Amcom mk66 project
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AMCOM Mk66 Project. Adrian LaufFiliz Genca Ashley DevotoJason Newquist Matthew GalanteJeffrey 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 LaufFiliz Genca

Ashley DevotoJason Newquist

Matthew GalanteJeffrey 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

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


Amcom mk66 project

IMU

  • Selected system: Honeywell GunHard MEMS IMU

  • Serial I/O

  • 5VDC power supply

  • 9600bps data transfer rate

  • Requires 422 to 232 conversion


Amcom mk66 project

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


Amcom mk66 project

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


Datamap

Datamap

ser.

GPS

RMS

3

3

RS232

Actuator Control

Cyclone

ser.

4

ADC

3

IMU

Feedback

n

8 par.

SDRAM

PC100


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

Design

Finalization

One Month

Two Months

Present

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

Front


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


References

References

  • Pictures: Tensile Testing http://www.instron.us/wa/products/universal_material/3300/default.aspx

  • Press-fit Calculations

  • http://facta.junis.ni.ac.yu/facta/me/me2001/me2001-15.pdf

  • AMCOM


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