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AMCOM Mk66 Project. Adrian Lauf Filiz Genca Ashley Devoto Jason Newquist Matthew Galante Jeffrey Kohlhoff Shannon Stonemetz. What we have. Program source code/operating system (core) Interface specification identifications Processing core. RMS procedural outline.

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Amcom mk66 project

AMCOM Mk66 Project

Adrian Lauf Filiz Genca

Ashley Devoto Jason Newquist

Matthew Galante Jeffrey Kohlhoff

Shannon Stonemetz

What we have
What we have

  • Program source code/operating system (core)

  • Interface specification identifications

  • Processing core

Rms procedural outline
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

Rocket management system
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

Rocket management system cont d
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

Amcom mk66 project

  • 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

Amcom mk66 project

  • Selected system: Honeywell GunHard MEMS IMU

  • Serial I/O

  • 5VDC power supply

  • 9600bps data transfer rate

  • Requires 422 to 232 conversion

Amcom mk66 project

  • 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

Amcom mk66 project

  • 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








Actuator Control









8 par.



How we will simulate
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

To be done
To be done

  • Physics modeling

  • I/O polling routines

  • System software compilation and loading

  • Bus/Battery power transition

Me timeline
ME Timeline

Canard Deployment System Construction



One Month

Two Months


Outer Shell Construction

Simulation and Amcom Presentation

Outer shell construction current configuration
Outer Shell ConstructionCurrent Configuration

  • 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

Outer shell construction current configuration1
Outer Shell ConstructionCurrent Configuration

  • Threaded interface on motor-receiving end

  • Threads matched to rocket motor

  • No construction/machining operation defined

  • Substantial warhead modification required

Outer shell construction proposed configuration
Outer Shell ConstructionProposed Configuration

  • Press-fit interfaces for both ends of avionics module:

  • Ease of construction

  • Greater area of

  • material for force

  • distribution

  • 15in length

Outer shell construction proposed configuration1
Outer Shell ConstructionProposed 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

Outer shell construction proposed configuration2
Outer Shell ConstructionProposed 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

Outer shell construction proposed configuration3
Outer Shell ConstructionProposed Configuration

Press fit interfaces joint strength background
Press-Fit Interfaces Joint StrengthBackground

  • Fμ = μFN = μpA = μpπdl

  • FN : normal force

  • μ : coefficient of static friction

  • p : contact pressure

  • A : area of surface contact

  • d : joint diameter

  • l : joint length

Press fit interfaces joint strength design considerations
Press-Fit Interfaces Joint StrengthDesign Considerations

  • Design for worst case scenario:

  • Max. Weight : 34.4 lbs

  • Max. G’s : 80 @ .965 seconds

  • Max Jerk: 957,303 ft/s^3 @ .01 seconds

  • Material:

  • Aluminum 3356-T06 Alloy

Press fit interfaces joint strength design considerations graphs
Press-Fit Interfaces Joint StrengthDesign Considerations: Graphs

Press fit interfaces joint strength design considerations graphs1
Press-Fit Interfaces Joint StrengthDesign Considerations: Graphs

Press fit interfaces joint strength calculations
Press-Fit Interfaces Joint StrengthCalculations

μ = 1.35

m = 34.4 lbs.

gmax = 80

 Fμ = μFN

mgmax = μFN

 FN = 65,640 Slugs

  • l = .5in

  • d = 2.3895in

  • P = 17.5 kpsi

    Yield Strength:43.5 kpsi

    Mod. Of Elasticity:53.7 kpsi

Press fit interfaces joint strength testing
Press-Fit Interfaces Joint StrengthTesting

  • Simulation

  • ETB (Engineer’s Toolbox) Interface

  • Fit Software

  • Tensile Testing Machine

  • Load to failure

Canard configuration
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

Canard characteristics con d
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

Canard deployment
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


Deployment forces
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

Canard actuation
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

Canard actuation1
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

Missile simulation
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


  • Pictures: Tensile Testing

  • Press-fit Calculations