Where:

The constant, *k, *was determined by letting γ = 1.25, *e *= 0.10, and F = 3.14X105 ft lb/lb for M6, H8,

and T8 propellants and 3.56X105 ft lb/lb for M6 and M2 propellants. *k *also includes a term to convert

the answer to grams. The constants were found to be *k *= 2.66X10-4 gm sec2/ft2 lb and 3.01X10-4 gm

sec2/ft2 lb for M6 and M2 propellants respectively.

under an aerodynamic load, *F*a, which is a linear function of stroke, as shown in figure 47. The hatch

weighs 100 lbs and has a mass moment of inertia, Iy, about its hinge of 90 in.-lb-sec2. In addition,

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