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AMCOM MK66 guidance system. 11-18-2004. System interface specifications. Rocket management system (Target acquisition system on helicopter) IMU GPS Actuator system control Controller I/O bus. Rocket management system.

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system interface specifications
System interface specifications
  • Rocket management system
    • (Target acquisition system on helicopter)
  • IMU
  • GPS
  • Actuator system control
  • Controller I/O bus
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
  • 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
  • I/O types:
    • Δv, Δθ
  • 9600bps transmission rate allows more than 8 times the necessary data rate for 16 corrections/second
  • Digital serial I/O lines
  • Provides P(x, y, z), ΔP(x, y, z)
  • 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
altera cyclone system buses
Altera Cyclone system buses
  • Memory R/W/ADDR bus, 16MB system memory (SDRAM), interface specifications allow for SDRAM
  • SDRAM in PC100 specification, managed by onboard memory controller
  • Local serial, parallel buses
  • Actuator control:
    • Via parallel ports, can be used in conjunction with LM741/MIL741 and transistor drivers coupled to relays to trigger actuator assemblies
    • ADC ICs provide actuator position feedback, 8-bit parallel port solution for feedback to FPGA controller
  • System clock rates allow for 50MHz modulation (more than enough)







Actuator Control









8 par.



additional fpga considerations
Additional FPGA considerations
  • Nios devel. kit has two serial ports; three are required for this application:
    • The RMS and IMU or GPS ports may be shared and appropriately multiplexed
  • Actuators:
    • 8-bit parallel port can be set to drive actuator driver circuit.
    • 8-bit parallel ports (4) will be used for feedback purposes from each servo with ΔV coming from an ADC
force resisting canard deployment
Force Resisting Canard Deployment
  • Force acting on the canard due to acceleration of 80g’s is 42.7N (10 lb) acting on the centroid. (assuming canard dimensions in diagram)
  • This relates to a torque of 2.7225 Nm
  • To open the canards with a force applied 1 in from the pivot point, a force of 106.75N (24lb) is needed
  • This force is possibly to large to produce within the design limitations (space and weight)
optional canard deployments
Optional Canard Deployments

2. Different Shapes

1. Suicide

naca airfoil
NACA Airfoil
  • 4 digit airfoil
  • Example: 2412
    • Max chamber 0.02c
    • Camber max location 0.4c
    • Max thickness 0.12c
simulation upcoming goals
Simulation: Upcoming Goals
  • Researching and understanding DATCOM
  • Locating Aerospace Block Set and learning the software
  • Analyzing various fin geometries
  • Creating new deployment mechanisms