Slide 1

1 Preliminary Design Review (PDR) The University Of Michigan 2011

Slide 2

2 Vehicle: i.

Slide 3

3 Vehicle: ii. Nose Main Chute Separation Bay Main Chute Separation

Slide 4

4 Vehicle: iii. Main Chute Seperation Aviation Bay Aviation Bay Access Cut Apogee Separation Apogee Separation Bay

Slide 5

5 Vehicle: iv. Apogee Separation Motor Apogee Separation Bay

Slide 6

6 Vehicle Dimensions Body Tube 5.5 in dia. Can 2.0 in dia.

Slide 7

7 Launch Vehicle Verification Vehicle/Payload design justification Static stability analysis Materials/system justification (discussed in further detail in proceeding slides)

Slide 8

8 Vehicle Design Justification Different ideas for reducing drag Requirements Stable Fast Precise Consistent Highly variable

Slide 9

9 Vehicle Materials NoseconePolystyrene Plastic Body Blue Tube (Apogee Comp.) CansBlue Tube (Apogee Comp.) FinsG10 fiberglass

Slide 10

10 Material Justifications Phenolic Tubing Cured paper fibers Cheapest, strong, brittle Blue Tube 2.0 High-density paper More expensive, durable, dense Carbon Fiber Strands of woven carbon Most expensive, strongest, labor-intensive

Slide 11

11 Static Stability Margin 1.5 in neutral configuration pre-launch 2.4 after engine burnout Drag mechanism actuated RockSim estimated CP/CG locations On the unstable side Add mass to nose of rocket

Slide 12

12 Recovery Scheme Two Separations Apogee Drogue-less 500 Feet Main Parachute Double Redundancy Flight computer Altimeter Apogee 500 Feet

Slide 13

13 Vehicle Safety Verification Plan This matrix shows detrimental failures in red, recoverable failures in yellow, and failures with a minimal effect in green

Slide 14

14 Testing Plans Ground test proper body tube separation during E-Charge ignition Use a multimeter to measure the current the Flight Computer sends to each E- Charge during ground simulations Servo selection through torque testing on flap from collected simulation/wind tunnel data

Slide 15

15 Motor Selection Motor Manufacturer: Loki Motor Designation:L1482-SM Total Impulse:868.7 lb-s Mass pre/post burn:Pre:7.8 lb Post:3.8 lb Motor Retention System: Aero Pack RA75

Slide 16

16 Thrust-To-Weight Ratio

Slide 17

17 Rail Exit Velocity Rail Exit Velocity:??? ft/s Rail Length:6 ft

Slide 18

18 Recovery Avionics Raven Flight Computer Competition Altimeter 4 Total E-Charges 2 from Flight Computer 2 from Altimeter 1 Main Apogee Charge @ 5280 feet 1 Backup 1 Main Chute Charge @ 500 feet 1 Backup Apogee TB Main Chute TB AvBay Flight Computer Competition Altimeter 9V Batteries Positive TB

Slide 19

19 Aerodynamics-Linear Flaps: i. Flap Geometry 0% closed corresponds to the position where the flap is not exposed to air flow 100% closed corresponds to where the flap is fully extended into the flow FlapMax % Closed Flap End Geometry Can Inner Dia [in] Flap Width [in] A100Semi-Circle1.504 B100Semi-Circle2.551 C65Rectangular2.551 D75Rectangular2.5512.051

Slide 20

20 Aerodynamics-Linear Flaps: ii. Flap A Flap B

Slide 21

21 Aerodynamics-Linear Flaps: iii. Flap CFlap D

Slide 22

22 Aerodynamics-Linear Flaps: iv. Drag data from cases run at 300 m/s FlapMaximum Drag [N] A81.7235 B240.396 C204.086 D197.838 *NOTE: All flap data is for one flap and all rocket data is for half-body

Slide 23

23 Aerodynamics-Rotating Flaps: i. Moment Concerns with the y component of the force generated by the flap at various angles Analyzed at the most extreme case (largest can and flap size at 45 ) Force in the y direction caused by the flap angle deflection is negated by the force it creates on the wall of the can ComponentForce in y-direction [N] Rocket-199.8 Flap199.61 *NOTE: All data is from a simulated wind speed of 300 m/s

Slide 24

24 Aerodynamics-Rotating Flaps: ii. ANSYS Fluent CFD mesh sizes were refined in areas of interest such as the flap and the interior wall for optimal results.

Slide 25

25 Structures-Can Analysis Analyzed the worst case scenario (flaps 100% closed) Pressure forces in front of the valve are not a concern Low pressure pockets behind the valve are not a concern

Slide 26

26 Controls: i. Proportional Integral Derivative (PID) controller that will induce pressure drag as a means of regulating vehicle altitude Drag is calculated dynamically during flight Controller should respond to physical system changes in no more than 50 milliseconds and recover within 2% of the goal altitude

Slide 27

27 Controls-System Model: ii. Dynamic Apogee-Rectifying Targeting (DART) Control System Dynamic Target : Used to aid in assuring the mean energy path solution is followed Restrained Controller : Proportional Integral Derivative (PID) derived controller with physical limits Physics Plant : Simulation of vehicle-environment interaction given controller commands Instrument Uncertainty : Propagation of instrument uncertainty into system values Alt. Projection : Projection of rocket apogee altitude with same physics plant model for consistency

Slide 28

Controls Dynamic Target

Slide 29

Controls Restrained Controller

Slide 30

Controls - Physics

Slide 31

Controls Instrument Uncertainty

Slide 32

Controls Apogee Calculation

Slide 33

33 Flight Avionics Competition Altimeter Drag Computer Drag Servo 9V Batteries Drag Servo Drag Computer Competition Altimeter

Slide 34

34 Payload Design Drag Control System Actuating flaps located within side cans to control drag Control system will activate under specific altitude and/or velocity conditions

Slide 35

35 Payload Test Plan i. Flap Drag Testing Simulations/flow characterization using compressible flow in ANSYS Fluent CFD over a range of Mach numbers Test drag flap mechanism in various configurations to confirm results from simulated model Produce a function for control system relative to drag, flow speed and flap deflection

Slide 36

36 Payload Test Plan ii. Drag Flap Control System Testing 4 constants to vary (Kp, Ki, Kd, Dt) N^4 simulations for N possible different constants Parallel processing in Matlab to tackle Monte Carlo simulation NYX / FLUX supercomputers from UM Center for Advance Computing used to tune constants for best performance

Slide 37

37 Outreach Project We have contacted a teacher at a high school that has agreed to make rocketry a unit in his class. We plan to go in and teach about the basics of rocketry. We are aiming to have the students work in groups and design rockets to eventually launch in a class competition. We also plan to outreach to lower level grades and invite them to the final launch. The point is to get kids excited about rocketry. We want the entire district to participate.

Slide 38

38 Questions?