Verification Data (Spatial and Weight) Unguided MK66 Weight = 23.4 lbs. (7.14 lbs fuel) Length = 55 in. x (c.g.) = 30 in. y (c.g.) = 0.0 in. z (c.g.) =.002.

Verification Data(Spatial and Weight)

Unguided MK66

• Weight = 23.4 lbs. (7.14 lbs fuel)

• Length = 55 in.

• x (c.g.) = 30 in.

• y (c.g.) = 0.0 in.

• z (c.g.) = .002

Guided MK66

• Weight = 34.4 lbs. Max

• Length = 79.7 in. Max

• Center of Gravity

- Move Aft

- Decrease Yaw Rate on Missile

- Remain Neutral in y & z

Verification Data(Performance)

Consideration #1: Design to sustain Max g’s.

• Mechanical – stress concentrations on moving parts (i.e. canards)

• Electrical – tracking, servo response

•SL-MTI DC Servomotor

•MIL spec, designed for missile fin actuation

G Load vs. Time

-10

0

10

20

30

40

50

60

70

0 0.2 0.4 0.6 0.8 1 1.2 1.4

Time (s)

G's

(g

)

Max G’s: 64.8g

0

10

20

30

40

50

60

70

80

90

0 0.2 0.4 0.6 0.8 1 1.2 1.4Time, s

G-L

oad

G-LOAD TREND FOR HYDRA MISSILE SERIES WITH AND WITHOUT AVIONICS MODULE

G-Load W/ Maximum Avionics Module Weight (7.3 lbs)

G-Load for Unmodified Hydra Missile

Guided Max G’s: 80g

Consideration #2: Design to sustain max jerk.

• Jerk is the rate of change of acceleration

• Commonly called pulse, impulse, shock, bounce, or jolt

• Important when evaluating destructive force on components

Jerk vs. Time

-400000

-300000

-200000

-100000

0

100000

200000

300000

400000

0 0.2 0.4 0.6 0.8 1 1.2 1.4

Time (s)

Jerk

(m

/s^

3)

Max. Jerk: 291,786.7 m/s^3

Consideration #3: Thrust and Engine Burn-out

• Engine burns out at 1.2 seconds

• Max thrust occurs at .965 seconds

• Burn-out corresponds to approx. horizontal distance of 317m (4000m range)

Thrust vs. Time

01000200030004000

50006000700080009000

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1 1.1 1.2 1.3 1.4

Time (sec)

Thru

st (N

)

Max. Thrust: 8142 N

Plans for Progress1. Begin programming/simulation with Datcom

• Upsides

• Multiple Inputs

• Simple Programming (Dos-Prompted)

• Calculates Aerodynamic Forces on Missile and automatically generates plots

• Downsides

• Doesn’t model canards accurately at supersonic speeds

• 125 input lines vs. 26,000 output lines

Plans for Progress2. Solid Modeling of Missile (ProE Wildfire)

•Will depict areas of stress concentrations

•Spatial Considerations

•Material Selection

Plans for Progress3. Obtain Aerospace Blockset (Mathworks)

• Inputs:

•Aerodynamic Coefficients

•Dynamic Pressure

•Center of Gravity (CG)

•Center of Pressure

• Outputs:

•Aerodynamic Forces at CG (Drag, Lift)

•Aerodynamic Moments at CG

Aerospace Blockset Screenshot

Processor Solution - Altera

• Provides flexible I/O interfaces for purposes of acquiring GPS and IMU data

• Re-programmable if solution is not optimal according to design

• Have contact information within Altera

Why not M68K?

• No included/implicit interfacing without BIOS support

• No hardware multiplier support

• FPGA allows greater configuration flexibility than fixed-core CPU

Why not LabView?

• Proprietary FPGA solution requires PCI bus – not feasible for use inside a missile

• Possible overhead involved in using LabView as programming language instead of VHDL

• We already have Altera development software

Processor State Diagram