Structural analysis and design of airplanes (1920)
United States. Army. Air Corps · [Washington] · leaf 208
tor Tubes Tubc-y •M 4? 6 A fr^4 V« J^ V Judder C(?6/etoken off here Fig. 114. Rudder Bar Shearing = f s = \/(745 or- (29,900) ( 2 )■ 16,700 lbs. per sq. in. (satisfactory) 136. Investigation of Mast on Elevator Tubes—A foment of elevatorload = 3620 in. lbs. Refer to Fig. 115. 3620 Pull on elevator… … Fig. 115. Elevator Control Mast189 Control Systems Art. 137 Stress on section D—D. m=1.0X 805 = 805 in. lbs. 1.203X .40—1.0753X -275 I = =.0291 12805 X .6 fb = = 16,600 lbs. per sq. in. (satisfactory) .0291Stress on section C—C. m = 3.6X805 = 2900 in. lbs. 1.0 X 2.03— .875 X 1-8753 I = =.185 122900…
Airplanes
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