Nosecone Pitot payload

1
Saint Andrews Orion Project II 2008 Student
Launch Initiative
Our Rocket will dominate the skies over
Huntsville while our Payload hunts for valuable
data to gather for our experiments.
Flight Readiness Review March 24, 2008
Robotic Deployment Recovery-Search Locate
Mother Ship Surface Sample Analysis-Pitot-Tube
Air Speed Factors
Video Study of Vehicle Stability Flight
Profile Pitot Readings for Velocity and Air
Speed 1st test flight, 5216, 3/9/08!
Contact LT. Leonard Johnson- Project Team
Leader PH [phone] E-mail
firebrick720_at_yahoo.com
2
Rocket Flight Stability

• Via Rocksim, the new data has been uploaded and
  tested.
• Rocksim simulations have been run, verifying our
  rockets flight worthiness.
• Test flight on 3/9/08 positively confirmed
  stability.

3
CG-CP
4
Rail Exit Velocity

• Rocksim analysis, 6 Diam, 40 lbs loaded with
  L1300, 10 rail
• Rail Departure Velocity35 ft/sec
• Minimum velocity for Stable flight46ft/sec

5
Rocket Specifications and Performance

• Total length of vehicle10ft, 9in
• Diameter of vehicle airframe.6in
• Liftoff Mass fully loaded.45lbs, 10oz.
• Vehicle stability positive two caliber (airframe
  diameter) Separation between CG and CP (center of
  gravity and center of pressure)
• Thrust to weight ratio..6.48 1
• Liftoff velocity off launch rail..35
  ft/sec
• Maximum velocity during flight..700ft/sec
• Time to Apogee (peak altitude).20.5 sec
• Drogue chute descent Velocity.76f
  t/sec
• Main parachute deployment at ...800ft AGL
  (above ground level)
• Descent velocity rate on main chute...19.8ft/s
  ec
• G-Forces experienced by rocket and
  payloads...5.86Gs
• Maximum Altitude achieved at apogee.5,216ft
  AGL
• NASA required an apogee of.5,280ft AGL
• Pitot Cruiser RDV was 64ft off the NASA required
  target altitude.

6
Motor specifications and performance

• Motor used L1300 APCPR
• L Total Impulse in Newton-seconds
• 1300 Average Thrust in Newtons
• 4.45 Newtons 1 pound of thrust
• Our motor has an average thrust of 292 pounds
• APCP Ammonium perchlorate composite propellant
  same fuel and oxidizer used on the Space
  Shuttle Solid Rocket Boosters (SRBs)
• R Reloadable motor (motor case can be reused
  again)
• Manufacturer Aerotech
• Propellant mass 2,632g 5.8lbs
• Total Impulse rating 4,567 Newton-seconds
• Total Impulse is proportional to the total energy
  released by the propellant in a propulsion system
• Motor dimensions 98mm diameter x 443mm length
  (3.9in diameter x 17.4in length
• Burn time 3.5 seconds
• Burn time is calculated by dividing the Total
  Impulse by the average thrust ratings L5120
  Newton-seconds
• Thrust to weight ratio 50 1

7
Parachute Sizes and Descent Rate

• Five parachutes
• 1- 36 drogue chute
• 78.3ft./sec. descent rate
• 1- 45 nose cone chute
• 19.8ft./sec. descent rate
• 1- 45 capsule chute
• 19.8ft./sec. descent rate
• 1- 120 main chute
• 20.8ft./sec. descent rate
• 1- 12 safety chute for Mission Cdr. Gumby
• 28.6ft./sec. descent rate

Rocket Hunter frequency is 219.719 MHz
8
Test Plans and Procedures

• Robot Pilots practicing control via radio/video
  link
• Pitot tube 220MPH leafblower test done
• BP ejection test done
• CO2 ejection test done
• Flight video successful integration into
  nosecone!
• 1st test flight successful!

9
Scale Model Flight Test

• ½ Scale model flew successfully, with Video!
• 1st Pitotcruiser RDV flight 3/9/08
• Internal video camera running during flight.

10
Dual Deployment of Avionics Test

• Dual Avionics Payload
• Aft Black Powder 3g
• Fore Carbon Dioxide (for low temperature,
  noncorrosive gasses on robot. 38g x 2)
• Dual, redundant altimeters for maximum flight
  safety.
• Worked perfect, 3/9/08!

11
Ejection Charge Amount Test-CO2

• Forward Section Ejection, 38 gram cartridges, x2
• Components of CO2-Rouse-Tech, has been test fired
  twice.
• Successfully ejected main at 800 on 3/9/08!!!

12
Ejection Charge Amount Test-BP

• Aft Section Black Powder Ejection Charge section.
• Successfully (static) tested 2/08.
• Successfully ejected at apogee, 5216, on
  3/9/08!!!

13
Nosecone Pitot/Video payload

• Circuit integrated fully into nosecone
• ½ Plywood Flange epoxied screwed in nosecone
• 5 bolts hold bulkhead to flange
• Offset center for ease of reaching switches
• Camera below pitot electronics.

14
Nosecone Pitot circuit

• Same circuit as last year
• Tube to Hose to Sensor to Data Logger
• Data downloaded to Laptop PC, Excel
• Calibration via 220MPH blower

15
Mission Commander

• Team Orion is honored to have a passenger!
• Gumbys safety is mission critical
• Will have backpack parachute for safety
• Moved to shock cord just forward of main chute.
• A stunt-double Gumby flew and was recovered
  unharmed on 3/9/08!

16
Altimeter Payload Bay

• All fiberglass for maximum strength
• Double-thickness bulkplates
• 2 x ¼ threaded rods hold it together
• Two redundant altimeters (Missile Works and
  Ozark)

17
Altimeter Bay Main Deployment

• Black powder for aft deployment, redundant,
  cartridges bolt to aft bulk plate
• CO2 for foreward deployment, redundant, Rouse
  Tech., bolted to fore bulk plate
• Pyrodex combustion forces piston pin into CO2
  cartridge

18
SRV-1Robot- Scorpio Capsule

• First basic design of capsule
• First modified design of Capsule
• Final design of Capsule in airframe
• Successfully ejected from airframe by CO2 2/08.
• Prototype successfully ejected at 800 on 3/9/08

19
Payload Assembly

• All components of the capsule
• Robots G force frame support

20
Payload Integration Readiness

• Capsule locked inside airframe
• Operation of the door

21
Conclusion

• Orion has 1 successful flight completed, 5216,
  on 3/9/08.
• Orion is ready for Huntsville!