1.6mm styrene rod inserted into a section of brass tubing mounted through the coupler into the bulk head plate for the booster section of Eagle 1. This photo demonstrates the use of shear pins. The brass tubing is used insure the rod is cut upon ejection. The mid section of Eagle 1 will be inserted over this coupler and then the rod will be inserted through the mid section body tube into the brass tubing, thus holding the mid section and the booster section together. The extra rod length is cut flush with the outside of the mid section body tubing. Four shear pins hold the midsection to the booster section. The pins are symmetrically placed.

Photo 26: showing some of the travel team for “Operation Eagle 1holding up Eagle 1. Wow, it is big!

Level III Certification: Photo Package: John Sorrel Photo 27: Black-sky AltAcc2C Avionic Computer mounted on PML CPR System Photo 28: PML CPR 3000 Avionic Computer being inserted into avionic tube

Level III Certification: Photo Package: John Sorrel Photo 29: Colonel Sorrel installing internal fin filet joint.

Photo 30: Colonel Sorrel inspecting external fin filet application

Level III Certification: Photo Package: John Sorrel Photo 31: Packing of B2 Sky-Angle Cert III XXL Parachute into deployment bag

Photo 32: Colonel Sorrel test fitting Main Parachute