kdi precision products, inc
TRANSCRIPT
Presented by: Mr Ted Lewis
KDI Precision Products, Inc.An ISO 9001 Registered Company
www.kdi-ppi.com
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