Amcom mk66 guidance system
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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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AMCOM MK66 guidance system

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Amcom mk66 guidance system

AMCOM MK66 guidance system

11-18-2004


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


Amcom mk66 guidance system

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

  • I/O types:

    • Δv, Δθ

  • 9600bps transmission rate allows more than 8 times the necessary data rate for 16 corrections/second


Amcom mk66 guidance system

GPS

  • 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)


Amcom mk66 guidance system

ser.

GPS

RMS

3

3

RS232

Actuator Control

Cyclone

ser.

4

ADC

3

IMU

Feedback

n

8 par.

SDRAM

PC100


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


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