Center of Gravity
The center of gravity (CG) is the point about which the weight of an aircraft is equally distributed. If you were to suspend the aircraft from this point, it would be perfectly balanced. The location of the CG is crucial for such purposes as aircraft stability, control surface design, and landing gear design. If the CG is too far forward, the control surfaces will be unable to trim the aircraft. If too far back, the plane becomes unstable. The position of the CG changes throughout an airplane's flight as fuel is burned, bombs are dropped, landing gear are extended and retracted, and so on. Thus, the aircraft designer must be very careful when placing each component within the aircraft to maintain its stability and controllability throughout the range of operating conditions and stages of flight.
The relationship used to compute an airplane's center of gravity (CG) is actually quite simple. What is often difficult is estimating the weights of all the major components and where those weights act. In general, the CG is computed by the following method
1- Select a baseline point from which all dimensions are measured, or a datum. We typically use the airplane nose and measure all distances aft of this location
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2- Estimate the weights of the major components (engines, fuselage structure, tail assembly, landing gear, wing structure, control surfaces, fuel load, pilots, passengers, payload, avionics, etc.) as accurately as possible. In the early stages of design, we may only be able to make rough guesses, but our estimates become more accurate as specific systems and materials are selected
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3- Estimate the center of gravity of each component and measure its location aft of the datum point. Again, we may be forced to use rough approximations until the design becomes more settled
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4- Sum up all of the component weights to determine the total weight of the airplane
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5- Compute the CG of the entire aircraft using weight ratios (i.e. weight of the component over the total weight) and summing up the moments created by each component about the datum point. The position of the CG along the length of the aircraft is computed by the following equation, where Wn/W is the weight of each component divided by the total weight and xn is the estimated CG of that component.
6- The above equation gives us the x-location of the aircraft CG. If we want to know the z-location, we follow the same procedure. We need to select a new datum point, typically the ground, and measure the centers of gravity of each component from this location. We can then compute the height of the CG by this equation:
7- Assuming that the aircraft is symmetrical, the y-location of the CG should be the centerline of the aircraft (or y=0). However, there are a few asymmetrical planes out there, and the CG calculation can be performed using the same method previously discussed.
An example of this procedure is illustrated below: