awcgs

Here is a triangle, such as △ABC,∠ B as supporting an object's former vertices, Its weight is:Gn,objects behind the fulcrum weight is: Gm,Is the total weight: Ge,As shown in figure. The graph of the symbol definition is:d=AC,AB=c,AC=b,BC=a,AL=x,OL=y, tanθ=BC/AC=a/b,Cosθ=AC/AB=b/a. The problems need to be solved as follows: 1.When the object's centerline is horizontal reference line (green line) above,also is h1＞h2,θis positive angle(that is ＋3°、＋5°、＋7°、＋10°,etc),at this time B Angle (B point) is rising,so that the object front-end(B point) rising status. 2.1.When the object's centerline is horizontal reference line (green line) below,also is h1＜h2,θis negative angle,(that is -3°、-5°、-7°、-10°,etc),at this time B Angle (B point) is to drop,so that the object front-end(B point) declining state. ⑴ I write the formula is:Ge*(x－y*tanθ)*cosθ＝Gn*b,but I don't know whether it is right, please revise and work out y, ⑵ Calculate + 3°、+ 5°、+ 7°、+ 10°and - 3°、- 5°、- 10 °to correspond a (BC) in length.

Please help me to solve this problem, it needs to calculate aircraft's centre of gravity, as follows: 1.Weight and the ARM: (1) Front wheel weight: 600kg,to Datum distance:372mm, (2) Main wheel(Wl+Wr) weight:1400kg,to Datum distance:2200mm,Wing frontier to the Datum distance:1963mm, (3) Total weight: 2000kg, 2.I need to calculate the following results: (1) The aircraft was in a horizontal status of longitudinal CG position, vertical CG position. (2) The front end of the aircraft rise an angle (such as 3 degrees or 5 degrees),its vertical CG position. (3) The front end of the aircraft drop an angle (for example -3 degrees or -5 degrees),its vertical CG position. Thanks for you!