Presented by: Mr Ted Lewis

KDI Precision Products, Inc.An ISO 9001 Registered Company

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45th Annual Fuze Conference "The Evolving Nature of Value Added Fuzing'

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Report Documentation Page

Report Date 16Apr2001

Report Type N/A

Dates Covered (from... to) -

Title and Subtitle The Evolving Nature of Value Added Fuzing

Contract Number

Grant Number

Program Element Number

Author(s) Lewis, Ted

Project Number

Task Number

Work Unit Number

Performing Organization Name(s) and Address(es) KDI Precision Products, Inc.

Performing Organization Report Number

Sponsoring/Monitoring Agency Name(s) and Address(es) NDIA (National Defense Industrial Assocation) 211Wilson BLvd., Ste. 400 Arlington, VA 22201-3061

Sponsor/Monitor’s Acronym(s)

Sponsor/Monitor’s Report Number(s)

Distribution/Availability Statement Approved for public release, distribution unlimited

Supplementary Notes Proceedings from The 45th Annual Fuze Conference, 16-18 April 2001 Sponsored by NDIA, The originaldocument contains color images.

Abstract

Subject Terms

Report Classification unclassified

Classification of this page unclassified

Classification of Abstract unclassified

Limitation of Abstract UU

Number of Pages 19

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GUIDED MLRS USA ANDFOREIGN PARTNERS

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KDI PROGRAM TEAM• Mike Buckhanan - Program Manager• Ted Lewis - Electrical Project Engineer• Cory Hatch - Electrical Engineer• Tony Zucker - Mechanical Project Engineer• Mike Sowder - Test Equipment Electrical Engineer• Steve Gemperline - Quality Engineer, CQE• Bob Garrett - Reliability Engineer• Tom Moore - Manufacturing Engineer• Bob Butts - Configuration Management

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GMLRS OPERATION

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GMLRS ROCKET• The GMLRS Rocket Is Nominally a Ballistic Round• The Maximum Off-axis Shot Is 4° Degrees• The Canards Are Used Only for Trimming the

Trajectory During the Flight

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ESADUmbilical

GPS AntennaGuidance

Set

Control Actuation Set

GUIDANCE AND CONTROLSECTION

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HOUSING

• Material: 304L Stainless Steel• Function

– Interfaces to LEEFI Adapter Assembly– Interfaces With Rocket– Alignment Feature Incorporated– Hermetic Environment– Supports Printed Wiring Board (PWB)

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SEALING

• The ESAD Will Be Hermetically Sealed andTested to Meet a Leak Rate of 1 X 10-6 cc/secHe/Mass Spectrometer at 1 Atmosphere PressureDifferential

• Laser Welding Will Be Used to Seal the Housing,Similar to the Other Qualified Programs at KDI

• The GMLRS ESAD Will Be Back-filled WithNitrogen With A Trace Of Helium Through A FillPlug

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EXPLODED VIEW

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LEEFI ADAPTER ASSEMBLY

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GMLRS ESAD WITH LEEFI ADAPTERASSEMBLY

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DETAILED BLOCK DIAGRAM

5 VoltRegulator

>500VDETECT

Accelerometer TEST

RC Clock

UmbilicalDisconnect

Arming Power

RC Clock

SequenceVerification

Logic

Sequence VerificationAnd Error DetectionLogic

Acceleration Detect Logic

2 PhaseClock DriverLogic

ProgrammableArm Delay Timer

+12 Volt

Hi Side FET

Ground FET

ErrorDetectionLogic

ClockVerifier

SerialDataLogic

MasterClock

Accelerometer A to DConvertor

RC Osc

Crystal Osc

RC FPGA

Data Out

Clock In

Data In

TXData

422TXData

TXData

422 Clock

422Receiver

422 Clock

Receive Data

+26/36VArm Power

1

ARMED STATUS-TM SignalConditioning

LEEFI

StaticSwitch

Static Switch

DynamicSwitch

Trigger

Circuit

TriggerEnergy

Storage

HVEnergyStorage

Voltage Multiplier

HVTransformer

Filter 5 VoltRegulator

12 VoltRegulator

Transient PowerInterruption Filter

Logic Power +12 Power

+5V Logic Power

Arming Power

SOLID STATE SWITCH

Filter

GROUND

1

422Receiver

Receive Data

ISOLATION Circuit

UmbilicalDisconnect

DRIVER

DRIVER

DRIVER

Serial Data FPGA

GMLRS ESAD

FEEDBACKCIRCUIT

+26/36V

OPTO Coupler

OPTO Coupler

OPTO Coupler

Floating+5V Supply

OPTO Coupler Power

CounterCheck

CounterCheck

Accelerometer Test Circuit

Filter

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TIMING DIAGRAMLauncher Power

Acceleration

Umbilical

Serial Commands 0 - Report Current Status Command (Sent Periodically Throughout Flight)

1 - Load Arm Delay Time Command

2 - Arm/Fire Warhead Command

Disconnected

Connected

Serial Data0 1

Thermal Battery

Arm Delay Timer

Static Switch 1

Static Switch 2

Dynamic Switch

Dynamic Switch

HV Status

2

Arm Delay TIme

0.200 Sec

5.08 - 26gfor 5.7 Sec

LEEFI Ignited

Note 1: Arm/Fire Warhead Commands Are Rejected Until Arm Delay Timer Expires

Note 1

Arm/Fire Command Window

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SERIAL INTERFACE• 442 Drivers/Receivers• SDLC Message Formats

Guidance to ESADMessage

48 BITS- 8 BIT Start Word- 8 BIT Command Word- 8 BIT Delay Time- 16 BIT CRC- 8 BIT Stop Word

ESAD to Guidance Message64 BITS

- 8 BIT Start Word- 20 BIT Command Word- 4 BIT Delay Time- 8 BIT Timer Status- 16 BIT CRC- 8 BIT Stop Word

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ACCELERATION PROCESSING

• Motorola MMA1201P Analog Accelerometer– ± 40g Capacitive, Micromachined Accelerometer– Output Sensitivity = 50 ± 2.5 mV/g

• Accelerometer Readings Are Taken Every 340µS• Accelerometer Output Level Checked During BIT• Accelerometer Output Level “Nulled” When Battery

Power is Applied• Specification Requirements:

– 1st Motion = 5.08g for 6 msec Within 0.5s From UmbilicalDisconnect

– Safe Separation = 5.08g for 5.7 ± 0.1 Seconds

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LEEFI ASSEMBLY

• Designed in Unison by China Lake,Reynolds Systems and Silicon Designs

• The LEEFI Has Been Qualified by ChinaLake IAW MIL-STD-331, Test G1

• Specific Tests Designed to Demonstrate theInitiator Meets a Reliability of 0.99 at a95% Confidence Level Were Performed

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MCT SEMICONDUCTORDISCHARGE SWITCH

• N-Type MOS-Controlled Thyristor• 1400 Volt• 4ka Surge Current• Silicon Power Corporation• Tested in KDI IRAD Program

– > 20,000 Discharges

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PROGRAM STATUS / SCHEDULE

• Initial AFSRB Presentation - Completed 19 Dec2000

• PDR - Completed 1-2 Feb 2001• Engineering Tests - 15 Nov 2000 To 31 Mar 2001• CDR - 27-28 Mar 2001• Qualification - 30 May 2001 To 17 Jul 2001• Flight Hardware Delivery 1 June -28 Sept 2001

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QUALIFICATION TESTING

• Twenty ESADS Will Be Subjected to QualificationTesting

• The Qualification Test Environments Will ConsistOf:– Thermal Shock– Tactical Vibration– Launch Shock– High Temperature Operation– Low Temperature Operation– Acoustic Noise and Flight Simulation

• Electromagnetic Environment