1. AMCOM Mk66 Project Adrian LaufFiliz Genca Ashley DevotoJason Newquist Matthew GalanteJeffrey Kohlhoff Shannon Stonemetz

2. What we have Program source code/operating system (core) Interface specification identifications Processing core

3. RMS procedural outline Inform missile of ready state Feed missile coordinates of target and position Send fire go signal Receive error control signals via serial End

4. Rocket management system Current system uses analog line for purposes of charging a timing capacitor Proposed implementation of an RS-232 digital serial interface RS-232 allows for target data transfer at comfortable data rates, from 300bps to 115200bps. Standard 9600bps baud rate will more than likely suffice

5. Rocket management system (cont’d) RS-232 implementation at 12V active-low –Allows for extended serial cable lengths Allows for debugging based on a PC serial port using 12V active-low –PC may be used in conjunction with Matlab, C or other to simulate rocket management system outputs Data format based on target data: –Current position and elevation –Target position and elevation –Current speed Guidance module returns “target acquired” signal

6. IMU IMUs may provide analog or digital outputs; IMUs that we have researched mostly output serial digital signals 2-wire serial outputs, 5V TTL to Altera serial I/O line –Standard to be defined

7. IMU Selected system: Honeywell GunHard MEMS IMU Serial I/O 5VDC power supply 9600bps data transfer rate Requires 422 to 232 conversion

8. GPS G12-HDMA receiver –4.25’’ tall x 2.3’’ wide –Weight – 0.175 lb –Power – 1.8 W receiver 0.3 W antenna –Max Acceleration – 23 Gs up to 30 Gs Initialization time – 45 sec cold and 11 sec hot Time-To-First-Fix – 3 sec Reacquisition – 2 sec Operating Temperature - (-30) C to 70C

9. GPS Digital serial I/O lines 5VDC (TTL-level power), no voltage division required Data transmission rate at 9600bps will allow for more than 8 times the necessary data rate for 16 corrections/sec

10. Cyclone IMU 3 GPS 3 RMS 3 RS232 SDRAM ser. Actuator Control 8 par. Feedback n PC100 ADC 4 Datamap

12. How we will simulate RMS, GPS and IMU data will be provided (simulated) by a PC All I/O will take place through one RS-232 port

13. To be done Physics modeling I/O polling routines System software compilation and loading Bus/Battery power transition

14. ME Timeline Outer Shell Construction Design Finalization Simulation and Amcom Presentation Present One Month Canard Deployment System Construction Two Months

15. Outer Shell Construction Current Configuration 1.Splined connection on warhead-receiving end Intended to align pin connection on module with warhead Warhead secured by bolts Axial forces concentrated on bolts Difficulty in machining

16. Outer Shell Construction Current Configuration 2.Threaded interface on motor-receiving end Threads matched to rocket motor No construction/machining operation defined Substantial warhead modification required

17. Outer Shell Construction Proposed Configuration Press-fit interfaces for both ends of avionics module: Ease of construction Greater area of material for force distribution 15in length

18. Outer Shell Construction Proposed Configuration Male threaded interface: 2.3895in OD 6 threads/in pitch.5in press-fit shank 1.5in threaded end 7/32in wall thickness Shoulder machined for positive stop

19. Outer Shell Construction Proposed Configuration Female threaded interface: 2.625 OD 7/32in wall thickness ID machined to match size/pitch of war head.5in press-fit shank Shoulder machined for positive stop

20. Outer Shell Construction Proposed Configuration

21. Press-Fit Interfaces Joint Strength Background F μ = μF N = μpA = μpπdl F N : normal force μ : coefficient of static friction p : contact pressure A : area of surface contact d : joint diameter l : joint length

22. Press-Fit Interfaces Joint Strength Design Considerations Design for worst case scenario: 1)Max. Weight : 34.4 lbs 2)Max. G’s : 80 @.965 seconds 3)Max Jerk: 957,303 ft/s^3 @.01 seconds Material: Aluminum 3356-T06 Alloy

23. Press-Fit Interfaces Joint Strength Design Considerations: Graphs

25. Press-Fit Interfaces Joint Strength Calculations μ = 1.35 m = 34.4 lbs. g max = 80  F μ = μF N mg max = μF N  F N = 65,640 Slugs l =.5in d = 2.3895in  P = 17.5 kpsi Yield Strength:43.5 kpsi Mod. Of Elasticity:53.7 kpsi

26. Press-Fit Interfaces Joint Strength Testing 1.Simulation ETB (Engineer’s Toolbox) Interface Fit Software 2.Tensile Testing Machine Load to failure

27. Canard Configuration Due to poor supersonic behavior, flat plate canards are unacceptable Will use a NACA four digit series symmetric airfoil to accommodate supersonic portion of mission NACA 0012 with a chord length of 1.25in Force analysis from last year determined TI-6A1- 4V alloy is the desired canard material

28. Canard Characteristics Con’d total length- 3.4375 in external length- 3 in individual mass-.031 lb total mass-.123 lb NACA 0012 cross section chord length- 1.25 in

29. Canard Deployment Current design has canards opening towards front of missile Deployment forces required are too high to implement Proposed design takes existing internal setup and rotates 180 deg Canards open towards rear of missile Front

30. Deployment Forces 12 lb force needed to deploy canards in current design due to g-force Aerodynamic force not included in calculation. This is not feasible These forces aid in deployment when canards open towards missile rear

31. Canard Actuation Considered use of gearbox with the servo motors to actuate canards Gear boxes are compact and provide reductions Some gear boxes prevent motor back drive However, due to limited space, gear boxes are too large to implement

32. Canard Actuation Decided to use actuation mechanism designed previously Spatially will meet requirements Drive system always engaged Allows for addition of damping system Further development required –Gear system –Damping mechanism –Deployment mechanism

33. Missile Simulation Utilizing Matlab’s Aerospace Blockset to simulate mission Building on the simulation from last year. –6 dof, determine forces on airframe, determine required guidance forces Current Improvements –Determine missile orientation upon deployment, determine fin actuation needed to produce guidance forces, model airfoil shape in simulation

35. References 1.Pictures: Tensile Testing http://www.instron.us/wa/products/universal_material/3300/defau lt.aspx http://www.instron.us/wa/products/universal_material/3300/defau lt.aspx 2.Press-fit Calculations http://facta.junis.ni.ac.yu/facta/me/me2001/me2001-15.pdf 3.AMCOM