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

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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

  • 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

  • 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)

  • 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


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


IMU

  • Selected system: Honeywell GunHard MEMS IMU

  • Serial I/O

  • 5VDC power supply

  • 9600bps data transfer rate

  • Requires 422 to 232 conversion


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


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

ser.

GPS

RMS

3

3

RS232

Actuator Control

Cyclone

ser.

4

ADC

3

IMU

Feedback

n

8 par.

SDRAM

PC100


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

  • Physics modeling

  • I/O polling routines

  • System software compilation and loading

  • Bus/Battery power transition


ME Timeline

Canard Deployment System Construction

Design

Finalization

One Month

Two Months

Present

Outer Shell Construction

Simulation and Amcom Presentation


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 ConstructionCurrent Configuration

  • Threaded interface on motor-receiving end

  • Threads matched to rocket motor

  • No construction/machining operation defined

  • Substantial warhead modification required


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 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 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 ConstructionProposed Configuration


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 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 StrengthDesign Considerations: Graphs


Press-Fit Interfaces Joint StrengthDesign Considerations: Graphs


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 StrengthTesting

  • Simulation

  • ETB (Engineer’s Toolbox) Interface

  • Fit Software

  • Tensile Testing Machine

  • Load to failure


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

  • 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

  • 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

  • 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

  • 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 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

  • 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

  • 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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