AIR CORPS  TM 1-320  48  d.  The initial step in the computation is determination of .distribu› tion of weights.  This is taken from the detailed weight  s t~tement,  weights therefrom being distributed to the proper frames.  Lift of  the gas in each cell is computed next and distributed as concentrated  forces on the frames.  The static loads on the hull are the differences  between weight and buoyancy at each frame, lift being considered  positive and loads negative.  When the airship is in static equilibrium,  the algebraic sum of the loads must equal zero.  Figure 27 illustrates  the computation of loads at each frame of an airship 50 meters long,  having four frames spaced 10 meters apart. The method shown is  applied to the largest airships.  e.  Commencing at either end of the airship, the shear at any frame  equals the algebraic sum of loads up to that frame.  This system  gives a constant shear between frames, changing at each frame QY  9  1000  so  - .Jo  /..  tq 000  {Plane conftnl1in? C.G al1d C.8.  90 po  80 I  20  /0 000  00  /()  00  &olf4ncr  <~ncl  1000  Loadi~  ,.,  0  LBS.  2  000  I""’!•,__--- Overall len9rh oF  /lir.ship----~  t  1  I  Loads’"  1.85.  j  2000  2000  •  ~----~------~~-----~.r-----~------~.  1000  /000  /000  1000  I  1+1000  I  - 1000  I  ...__ ____ __,,_,QOQ  fjft1. IN  LB. Meter.s  F tcu•n:  :.!7.-Loads, shear, a1111 bending moments caused by static loading.  62 