AMCOM MK66 Guidance Module team

Module Casing Length: in Outer Diameter: 2.75 in Thickness: 1/16 in Interface Thickness: 7/32 in Male Threaded Interface Length: 2.5 in Male Splined Interface Length: 1 in

Outer Shell Construction Fittings Splines and Threads: Two Options 1. Press-fit threaded inserts into outer shell 2. Machine outer shell in three pieces and weld together

Outer Shell Construction Connections - Mechanical Current Configuration: - Splines slide into receptacle - Outer shell bolted to missile body at front - Outer shell threads into motor Predicted Configuration: - Outer shell threaded on both ends - Ease of Construction - Force distribution

Outer Shell Construction Connections – Electrical Current Configuration: - Umbilical chord enters through nose cone - 14 pin connection oriented by spline fittings Possible Configuration: - Redesign umbilical into contact system - Create pigtail to allow for threading on both ends - Four pin connection needed

Fin Deployment Suicide configuration Force Analysis Greater moment arm from center of gravity Greater moment arm from center of gravity Less fin deflection to create same path correction Less fin deflection to create same path correction Larger stress on interfaces handled by threaded connections Larger stress on interfaces handled by threaded connections

Short-term Goals 1.Teleconference with Amcom Outer Shell Construction - Weld vs. Press-fit interfaces - Umbilical modification - fixed vs. pigtail Alteration of warhead - Excess material removal - Electrical/umbilical schematic 2.Simulation 3.Solid Modeling

Algorithms Software core is done (C) Features cascading error handling within parent subroutines Features cascading error handling within parent subroutines All errors can be handled in a consecutive case-by-case manner All errors can be handled in a consecutive case-by-case manner Different failure points trigger feedback to RMS if failure occurs in launcher and cannot be handled Different failure points trigger feedback to RMS if failure occurs in launcher and cannot be handled Memory allocation is done statically with predefined GPS/IMU datastructures Memory allocation is done statically with predefined GPS/IMU datastructures

Algorithms – Physics Modeling Initial trajectory plot performed by Nios core processor – system and target position information fed by RMS Differential correction scheme performed after launch sequence completes

Software core Current program size is ~250 lines of C Expected program length approx lines, depending on depth of I/O transfer routines and mathematical modeling

Thermal battery, other power concerns EaglePicher will custom-build battery to power and dimension specifications. Regulated voltage target between volts, after voltage regulator output = 5VDC, 12VDC Altera FPGA loses programming on power off; possible solutions include: Lithium battery support for program hold Lithium battery support for program hold Boot PROM on-demand reprogramming Boot PROM on-demand reprogramming

Interfacing Require RS-422 to RS-232 converter (commercially available) I/O polling strategy/request format to be determined Bus to Battery transition Servomotor via Parallel control