1. Adjunct Missile Seeker Deployment Mechanism Design Review

2. Adjunct Missile Seeker Deployment Mechanism 2 RF2IR Team Members Ryan Moore –Mechanical Engineering Scott Nielsen –Optical Sciences Karl Heiman –Aerospace Engineering Philip Pierson –Optical Sciences David Kraemer –Electrical Engineering Thomas Jefferson –Material Sciences Brian Perona –Raytheon Missile Systems –Project Sponsor Dr. Larry Sobel –AME Department –Faculty Advisor Charles Hodges –Project Mentor

3. Adjunct Missile Seeker Deployment Mechanism 3 Outline Introduction Requirements Design Overview Trade Studies Software Subsystem Design Interfaces Analysis Requirements Review

4. Adjunct Missile Seeker Deployment Mechanism 4 Project Overview Raytheon Missile Systems –Designs, develops, and produces critical missile systems for national defense Project motivation –Enable a missile to utilize long range strike capability of radar frequency (RF) guided systems with the precision of infrared (IR) guided systems with little drag penalty

5. Adjunct Missile Seeker Deployment Mechanism 5 Concept of Operation The IR seeker will only be deployed during the terminal phase of flight

6. Adjunct Missile Seeker Deployment Mechanism 6 Project Statement Design an adjunct seeker deployment mechanism (ASDM) –Mechanism will be deployed on a proven missile design –Seeker will deploy during the terminal flight phase –Design shall minimize impacts to existing system

7. Adjunct Missile Seeker Deployment Mechanism 7 Requirements System must adhere to these specific requirements. –Physical Properties –Dome Properties –Environmental Concerns –Electrical Constraints –Performance

8. Adjunct Missile Seeker Deployment Mechanism 8 Major Design Constraints

9. Adjunct Missile Seeker Deployment Mechanism 9 Design Overview Our mechanism will be located near the front of the missile and fit into the allotted space specified by the customer.

10. Adjunct Missile Seeker Deployment Mechanism 10 Design Overview (cont) Our design is a spring driven slide rail system

11. Adjunct Missile Seeker Deployment Mechanism 11 Subsystems Assembly: Seeker deployment mechanism –Three Main Subsystems Door Mechanism Deployment Mechanism Electronics

12. Adjunct Missile Seeker Deployment Mechanism 12 Door Mechanism Shape and size of door

13. Adjunct Missile Seeker Deployment Mechanism 13 Door Mechanism

14. Adjunct Missile Seeker Deployment Mechanism 14 Deployment Mechanism Components Deployment Mechanism Components Driving Spring Dampener

15. Adjunct Missile Seeker Deployment Mechanism 15 Slide Track Slider Deployment Mechanism Components Deployment Mechanism Components Mounting Bracket

16. Adjunct Missile Seeker Deployment Mechanism 16 Mechanism Assembly Allotted space for design

17. Adjunct Missile Seeker Deployment Mechanism 17 Mechanism Assembly Sliding rail

18. Adjunct Missile Seeker Deployment Mechanism 18 Mechanism Assembly Slider

19. Adjunct Missile Seeker Deployment Mechanism 19 Mechanism Assembly Seeker mounted to slider

20. Adjunct Missile Seeker Deployment Mechanism 20 Mechanism Assembly Brace for spring and dampener

21. Adjunct Missile Seeker Deployment Mechanism 21 Mechanism Assembly Damping unit

22. Adjunct Missile Seeker Deployment Mechanism 22 Mechanism Assembly Spring Driver

23. Adjunct Missile Seeker Deployment Mechanism 23 Deployed State

24. Adjunct Missile Seeker Deployment Mechanism 24 Trade Studies The following trade studies were completed to achieve this design –Structural Materials –Dome Materials –Door Mechanism –Electrical Sensor Types –Drive/Actuation Devices

25. Adjunct Missile Seeker Deployment Mechanism 25 Trade Studies (Cont.) Following slides present an example of the decision matrix used and the results of the various trade studies Finer details are available during the questioning session

26. Adjunct Missile Seeker Deployment Mechanism 26 Structural Materials Chosen material: Ti 6Al-4V –Based on availability and decision matrix ranking

27. Adjunct Missile Seeker Deployment Mechanism 27 Trade Studies Results Dome Material –Sapphire Door Mechanism –Torsion spring ejection Electrical Sensors –Microcontroller: TI MSP430F167 –Position sensor: Honeywell SS46 –Temperature sensor: TI TMP123 Drive Actuation –Linear spring with damper

28. Adjunct Missile Seeker Deployment Mechanism 28 Software Subsystem Design Software Modules –Primary Deployment Module (PDM) Manages deployment sequence and error procedures, sends seeker deployment complete to circuit cards (120 Lines of code) –Temperature Sensor Module (TSM) Reads missile temperature to load calibration data (40 Lines) –Door Actuation Module (DAM) Manages door deployment sequence and indicate (80 Lines) –Seeker Actuation Module (SAM) Manages seeker deployment sequence and indicate (80 Lines)

29. Adjunct Missile Seeker Deployment Mechanism 29 Software Flow Diagram

30. Adjunct Missile Seeker Deployment Mechanism 30 Interfaces Physical Interfaces –Seeker Analog and Digital Connectors –Sensor connections to microcontroller (μC) Software Interfaces –Variables passed from TSM, DAM, and SAM to PDM Temperature, Door_Eject_Ind, Seeker_Index_Ind –Stored calibration data passed to μC

31. Adjunct Missile Seeker Deployment Mechanism 31 Design Space Anaysis Tin cans, a cardboard tube, and a wood block were modified to approximate the final system Seeker 1 Seeker 2 Seeker 3

32. Adjunct Missile Seeker Deployment Mechanism 32 Aerodynamic Analysis Flow properties at pt. 1 are given by Raytheon Flow properties at pt. 2 are determined using shock tables Results flow into dome analysis and force analysis 1 2

33. Adjunct Missile Seeker Deployment Mechanism 33 Optical Analysis An analysis will be done to determine the amount of defocus provided by the additional dome This defocus must be within the limits of the provided seeker

34. Adjunct Missile Seeker Deployment Mechanism 34 Force Analysis System input: –Aerodynamic forces –Frictional constants System outputs: –Required structural stresses –Actuation force –Clamping force Seeker F aero,x F aero,y F actuation F friction M structure

35. Adjunct Missile Seeker Deployment Mechanism 35 Internal Structural Analysis Finite element computer modeling is used to ensure assemblies will support loading requirements Goal: Factor of Safety > 1.5

36. Adjunct Missile Seeker Deployment Mechanism 36 Requirements Review

37. Adjunct Missile Seeker Deployment Mechanism 37 Risk Mitigation Weight –Parametric design using removal of material while maintaining structural integrity –Possibly using chassis design of another team to save weight –If necessary use higher cost materials with higher specific strength

38. Adjunct Missile Seeker Deployment Mechanism 38 Risk Mitigation Deployment Shock –Addition of dampeners Damping materials Dashpot Eddy current dampener –Additional EM field issues –Shock isolator Increases deployment time –Optimize spring coefficient

39. Adjunct Missile Seeker Deployment Mechanism 39 Future Outlook Further development of –Seeker shroud –Indexing feature –Spring release mechanism –Door release mechanism Maintain focus on –High risk areas

40. Adjunct Missile Seeker Deployment Mechanism 40 Questions?

41. Adjunct Missile Seeker Deployment Mechanism 41 Physical Properties Ex: The outer missile body diameter is 8 in. ITAR

42. Adjunct Missile Seeker Deployment Mechanism 42 Dome Properties E.g. The dome must be transparent to EM radiation with a wavelength (λ) between 3 to 6 microns. ITAR

43. Adjunct Missile Seeker Deployment Mechanism 43 Environmental Concerns Ex: The system may be stored for up to a maximum of 10 yrs., or may be used immediately. ITAR

44. Adjunct Missile Seeker Deployment Mechanism 44 Electrical Constraints Ex: The system shall use less than 100 Watts max of power during deployment. ITAR

45. Adjunct Missile Seeker Deployment Mechanism 45 Performance Ex: The seeker must survive deployed flight conditions for maximum of 25 sec. ITAR

46. Adjunct Missile Seeker Deployment Mechanism 46 Dome Materials Con’t Ex: Weight Characteristic Matching of Materials StrengthThermal ExpansionPoisson's Ratio "of strain rate" 10%5%10% Material(s)(MPa)RankWtd.(1/K)RankWtd.Unitless #RankWtd. Sapphire40050.505.30E-0650.250.2750.50 ALON30040.407.80E-0630.150.2430.30 Y2O312520.207.10E-0640.200.2960.60 MgAl2O419030.308.00E-0620.100.2610.10 MgF25210.101.37E-0510.050.2740.40 Diamond100060.601.00E-0660.300.1620.20

47. Adjunct Missile Seeker Deployment Mechanism 47 Dome Materials Con’t Thermal ConductivityElastic ModulusHardnessRefractive IndexTotal: 10%20%10%35%100% (W/mK)RankWtd.(GPa)RankWtd.(kg/mm2)RankWtd.nRankWtd. 3420.2038051.00180040.41.741.44.25 1150.5031740.80197050.51.651.754.40 1440.4016410.2065020.21.920.72.50 1530.3019330.60164530.31.731.052.75 0.2560.6013920.4041510.11.362.13.75 200010.10105061.20900060.62.410.353.35 Note: In the tables you will see that colors green, yellow, and red.  Red denotes high risk material to use for application.  Yellow denotes border line risk material.  Green denotes least possible risk material. Chosen material: Sapphire due to widespread use by industry

48. Adjunct Missile Seeker Deployment Mechanism 48 Door Ejection Method Con’t Requirement –Use dead bolt locking system to hold down door during flight before acquire phase. Fig. 2: Side View of Door

49. Adjunct Missile Seeker Deployment Mechanism 49 Microcontroller Type Chosen Microcontroller: TI MSP430F167 –Based on overall ranking and secondary requirements

50. Adjunct Missile Seeker Deployment Mechanism 50 Position Sensor Chosen position sensor: Honeywell SS46 –Highest decision matrix overall rating

51. Adjunct Missile Seeker Deployment Mechanism 51 Temperature Sensor Chosen Temperature Sensor: TI TMP123 –Highest overall ranking

52. Adjunct Missile Seeker Deployment Mechanism 52 Drive / Actuation Devices Chosen drive device: Spring –Highest overall ranking

53. Adjunct Missile Seeker Deployment Mechanism 53 Software Flow Diagram (Cont.)

54. Adjunct Missile Seeker Deployment Mechanism 54 Software Flow Diagram (Cont.)

55. Adjunct Missile Seeker Deployment Mechanism 55 Software Flow Diagram (Cont.)