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Preliminary Design Review - BYU Rocketry - Brigham Young


									         2010-11 NASA USLI

Robb Hays, Kei Eto, Jeff Kitchen,
Manil Poudyal, Joel Shepherd,
and Sam Wood
    Jerry (Faculty Advisor)
    David (Faculty Advisor)
    Jeff (Team Leader)
Technical Personnel
    Robb (Lead Payload Designer)
    Kei (Lead Electrical Systems Designer)
    Sam (Lead Vehicle Designer)
    Joel (Propulsion Specialist)
    Manil (Weight Reduction Specialist)
    Garrett (Design Assistant)
    Roger (Design Assistant)
    Tim (TRA Mentor)
                                             TRA Mentor
                                             Tim, Level 3 TRA Certification
                                             Systems Planning and Programming
                                             P.O. Box 143600
                                             Salt Lake City, UT 84114-3600
       To design and build a rocket that will
reach an altitude of 5,280 ft AGL, deploy an
autonomous recovery system that will guide
itself to a predetermined landing zone, and be
reusable after recovery.
    38 mm mount

Motor: Cesaroni I195RL
        Component      Weight (oz)
         Nose cone            4.9
          Body tube          15.6
  Motor mount tube            3.5
     Bulkheads (4)            1.4
      Altimeters (2)          2.9
        Charge well           0.2
     Terminal strip           0.1
       Eyebolts (2)           1.4
           Autopilot          1.8
               GPS            0.9
       Battery pack             2
          Parachute           4.2
         Springs (2)          0.7
          Servos (2)          2.8
Arming switches (2)           0.4
 Centering rings (2)           1.5
    Motor retainer             1.4
  Support keels (3)            2.9
           Fins (3)             48
              Total             97
 Servo arms will control a parachute
  using the Kestrel autopilot system
  designed at BYU to a determined
  location either visually or by GPS
 A velocity profile will be mapped, much
  like a sounding rocket, using a pitot-
  probe in addition to other data gathered
  such as pressure and temperature
Potential Failure Mode                     Potential Effects of Failure                      Mitigation
Parachute lines get tangled during         Payload system fails. Rocket is unable to be      (Completed) Specific packing technique. Ground and
deployment.                                guided accurately.                                flight testing.
Parachute lines get burned during          Parachute detaches from rocket body. Ballistic    (Completed) Use of cellulose insulation and Kevlar
deployment.                                entry and injury possible. Rocket is destroyed.   parachute protector. Extensive ground testing.

Shear pins do not break.                   Parachute fails to deploy. Ballistic entry and    (Completed) Testing and proper inspection prior to
                                           injury possible. Rocket is destroyed.             launch.

Ejection charge fires early.               Stress on rocket body and parachute. Desired      (Proposed) Proper inspection and testing prior to
                                           altitude is not met.                              flight.

Ejection charge fails to fire.             Parachute fails to deploy. All effects of Mode 3. (Completed) Proper inspection and testing.

Rocket body buckles at the location of     Catastrophic damage to rocket. Rocket will not (Ongoing) Extensive test flights prior to competition.
the side-hatch during launch.              follow flight path.                            (Completed) Reinforcement of rocket body.

Fins tear off during flight.               Rocket will not follow flight path.               (Ongoing) Fin inspection and test launches.

Fins tear off during landing.              Rocket is unable to launch again in required      (Ongoing) Slower descent rate upon landing and
                                           time.                                             testing.
                                                                                             Analytical calculations of landing speed.
Rocket body buckles due to high stress     Rocket fails to be guided accurately to a         (Proposed) Use a ‘slider’ to allow main parachute to
during parachute deployment.               ground location. Payload failure.                 open slower.
                                                                                             (Completed) Reinforcement of rocket body and FEA
                                                                                             analytical calculations.
Wind velocity and target coordinates are   Rocket drifts outside of acceptable landing       (Proposed) Rocket will land (not into the wind) at the
never found.                               range.                                            preprogrammed GPS location.

Wind velocity estimated, but target        Rocket drifts outside of acceptable landing       (Proposed) Rocket will land into the wind at the
coordinates never found.                   range.                                            preprogrammed GPS location.
 Main parachute wingspan: 63 in
 Main parachute chord length (width): 23.5 in
 Expected glide angle: about 15 degrees
 Expected flight velocity: about 15 mph
  (good for overcoming headwinds of 10 mph)
 Expected descent rate: about 3.3 ft/s
 Main parachute material: Ripstop Nylon
   Kestrel Autopilot v2.1
          Combines sensor information with GPS information
           to provide position and velocity data between GPS
          Uses absolute/differential pressure to measure
           airspeed and altitude
   Virtual Cockpit v2.5
          Allow user to control settings such as map display,
           video settings, audio warnings, etc.
   Maxstream Xtend Modem
          Controls the motion of the parafoil
   9V battery
          Provides power to components
   ¼ wave dipole antennae
          Allow for a range of up to 14 miles
   Comm Box 1.1
          Communicates with ground station
          Gives location of rocket during flight
          Controls camera

Acknowledgement: Procerus (founded by BYU Almuni)
Side Deployment:
     Simple placement of
     camera that allows for
     unobstructed view during
     entire descent
     Better maneuverability
     Structural Integrity
     Less reliable deployment
               Screw               Diameters (in)               Areas (sq in)      Shear Strength (lbs)

                Size      Major        Pitch        Minor     Pitch      Minor       Min         Max

                6/32      0.138       0.1177        0.0997   0.01088    0.00781       75         114

      C * D * D * L = grams of BP Where:                       Fmax = (114 lbs)*(4 pins) = 456 lbs  12.67 psi
       C - one of the values listed below                                   C = .005 = 12.67 psi
                   0.002 = 5 psi
                  0.004 = 10 psi
                  0.006 = 15 psi
                 0.0072 = 18 psi
                   0.008 = 20 psi
         D = airframe diameter, in inches                                           D = 3 in

L = length of the cavity to be pressurized, in inches                              L = 12 in

                         grams in BP = (.024)*(3)*(3)*(12) = .54 grams

               **1-2 grams of BP should be used (FFFG)**
Date(s)           Activity
16 Oct            First Utah Rocketry Club launch
19 Nov            PDR due
8 Dec             PDR presentation
15 Jan            Scale model test launch
24 Jan            CDR due
25 Jan - 2 Feb    Manufacture full-scale launch vehicle
25 Jan - 19 Feb   Ground test autopilot and camera system
28 Jan            Book hotel rooms/flights
3-19 Feb          Test full-scale launch vehicle (without autopilot)
4-8 Feb           Educational engagement activities
8 Feb             CDR presentation (tentative)
21 Feb - 11 Apr   Test full-scale launch vehicle (with autopilot)
21 Mar            FRR due
13 Apr            Travel to Huntsville
14-15 Apr         Flight hardware and safety checks (tentative)
16 Apr            Launch Day
9 May             PLAR due
Component                                 Qty.               Price
Apogee Components PNC-3.00" Nose Cone      1     $      18.85
Apogee Components Blue Tube 75mm           1     $      26.88
Apogee Components LOC Tube 54/34           1     $       3.00
1/4" Aircraft plywood bulkheads            4     $       4.00
MAWD PerfectFlite Altimeters               2     $     170.00
Terminal Strip                             1     $       0.50
1/4" Eyebolts                              2     $       1.00
Kestrel Autopilot v2.1 (cost estimated)    1     $   3,500.00
Modem (cost estimated)                     1     $     500.00
Camera (cost estimated)                    1     $      25.00
Dipole Antenna (cost estimated)            1     $     100.00
Parachute                                  1     $     300.00
Igniters                                   2     $       2.00
1/2 teaspoon FFFg blackpowder                    $       0.25
Servos                                     2     $      70.00
Wiring                                           $       2.00
Fiberglass fins                            3     $      20.00
Battery pack                               1     $       4.00
Springs                                    2     $       1.00
Centering rings                            2     $       1.00
Motor retainer                             1     $      20.00
.32" Carbon fiber tubing                   3     $      60.00
Arming switches                            2     $       5.00
Total                                            $   4,834.48
Launch Pad Characteristics:
    Structural Steel
    8-ft launch rail
    High degree of stability
    Easy to transport

Launch System Characteristics:
    Aerotech ‘Interlock Launch Controller’
    Sufficient for small high-power rockets
     (such as ours)

                                                Apogee Components
                                               ‘Gun Turret’ high power
                                                    rocketry pad
The stability increases because of the following
   -The Center of Gravity is lower, i.e. 2 ft above
     the base of support/ground
   -The Center of gravity lies exactly at the center
     line of the base area due to the symmetric
     geometry of the launch pad
   -The launch pad has a larger base (800 in2)
   -The launch pad is heavy (30 lbs)
•Pre-launch instructions and a safety review will be given prior to each
•First aid kits are located in each facility used for rocket construction
and at each test launch.
•All team members are aware of the following regulations.
     Aviation Regulations 14 CFR, Subchapter F, Part 101, Subpart C
     NFPA 1127 “Code for High Power Rocket Motors”
     Code of Federal Regulation Part 55

•MSDS documents, pre-launch procedure, safety presentation, and
other safety documents are available to all team members and posted
on our website for quick reference (
Aerotech J90W
Velocity = 50 ft/s
Name                             Comments                                            Students

Boy Scout merit badge jamboree   Taught scouts about rocketry                            350

Boy Scout rocket launch          Helped scouts launch and recover their rockets          350

Spring Creek Elementary School   Show pictures. Have a coloring activity. Launch a        80

Centennial High School           Teach why math and science are important.               100
                                 Launch a rocket.

School for the Gifted            Bring rocket to show and tell. Launch a rocket.          150

High School Technology Fair      Man a booth about rocketry and about our                500

Total                                                                                   1530

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