Critical Design Review

Transcription

1 Critical Design Review 1/27/2017 NASA Student Launch Competition California State Polytechnic University, Pomona 3801 W Temple Ave, Pomona, CA /27/2017 California State Polytechnic University, Pomona CDR 1

2 Agenda Introduction Subscale Model Overview Final Launch Vehicle Overview Final Primary Payload Overview (RIS) Launch Vehicle Performance Final Secondary Payload Overview (FMP) Recovery Subsystem Launch Vehicle Interfaces Mission Performance Predictions Project Plan Test Plans and Procedures Probability of Success 1/27/2017 California State Polytechnic University, Pomona CDR 2

3 Introduction Introduction Subscale Model Overview Final Launch Vehicle Overview Final Primary Payload Overview (RIS) Launch Vehicle Performance Final Secondary Payload Overview (FMP) Recovery Subsystem Launch Vehicle Interfaces Mission Performance Predictions Project Plan Test Plans and Procedures Probability of Success 1/27/2017 California State Polytechnic University, Pomona CDR 3

4 Introduction 1/27/2017 California State Polytechnic University, Pomona CDR 4

5 Advisors and Mentors Dr. Donald L. Edberg Faculty advisor Professor of Aerospace Engineering Dr. Todd Coburn Structural mentor Professor of Aerospace Engineering Rick Maschek Rocketry mentor Tripoli Rocketry Association level 2 certification 1/27/2017 California State Polytechnic University, Pomona CDR 5

6 Team WBS Team lead Deputy/systems engineer Safety officer Structures sub-team Aerodynamics sub-team Avionics sub-team Support sub-team 1/27/2017 California State Polytechnic University, Pomona CDR 6

7 Task Force WBS 1/27/2017 California State Polytechnic University, Pomona CDR 7

8 Final Launch Vehicle Overview Introduction Subscale Model Overview Final Launch Vehicle Overview Final Primary Payload Overview (RIS) Launch Vehicle Performance Final Secondary Payload Overview (FMP) Recovery Subsystem Launch Vehicle Interfaces Mission Performance Predictions Project Plan Test Plans and Procedures Probability of Success 1/27/2017 California State Polytechnic University, Pomona CDR 8

9 Major Changes Since PDR Nose Cone Weight and length Coupler size Main parachute Parabolic nose cone to Elliptical nose cone Length increased from 7.3 ft. to 8.92 ft. Weight increased from 28.1 lb. to lb. Increased from 7 in. to 13.5 in. Increased from 27.4 ft 2 to 80 ft 2 Drogue Parachute Decreased from ft 2 to 5 ft 2 Avionics, Recovery Bay Redundant GPS systems in nose cone Recovery Avionics and Payload Electronics Sleds Redesigned Motor Bay Motor changed from L1150P to L1120W-O Size of motor bay slightly increased to accommodate new motor 1/27/2017 California State Polytechnic University, Pomona CDR 9

10 Final Launch Vehicle 1/27/2017 California State Polytechnic University, Pomona CDR 10

11 Final Launch Vehicle 1/27/2017 California State Polytechnic University, Pomona CDR 11

12 Final Launch Vehicle 1/27/2017 California State Polytechnic University, Pomona CDR 12

13 Final Launch Vehicle 1/27/2017 California State Polytechnic University, Pomona CDR 13

14 Final Launch Vehicle Elliptical Nose Cone: Offers highest structural Integrity compared to previous Parabolic Design Aerodynamic blunt tip design offers low Cd Housed GPS sled for tracking 3D printed using 100% fill PLA plastic GPS Sled 1/27/2017 California State Polytechnic University, Pomona CDR 14

15 Final Launch Vehicle Main Parachute Bay Drogue Parachute Bay Recovery Sub Systems: This encompasses the Main Parachute Bay, Recovery Bay, and Drogue Bay Recovery bay includes the flight altimeters Access to Outside 1/27/2017 California State Polytechnic University, Pomona CDR 15

16 Final Launch Vehicle Fragile Materials Protection Bay (FMP): Secondary payload we are testing The Pill will contain packing material for fragile object It will be suspended by surgical tubing within a custom frame within the body tube to dampen oscillations Entirely self contained, assembled outside body tube and inserted within the tube when ready for flight The Pill 1/27/2017 California State Polytechnic University, Pomona CDR 16

17 Final Launch Vehicle RIS Payload/ Observation Bay and Motor Bay: Most technically complex section of rocket Fin Integration of the rocket Including attachments Motor Integration and Retention for structural integrity RIS Payload accomplishing roll of rocket Observation system for visual confirmation of roll of rocket Observation RIS Payload Motor Integration Fin Integration 1/27/2017 California State Polytechnic University, Pomona CDR 17

18 Payload Dimensions 1/27/2017 California State Polytechnic University, Pomona CDR 18

19 Design Features Elliptical Nose Cone: Greater Structural Integrity FMP Bay: Secondary payload for more scientific data Motor Bay: Hand made carbon fiber composite motor tube Aileron: Used to create lift with varied angle of attacks Piston recovery System: Offers a more reliable parachute ejection RIS Bay: Main payload for roll induction using coupled servo design Fins: 3D printed material with actual NACA airfoil design for optimum Cd and Cl 1/27/2017 California State Polytechnic University, Pomona CDR 19

20 Final Motor Selection and Justification Performance 5148 feet simulated 92% L motor Thrust-to-weight ratio: 4.60 Rail Exit Velocity: fps Aerotech L1120W Propellant Weight Total Weight Average Thrust Peak Thrust Total Impulse Burn Time 6.08 lbm lbm lbf lbf Ns 5.01 s 1/27/2017 California State Polytechnic University, Pomona CDR 20

21 Launch Vehicle Performance Introduction Subscale Model Overview Final Launch Vehicle Overview Final Primary Payload Overview (RIS) Launch Vehicle Performance Final Secondary Payload Overview (FMP) Recovery Subsystem Launch Vehicle Interfaces Mission Performance Predictions Project Plan Test Plans and Procedures Probability of Success 1/27/2017 California State Polytechnic University, Pomona CDR 21

22 Launch Vehicle Performance Stability Analysis OpenRocket Hand Calculations Stability Margin 2.65 Calibers 3.00 Calibers Center of Gravity (from Nose Cone) in Center of Pressure (from Nose Cone) in Outer Diameter 6.16 in Total Length 107 in Apogee: 5148 Max. velocity: 574 ft/s Mach number= /27/2017 California State Polytechnic University, Pomona CDR 22

23 Launch Vehicle Mass Statement Component Mass Statement Total Mass (lbs.) Mass Margin % Module 1: Nose cone, GPS % Module 2: Main and Drogue Parachutes, Avionic Bay, FMP Module 3: Payload Bay, Observation Bay, Motor Bay % Total % After Burnout % 1/27/2017 California State Polytechnic University, Pomona CDR 23

24 Recovery Subsystem Introduction Subscale Model Overview Final Launch Vehicle Overview Final Primary Payload Overview (RIS) Launch Vehicle Performance Final Secondary Payload Overview (FMP) Recovery Subsystem Launch Vehicle Interfaces Mission Performance Predictions Project Plan Test Plans and Procedures Probability of Success 1/27/2017 California State Polytechnic University, Pomona CDR 24

25 Parachute Overview Main Parachute Drogue Parachute Toroidal Parachute 80 ft 2 effective area 400 lb paraline Manufactured by Fruity Chutes Cruciform Parachute 5 ft 2 effective area 550 lb paraline Manufactured in-house 1/27/2017 California State Polytechnic University, Pomona CDR 25

26 Parachute Sizes Main Parachute 80 ft 2 effective area 120 D o 36 oz 200 in 3 packing volume Drogue Parachute 5 ft 2 effective area 3.0 D o 3.90 oz 14 in 3 packing volume 1/27/2017 California State Polytechnic University, Pomona CDR 26

27 Recovery Harnesses Main Parachute 40 ft. length 1 Τ2 Kevlar 2200 lb. cord 1 Τ4 Steel Quicklinks at all 3 attach points Attaches to 3000 lb. swivel linking to main Mounted to rocket by 1 Τ3 Steel U-bolt Drogue Parachute 40 ft. length 1 Τ2 Kevlar 2200 lb. cord 1 Τ4 Steel Quicklinks at all 3 attach points Attaches to 1500 lb. swivel linking to drogue Mounted to rocket by 1Τ 3 Steel U-bolt 1/27/2017 California State Polytechnic University, Pomona CDR 27

28 Recovery Avionics: GPS and Altimeters Major components Primary PerfectFlite stratologgercf Secondary PerfectFlite StratologgerCF Two 1000 Mah Lipo batteries StratologgerCF Primary Secondary Deployment of drogue Deployment of Main Apogee (5280 ft) One second post Apogee 700 ft 500 ft Subscale Assembly 1/27/2017 California State Polytechnic University, Pomona CDR 28

29 Recovery Avionics: GPS and Altimeters Ejection Charges - Fore Charge: Ejects main Parachute Attached to fore Bulkhead of recovery bay - Aft Charges: Ejects drogue parachute Attached to aft bulkhead of recovery bay - Recovery Bay EMI shielded with copper foil tape 1/27/2017 California State Polytechnic University, Pomona CDR 29

30 Recovery Avionics: GPS and Altimeters Major components BRB900 Trackimo GPS Operating frequency Operating range BRB MHz 6 miles Trackimo 850/1900MHz Indefinite (Requires cell reception) BRB900 Trackimo 1/27/2017 California State Polytechnic University, Pomona CDR 30

31 Recovery Avionics: GPS and Altimeters GPS Specifications BRB mah single cell LiPo ublox 7 GPS chipset XBee pro HP S3B 900 MHz Trackimo 600 mah Li-ion battery Quad Band frequency In US 850 and 1900 MHz GPS sled fitted in nose cone 1/27/2017 California State Polytechnic University, Pomona CDR 31

32 Mission Performance Predictions Introduction Subscale Model Overview Final Launch Vehicle Overview Final Primary Payload Overview (RIS) Launch Vehicle Performance Final Secondary Payload Overview (FMP) Recovery Subsystem Launch Vehicle Interfaces Mission Performance Predictions Project Plan Test Plans and Procedures Probability of Success 1/27/2017 California State Polytechnic University, Pomona CDR 32

33 Descent Rates Post burn rocket weight is lb Main chute area is 80 ft 2 Drogue chute are is 5 ft 2 Component Max Velocity Terminal Main Velocity Terminal Drogue Velocity (ft/s) (ft/s) (ft/s) Nose Cone Forward Rocket Section Aft Rocket Section /27/2017 California State Polytechnic University, Pomona CDR 33

34 Kinetic energy at key phases of the mission Main Parachute area is 80 ft 2 75 ft-lb f Max Kinetic energy of module at touch down Component Mass Max Velocity Terminal Main Velocity Terminal Main KE Terminal Drogue Velocity Terminal Drogue KE (slugs) (ft/s) (ft/s) (ft-lb f ) (ft/s) (ft-lbf) Nose Cone Forward Rocket Section Aft Rocket Section /27/2017 California State Polytechnic University, Pomona CDR 34

35 Predicted drift from the launch pad with 5, 10, 15, 20 mph wind Wind Velocity (mph) Drift Distance (ft) Note: For the 20 mph condition Main parachute deployment at 500 ft will cause drift outside of desired zone. To keep the rocket within the 2500 ft drift limit deployment of the main has to be reduced to 325 ft. 1/27/2017 California State Polytechnic University, Pomona CDR 35

36 Test Plans and Procedures Introduction Subscale Model Overview Final Launch Vehicle Overview Final Primary Payload Overview (RIS) Launch Vehicle Performance Final Secondary Payload Overview (FMP) Recovery Subsystem Launch Vehicle Interfaces Mission Performance Predictions Project Plan Test Plans and Procedures Probability of Success 1/27/2017 California State Polytechnic University, Pomona CDR 36

37 Test Plan Matrix # Test Requirement Fulfilled Team Responsible Test Planned Status Actual Test Completed Verification Method Success Criteria Subscale Launch Full-scale Launch Drogue Parachute Test Main Parachute Test VR1.2.5, VR1.4, VR1.9, VR1.16, VR VR1.17.1, RSR2.10 VR1.1, VR1.4, VR1.17, VR1.17, RSR2.10 ALL 12/10/2016 Done 12/10/2016 ALL 2/11/2017, 2/18/2017 Not Done TBD RSR2.1 Aerodynamics 1/28/2017 Not Done TBD RSR2.1 Aerodynamics 1/28/2017 Not Done TBD The launch of the subscale rocket is a holistic overview of procedures. The subscale launch was intended to be a halfscaled model of the full-scale launch vehicle and was designed as such. To that effect, the launch of the subscale is primarily intended as a proof of concept for the stability margin of the full-scale design. The team will run through the entire launch procedure and analyze the resulting data to determine what changes must be made, if any, to the full-scale launch vehicle prior to the competition Attach a 5lb weight to the parachute and view performance of parachute and take measurements Attach a 10lb weight to the parachute and view performance of parachute and take measurements (1) After launch, the launch will be recoverable and reusable (2) Subscale launch successful (3) On-board altimeter capable of recording peak altitude (4) recovery system functions as designed (1) Launch vehicle reaches an apogee of 5,280 ft. 75 ft (2) Launch vehicle is recoverable and usable after launch. (3) Full scale test launch occurs prior to FRR. (4) Recovery system functions as designed. (1) Inflation of Drogue (2) Matching estimated drop test specimen descent time (1) Inflation of Drogue (2) Matching estimated drop test specimen descent time 1/27/2017 California State Polytechnic University, Pomona CDR 37

38 Test Plan Matrix Continued 5 Test Ejection Charge Test Requirement Fulfilled Team Responsible Test Planned Status Actual Test Completed RSR2.2 Avionics 1/29/2017 Not Done TBD Verification Method Success Criteria (1) The sections separate with enough energy to break shear pins and pull the entire length of the Ejection charge is sufficient to deploy shock cord taunt (2) The body tube does not rip or the recovery system tear near shear pin interface or bulkhead screw interface (3) Parachute and shock cord undamaged from ejection charge hot gasses Recovery Avionics VR1.3, RSR2.12 Avionics 1/29/2017 Not Done TBD RIS Test: Wind Tunnel FMP Test Body Tube Materials Properties Test for Crippling ER3.3.1, ER , ER , DR1.0ALL ER3.4.1, ER , ER , ER RIS 2/4/2017 Not Done TBD FMP 2/4/2017 Not Done TBD DR4.1 Structures 1/21/2017 Not Done TBD Recovery shielding must be capable to blocking radio frequency transmissions Measure the side force and moments experienced by the RIS at a zero-degree deflection then at a deflected position (1) Radio frequency signals substantially reduced within the recovery bay (1) Accurate data for Normal force, pitching moment, yawing moment, rolling moment, drag is collected at different speeds and angles of attach (2) Flow conditions are matched to subscale wind tunnel testing Drop fragile material system from (1) Fragile material unbroken (2) Fragile material height of 68 ft. to mimic max impulse system re-usable experienced during rocket flight. (1) The body tube will experience absolutely no (1) Static Load Test: load applied to localized crippling (2) The body tube will maintain continuous section of a body tube (2) its structural integrity with no permanent Dynamics Drop Test: simulate same deformations to the material (3) Fastener bulkhead impulse during launch on body attachment point holes located on body tube will section show no signs of tearing, ripping, or shearing at these specified locations 1/27/2017 California State Polytechnic University, Pomona CDR 38

39 Test Plan Matrix Continued Test Bulkhead Shear and Shear Tear- Out Test Requirement Fulfilled Team Responsible Test Planned Status Actual Test Completed DR4.2 Structures 1/21/2017 Not Done TBD PLA Shear Test DR4.3 Structures 1/21/2017 Not Done TBD Water Tunnel Test Wind Tunnel Test DR4.4 Aerodynamics 1/25/2017 Not Done TBD DR4.5 Aerodynamics 1/23/2017 Not Done TBD GPS Test DR5.3 Avionics 1/28/2017 Not Done TBD Verification Method (1) Static Load Test: load applied to bulkhead (2) Dynamics Drop Test: simulate same impulse during launch on bulkhead Success Criteria (1) The bulkhead will experience no shearing at fastener locations (2) The bulkhead will maintain its structural integrity, meaning the material the bulkhead is made from will not show any sign of damage or material degradation (3) Fastener bulkhead attachment point holes will show no signs of yielding due to bearing stress thus deforming the area around the fastener verify the impulse force caused by (1) The PLA will experience no shearing at the fastener the main parachute does not cause locations (2) The PLA will maintain its structural integrity, with the screws to shear through the no permanent deformation or any signs of damage to the nosecone during midflight material Full scale test models of nose cone and fins will be placed in water tunnel Compare theoretical data calculated for the full-scale rocket with experimental data from wind tunnel; forces, moments, and drag are reasonable Run the GPS and see if it performs properly, determining the accuracy of the coordinates and proper transmission (1) Tests show flow is turbulent as is expected (2) No separation occurs during the simulated flight envelope (3) No vortices or other disturbances form on the rocket that degrade performance (4) Clear and useable data can be drawn from the tests (1) Useable data is recovered from the testing (2) Data from the test matches with models and known results (1) Both systems still transmit properly when placed next to one another (2) Both of the transmitted coordinates received are similar to each other. 1/27/2017 California State Polytechnic University, Pomona CDR 39

40 Test Plan Matrix Continued Test Observation Subsystem Test Arduino MEGA 2560 Test Requirement Fulfilled Team Responsible Test Planned Status Actual Test Completed ER6.1.2, DR5.2 Avionics 1/28/2017 Not Done TBD DR5.5 Avionics 1/28/2017 Not Done TBD 10 DOF Test DR5.1 Avionics 1/28/2017 Not Done TBD Verification Method Recording for 20 minutes, extract the video and watch to verify camera record video. Follow same steps but place the camera in the rocket at an angle to view downwards After circuit and code baseline functionality established, system will be attached to the rotation table at a measured radius. Data points will be taken at (1) Constant angular velocities (2) Changing angular velocities (angular acceleration) After circuit and code baseline functionality established, system will be attached to the rotation table at a measured radius. Data points will be taken at (1) Constant angular velocities (2) Changing angular velocities (angular acceleration) Success Criteria (1) Clear video recorded (2) Video recorded for full duration (1) MEGA outputs viable data at 10 samples per second (2) 10 DOF acceleration/gyroscope data matches specifications within 5% (3) Rotation table angular velocity (4) Rotation table angular acceleration (1) MEGA outputs viable data at 10 samples per second (2) 10 DOF acceleration/gyroscope data matches specifications within 5% (3) Rotation table angular velocity (4) Rotation table angular acceleration 18 Xbee Pro 900HP Test DR5.4 Avionics 1/28/2017 Not Done TBD A 2 mile distance test for data transmission The Xbee transmitting data at over 2 miles 1/27/2017 California State Polytechnic University, Pomona CDR 40

41 Safety Plan Personal Hazards Hazard Cause Effect Pre Mitigation RAC Personnel injury when working with chemicals Chemical spill/splash Exposure to chemical fumes Skin, eye, and lung irritation Mild to serve skin burns Lung damage or asthma 3C Medium Mitigation Post - Risk MSDS will be readily available in all labs at all times. They will be reviewed prior to working with any chemicals Gloves and safety glasses will be worn when handling hazardous chemicals All personnel will be familiar with locations of safety equipment including chemical showers and eye wash stations 4C Minimal 1/27/2017 California State Polytechnic University, Pomona CDR 41

42 Safety Plan Launch Vehicle Failure Modes and Effects Analysis Hazard Cause Effect Pre Mitigation RAC Rocket is pitched in an unwanted direction Aileron rotating in the same direction Personnel Hazard Potential hazard to surrounding property 2B High Mitigation Number of actuated ailerons reduced from four to two Ailerons mechanically constrained to only induce roll Post Mitigation 2E Low Divergent oscillation around roll axis Payload control system malfunction Ground hazard Personnel Hazard Loss of rocket 2B High Open loop control system Autonomous control 2E Low 1/27/2017 California State Polytechnic University, Pomona CDR 42

43 Safety Plan From Environment: To Environment: Environmental Hazards Hazard Cause Effect Pre Mitigation RAC Blue Tube Warping Moisture Absorption Heat PLA Warping Heat Part Deformation Mitigation Post Mitigation Swelling 3C - Medium Avoid rainy weather Avoid transonic velocities 2D - Medium Avoid surrounding heat source Avoid transonic velocities 4D - Minimal 4E - Minimal Wood Moisture Swelling 3D - Low Avoid rainy weather 4E - Warping Absorption Minimal Hazard Cause Effect Pre Mitigation RAC Mitigation Post Mitigation Ammonium Storage 2E - Low Perchlorate Malpractice Hydrochloric Acid Motor byproduct Contamination Wildlife development retardation Corrosion Toxicities in wildlife 2B - High Store in designated box Avoid unnecessary transportation and contact 2B - High Test in desolate areas 2E - Low 1/27/2017 California State Polytechnic University, Pomona CDR 43

44 Subscale Model Overview Introduction Subscale Model Overview Final Launch Vehicle Overview Final Primary Payload Overview (RIS) Launch Vehicle Performance Final Secondary Payload Overview (FMP) Recovery Subsystem Launch Vehicle Interfaces Mission Performance Predictions Project Plan Test Plans and Procedures Probability of Success 1/27/2017 California State Polytechnic University, Pomona CDR 44

45 Subscale Launch Vehicle Scaling Diameter of Subscale was created to be ½ scale Subscale had a larger stability margin, but is still within the same range and greater than 2.0 Lengths were not scaled Velocity values were not scaled either Acceleration values were higher to try to simulate larger loads on the rocket Scale Diameter Stability Margin Length Velocity Acceleration Subscale ft/s 11.3 (g) Full Scale ft/s 6.40 (g) 1/27/2017 California State Polytechnic University, Pomona CDR 45

46 Subscale Flight Test Results All flight test data came from altimeter Apogee 3122 ft Velocity profile came from altitude data, but extrapolated acceleration data was too noisy Velocity profile is a little noisy, but a curve fit helps get a better idea of the velocity profile Max Velocity about 460 ft/s 1/27/2017 California State Polytechnic University, Pomona CDR 46

47 Predicted Flight vs True The predicted model for subscale performance is based on data obtained from open rocket The Matlab predictions are based upon an average thrust approximation for the J460 engine used The actual flight data is based on the position and time data collected from the Strattologger CF, velocity was then calculated The velocity data was very noisy so a curve fit can seen in red for better approximation 1/27/2017 California State Polytechnic University, Pomona CDR 47

48 Predicted Flight vs True 1/27/2017 California State Polytechnic University, Pomona CDR 48

49 Predicted Flight vs Actual Flight 1/27/2017 California State Polytechnic University, Pomona CDR 49

50 Predicted Flight vs True Drogue Video Descent Time 36 s Drogue Predicted Descent Time 38 s Main Video Descent Time 29 s Main Predicted Descent Tine 26 s Error 5.26 % Error % 1/27/2017 California State Polytechnic University, Pomona CDR 50

51 Drag Coefficient Models Sub-Scale Full-Scale Open Rocket Excel % Error Matlab % Error /27/2017 California State Polytechnic University, Pomona CDR 51

52 Lessons Learned All models assume vertical flight and don t account for disturbances or weather cocking The Cd obtained from the subscale launch is higher from than the predicted models due the weather cocking experienced by the subscale The discrepancy shows that simplistic models are good for initial estimates but ultimately wind tunnel testing and CFD analysis are needed for accurate calculations 1/27/2017 California State Polytechnic University, Pomona CDR 52

53 Lessons Learned Continued Hand calculations are a necessity the teams initial open rocket model underestimated the height achieved, this was later corrected Pointed nose cones do not handle impacts well as a result the design was changed to a blunter elliptical Coupler size will be increased to reduce bending moments PLA plastic performed well and exceeded durability expectations Better planning for screw locations for body 1/27/2017 California State Polytechnic University, Pomona CDR 53

54 Final Primary Payload Overview (RIS) Introduction Subscale Model Overview Final Launch Vehicle Overview Final Primary Payload Overview (RIS) Launch Vehicle Performance Final Secondary Payload Overview (FMP) Recovery Subsystem Launch Vehicle Interfaces Mission Performance Predictions Project Plan Test Plans and Procedures Probability of Success 1/27/2017 California State Polytechnic University, Pomona CDR 54

55 Final Design: RIS-B Minimizes mass burden on the vehicle by taking advantage of the low altitude flight profile of our mission Challenging servo-mechanical design and execution; yet within our capabilities Design features mitigate chances of erratic trajectories 1/27/2017 California State Polytechnic University, Pomona CDR 55

56 Final Design: RIS Overall Design Features: Pull-pull servo configuration utilizing stranded steel cables Single set of actuating ailerons; ±24 deflection range Two physically coupled servos 1/27/2017 California State Polytechnic University, Pomona CDR 56

57 Servo Block Assembly: Design Features Servos receive the same electrical signal Configuration constrains ailerons to counter-rotating motion (2) HS-7955TG Servos: operational redundancy and double effective torque Pulleys provide cable redirection and allow lateral movement 1/27/2017 California State Polytechnic University, Pomona CDR 57

58 1/27/

59 Hitec HS-7955TG Servos 1/27/2017 Specifications Motor Type: Coreless Bearing Type: Dual Ball Bearing Speed (4.8V/6.0V): 0.19 / 0.15 Torque oz-in. (4.8V/6.0V): 250 / 333 Torque lbf-in. (4.8V/6.0V): 15.6 / 20.8 Weight ounces: 2.29 Weight grams: Justification Aileron Area 8 in 2 Max. Airspeed 750 ft/s Max. Deflection 25 Torque Needed 220 oz-in (13.8 lbf-in) 59

60 Aileron Assembly 1/27/2017 California State Polytechnic University, Pomona CDR 60

61 Torque Needed Using τ = Iα Method Moment of Inertia Value (lb m *ft 2 ) I = mr 2, r = 3.0 in 2.6 I = mr 2, r = 3.5 in 3.6 OpenRocket 3.7 Assumed Value 4.0 θ = ω 0 t αt2 θ = 4π; ω 0 = 0; t = 5s, α = 1.0 rad s 2 τ = 4.0 lb f ft 1/27/2017 California State Polytechnic University, Pomona CDR 61

62 Lift Provided by Aileron d = r bdy + d l d = 0.5 ft L = F = τ d 0-5s post-burnout V avg = 425 ft/s L = 8 lb f 1/27/2017 California State Polytechnic University, Pomona CDR 62

63 Payload Bay Electronic Systems 1/27/2017 California State Polytechnic University, Pomona CDR 63

64 PBE Block Diagram Overview 1/27/2017 California State Polytechnic University, Pomona CDR 64

65 Payload Control System (PCS) Small and efficient open-loop servo control 70+ Hz sampling rate Offloads data points to DCS LIS331HH Accelerometer Operating Voltage V Current Consumption < 0.25 ma (normal mode) Detection Range ±6g/±12g/±24g Data Output 16 bit Survivability 10,000g shock resistance (for 0.1ms) Operating -40 C to 85 C Temperature Range 1/27/2017 California State Polytechnic University, Pomona CDR 65

66 Payload Control System Schematic 1/27/2017 California State Polytechnic University, Pomona CDR 66

67 Data Collection System 1/27/2017 California State Polytechnic University, Pomona CDR 67

68 Observation System: Raspberry Pi Zero 1/27/2017 California State Polytechnic University, Pomona CDR 68

69 60W Power Switch; Power Consumption Expected System Power Consumption Table (Battery #1) System Microprocessor Expected Current Draw Payload Control System (PCS) Data Collection System (DCS) Observation System (OS) Arduino Nano v3.0 Arduino Mega R Raspberry Pi Zero v ma ma ma 1/27/ California State Polytechnic University, Pomona CDR

70 Payload Integration Aileron Section attachment to axle Fin with Airfoil design and aileron section cut out Integration of aileron section with fin Servo Arm used for actuation 1/27/2017 California State Polytechnic University, Pomona CDR 70

71 Payload Integration Lubricated joints will offer low friction for maneuver Aileron has the ability to turn up to plus or minus 24 degrees 1/27/2017 California State Polytechnic University, Pomona CDR 71

72 Payload Integration Cut away segments for cabling Fin section integrates with bulkheads 1 through 4 Hose clamp holds the fins in place and allows easy removal 1/27/2017 California State Polytechnic University, Pomona CDR 72

73 Payload Integration Mounting attachment for sled, allowing sled to be removable Sled Integration for RIS Electronics (not shown here) 1/27/2017 California State Polytechnic University, Pomona CDR 73

74 Payload Integration Mounting occurs on the top end of the motor block bulkhead Mounting attachment for servos pulleys and cable attachment Note: More detailed Drawings of system present in previous sections 1/27/2017 California State Polytechnic University, Pomona CDR 74

75 Payload Dimensions and Mass Statement Items Purpose Number of items Mass (oz) HS-7955TG Servo Servos for Roll Induction System Mounting Hardware Servo cabling, mounting hardware V, 2200mAh LiPo Payload Bay power supplies Arduino Micro Controls Roll Induction System Arduino MEGA 2560 Controls Data Collection System Adafruit 10 DOF IMU DCS sensor XBee Pro 900HP DCS transmitter High Gain Antenna For XBee (adds 15mi+ range) XBee Adapter For XBee SD Breakout + Card DCS local data storage Raspberry Pi Zero v1.3 Controls Observation System Pi Camera v2 Camera for Observation System Switch Switch for entire payload system Items Mass (oz) Electronics associated with Payload and Observation RMS-75/5120 Casing w/ forward seal disk mm aft closure mm Forward Closure Aeropack 75 mm Retainer Motor Motor Bay + RIS/Obs Bays + Fins Total Misc. mounting hardware - Approx /27/2017 California State Polytechnic University, Pomona CDR 75

76 Primary Payload Test Plans Objective: Develop Cl vs AoA relationship for aileron Low speed wind tunnel tests; scale up results Objective: Verify strength and determine proper diameter of stranded steel cabling Stress, tension tests Objective: Ensure proper detection of motor burnout Accelerometer and various scenario testing 1/27/2017 California State Polytechnic University, Pomona CDR 76

77 Final Secondary Payload Overview (FMP) Introduction Subscale Model Overview Final Launch Vehicle Overview Final Primary Payload Overview (RIS) Launch Vehicle Performance Final Secondary Payload Overview (FMP) Recovery Subsystem Launch Vehicle Interfaces Mission Performance Predictions Project Plan Test Plans and Procedures Probability of Success 1/27/2017 California State Polytechnic University, Pomona CDR 77

78 Final Secondary Payload Overview 3D Printed Plastic Container; Pill Filled with foam Suspended in surgical tubing net Secured to removable bulkhead 78

79 Payload Design Changes from PDR Central ring changed to separate into two pieces for easy removal of pill. Number of surgical tubes from 24 to 10. Coupler enlarged to 12 allowing for more room. Frame Design Steel instead of plywood Two beams instead of four 79

80 Payload Integration Steel U-shaped frame attached to removable bulkhead Bulkhead attached to body tube with bolts Tied to an eye-bolt, surgical tubing will suspend the pill which holds fragile material 80

81 FMP Operations Summary Final design allows for: Lightweight structure that doesn t compromise the strength. Simple integration of pill and collar. Maintains easy access to pill and frame. Increase in size of coupler allows for more room for vertical deflection Dimensions Total Bay length - 12 Total weight - 2 lbs Width of Pill - 4 Height of Pill

82 Launch Vehicle Interfaces Introduction Subscale Model Overview Final Launch Vehicle Overview Final Primary Payload Overview (RIS) Launch Vehicle Performance Final Secondary Payload Overview (FMP) Recovery Subsystem Launch Vehicle Interfaces Mission Performance Predictions Project Plan Test Plans and Procedures Probability of Success 1/27/2017 California State Polytechnic University, Pomona CDR 82

83 Internal Interfaces with Launch Vehicle GPS System Parachute Charges GPS System Self-Enclosed System of GPS/Battery No interface Parachute Charges Recovery Bay Payload Bay Pulley System Ailerons No interface No interface No interface No interface No interface Set of dual charges for main/drogue Recovery Bay No interface Ignites the parachute charges Ignites the parachute charges Altimeter/ Charge Igniter No interface No interface No interface No interface No interface No interface Payload Bay No interface No interface No interface PCS/DCS/OS Controls the pulley system Pulley System No interface No interface No interface Controls the pulley system Cable system to control ailerons Controls the ailerons Controls the ailerons Ailerons No interface No interface No interface Controls the Controls the Two actuating 1/27/2017 California State Polytechnic University, Pomona ailerons CDR ailerons ailerons83

84 External Interfaces with Launch Vehicle Ailerons Generate C L and rotate rocket post burnout and interfaces with RIS Payload Launch Lug Connects launch rail to launch lug Launch Rail Slides over the launch lug to guide rocket Igniter Interfaces with motor to initiate launch Rotary Key Interfaces with recovery avionics 12 V Battery Interfaces with igniter for direct launch 1/27/2017 California State Polytechnic University, Pomona CDR 84

85 Project Plan Introduction Subscale Model Overview Final Launch Vehicle Overview Final Primary Payload Overview (RIS) Launch Vehicle Performance Final Secondary Payload Overview (FMP) Recovery Subsystem Launch Vehicle Interfaces Mission Performance Predictions Project Plan Test Plans and Procedures Probability of Success 1/27/2017 California State Polytechnic University, Pomona CDR 85

86 Educational Engagement Charter Oaks Elementary ipoly High School Country Springs Elementary Tustin High School Almondale Elementary 1/27/

87 Requirements Status Requirement Verified In Progress Not Verified Vehicle Recovery System Experiment Safety General Derived /27/2017 California State Polytechnic University, Pomona CDR 87

88 Timeline 1/27/2017 California State Polytechnic University, Pomona CDR 88

89 Timeline Continued Current Team Focused Milestones 1/27/2017 California State Polytechnic University, Pomona CDR 89

90 Timeline Continued 1/27/2017 California State Polytechnic University, Pomona CDR 90

91 Probability of Success Introduction Subscale Model Overview Final Launch Vehicle Overview Final Primary Payload Overview (RIS) Launch Vehicle Performance Final Secondary Payload Overview (FMP) Recovery Subsystem Launch Vehicle Interfaces Mission Performance Predictions Project Plan Test Plans and Procedures Probability of Success 1/27/2017 California State Polytechnic University, Pomona CDR 91

92 Probability of Success Leading Design Subscale Manufacturing Testing Subscale Launch Evaluation Final Design 1/27/2017 California State Polytechnic University, Pomona CDR 92

93 CPP NSL Team CDR Presentation Thank You! Questions? 1/27/2017 California State Polytechnic University, Pomona CDR 93